FRACTURE CONTROL PRACTICES FOR METAL STRUCTURES

H.l. McHenry ^

S.T. Rolfe

^

^ Fracture and Deformation Division

National Measurement Laboratory

National Bureau of Standards

Boulder, Colorado 803.03

2

University of Kansas

Civil Engineering Department

Lawrence, Kansas 66044

Sponsored by;

David Taylor Naval Ship Research & Development Center

Annapolis, MD 21402

QC

100

.U56

79-1623

1980

January 1980

NBSIR 79-1623

FRACTURE CONTROL PRACTICES FOR METAL STRUCTURES

H.l. McHenry ^

S.T. Rolfe

^

Fracture and Deformation Division

National Measurement Laboratory

National Bureau of Standards

Boulder, Colorado 80303

2

University of Kansas

Civil Engineering Department

Lawrence, Kansas 66044

Sponsored by:

David Taylor Naval Ship Research & Development Center

Annapolis, MD 21402

January 1980

U.S. DEPARTMENT OF COMMERCE, Philip M. Klutznick, Secretary

Luther H. Hodges, Jr., Deputy Secretary

Jordan J. Baruch, Assistant Secretary for Science and Technology

NATIONAL BUREAU OF STANDARDS, Ernest Ambler, Director

TABLE OF CONTENTS

Page

ADMINISTRATIVE INFORMATION 1 1. INTRODUCTION - 1 2. ELEMENTS OF FRACTURE CONTROL 2 2.1. Structural Design Conditions 2 2.1.1. Design Life 3 2.1.2. Loads 3 2.1.3. Environment 3 2.1.4. Initial Damage Assumption 3 2.1.5. Safety Factors 3 2.2. Materials 4 2.2.1. Selection 4 2.2.2. Properties 4 2.2.3. Specifications 4 2.3. Design 5 2.3.1. Design for Fracture Control - 5 2.3.2. Standard Details 5 2.3.3. Joining Practices 5 2.4. Analysis 6 2.4.1. Stress Analysis 6 2.4.2. Fatigue Analysis 6 2.4.3. Fracture Mechanics Analysis 6 2.4.4. Fail-Safe Analysis 6 2.5. Quality Assurance 7 2.5.1. Material Procurement Controls 7 2.5.2. Fabrication and Processing Controls 7 2.5.3. Inspection 7 2.5.4. Proof Testing 7 2.5.5. Traceability 8 2.5.6. Verification Testing 8 2.6 In-Service Controls 8 2.6.1. In-Service Monitoring 8 2.6.2. Periodic Inspection 8 2.6.3. Maintenance 8 2.6.4. Repair 9 3. THE CODE APPROACH TO FRACTURE CONTROL 9 3.1. Structural Design Conditions 9 3.1.1. Design Life 10 3.1.2. Loads 10 3.1.3. Environment 10 3.1.4. Assumed Initial Damage 10 3.1.5. Safety Factors 11 3.2 Materials 11 3.2.1. Specifications 11 3.2.2. Properties 12 3.2.3. Toughness Requirements 13 3.3. Design and Analysis 14 3.3.1. Design for Fracture Control 14 3.3.2. Standard Details 15 3.3.3. Analyses 15 3.3.4. Fatigue Control 16 3.4. Quality Assurance 17 3.4.1 Material procurement controls 17 3.4.2 Fabrication and processing controls 17 3.4.3 Inspection 18 3.4.4 Verification testing 18

i i i
contents (continued) Page

3.5. In-Service Controls 19 3.5.1. Periodic inspection 19 3.5.2. Maintenance and repair 20 4. THE PERFORMANCE SPECIFICATION APPROACH TO FRACTURE CONTROL— 20 4.1. Structural Design Condit'ons 20 4.2. Materials 21 4.3. Design and Analysis 21 4.4. Quality Assurance 22 4.5. In-Service Controls 23

5. FRACTURE CONTROL CONCEPTS FOR NAVAL SYSTEMS 23 5.1. Steel Toughness Requirements 23 5.1.1. The strain rate shift 23 5.1.2. Metallurgical controls 24 5.1.3. Toughness saturation 24 5.2. Weld Quality Standards 24 5.2.1. Fitness-for-service 25 5.2.2. Assessment of flaws detected during in-service

inspection 25 5.3. Aerospace Practices for High Performance Structures 26 5.3.1. Loads 26 5.3.2. Full-scale testing 26 5.3.3. Fracture critical parts 27

6. SUMMARY COMMENTS 28

7. ABBREVIATIONS 29 APPENDIX 31 MERCHANT SHIPS 32 LNG SHIPS - CONTAINMENT SYSTEMS - 36 FIXED OFFSHORE STRUCTURES 44 FLOATING NUCLEAR POWER PLANT 53 LNG STORAGE TANKS 56 STEEL BRIDGES 61 LARGE ROTATING EQUIPMENT 65 PRESSURE VESSELS 68 NUCLEAR PRESSURE VESSELS 72 GAS AND OIL PIPELINES 75 PRESSURE PIPING— POWER AND CHEMICAL INDUSTRIES 82 USAF AIRCRAFT 88 NASA SPACE VEHICLES 98

i V
LIST OF FIGURES

Page

1. The Effect of Strain Rate on the Fracture Toughness of 106

a Structural Steel

2. Critical Crack Length as a Function of Charpy V-Notch 107 Toughness for a Specific Type of Size of Line Pipe

A-1 Logic Diagram for the Selection of Fracture Critical 108 Parts of the Space Shuttle System

V

FRACTURE CONTROL PRACTICES FOR METAL STRUCTURES

H. I. McHenry

S. T. Rolfe

Fracture control practices are the engineering procedures and requirements that

contribute to the prevention of fracture in metal structures. These practices

are identified as the elements of fracture control and each element is defined

and described. The systematic application of these practices to the prevention

of fracture in a particular structure is accomplished by either the code approach

or the performance specification approach to fracture control. In these two approaches, the consideration given to each of the elements of fracture control is discussed and illustrated with examples for specific types of structures. Selected

practices that may be of use in Naval systems are discussed. An Appendix contains

detailed summaries of the fracture control practices used in each of thirteen

classes of metal structures, including ships, offshore structures, bridges, cryogenic tanks, pressure vessels, piping, power generation equipment, and aerospace

structures.

Key words: Fracture control; fracture mechanics; mechanical properties;

quality assurance; stress analysis; structural safety.

Note on Units: Duplicate units are used throughout this document. SI units appear

first followed by English units except when quotations from codes and specifications

are given. In that case the first unit is a direct quotation and the second is a conversion

ADMINISTRATIVE INFORMATION

This project was sponsored by the Naval Sea Systems Command (SEA 05R) under Program

Element 62761N, Task Area SF54-591-506 . The program manager is Dr. H. H. Vanderveldt

(SEA 05R). The project monitor was John P. Gudas of the David W. Taylor Naval Ship Research

and Development Center (Code 2814).

1. INTRODUCTION

In the fall of 1977, the Naval Sea Systems Command started a program entitled "Fracture

Control Technology for Ships and Submarines". The initial tasks included the identification

of Navy fracture control requirements and an assessment of fracture control practices used by U.S and foreign industries. As part of this program, NBS was requested to review fracture

control practices used by American industry and by government agencies other than the Navy

and to identify practices that may be useful to the Navy.

The approach used in this study was first to identify and define the elements of frac- ture control, and then to prepare detailed summaries of the fracture control practices used

for thirteen classes of metal structures. Concurrently, Navy personnel were reviewing Navy

practices and requirements relative to fracture control. Discussions with the Navy investigators led to the identification of fracture control concepts that are potentially useful to

the Navy.
The report consists of the review of fracture control elements and approaches, and the identification of innovative and cost-effective fracture control concepts that merit consideration for Naval systems. The detailed summaries of fracture control practices used for thirteen types of structures are presented in the Appendix.

2. ELEMENTS OF FRACTURE CONTROL

The objective in design of large complex structures such as ships, bridges, pressure

vessels, aircraft, etc. is to optimize the desired performance requirements relative to cost considerations (i.e., the overall cost of materials, design, fabrication, and operation) so that the probabil ityland economic consequences)of failure are low. To achieve these objectives, engineers make predictions of service loads and conditions, calculate stresses in various structural members resulting from these loads and service conditions, and size the

members such that the stresses are limited to values below the critical stresses for the potential failure modes of the structure, i.e., yielding, buckling, fatigue, creep, and

brittle fracture.

The prevention of brittle fracture is an important consideration because of the sudden

and uncontrolled nature of such failures. Experience gained from service failures of many

engineering structures indicates that most brittle fractures are initiated by small flaws

that grow, as cracks, to a critical size during service. Accordingly, there are three parts

to the fracture problem: (1) The initial flaw size, (2) crack growth, and (3) crack tolerance.

The initial flaw size is a function of material and weld quality, the workmanship during

fabrication, and the inspection and quality control. The crack-growth behavior is controlled

by the cyclic stress history, the thermal and chemical environment, and the design detail.

The crack tolerance is governed by the material toughness, the crack size, and the maximum

stress level.

A complete understanding of all these factors is obviously not possible for a complex structure. Thus, to assure safety, it is necessary to devise a plan to limit the uncertainties. Such a plan is a fracture control plan and consists of the systematic consideration

of the numerous elements of the fracture problem. The elements of fracture control are all of the factors that must be considered during design, fabrication, and operation of a structure to assure satisfactory fracture resistance of the structure during its intended service

life. The various elements of fracture control are listed and defined in this section.

2.1. Structural Design Conditions

The structural design criteria are the operational and performance standards against

which the expected (or actual) behavior of the structure can be judged. They are based on the specified operating conditions that the structure must be designed to tolerate, and the analysis assumptions and safety factors used in design. Operating conditions relevant to fracture control include the design service life, the anticipated service load history, and

2
the thermal and chemical environment. Analysis assumptions may include consideration of

failed members, preexisting flaws, superimposed loads, and methods of combining stresses.

Safety factors on loads or on material properties may be used to account for uncertainties

in the loads and material properties.

2.1.1. Design life

Design life is the specific number of years of service (e.g., 20 years) or application

of loads (e.g., 2,000,000 cycles) that a structure must withstand. A distinction should be

made between total design life (useful service) and intermediate design life (time for

replacement of critical parts or membe'rs to extend the total design life of the structure).

2.1.2. Loads

Loads are all the forces that the structure must withstand throughout its life, such as gravity, applied, displacement, natural (e.g., earthquake), repeated (e.g., fatigue, wave

action) , etc.

2.1.3. Environment

The environment in which the structure must perform is the anticipated thermal and

chemical exposure. Temperature extremes, time at temperature, and number of thermal cycles

should be used to account for strength reductions due to thermal exposure and to analyze for

creep and thermal fatigue. The chemical environment (e.g., sea water, fuel, air, etc.)

should also be characterized in terms of duration and repetitions of exposure. For

environmental considerations, the load vs. time profile also becomes important to properly

account for environmentally enhanced fatigue crack growth.

2.1.4. Initial damage assumption

Flaws, deformation, the failure of members, etc. should be considered during design. In certain design codes, the designer is required to account for the possibility of flaws and to

conduct a fracture mechanics analysis to insure the satisfactory behavior of the flawed

structure.

2.1.5. Safety factors

Limit criteria (e.g., yield strength, Kj^, etc.) generally are reduced by factors,

or applied loads increased by factors, to reach an allowable working stress that accounts

for unexpected variations in loads or material properties. These factors are called safety

factors. Increasing the factor of safety for a particular mode of failure, reduces the

likelihood of failure by that particular mode.

3
Probabilistic analysis is an emerging design concept that can be used instead of safety

2.2. factors.

Materials

The fracture resistance of a structure is strongly dependent on the materials of construction. Controls on material procurement and subsequent processing (heat treatment,

welding, etc.) must be implemented such that the material in the as-fabricated structure

retains the properties assumed in design.

2.2.1. Selection

Often, the materials for a particular class of structures are specified by codes, and

the material selection process is automatic. That is, materials that have been used

successfully in the past are selected for similar applications. However, for new systems or applications, material selection actually depends on an optimization of strength, ductility,

toughness, fabricabi 1 i ty, fatigue, environmental, and cost factors. Thus, material selection

should be based on an understanding of the material response to all anticipated service

loadings and environments.

2.2.2. Properties

Material properties used in design are generally based on the minimum values required in the material procurement specification such as yield strength, tensile strength, and in some cases, toughness properties such as CVN, NDT, or Alternatively, data compilations

such as MIL Handbook-V may be used as the source of statistically derived property values.

Properties such as fatigue behavior may be included in the code or code-approved handbooks.

Code-approved procedures, or in some cases, code-body approvals, generally are required

to develop properties of materials needed for design but not available from approved sources.

2.2.3. Specifications

Material procurement specifications are used to provide assurance that the materials of construction do not have properties inferior to those assumed in design. Specifications

generally are required for each material and product form. These documents specify the mini- mum acceptable values for the tensile properties and, in some cases, fracture properties.

Requirements may also be established for melting and primary processing (such as in ABS*

specifications), heat treatment, chemical composition, ultrasonic quality, and dimensional

tolerances. Quality assurance provisions, testing procedures, and reporting requirements

may be stipulated. *Abbreviations defined in Section 7,

4
Material processing specifications nay be required for all processing operations that

nay alter the as-fabricated properties of the material. Examples are specifications for heat

treatment, v/elding, and electroplating. These documents specify requirements for equipment

control, processing procedures, acceptance standards, quality assurance provisions, and

workmanship. Where applicable, tests may be required to measure mechanical properties,

chemical composition, surface condition, and dimensional tolerances. Procedures are defined

for surface preparation, rework and repair, temperature control, etc. Applicable testing

procedures, subcontractor provisions, and reporting requirements may be stipulated.

2.3 Design

Design is the overall process of proportioning and arranging members into a structural

configuration that will perform the intended functions under the specified design conditions.

As part of a comprehensive fracture control plan, design responsibilities include the

following; a) Minimize the probability of structural failure by using damage-tolerant design

concepts and materials, b) reduce the incidence of fatigue cracking and corrosion problems

by careful attention to design detail, and c) provide adequate accessibility for inspection

and repair.

2.3.1. Design for fracture control

Certain codes require that damage in the as-fabricated structure or damage that occurs during service be considered during the initial design process. The methods most commonly

used are the safe life and fail-safe approaches. The safe-life approach requires that a flaw

will not grow to critical size during service due to the anticipated loads and environment.

The fail-safe approach requires that the structure remaining after failure of any given member

will not fail within a period of service sufficient to detect and repair the failed member.

2.3.2. Standard details

Standard details are those that are known to give satisfactory performance in other structures. Many codes stipulate that the standard details described in the code be used

where applicable. For example, certain welded connections such as ground butt welds have

better fatigue lives than partial -penetrati on butt v/elds- Hence these standard details can

be specified with some assurance of the level of performance.

2.3.3. Joining practices

The design should require qualified joining practices to assure satisfactory reliability

in welded and mechanically fastened joints. Most codes require qualification of each welding

procedure, i.e., for each material (or class of materials), welding process, position, and

thickness range. Similarly, codes for bolted or riveted structures such as aircraft may stipulate hole preparation and fastener installation procedures that assure satisfactory

fatigue resistance.

5
2.4. Analysis

Analysis is the analytical evaluation of the design to determine the distribution and

magnitude of the stresses and to determine if the design conforms to the structural design

criteria relative to strength, deformation, fatigue, fracture, and safety.

2.4.1. Stress analysis

Stress analysis consists of the analytic determination of the stresses and deformations

resulting from the external loads and temperature imposed on the structure. The results are compared v/ith the specified design criteria to determine margins of safety. Design iterations are required until there are adequate margins of safety throughout the structure.

2.4.2. Fatigue analysis

Fatigue analysis is the assessment of the expected behavior of the structure to assure

that fatigue failure will not occur within the specified service life due to application of

the anticipated loads. This may be accomplished by reducing the stresses below a level

specified in the code for fatigue critical details (as is the case for bridges) or by

calculating the fatigue damage in the structure using semi empi ri cal methods. The calculated

fatigue damage is compared with the specified design criteria to determine if the requirements are met. If the fatigue damage is too high, design iterations are required until the

stress levels throughout the structure are sufficiently low to meet the fatigue requirements.

2.4.3. Fracture mechanics analysis

Fracture mechanics analysis is the analytical determination of the influence of loading,

crack size, and structural geometry on the fracture resistance of materials containing cracks.

When applied to design, the objective of the fracture mechanics analysis is to limit operating

stresses such that a flaw of a specified initial size located anywhere in the structure will

not grow to critical size during the service life of the structure. Service life for a given location is calculated on the basis of the specified initial flaw size, a stress analysis of the structure for the location in question, and experimental data describing the crack

growth and fracture behavior of the material used. Fracture mechanics parameters are used

to compare the stress field ahead of a crack (Kj) with the critical material toughness

(Kj^), i.e., analogous to comparing a design stress (c) with a limiting stress

(ays).

2.4.4. Fail-safe analysis

Fail-safe analysis is the stress analysis of the structure with one or more elements

failed as specified in the criteria. Dynamic release of energy during failure of the element(s)

6
must be taken into account. The stresses in the remaining structure must be sufficiently

low to meet the design criteria for residual strength and fatigue life.

2.5 Quality Assurance

Quality assurance is the system of controls used to ensure that the as-fabricated structure conforms to the code requirements.

2.5.1. Material procurement controls

Receiving inspection verifies that the raw material meets the requirements of the

applicable procurement specifications. This is accomplished by reviewing the records supplied

by the vendor and, where applicable, by conducting acceptance tests. All material should bo

clearly marked and allocated such that the correct material is used throughout the structure.

2.5.2. Fabrication and processing controls

Production processing and fabrication should be conducted by qualified personnel in

accordance with documented work instructions, using adequate equipment.

Testing requirements invoked by the processing specification should be performed as required on a timely basis. Processing variables such as temperature, time, welding parameters, etc. should be monitored using calibrated equipment, and the variables should bo

controlled within acceptable ranges.

2.5.3. Inspection

Inspection should insure that the structure conforms to the material, dimensional, and

installation requirements of the structural drawings and that defects which could cause premature failure are not present in the raw material or the as-fabricated structure.

Inspection consists of the dimensional checks, nondestructive evaluation of specified areas

such as the welds, and in some cases, destructive tests to verify conformance to standards

generally specified on the drawing.

2.5.4. Proof testing

Some structures, e.g., pressure vessels, pipes, etc. are loaded to stress levels greater

than the anticipated service loads to verify structural integrity. This loading, generally

hydrostatic, is called proof testing, and is intended to bo nondestructive.

7
2.5.5.

Traceability

Traceability refers to the ability to trace the history of the materials of construction

through records indicating original manufacturing procedures, test results, fabrication

sequence, etc. These records may be used to predict the remaining life of a structure, to help establish the reasons for any failures, and to determine if other similar structures

have a potential problem.

2.5.6. Verification testing

Accelerated total-service-life testing of completed documents or entire structures is

referred to as verification testing. It usually is only done v/hen there are numerous identical structures such as small pressure vessels, automobiles, insulation panels, etc. in which

actual service loads can be applied and the behavior verified by testing to failure.

2.6. In-Service Controls

Once the structure is put into service several controls should be implemented to prevent

fracture. These controls include: Monitoring the severity of service usage, periodic

inspection and maintenance, and approved repair procedures.

2.6.1. In-service monitoring

For certain structures, the time history of loads (and sometimes temperature) should be

recorded to verify that the load history assumed in design is at least as severe as the actual

load history. This is accomplished for USAF aircraft through the loads/environment spectra

survey and for commercial aircraft by instrumenting representative aircraft with flight load

recorders which monitor the principal load parameters, i.e., velocity, acceleration, and

altitude. In other structures (such as nuclear pressure vessels), time, temperature, and

pressure recorders are used to monitor service usage.

2.6.2. Periodic inspection

Many structures, particularly those susceptible to extensive fatigue and/or corrosion,

are subjected to periodic inspection to assure that structural damage is detected prior to

fai lure.

2.6.3.

Maintenance

A maintenance plan should be developed for many classes of structures to prevent damage

due to wear and corrosion that may enhance fatigue damage or otherwise lead to premature

fai lure.

8
2.6.4. Repair

When structural damage is detected, approved repair procedures should be used to assure

the structural integrity of the repaired region. In general, the repair procedure should

adhere to the code requirements governing materials and processes, such as welding consum- mables and post-weld thermal treatments.

3. THE CODE APPROACH TO FRACTURE CONTROL

Current approaches to fracture control vary widely from industry to industry.

Consideration of the numerous practices’ summarized in the Appendix reveals two general

approaches: 1) The design and fabrication codes, and 2) performance specifications. In the

code approach to fracture control, the design and fabrication of a particular structure

conform to a set of rules established for the general class of structures that includes the

particular structure, e.g., bridges, pressure vessels, and ships. The performance specification approach, discussed in section 4 is applicable to high performance structures where

the inefficiencies associated with general rules cannot be tolerated, e.g., airplanes and

spacecraft.

The code approach to fracture control is used for general classes of structures where

loading modes, design procedures, fabrication methods, and inspection procedures are fairly

uniform. A code is a set of rules established for a general class of structures by committees of interested and knowledgeable engineers. Examples are the ABS Rules for Shipbuilding,

the ASME Boiler and Pressure Vessel Code, and the AASHTO Standard Specifications for Highway

Bridges. Sometimes these codes, combinations of code segments, and/or additional rules are incorporated into Federal regulations, e.g., the U.S. Coast Guard regulations for shipbuilding or the Office of Pipeline Safety Operations regulations for pipeline construction.

Each of the elements of fracture control is considered in the context of the code

approach in the following subsections. The examples used to illustrate specific practices

are taken from the detailed summaries of fracture control practices presented in the Appendix.

3.1. Structural Design Conditions

The design conditions, analysis assumptions, and safety factors on material properties

used as the basis for structural design criteria vary from code to code depending on the

severity of the design conditions, the scope of the structural analysis, and the complexity

of the design. Variations from structure to structure within a code class are accounted for

by stating the design and analysis requirements in general terms. For example, the code may

require consideration of loads due to earthquakes, a negligible factor for most structures

but a primary requirement for others.

9
3.1.1.

Design 1 i fc

Design life is not a specific requirement in codes. Generally the procurement

specification for a code structure specifies the design life. The number of fatigue cycles

and the corrosion allowance are related to design life and accounted for by code rules.

3.1.2. Loads

Loads are conservatively estimated in the code approach. For many classes of structures,

there is a dominant load source, e.g., internal pressure for pressure vessels and piping and

centrifugal forces for steam turbine rotors. In more complex structures, the loads are estimated on a worst-case basis. For example, to estimate bridge loads, it is assumed that

each lane is occupied by a line of trucks that extends over the complete span. The most

approximate treatment of loads is the case of merchant ships where design is based on scaling

of known proportions of structural sections rather than on specific loadings. Superimposed

on the primary loads are thermal stresses, dead loads due to structural weight and, where

applicable, the loads duo to wind, earthquakes, ice, and snow.

3.1.3. Environment

The anticipated service environment is an important consideration in the design of many

structures. The minimum design temperature is particularly important for the selection of

steels with satisfactory toughness. The API 620 code for storage tanks specifies minimum

temperatures as a function of location. Elevated temperature exposure must be considered

because of reduced strength and creep as temperature and time at temperature increase.

Chemical environment is considered because of corrosion in containers for chemicals and for

structures that operate in adverse environments such as offshore structures.

3.1.4. Assumed initial damage

Initial damage assumptions are not generally required in codes. For example, the AASHTO

bridge code simply requires that all injurious defects be removed. Weld defects are permitted within acceptance limits defined by the codes, but the defects are sufficiently small so that they need not be considered in the design. In view of actual service experience with

large welded structures, this assumption may not be realistic.

Structures where initial damage is assumed include LHC ships and cargo tanks and gas

pipelines. LIIC ships are required to have a double bottom, double side shells, and transverse bulkheads to localize hull damage to a portion of the ship. LNC containment systems

arc designed to tolerate failure of the primary barrier either through the use of a secondary

barrier or through a 1 eak-before-break approach that has been approved for a specific pressure

vessel design. An initial damage assumption is not explicitly required for gas pipelines but

10
toughness requirements for the line pipe are generally established by the owner company such

that the material can arrest a running through-thickness crack.

3.1.5. Safety factors

Safety factors in codes are generally applied to material properties to arrive at acceptable design stress levels. For example, a factor of safety of 3 on burst strength is

required in the AIISI B31.1 and B31.3 piping codes, ASME Pressure Vessel Code Section VIII Division 2, and the API G20 Storage Tank Code. This is achieved by specifying that the

allowable stress in tension is the lesser of 1/3 of the ultimate strength or 2/3 of the yield

strength. Additional factors may be required for castings and weldments. In certain codes,

factors may depend on steel quality, type’of welding, degree of inspection, and production

form. For example, in API 620 a factor is applied to allowable stress that depends on steel

quality. A factor of 1 on pressure vessel steel, and a factor of .92 on structural steel.

The magnitude of the safety factor varies with the scope of the structural analysis,

the complexity of the design, and the possible consequences of failure. For pressurized com- ponents, some factors on burst strength are. 4 for ASME Section VIII, Division 1 Pressure

Vessels; 3 for ASME Section VIII, Division 2 Pressure Vessels which require a more thorough

analysis and inspection than Division 1 vessels, and approximately 2 (allowable stress is

72 percent of the yield strength) on oil pipelines. For gas transmission pipelines, the

allowable stresses are based on the specified minimum yield strength reduced by factors that

range from 0.4 to 0.72 depending on the population density and degree of development in the

vicinity of the pipeline, i.e., stress levels are reduced as the consequences of failure

are increased.

3.2. Materials

In the code approach to fracture control, materials that have been used successfully for

years in similar structures or that have undergone extensive testing generally are the only

ones used. Before new materials can be specified for structures that are designed according

to codes, the code writing bodies must be satisfied (on the basis of material and structural

tests) that these materials will indeed perform satisfactorily.

3.2.1. Specifications

Materials of construction must conform to the requirements of material specifications

listed in the applicable code. In general, unlisted materials may bo used providing the

material is certified to meet all the requirements of a listed material specification, and

its use is approved by either the cognizant code committee (e.g., ASME Pressure Vessel Code)

or by the purchaser (e.g., API 620 Storage Tank Code). Materials are listed by specification

and by grade, i.e., not all grades for a given specification may be used. Usage is further

restricted by notes to avoid improper application of the material.

11
ASTM material specifications are used in many of the codes, including the ANSI B31 piping codes, the API 620 storage tank code, and the AASHTO bridge code. ASME material

specifications are used in the ASME Boiler and Pressure Vessel Code. The ASME and ASTM

specifications are often related and carry similar numbers, e.g., ASME SA-240 specification

for stainless steels is similar to ASTM A 240. Other material specifications include the

ABS ship steels, and the API specifications for steel line pipe.

Many of the ASTM and ASME material specifications are for product types and cover many

grades. For example, ASTM A 240 is the Standard Specification for Heat-Resisting Chromium

and Chromium-Nickel Stainless Steel Plate, Sheet, and Strip for Fusion Uelded Unfired

Pressure Vessels. It includes many types of stainless steel suitable for this application.

Wherever possible, types are designated by numbers conforming to grade specifications put out by other organizations. In the case of A 240, grades are specified by the AISI designation such as 302, 304, 304L, etc. Grades not covered by the AISI designation system are given ASTM-desi gnati ons such as XM17, a nitrogen-strengthened CK-Ni-Mn stainless steel.

Similarly, ASTM A 131 is the standard specification for structural steel for ships and the

grade designations are related to the ABS grades of ship steel.

Some codes, such as the API RP 2A code for offshore structures, use many types of material specifications. The approved materials list in API RP 2A includes Canadian (CSA),

German (DIN), British (BS), and International (ISO) designations and several types of American Speci f i cati ons--ASTM, API, and ABS.

3.2.2. Properties

The material specifications specify the minimum tensile properties that are used as the

basis for determining allowable stress values. Usually minimum values for tensile strength,

0.2 percent offset yield strength and elongation are specified. Sometimes a range of tensile

strength is specified to avoid brittle behavior associated with higher strength levels.

Other properties sometimes specified include minimum reduction of area, maximum hardness,

and minimum bend ratios (bend diameter to thickness).

Properties used for fatigue and fracture analyses are included in certain codes which

require these analyses. The ASME Section VIII, Division 2 Rules for Pressure Vessels require

a fatigue analysis for vessels subject to fatigue cycling that exceeds specified conditions.

The fatigue data used in the analysis are summarized in fatigue design curves applicable to broad classes of materials. The ASME Section XI, Division 1 Rules for Inservice Inspection

of Nuclear Power Plant Components provide a fracture mechanics analysis procedure for

determining the acceptability of flaws that have been detected during in-service inspection.

The analysis is based on measured material properties applicable to the part of interest or on conservative representations of fracture toughness and fatigue crack-growth data. The

material property data are applicable to the most common grades of nuclear vessel steels.

12
The lower bound fracture toughness data are presented as a function of temperature indexed

to the ni 1 -ducti 1 ity transition (NOT) temperature of the material and are referred to as the

reference fracture toughness (Kj|^) curve. The NOT, measured at the time of purchase,

is shifted to account for irradiation during service. Upper bound fatigue crack-growth data

are given for buried flaws and for surface flaws where the growth rates are accelerated due

to environmental effects.

3.2.3. Toughness requirements

To assure satisfactory fracture resistance, codes generally specify minimum levels of

Charpy V-notch (CVH) impact toughness for low- and intermediate-strength steels. Nonferrous

materials such as aluminum and copper alloys do not exhibit a ducti le-to-brittle transition,

and, thus, are not usually toughness tested. Toughness requirements for most types of

structures are based on prior experience, however, an increasing number of fracture criteria are being derived on the basis of fracture mechanics considerations as is the case for

bridges, gas pipelines, and nuclear pressure vessels. The various requirements are summarized below.

The toughness requirements for pressure vessels (ASME Section VIII) and piping (ANSI

B31.1 and B31.3) are a function of strength level, deoxidation practice, and heat treatment.

Minimum CVfl values for carbon and low alloys steels are specified in terms of average absorbed energy at a specified temperature. 17. 7J (13 ft lb) for strengths of 448 MPa (65 ksi)

and lower, 20. 4J (15 ft lb) for strengths ranging from 448-517 MPa (65 to 75 ksi), and 27 .2J

(20 ft lb) for strengths ranging from 517-655 MPz (75 to 95 ksi). The toughness requirements

for higher strength steels, steels heat treated to enhance strength, and stainless steels are specified in terms of notch ductility as measured in a CVN test, .38 mm (.015 inch) lateral

expansion is required. The test temperature for all grades is the design temperature or the

minimum temperature at which pressure will be applied, whichever is lower. A lower test

temperature must be used when subsize tests are conducted and the subsize width is less than

80 percent of the material thickness.

The toughness requirements on ship steel plates depend on the grade, plate orientation,

and strength level. The steels used in low stress and moderate temperature locations.

Grades A, B, and AH, do not have any fracture toughness requi rements . Steels used for crack

arrestor strakes, for low temperature applications, or for locations otherwise deemed critical must meet toughness requirements specified in the ABS rules. The CVN toughness requirements range from 19-34J (14 to 25 ft lb) depending on strength level and orientation. Tost

temperature and frequency of testing depend on the grade. For example, grades D and DH are tested at -200C, 3 specimens from each 36.4 Mg (40 tons); and grades E and EH are tested at -40 C, 3 specimens from each plate. For many applications, it is permissible to use grades

DS or CS, which do not require testing, in place of grades D or E, respectively.

13
Experience has shown that grades DS and CS consistently meet the toughness requirements

for grades D and E, respectively, due to the controls on chemistry, deoxidation practice,

and heat treatment. The idea of using metallurgical controls to assure toughness in place of CVn requirements is unique to the ABS rules. This precedent has potential value for other

codes because the metallurgical controls contribute directly to toughness whereas the Charpy

requirements simply measure toughness.

The CVn toughness requirements discussed above are conducted either at the minimum

service temperature (e.g., the ASME approach) or at an arbitrarily low temperature (e.g.,

ABS grade E) under impact loading conditions. An alternative approach is to use actual

loading rates and factor in the various design features pertinent to the particular design.

This approach is used in the AASHTO bridge code. Here, the test temperature is increased by

an amount equal to the shift in transition temperature as the loading rate is decreased from

the impact rate used in CVM tests to the maximum loading rate expected in bridges. The

resulting CVN impact toughness requirements are 34J (25 ft lb) at EPC (7QOF) above

the minimum service temperature for low- and intermediate-strength steels.

3.3. Design and Analysis

Design is the arrangement and proportioning of structural members to withstand specified

loads whereas analysis is the determi nati on of the stress distribution in given structural

members. Both procedures are based on analytical methods of stress analysis, ranging from

strength of materials techniques to finite-element analysis using large computers. Obviously

the functions are closely related.

3.3.1. Design for fracture control

Good design practices are essential to fracture control. The most common methods of

fracture control used in design are to lower the design stress, to improve the design of

details, and to provide redundant load paths. Another design practice that is very helpful,

but less formalized in the codes, is to provide the accessibility needed to facilitate

fabrication, erection, and inspection.

The use of lower design stresses has evolved as a means of reducing the incidence of

fracture in many codes. The approach was used in the boiler and pressure vessel industry

where numerous failures occurred in the early 1900's. Through the years, the allowable

stress was lowered (as a percentage of minimum tensile strength) thereby greatly decreasing

the number of failures in succeeding years. The approach is basic to most codes. For example, the ASME code for pressure vessels limits the allowable stresses in welds in accordance

with joint location, joint design, and degree of inspection. The API code for offshore

structures requires lower stresses for waterline braces because of corrosion fatigue

considerations. The ANSI gas pipeline code requires lower stress as a function of geographic

location, i.e., lower stresses where the consequences of failure are greater.

14
The elimination or reduction of stress concentrations and structural discontinuities

is an effective means of fracture control. Cracks usually start at specific design details

(e.g., connections, cutouts, stiffeners, etc.). Considerable improvement in fatigue behavior

can be obtained in smoothing the flow of stress at details. The most notable examples to illustrate the significance of poor design details are the Liberty Ships of World War II. The majority of fractures in these ships started at the corners of square hatch cutouts at the top of the shear strake--desi gn practices that were subsequently eliminated in the ABS

rules

Design detail has the greatest importance in fatigue critical structures. For example,

the allowable fatigue stress range in the AASHTO bridge code varies from 110 flPa (16 ksi)

for butt wolds ground flush to 17.2 MP'a (2.5 ksi) for an as-welded cover plate whore there

is an abrupt change in section. Similarly, the AWS fatigue curves for offshore structures

vary by more than a factor of 10 on stress, depending on the particular structural detail.

The use of multiple load paths to provide structural redundancy is an effective moans

of preventing fracture in structures such as bridges, offshore structures, and ships. This

practice is encouraged in the AASHTO bridge code by designating as fracture critical those

tension components that are not redundant and whose failure might result in the collapse of

the bridge. Ships are not normally fail-safe, but the IMCO code for LNG carries (adopted

by ABS and USCG) requires double side shells, a double bottom, and transverse hull heads to separate the cargo spaces--provi si ons that provide multiple load paths.

3.3.2. Standard details

Standard design details and associated analysis procedures are specified in most codes

to assure continued use of practices known to give satisfactory performance in other structures. notable examples are weld joint designs, welded connections, and rei nforcoment of

openings. Standardized design practices are particularly well developed for design codes

for pressurized containers such as the ASME pressure vessel code, the AtJSI piping codes, and

the API storage tank code.

3.3.3. Analyses

Design codes for most classes of structures require the analytical determination of the

stresses and deflections caused by the imposed loads and the determination of their signifi- cance with respect to strength, stiffness, and stability criteria. To perform satisfactorily

the structure must withstand the service loads without yielding, deflecting excessively or buckling. After designing to these criteria, the code may require that the fracture and

fatigue characteristics of the structure be evaluated. Because many failures of structures

or structural members occur by fatigue or fracture, it is desirable to consider these failure

modes during initial design when it is easier to make changes, e.g., in the geometry of cer- tain details.

15
Codes that require fatigue analysis include the ASME Pressure Vessel Code Section VIII,

Division 2, the AWS Structural Welding Code (offshore structures), the AASHTO Bridge Code,

and to a lesser extent, the ANSI B31.1 and B31.3 piping codes. Two types of structures may

require a fracture mechanics analysis: 1) LNG shipboard containment systems designed to pressure vessel requirements and not requiring a secondary barrier, and 2) nuclear pressure

vessels when in-service inspection reveals flaws that exceed original acceptance requirements.

3.3.4. Fatigue control

Fatigue control in the code approach generally is based on the prevention of crack

growth by using S-N curves to prevent initiation of a crack. The analysis is based on extensive testing, a conservative estimate of the loads, a fairly accurate stress analysis,

and large factors of safety to account for material and fabrication variability. Design of

details can affect the allowable stress range significantly, as was noted in section 3.3.1.

S-N curves usually are obtained in one of two ways:

a) Results of smooth polished test specimens are used to obtain the basic fatigue

properties of the material. The stress range is divided by a fatigue stress concentration

factor to estimate the fatigue lives for a particular local geometry (e.g., as received sur- face, notches, weldments, etc.). This "derived" S-N curve is then used to estimate the life

of a structure at a particular stress range, with appropriate factors of safety on life.

b) Results of actual fabricated members are used to obtain the fatigue properties

of the material in the actual service condition. Obviously there is no need to use any

stress-concentration factors to further reduce these results because the geometrical factors

(e.g., stress concentrations) are an integral part of the test specimens. The AASHTO bridge

specifications follow this approach by categorizing details from A to E. Category A refers

to smooth plates, category B to butt welds with reinforcement ground smooth, and categories

C, D, and E refer to weldments with increasing severity of stress concentration. For each

category from A to E, the code allowable fatigue stress level for 2,000,000 load cycles is reduced from 110 MPa (16 ksi) to 17.2 MPa (2.5 ksi).

Conventional procedures for estimating structural fatigue-life expectancy are based on the establishment (through appropriate material or structural tests) of a life estimate as described above. After obtaining these results, a somewhat arbitrarily chosen factor

(usually ranging from 2 to 5) is applied to reduce this estimate to a presumably safe

service life. The size of this factor usually is based on judgment or probability analysis

to account for the variability or scatter associated with fatigue testing.

16
3.4. Quality Assurance

Quality assurance is the system of controls used to ensure that the as-fabricated

structure conforms to the code requirements. For many structures built to code requirements,

the Q/A system can be complicated by the use of different organizations to design, fabricate,

erect, inspect, and use the structure. Many of the codes clearly define these responsibilities, as discussed below.

3.4.1. Material procurement controls

As discussed in section 3.2.1., a variety of material procurement specifications is used in the various codes. The most common types are the ASTM specifications. The ASTM

specifications have requirements on manufacture, heat treatment, chemistry, mechanical

properties, dimensional variations, test specimens and methods, quality, repair by welding,

marking, inspection, and test reports.

For many products, including structural and pressure vessel steels, the purchaser has

rights of inspection. For example, ASTM A6 (structural steels) and ASTM A20 (pressure vessel

plates) specify: "The inspector representing the purchaser shall have entry, at all times

while work on the contract of the purchaser is being performed, to all parts of the

manufacturer's works that concern the manufacture of the material ordered. The manufacturer

shall afford the inspector all reasonable facilities to satisfy him that the material is

being furnished in accordance with the specification."

The manufacturer reports all test results, including the chemical analysis of the heat,

to the purchaser when required and requested. Conformance to the applicable specification

requirements is certified on the mill test reports. Subsequently, the purchaser may perform

a product analysis on all or any part of the order and has the right to reject the material

if it fails to meet the chemistry requirements of the procurement specification.

3.4.2. Fabrication and processing controls

The fabrication and processing controls comprise a major part of most codes. Good

workmanship is essential to fracture control in code structures because of the uncertainties

of inspection during fabrication and erection and because of the limited inspection most

structures receive during service. Each of the codes establishes requirements and/or

recommended practices for the major fabrication and processing operations applicable to that

class of structures, e.g., welding, forming, and heat treatment.

Detailed consideration is generally given to welding and associated activities. The

general approach used in most codes to assure weld integrity is to specify requirements for

workmanship, for qualification of materials, procedures and welders, for weld quality,

inspection and repair welding, and for post-weld heat treatment.

17
In addition to the design and fabrication codes, there are codes that relate specifically

to welding e.g., API Standard 1104--Standard for Welding Pipelines and Related Facilities,

Section IX of the ASME Boiler and Pressure Vessel Code--Wel di ng and Brazing Qualifications,

and the AIJS Structural Welding Code--Steel. The qualification requirements of ASME Section

IX are used for many types of pressure-containing weldments, e.g., by the other sections of

the ASME code, by the AIISI B31.1 and B31.3 pressure piping codes, and by the API 620 Storage

Tank Code.

3.4.3. Inspection

Many of the codes distinguish between examination, a quality control tool, and inspection,

a proof of compliance to code and contract requirements. Examinations are the quality control functions performed by personnel employed by the material supplier, fabricator, or erector. Inspections are the proof-of-compl i ance functions performed for the owner by the

authorized inspector. Codes generally specify the qualifications of the authorized inspector.

The inspector is permitted free access to all parts of the site whore manufacture of the

material or fabrication and erection of the structure takes place. The duty of the inspector

is to conduct all tests and inspections necessary to be satisfied that all code and contract

requirements are met.

Inspections common to most codes include verifications that 1) materials conform to the

applicable specifications, 2) welding procedures and welders are qualified, 3) heat treatments are properly performed, 4) nonconforming materials and welds are properly repaired and

re-examined, 5) required NDE and tests are performed and the results are acceptable, and

6) dimensional tolerances and arrangement conform to the engineering drawings.

3.4.4. Verification testing

Proof testing is used as a quality control tool for many classes of structures,

particularly pressure vessels and piping. For pressure containment structures, hydrotesting

or pneumatic testing generally involves loading the completed assembly to a pressure level

above that anticipated in service. The proof-stress factors (proof-pressure/design pressure)

range from 1.1 to 1.4, depending on the type of structure, the intended service, and the

testing medium. Oil pipelines, LNG storage tanks, and pressure vessels are hydrotested to

1.25 times the design pressure. If a pressure vessel cannot be filled with water, it is pneumatically tested to 1.15 times the design pressure. The proof-stress factors for gas

pipelines vary form 1.1 to 1.4 depending on location. Piping subject to low internal pressures is simply leak tested, e.g., gas pipelines with stresses below 30 percent of yield

strength or oil pipelines with stresses below 20 percent of yield strength.

18
3.5. In-Service Controls

Many of the codes are limited to the design and fabrication requirements and do not cover in-service controls. Notable examples are the ASME Section VIII Pressure Vessel Code,

ANSI B31.1 and B31.3 Pressure Piping Codes, and the API 620 Storage Tank Code. Extensive

coverage is given to in-service controls in the following cases: The ABS Rules for

Shipbuilding, the ANSI B31.4 and B31.8 codes for oil and gas pipelines, the API RP 2A

Recommended Practice for Offshore Platforms and the ASME Section XI Rules for Nuclear Power

Plant Components. In those cases where the codes do not cover in-service controls, the owner

and in some cases, local authorities, may require periodic surveys and maintenance. When

repairs are necessary, the materials and procedures may have to conform to the requirements

specified in the code for initial construction.

In pressure containment structures, time histories of pressure and temperatures, when

applicable, are generally recorded to monitor service usage. For complex structures such as bridges, ships, and offshore platforms, periodic surveys are preferred as discussed in

section 3.5.2. Pressure monitoring for oil pipelines is required to assure that at any point

in the piping system 1) the maximum steady-state operating pressure and static head pressure

do not exceed the specified pressure ratings, and 2) the pressure rises due to surges do not exceed the internal design pressure by more than 10 percent. Similar requirements are generally involved in all pressure containment structures.

3.5.1. Periodic inspection

Periodic inspections are required for most classes of structures and are known as patrol

programs, surveys, and in-service inspections. For pipelines, the operating company maintains periodic patrol program to observe surface conditions on and adjacent to the pipeline

right-of-way, indication of leaks, construction activity other than that performed by the

operator, and any other factors affecting the safety and operation of the pipeline. Patrols

are required at relatively short intervals, e.g., two weeks for oil lines and one week for

LPG lines in developed areas. Annual surveys are required for specified locations in offshore platforms (splash zone and critical above-water members), and ships (steering systems,

specified valves, coamings, hatch covers, and locations particularly liable to rapid

deterioration). Additional surveys are required for the remainder of the ship or offshore

structure; special periodic surveys are scheduled for ships at four-year intervals and for

offshore structures at five-year intervals or following exposure to severe loading conditions.

In-service inspections of nuclear power plant components are scheduled at intervals ranging

from 3 to 40 years, depending on the particular inspection program, the component class, and

the operating experience. The scheduling generally coincides with plant outages due to refueling or maintenance.

19
3.5.2. Maintenance and repair

The oil and gas pipeline codes (ANSI B31.4 and B31.8) are the only codes that explicitly

treat maintenance. The pipeline operator is required to have detailed plans and instructions

for maintenance of the system, including corrosion control, right-of-way maintenance, and

procedures for maintenance and repair of the pipeline, including valves, pump stations,

terminals, and tank farms.

4. THE PERFORMANCE SPECIFICATION APPROACH TO FRACTURE CONTROL

The performance specification approach to fracture and fatigue control is used for

high-technology weight-critical structures where structural safety and reliability are essential. The main feature of this approach is the requirement that crack-like flaws of

specified size must be assumed to exist in worst-case locations throughout the as-fabricated

structure. Parts deemed susceptible to crack growth and fracture are identified as fracture-critical and are subject to the requirements of a comprehensive fracture control

plan. The approach has been applied by the Air Force to aircraft, by NASA to spacecraft and

missiles, and by the Navy to hydrofoils.

The performance specification approach is based on 1) a detailed knowledge of the

anticipated operating conditions, particularly the service load history; 2) a thorough

evaluation of the selected materials and of representati ve joints and components; 3) a complete structural analysis of the design, including stress, fatigue, and fracture analyses,

4) a comprehensive quality control program to assure that the as-fabricated structure has the

properties and quality levels assumed in design; and 5) an effective in-service program of

usage monitoring, maintenance, inspection, and repair. The following discussion emphasizes

the approaches to each of the elements of fracture control taken by the Air Force in the

Aircraft Structural Integrity Program, which is the outstanding example of the performance

specification approach.

4.1. Structural Design Conditions

Structural design conditions are generally stipulated in the procurement contract. The

conditions may be explicitly stated, as is generally the case for service life, e.g., "the

design life shall exceed 20 years." More commonly, the conditions are stipulated indirectly

through performance requirements (e.g., a 7g aircraft at specified velocity and altitude),

planned operational usage (e.g., 4000 flights of specified mission profiles), and referenced specifications. Early in the design stage, the contractor must develop explicit

criteria consistent with the contract and specification requirements which are subject to approval by the contracting agency.

20
Success of the performance specification approach is dependent upon a valid and complete

set of structural design conditions. The basis for the structural design criteria for USAF

aircraft is briefly summarized below and given in more detail in the Appendix. Maximum design

loads are based on the specified performance requirements. The fatigue loads spectrum is

based on planned operational usage and the load exceedance data of MIL-A-8866B. The chemical and thermal environment is characteri zed in terms of intensity, duration, and

f requency-of-occurrence of all exposures based on planned operational usage. Initial damage

assumptions are based on the requirements of MIL-A-83444. Safety factors on static strength,

fatigue life, and safe crack-growth intervals are based on the applicable military

specifications.

4.2. Materials

In the performance specification approach, materials and processes are selected by the

contractor on the basis of prior experience, trade-off studies to optimize weight and cost,

and requirements for system safety and reliability. There is not a set list of materials

that limits material choice as in the code approach, but the need for extensive characterization of the mechanical properties tends to result in the choice of materials previously

used. However, the selected materials and processes are subject to approval by the procuring

agency

The properties of the selected materials must be thoroughly characterized in the

appropriate product forms and thickness ranges. The influence of processing on the material

properties in the as-fabricated structure must be assessed. Several sources of data are available for most materials, including handbooks and data from previous programs available

to the contractor and to the procuring agency. Gaps in the data base are filled by tests

conducted by the contractor.

Material procurement and processing specifications are prepared for each material,

product form, and material /process combination selected for usage in fracture-critical parts.

These specifications should invoke controls that are sufficient to preclude the use of materials in the structure that have properties inferior to those assumed in design. The specifications are prepared by the contractor and approved by the procuring agency.

4.3. Design and Analysis

The role of the design and analysis functions is to integrate materials and structures

technology into the design of safe, functional, and economical structures. The design should

incorporate the results of the structural analyses of strength, rigidity, fatigue life, and

fracture resistance. Careful attention to design detail is essential because fatigue cracks

initiating at stress concentrations are perhaps the most likely source of failures.

21
The two principal design options for providing damage tolerance are the fail-safe and

the safe-life approaches. In the fail-safe approach, fracture safety is provided by structural redundancy. Inspectabi 1 i ty is essential to fail-safe design to assure detection of the

initial failure before the damage spreads beyond control. In the safe-life approach, the

stress levels are limited such that a flaw should not grow to critical size during the life

of the structure. When sufficient i nspectabi 1 i ty exists, this latter approach can be modified to provide for a safe inspection interval--at which time the structure is inspected and

certified for another interval of safe operation.

Extra caution is required in the design and analysis of structural joints--both

mechanically fastened and welded. Joints are the areas of greatest uncertainty because of

stress concentrations, fabrication defects, residual stresses, and questionable load paths.

Design concepts should be evaluated and analysis procedures should be verified by conducting

static strength and fatigue tests on representative joints. Care should be taken in locating

joints to avoid high-load areas and compounding stress concentrations whenever possible.

A complete structural analysis of the design should be conducted on a timely basis to permit iteration of the design/analysis sequence and optimization of the design. Stress

analysis is used to verify airframe strength, to provide stresses for fatigue and fracture

mechanics analyses, to identify fracture critical components, and to select components and

loading conditions for structural tests. Fatigue analysis is used to determine the stress

limits that must bo imposed throughout the structure to avoid fatigue failure during the

specified service life. Fracture mechanics analysis is used to determine the stress limits

necessary to assure that a preexisting flaw of assumed initial size will not grow to critical

size during the specified service life, or in the case of inspectable structures, during the

interval of service between inspections. Fail-safe analysis is used to verify that failure

of a single member will not cause complete structural failure and further to verify that the

fatigue life of the remaining structure is sufficient to permit detection and repair of the

failed member before total structural failure occurs.

4.4. Quality Assurance

The quality-assurance program is the system of controls that ensures that the as- fabricated structure conforms to the design requirements. The program should assure quality

throughout the design, fabrication, installation, and service life of the structure. Each

organizational element contributes to quality assurance e.g., engineering assures the

correctness of drawings and specifications;, inspection verifies dimensional and quality

requirements, etc.

In the performance specification approach, the engineering drawing should be used to transmit the fatigue and fracture control requirements relative to materials; processing,

fabrication, and inspection of specific parts. Fracture-critical parts should be so identified on the drawing. Notes on the drawing should be used to invoke the material procurement

22
material processing specifications, fabrication controls, and inspection and corrosion

protection requirements. Other elements of quality assurance such as traceabi 1 i ty , proof

testing, and verification testing should be applicable to the total system--! nstead of to individual parts.

4.5. In-Service Controls

An effective in-service program of usage monitoring, maintenance, inspection, and repair

is essential to the success of the performance specification approach to fatigue and fracture

control. The duration and severity of usage should be monitored to assure that service

operations do not exceed design limits. Safe-usage intervals should bo determined on the

basis of fatigue, fracture mechanics, creep, wear, and corrosion control considerations.

After completion of a usage interval, periodic inspection, maintenance, and repairs should be

performed to the extent necessary to assure satisfactory performance during the next usage

i nterval

5. FRACTURE CONTROL CONCEPTS FOR NAVAL SYSTEMS

The purpose of reviewing fracture control practices used in a wide range of industries

to identify promising concepts that could be developed for Naval use. In this section,

selected concepts are discussed. The relative importance of the various concepts and the

specific applicability are not addressed; the purpose is simply to identify those industry

practices that merit consideration by the Navy for further development.

5.1 Steel Toughness Requirements

The establishment of toughness requirements is a difficult task for all structures where

brittle fracture is a credible failure mode. Innovative approaches used in specific codes

that may have broad applicability are described below.

5.1.1. The strain rate shift

The rate of loading (slow, intermediate, or impact) can have a significant effect on the

fracture toughness of structural steels. This behavior is shown in figure 1 for a 345 MPa

(50 ksi) yield strength structural steel. Note that the toughness transition for

intermediate-loading rate occurs over 80OC below that for impact loading. The transition

temperature for slow-loading rate is even lower. If the service loading rates are intermediate

(as has been shown to be the case for bridges) or slow, satisfactory notch-toughness levels

can be obtained well below the dynamic transition behavior, i.e., below the NOT temperature.

For Navy structures subjected to slow or intermediate rates of loading, this approach

may be viable. However it should be emphasized that other factors such as service experience.

23
design and fabrication controls, and actual fatigue tests of welded beams were considered

before AASHTO established their material specification on the basis of the loading rate shift.

5.1.2. Metallurgical controls

The ABS rules for ordinary strength steels include two grades that require toughness

testing, grades D and E. For most applications, it is permissible to use grades DS or CS,

which do not require testing, and consequently cost less, in place of grades D or E,

respectively. The reason for deleting test requirements is that experience has shown that

grades DS and CS consistently meet the toughness requirements for grades D and E, respectively, due to controls on chemistry, deoxidation practice, and heat treatment. The idea of

using metallurgical controls to assure toughness in place of Charpy impact requirements has

potential applicability to Naval specifications. The metallurgical controls contribute directly to toughness whereas the test requirements simply measure toughness.

5.1.3. Toughness saturation

The toughness requirements for line pipe have been extensively studied by AISI, AGA, and

British Gas. The results indicate that the notch toughness (e.g., as measured by Charpy

V-notch or drop-weight tear tests) required to arrest a running crack is simply related to the hoop stress level and the pipe dimensions. Increasing the toughness to higher levels

does not improve performance; i.e., the toughness is saturated. Similar relationships have

been developed to control crack initiation. That is, above a certain toughness level, as shown in figure 2, critical crack size is flow-stress dependent and independent of toughness.

Figure 2 shows the relationship between flaw size and toughness for a given pipe geometry

and stress level using relationships developed by Battelle for the AGA. In this figure,

increasing the toughness above 70J (50 ft lb) has no further effect on critical flaw size.

Similar curves can be drawn for any grade or size of pipe operations at the specified stress

level. In summary, meaningful and quantitative toughness values can be specified above which

failure is independent of toughness. Since the values vary with pipe dimensions and stress

level, they are not included in the API pipe specifications, but are specified in procurement

specifications for specific pipelines.

5.2. Weld Quality Standards

Weld quality standards are generally established on the basis of workmanship

considerations, i.e., quality levels that a qualified welder can consistently meet when the

proper consummables and equipment are used and the welding conditions (weather, joint

accessibility, etc.) are satisfactory. Workmanship standards can be more restrictive than

necessary to achieve structural integrity in the weld. Two approaches to weld quality based

:4
on fitness-for-service considerations have recently been developed: One for as-welded

structures and the other for cases where defects have been found during periodic in-service

inspection.

5.2.1. Fitness-for-service

In 1976, alternative weld quality standards were developed for the girthwelds of the

trans-Alaska oil pipeline on the basis of a fitness-for-service evaluation. In this evaluation, allowable flaw size curves were calculated using fracture mechanics models that

relate flaw size to applied stress and material toughness. Parameters for the analysis were

the worst-case operating stresses and .the lower bound material properties. In addition,

safety factors were applied to the calculated flaw sizes to conservatively account for

uncertainties in the analytical models and the inspection methods. The end results of the

evaluation were curves of allowable flaw length plotted as a function of the flaw depth

estimated from radiographic inspection records. Flaw sizes above the curve required repair,

and those below the curve were acceptable.

The alternative standards permitted acceptance of weld defects that were considerably

longer than those permitted in the API 1104 code. As a result of this work, the code writing

body and the regulatory authorities (Office of Pipeline Safety Regulation) have been considering

revisions to the code (API 1104) and the regulations (49CFRI92 and 49CFRI95) to permit use of

the fitness-for-service approach in the future.

5.2.2. Assessment of flaws detected during in-service inspection

Section XI of the ASME Boiler and Pressure Vessel Code provides procedures for determining the acceptability of flaws detected during in-service inspection that exceed the size

limits applicable to the as-fabricated vessel. The procedures, summarized in Appendix A of

Section XI, "Analysis of Flaw Indications," are based on the principles of linear elastic

fracture mechanics. They are applicable to ferritic steels in thick sections (^ 102 mm,

4 inch) with specified minimum yield strengths less than 50 ksi (345 MPa) and to structural

configurations that have simple geometries and stress distributions. Procedures are given

to size the flaw, represent the flaw as an elliptical (or semi-el 1 iptical ) crack, calculate

the stress intensity, estimate material toughness including irradiation effects, account for

fatigue crack growth and conduct the analyses for the various operating conditions. The

results of the analyses are minimum critical flaw sizes for normal and upset conditions. The

calculated flaw sizes and flaw evaluation criteria are used to determine if continued operation without repair of the observed flaw indication is acceptable.

25
5.3. Aerospace Practices for High Performance Structures

Several practices commonly used in the design and evaluation of airplanes and spacecraft

may be useful for high performance Naval structures.

5.3.1. Loads

The USAF has a continuing effort to characterize the loads encountered by aircraft during

service. The detailed consideration given to loads is essential to the design of aircraft

because stress levels throughout the airframe are limited by fatigue; i.e., higher stresses

could lead to fatigue failure. In contrast, Naval ships are designed to withstand massive

overloads due to combat operations or extreme sea states. Consequently, the routine cyclic

loads are of lesser importance. Exceptions occur in advanced systems that are subjected to severe cyclic loading during normal operations, e.g., struts and foils in hydrofoil systems

and the 1 oad-transfer components in controllable-pitch propellers. For these exceptional

cases, detailed knowledge of the operational loads is essential to rational design.

Maneuver loads are statistical ly character! zed in terms of exceedance curves for each

mission segment, i.e., ascent, cruise, air-to-air combat, etc. Each exceedance curve indi- cates the number of times a given level of acceleration is exceeded. Ai rframe loads can then be computed for the velocity, altitude, gross weight, and configuration of the airplane,

during that mission segment. The number and magnitude of loads for each mission segment are computed on the basis of the planned operational usage of the aircraft. The grand total of

all the loads is the maneuver loads spectrum for the aircraft.

The gust loads spectrum is derived from the continuous turbulence model specified in

MIL-A-8861. The atmospheric turbulence environment is simulated as a continuous random

process. A power spectrum of the turbulence represents the forcing function in the frequency

domain and a dynamic analysis is used to determine the load response of the flexible airframe.

The response characteristics are a function of the velocity and configuration of the aircraft.

The severity of the turbulence is primarily a function of altitude. The sum of all the loads

duo to the airframe response to the power spectrum for each mission segment is the gust loads

spectrum of the aircraft.

Additional loads analyses are conducted to account for cabin pressurization, taxi and

ground handling loads, operation of control surfaces, and combined gust and maneuver loads

during low-level contour operations.

5.3.2. Full-scale testing

Full-scale testing is an essential part of the USAF Airframe Structural Integrity

Program. Similar tests are not normally required for ships because of obvious practical

26
limits. Normally, ships are simply too big, too expensive, and too few to justify testing a complete unit to destruction, flowever, there are some ships and, more commonly, subsystems

that may benefit from full-scale testing. Notable examples are, again (as in

subsection 5.3.1.), the struts and foils of hydrofoil ships and the controllable pitch propeller system. The full-scale tests generally conducted by the USAF on a new aircraft are described below.

Static tests are tests conducted on an instrumented airframe that simulates the loads

resulting from critical flight and ground handling conditions. The tests are used to verify

the stress analysis results by correlating strain survey results with analytical predictions

and to verify that the design ul timate -strength of the airframe exceeds specification

requi rements

Fatigue tests are tests conducted to evaluate the capability of the airframe to withstand

repeated applications of the fatigue loads spectrum. Cycling is continued for a minimum of two service lifetimes or until the economic life is exceeded, i.e., until repairs are so frequent or so major that the airframe is not worth fixing. The results are used to verify

that the economic life exceeds the design service life, to identify fatigue critical components, and to provide a basis for establishing special inspection and maintenance requirements.

Damage-tol erance tests are a relatively new requirement for USAF aircraft. A series of

tests are conducted on full-scale articles with specified levels of induced damage, usually

fatigue cracks in critical locations. The size of the induced damage and the applied loads

approximate the initial damage conditions and residual strength requirements used in design.

The results verify the damage tolerance of the fracture critical parts and the ability of

the analysis to predict structural performance.

Additional tests are conducted in operating aircraft that verify airframe safety without

requiring destruction of the airframe. These include loads surveys, dynamic response tests,

sonic response tests, flight vibration and flutter tests, and rigidity tests. The test

philosophy and certain of the techniques may be applicable to Naval ships during sea trials.

5.3.3. Fracture critical parts

In the performance specification approach, only parts designated as fracture-critical

must conform to the requirements of the fracture control plan that exceed normal design

requirements. For the space shuttle program, NASA requires that fracture-critical parts be

identified on the basis of criticalness to structural fl i ghtworthi ness and susceptibility to

cracking or fracture. For USAF aircraft, f racture-cri ti cal parts are defined as those members whose failure could result in loss of the aircraft and whose stress levels are limited

by the fracture mechanics analysis requirements. In summary, fracture-critical parts are identified on the basis of the consequence and likelihood of fracture.

27
Identification of fracture-critical parts is a useful exercise to limit over-application

of fracture control requirements and to focus attention on those parts most likely to cause fracture problems. Dravjing on the two Maval examples cited previously the performance

specification approach may bo limited to the controllable-pitch propeller instead of the

entire frigate, or to the struts and foils instead of the complete hydrofoil.

6. SUMMARY COMMEIITS

The prevention of fracture has always been a primary consideration in engineering design.

The many practices used in a variety of industries to prevent fracture have been reviewed.

Two general approaches are used; The code approach and the performance specification approach.

The code approach is used for nearly all commercial construction and is based on minimum

requirements on design, materials, fabrication, and quality assurance that are applicable

to a wide variety of configurations within a general class of structures, e.g., bridges,

pressure vessels, and merchant ships. The performance specification approach is used for

high performance structures where the inefficiencies associated with general codified rules

cannot be tolerated, e.g. aircraft and space vehicles.

Certain practices associated with the two approaches may be of potential value to the

Navy. The codes, which are continuously updated to incorporate potential improvements in

industry practice, contain many f racture-control concepts that may be less costly than the

practices used for Naval systems. The performance specifications used by the Air Force and

NASA include fracture-control practices that may be useful for high performance Naval sys- tems .

Fracture-control practices used by industry that offer potential cost reductions for

Naval systems are related to the establishment of steel toughness requirements and weld

quality standards. Alternative concepts for establishing steel toughness requirements include the strain-rate shift approach developed for bridges, the metal 1 urgi ca 1 -control

approach used for merchant ships, and the toughness-saturation approach developed for line

pipe. Weld quality standards based on f itness-for-servi ce considerations have been used in

place of more stringent workmanship standards for inspection of pipelines and offshore struc- ture and for in-service inspection of nuclear pressure vessels.

Fracture-control practices used for aerospace structures may improve the reliability of

certain Naval systems, particularly those advanced systems where the experience base is

limited. Practices worthy of consideration include loads characterization, full scale

testing, and formalized designation of fracture-criti cal parts.

28
7. ABBREVIATIONS

AASHTO

ABS

AGA

AIAA

AISC

AISI

ANSI

API

ASIP

ASME

ASM

ASTM

AWS

CFR

CSA

ECP

ENSIP

FAA

IMCO

ISO

American Association of State Highway and Transportation

Official

American Bureau of Shipping

American Gas Association

American Institute of Aeronautics and Astronautics

American Institute for Steel Construction

American Iron and Steel Institute

American National Standards Institute

American Petroleum Institute

Aircraft Structural Integrity Program

American Society of Mechanical Engineers

American Society for Metals

American Society for Testing and Materials

American Welding Society

Code of Federal Regulations

Canadian Standards Association

Engineering Change Proposal

Engine Structural Integrity Program

Federal Aviation Administration

International Maritime Consultive Organization

International Standards Organization

29
NASA National Aeronautics and Space Administration

MBS National Bureau of Standards

NRC Nuclear Regulatory Commission

OCS Outer Continental Shelf

OPSR Office of Pipeline Safety Regulation

USAF United States Air Force

USCG United States Coast Guard

USGS United States Geological Survey

The authors gratefully

Acknowledgment

acknowledge the contributions of Peter W. Marshall of the Shell Oil Company, Houston, Texas, who contributed the appendix section of Fracture Control for Fixed

Offshore Structures; and James A Begley of the Westinghouse Electric Corporation, Pittsburgh,

Pennsylvania, who contributed the appendix section on Large Rotating Equipment for Electric Power Generation.

30
APPENDIX

SUMMARIES OF FRACTURE CONTROL PRACTICES

USED FOR METAL STRUCTURES

CONTENTS: Page

Ships and Sea Systems

Merchant Ships------------------------------ 32 LNG Ships - Containment Systems --------------------- 35 Fixed Offshore Structures ------------------------ 44 Floating Nuclear Power Plant ----------------------- 53

Steel Structures

LNG Storage Tanks ---------------------------- 56 Steel Bridges ------------------------------ 61 Large Rotating Equipment for Electrical Power Generation --------- 65

Pressure Vessels and Piping Pressure Vessels ----------------------------- 68 Nuclear Pressure Vessels ------------------------- 72 Gas and Oil Pipelines -------------------------- 75 Pressure Piping - Power and Chemical Industries ------------- 82

Aerospace

USAF Aircraft ------------------------------ 88 NASA Space Vehicles --------------------------- 98

31
MERCHANT SHIPS

Ovcrvi ew

A. Codes and regulations

a. ABS Rules for Building and Classing Steel Vessels [1]

b. U.S. Coast Guard Inspection Regulations [2]

B. Historical

a. World War II ship failures [3]

b. Toughness considerations [4]

c. Principles of f racture--safe design [5]

d. Fracture-control guidelines for welded steel ship hulls [6]

Structural Design Conditions

A. Design life—not specified

B. Loads--compl ex combination of bending (longitudinal and horizontal) and torsional

loadings for various sea states. Loads can be rationally determined from analysis of

ship response to wave notions. ABS rules do not require this approach, but sets minimum standards for sizing hulls based on past experience.

a. Allowable design stresses not specified--rather section modulus is "proportioned"

as a function of the length squared, as well as the breadth, according to empirical relations. Above certain length (about 1000 ft) section modulus is

increased in proportion to the length, not the length squared.

b. Empirical relations based on satisfactory prior experience also are used to determine hull plate thicknesses as a function of overall ship length.

c. Hull deflection from still-water bending moment and wave-induced bending moment

is restricted by ABS Rules.

d. Using the hull-girder section modulus, a loading manual that shows effects of

various loaded and ballasted conditions on the longitudinal bending moments is

calculated for review by ABS.

e. Safety factors--not specified because of large variation in sea states.

Materials and Processes

A. Specifications

a. Ordinary strength steels, ABS Grades A to E. Also covered by ASTM A131 - Standard Specification for Structural Steel for Ships.

b. Higher strength steels--ABS grades AH, DH, and EH. Also covered by ASTM 131

c. Steels for low temperature service--ABS Rules, Section 24

32
B. Properties

a. Ordinary strength steels

Oy

5 1 34 ksi (234 MPa)

58 ksi (400 MPa) < o^-^j < 71 ksi (489 MPa)

b. Higher strength steels

AH32, DH32, and EH32: > 45.5 ksi (313 MPa)

68 ksi (469 MPa) < < 85 ksi (586 MPa)

AH36, DH36, and EH36: 1 51 ksi (351 MPa)

71 ksi (489 MPa) < < 90 ksi (620 MPa)

c. Low temperature steels

V-039, V-051, V-062: 35 ksi (241 MPa) < < 80 percent

58 ksi (400 MPa) < < 90 ksi (620 MPa)

Ni steels and stainless steels

Strength per applicable ASTM specification

C. Minimum toughness

a. Ordinary strength steels

Grade D: 14 ft lb (19 J) at -20°C transverse, 20 ft lb (27 J) at -20°C

1 ongitudi nal Grade E: 14 ft (19 J) lb at -40°C transverse, 20 ft lb (27 J) at -40°C

longitudinal

0thers--not specified. Toughness controlled by chemistry and processing

requi rements.

b. Higher strength steels

Grades DH32 and DH36: 25 ft lb (34 J) at -20°C longitudinal

17 ft lb (23 J) at -20°C transverse

Grades EH32 and EH36: 25 ft lb (34 J) at -40°C longitudinal

17 ft lb (23 J) at -40°C transverse

Grades AH32 and AH36--not specified

c. Low temperature steels

30 ft lb (41 J) longitudinal and 20 ft lb (27 J) transverse at 5°C below

minimum design temperature

4. Design

A. Members are proportioned using empirical guidelines as a function of the ship

length squared (up to about 1000 ft(305 m)--beyond that member sizes are proportional

to the length)

33
B. Standard details

Rules specify nininuui requirenents for all the nain structural sections of ships,

thus leading to use of standard conf i gurati ons

C. Joining practices

a. Specified in Section 30--Wel di ng--of ABS Rules

b. Nev/ procedures and nethods to be approved by ABS

D. Analysis

a. Strength and stability using classical and computer analyses

b. Fatigue analysi s--none

c. Fracture analysi s--none

5 . Qual ity Assurance

A. Material procurement controls

ABS Rules Sections 43 and 24 (low temperature service)

B. Welding control S--ABS Rules Section 30

a . Qual i fi ed wel ders

b. Qualified welding procedures

c. Workmanship provisions stated in rules for joint preparation and welding with

various processes and procedures

C. Inspection

Rules for TIDE of hull welds [6]

D. ABS personnel survey design and fabrication

E. Surveys after constructi on--annual and periodic

6. Operational Control

Wave forces can be reduced as much as 50 percent by speed reduction or change in

heading. This is controlled at sea by the captain and obviously can have a large

effect on the safety and reliability of the ship, which is completely out of control

of the designer.

References

1. Rules for Building and Classing Steel Vessels (American Bureau of Shipping,

45 Broad Street, Mew York, Annual).

34
Shipping, Chapter 1, Title 46 (Code of Federal Regulations).

Wheatcroft, M. F., Toughness considerations for merchant ship hulls, Fifth Annual

Forum on Prevention of Failure in the Transportati on Industry (Juno 1977).

Pellini, W. S., Principles of fracture-safe design. Parts I and II, The Uelding Journal

(March-Apri 1 1971)

Rolfe, S. T., Rhea, D. M., and Kuzmanovic, B. 0., Fracture control guidelines for

welded steel ship hulls. Ship Stucture Committee Report No. SCC 244 (1974).

Rules for Non-Destructive Evaluation of Hull Wolds (American Bureau of Shipping,

45 Broad St., New York).

35
LNG SHIPS - CONTAINMENT SYSTEMS

1. Overview

A. Codes and regulations

a. International Maritime Consultive Organization (IMCO) Code [1]

b. U.S. Coast Guard (USCG) Regulations [2]

c. American Bureau of Shipping (ABS) Rules [3]

B. Designs built in the U.S.

a. Avondale Shipyards, Inc. Conch containment system [4]*

Free-standing, prismatic tanks

5083 aluminum plates and extruded shapes

b. Newport News Shipbuilding

Techniqaz containment system [5]

Membrane, prismatic tanks

304L stainless steel sheet

c. General Dynamics Kvaerner-Moss , containment system [6,7]

Free-standing, prismatic tanks

5083-0 aluminum plates

2. Structural Design Conditions

A. Design life: 20 years

B. Loads: summarized in SSC-258 [8]

a. Static pressure: cargo weight

b. Vapor pressure: pressure relief value setting

c. Dynamic effects due to ship motions

roll, pitch and heave conditions defined [9]

d. Thermal streses: AT = 190°C

e. Flooding: applicable to free-standing tanks

f. Self weight: applicable to free-standing tanks (lifting required)

g. Fatigue loads [10]

C. Initial damage assumptions

a. Hull damage: IMCO Section 2.3 [1]

b. Prismatic design [4,5]

Secondary barrier required

Primary barrier assumed to be failed for hull temperature determination

^Commercial equipment is mentioned in this document to adequately identify certain LNG containment systems. In no case does this imply endoresement or recommendation by the National Bureau of Standards.

36
c. Spherical design [1]

Leak-before-break required

Assume through-thickness crack of length 2 x thickness

Safe crack growth for 15 days under worst-cast storm conditions

D. Safety factors

See section 3C on allowable stresses and 4B on fatigue analysis.

3. Materials and Processes

A. Selection, specifications '

a. Steel alloys

9 percent Hi; ASTM A353 and ASTM A553

36 percent Ni (Invar): ASTM A658

Austenitic stainless steels: ASTM A240

b. A1 umi num al 1 oy 5083-0 sheet and plate: ASTM B209

5083-H 111 extrusions: ASTM B221

B. Properties

a. Room temperature guaranteed minimum properties used [4]

b. Exception is Conch design where allowables are based on strength at LNG

temperatures [4]

C. Allowable stresses

a. Membrane tanks [l]--not specified (membranes not structural).

Tests and analyses must show compatibility of hull and containment system.

b. Free-standi ng-prismatic tanks [1] (independent tanks--type A)

Maximum stress is lesser of o^^j/2.66 or Otj,/l.33

where o^^j = tensile ultimate strength at room temperature

= tensile yield strength at room temprature

Note; Wold metal values for o^^j and o^y are used when the weld is

weaker than the base metal.

Froo-standi ng--spherical tanks [1,12] (independent tanks--type B)

om 1 f

OL < 1.5 f

Ob _< 1 .5F

OL + Ob 1 1 .5F

0[^ + Ob <. 1 .5F

37
where

Opi = equivalent primary general membrane stress

op = equivalent primary local membrane stress

Ob = equivalent primary bending stress

f = the lesser of o^y/A or o^y/B

F = the lesser of o^y/C or Oty/D

Equivalent stresses 0(~, are calculated by the Von Mises yield criterion:

2 2 o = 0 + 0 - OO + 0T

C X y X y xy

where and Oy are normal stresses and is the shear stress. The safety

factors A, B, C, and D specified by the USCG [10] are as follows:

9Ni FactorSteel Austenitic steels 5083-Al

A 4* 4

B 2 1.6 1.5

C 3 3 3

D ;L.5 1.5 1.5

*3 specified in IMCO **3.5 specified by IMCO

Allowable stresses may be further limited by fatigue analysis, crack propagation analysis,

and buckling criteria.

D. Minimum toughness

a. 9Ni steel

30 ft lb (41 J) longitudinal and 20 ft lb (27 J) transverse at -196C

b. Fe-36Ni and 5083 A1 : none required

c. Austenitic steels: not required by USCG, optional to IMCO

d. 9Ni welds

20 ft lb (27 J) at -196°C for the following notch locations:

(weld parallel to rolling direction, specimens perpendicular to weld, notch

perpendicular to surface)

Weld metal

Fusion line Heat affected zone: 1, 3, and 5 mm from fusion line

38
4. Desi gn

A. Design for danage tolerance

Double-side shell and double bottom required for hull structure

Fail safe provisions

a. Secondary barrier required for prismatic tank designs

b. Leak-before-break and safe crack growth after leak required for spherical

tank design. Fatigue spectrum for safe crack growth calculations is equivalent to 15 days of worst-case storm conditions.

B . Standard detai 1

Each containment system design must be approved by the U.S. Coast Guard if the

ship is to enter U.S. coastal waters.

C. Joining practices

a. Production weld procedures must be qualified for each base material, each

type of consumrnable and welding process, and each welding position. Tests

are as follows:

Cross-weld tensile test

Transverse bend tests

Charpy impact tests (if required for base material)

riacrosecti on, microsection, and hardness survey

b. Free-standing tank shells: full penetration butt welds and full penetration

nozzle welds required.

5. Analysis

A. Stress analysis

a. Limits set by stress allowables, buckling criteria, fatigue, and crack

propagati on

b. Finite-element and closed-form methods used

E. Fatigue analysis

a. Membrane; fatigue testing of models required

b. Free-standing prismatic, fatigue analysis not required

Insulation and secondary barrier system models subjected to fatigue testing.

c. Free-standing spherical: cumulation damage fatigue analysis required

39
n

2

n.

1

c w

where

n-j = number of stress cycles at stress level i in the fatigue

spectrum

N-j = number of cycles to fail for stress level i based on materials

S-N curve

Nj = number of cycles to fail for stress level correspond! ng to cargo

loading and unloading

1 i.e., safety factor >_ 2 on fatigue life

C. Fracture mechanics

a. Membrane and free-standing prismatic; not required

b. Free-standing-spherical

^cr f da

Life = Jworst-case storm conditions

^LBB

where C and n are crack growth rate parameters

^LBB “ crack size for leak before break = 2 x thickness

^CR = critical crack size

6. Qual ity Assurance

A. Material procurement and controls

ASTM requirements and IMCO minimum toughness requirements

B. Fabrication and processing controls

a. Held procedure qual ificaions required (See 2-D)

40
b. Production weld tests: free-standing tanks only

Frequency: every 50 m of butt weld

Type: bend tests and Charpy impact test (if required for procedure test)

Notch location:

9Ni steel: alternately in weld metal and HAZ

(worst location identified in procedure tests).

Austenitic steels: in center of weld

C. Inspection (NDE) [11,13]

a. Butt welds: 100 percent radiography

b. Ultrasonics, dye penetrant, and magnetic particle inspection sometimes

requi red

D. Hydrotesting

a. Membrane tanks

Coferdams and spaces adjacent to cargo tanks must be tested.

b. Free-standing tanks

1) Hydrotest to approximate as nearly as possible the design stresses

2) Pressure ip dome must at least equal the maximum allowable relief value

setting.

3) For spherical tanks, at least one tank per ship must bo instrumented

with strain gages to verify stress levels [13].

4) For prismatic tanks, stresses in primary members must not exceed

90 percent of Strain gage verification required if stresses

greater than 75 percent of are anticipated [4].

E. Verification testing

a. Membrane [14]

Component tests on: "Waffle" panels (primary barrier)

Insulation system

Test boxes: 5m3 specimens with full-size waffle panels

b. Free-standing prismatic [4]

Fatigue tests on insulation panels with secondary barrier

c. Free-standing spherical

Leak-before-break tests [11,15]

References

1. Code for the Construction and Equipment of Ships Carrying Liquified Gases in Bulk

(International Maritime Consultive Organization, London, 1975). See also. Proceedings

of the Maritime Safety Council 3^, No. 3 (1976).

41
2. Liquified Flammable Gases, Code of Federal Regulations, Title 46, Part 38 (1977). See

also: Liquified Natural Gas, Views and Practices, Policy and Safety (U.S. Coast Guard,

CG-478, Feb. 1976).

3. Vessels intended to carry liquified gases (sec. 24 of Rules for Building and Classing

Stool Vessels, American Bureau of Shipping, flew York, 1977).

4. Potts, W. K., and Cuthbert, W. L., LNG carriers using the conch containment system.

Paper presented at the SflAnE mooting, Vancouver, B. C., Canada, May 1975, Society of

Naval Architects and Marine Engineers, New York, 1975.

5. Throe stainless steel membrane LNG tankers first of type made in U.S. A., Nickel Topics

30, No. 1 (1977).

6. Howard, J. L., LNG marine carrier construction. Marine Technology 9, No. 3 (1972).

7. Glasfeld, R. D., Design of spherical shipborne LNG cargo tanks. Marine Technology 13 , No. 3 (1976).

8. Bass, R. L., Hokanson, J. C., and Cox, P. A., A study to obtain verification of liquid

natural gas (LNG) tank loading criteria. Ship Structures Committee Report SSC-258 (1976).

9. Thomas, W. D., and Schwendtner, A. H., LNG carriers: The current state of the art. Oceanology International 1_, No. lA (1972).

10. Construction and Classification of Ships for Transport of Liquid Cargoes and Liquified

Gases (Det Morske Veritas, H0vik, Norway, 1973). For specific examples, see Norwegian

Maritime Research I, Mo. 2 (1973) or ASTM STP 579, 238-260 (1973).

11. Tenge, P., and Solli, 0., Application of fracture mechanics for design and construction

of liquified natural gas tanks in ships. Book, Materials Engineering in the Arctic

(American Society for Metals, Metals Park, Ohio, 1977).

12. Henn, A. E., and Dickey, T. R., New regulations for liquified gas carriers, presented

in GASTECH 75, Paris, 1975.

13. Howard, J. L., Kvamsdal , R. S., and Naesheim, K., Building and operating experience of

spheri cal -tank LNG carriers. Marine Technology No. 2 (1977).

14. Jackson, R. G., and Kotcharian, M., Testing and technology of models of integrated

tanks for LNG carriers (Proc. 1st International Conf. on LNG, Chicago, 1968).

42
15. Kelsey, R. A., Wygonik, R. H., and Tenge, P., Crack growth and fracture of thick 5083-0

plate under liquified natural gas ship spectrum loading, ASTM STP 579, 44-79 (1975).

43
FIXED OFFSHORE STRUCTURES

1. Overview

A. Codes and regulations

a. uses OCS Order 8 [1]

b. API RP 2A [12]

B. Historical failures

a. Blowout, fire, and collision [3]

b. Overload by storms [3]

c. Fatigue [4]

d. Brittle fracture [5]

e. Lamellar tearing and hydrogen-induced cracking during fabrication [5,0]

2. Structural Design Conditions

A. Design life

a. Platform life is governed by economic depletion of the hydrocarbon reservoir,

and is generally in the range of 10 to 30 years. Fixed platforms are rarely

salvaged for re-use at another location.

b. Fatigue calculations for modern, shallow-water platforms in the Gulf of

Mexico generally indicate an allowable fatigue life of 100-200 years using

Alls criteria [7]. Deep-water platforms for which a fatigue design is made

generally aim for 90-100 years. Median fatigue life is estimated to be 5 to

8 times AllS allowable.

B. Loads

a. Static loads based on self-weight, buoyancy, equipment, supplies, fluids, and

drilling loads; corresponding nominal stresses limited to 60 percent of

yield or buckling

b. Design wave load based on most probable maximum wave in the nominal 100-years

storm, combined with wind and static loads, with allowable stresses at 80

percent of yield

c. Strength level earthquake having 5 to 40 percent probability of exceedance at platform sites during economic life, with stresses permitted to reach 100

percent of yield or buckling. In addition, structure must demonstrate

survival for ductility requirement motions twice as severe.

d. Other conditions sometimes encountered include ice loads, sea-floor

instability, and current-i nduced flutter.

e. Installation forces include lifting forces, loadout forces, launching forces,

upending forces, hydrostatic pressure, and soil bearing pressures.

44
c. Envi ronment

a

b.

c

Bulk of structure submerged in seawater with cathodic protection.

Temperature above freezing with minimum generally in the 35°-50°F

(2°-10°C) range, depending on geographical location

Splash zone subjected to accelerated corrosion attack, alternating wet-dry

salt spray

Air zone generally protected by paint. Lowest anticipated service

temperature as follows:

Gulf of Mexico

Southern California

Gulf of Alaska

Cook Inlet

Georgia Embayment

Baltimore Canyon

Georges Bank

14°F

320f

-13°F

-20°F

15°F

5OF

- 5 OF

:-iooc)

: QOc)

:-25°C)

:-29°C)

9°c)

:-i50c)

:-2ioc)

d. Interior of tubular members and exterior of piling below midlines exposed

only to stagnant, oxygen-depleted fluids

e. Where structural members are used for oil storage, these may be exposed to

H

2

S generated by bacterial action; however, this is unusual.

D. Initial damage assumption

a. API RP 2X relates permissible discontinuities in welds to the level of notch

toughness provided and to the fatigue S-N curve assumed in design [8]. The

commonly used class "C" criteria include the following: —Tubular T-4- and K-connection welds made from the outside only

typically have large discontinuities at the root up to 1/8 in (3 mm)

X 2 in (51 mm). —Internal discontinuities elsewhere are limited to less than

1/8 in (3 mm) x 1 in (25 mm) or 1/10 in (2.5 mm) x 2 in (51 mm). —Limitations are also placed on external weld profile—i.e., the weld

metal shall merge smoothly with adjoining base metal, with no undercut

over .01 in ( .25 mm)

—These requirements are consistent with the observation that fatigue

cracks in tubular connections usually start on the outside surface at the toe of the weld, with large root discontinuities rarely

propagati ng.

b. Structures which suffer significant damage (e.g., during construction or due

to overload) or deterioration (e.g., fatigue cracks or loss of section due to corrosion) may be reanalyzed for the actual conditions found.

45
3. Materials and Processes

A. Selection criteria [5]

a. In recent frontier areas structures, critical deck members, e.g., main

girders or truss chords, have been provided with pop-in protection; that

is, drop weight NDTT plus 20°F (7°C) or comparable Charpy requirements

(50 percent shear fracture) at the lowest anticipated service temperature.

This is comparable to recently proposed Federal criteria for

fracture-critical members in bridges.

b. For deck members whose sole failure would not be catastrophic , e.g., parallel

multiple deck beams, ordinary mild steel is used.

c. For redundant tubular bracing in the underwater jacket structure subjected to nominal stresses less than yield, dependences on the initiation barrier at slow to moderate loading rates [9] permit the use of ordinary mild steel.

Where higher strength steels are used, modest Charpy requirements similar to ASTM A709 are specified.

d. The requirements for piling are similar to those cited above for jacket

braci ng.

e. At tubular joints, or nodes, high local stresses occur at the toe of the

weld--typically 3 to 5 times nominal on the main member's side, and 1.5 to 2.5 times nominal on the branch member side. Typically a "joint can" of increased thickness is provided in the main member, having a pop-in

protection (NDTT plus 20°F, 7°C) or better. This also provides tolerance

to extremely large fatigue cracks at the anticipated wave loading rates. In addition, a "stub-end" piece in the branch member is sometimes used to provide enhanced notch toughness and weldability in the node area.

f. Consideration of these high local stresses (hot spot stresses) in fatigue

generally precludes effective use.

g. Comparable notch toughness criteria are also applied to weld metal and heat affected zones.

B. Specifications

a. Fracture critical members and joint cans

Shell FCM

API Spec 2H ASTM A 537 class I ASTM A 633 grades A,B,C,D,

BS 4360 grade 50D DIN St 52-3N

b. Redundant bracing, piling, etc. --Plate and shapes ASTM A-36

46
ASTM A 572 grade 42 ASTM A 709 grade 50T2 ASTM A 633 grade E --Mill pipe ASTM A 53 API 5L grade B API 5LX grades 42 and 52 --Fabricated pipe using API Spec 2B and plate listed above.

C. Processing

a. Structural quality ASTM A6; some plates are normalized; some are low sulfur with inclusion shape control.

b. Cold forming into pipe involves 2-5 percent strain. Subsequent strain aging

when welded may cause significant loss of notch toughness--e.g. , 20-40°F

(-7 to 4°C) shift in transition temperatures.

c. Welding processes

SMAW--I 0W hydrogen manual

SAW--mul ti-pass submerged arc GMAW--short arc and spray arc FCAW--open arc

4. Design and Analysis

A. Damage and tolerance--typical jackets are multiple load path, fail-safe

structures. Fatigue or brittle failure is generally localized to one brace. The

remaining structure exhibits sufficient strength and further deterioration is sufficiently gradual to permit survival until the next periodic inspection. This

behavior has been investigated in a case study [10] but is not analyzed for every

structure.

B. Joint design

a. Strength design of simple tubular joints utilizes API-AWS punching shear

requi rements.

b. Strength design of more complex joints utilizes the lower bound theorem of ultimate strength, commonly known as the cut-and-try approach [11].

c. Initial fatigue design is in terms of reduced allowable stresses, to be used with the cyclic part of the design wave load--for example, as shown in the following table:

47
AWS Typical Waterl i ne Category Braces Braces

Hot spot stress X 47 ksi (324 MPa) 34 ksi (234 MPa)

nominal fg + f^ D' 19 ksi (131 MPa) 15 ksi (103 MPa)

punching shear K 7.5 ksi (52 MPa) 5 ksi (34 MPa)

T 5 ksi (34 MPa)

These allowable stresses are derived from preliminary generic analysis

(e.g., [12]). Category X is used with empirical formulas for hot spot

stress concentration factors [13].

C. Standard details

These are given in Section 10 of AWS.

5. Analysis

A. Stress analysis

a. Global-scale analysis of elastic static or dynamic space frame program yields

nominal member stresses and AISC ratio checks.

b. Local-scale analysis of critical tubular joints may be performed using twin

shell or isoparametric solid finite elements, or model tests.

c. Microscopic effects at toe of weld are built into empirical S-N curves for

hot spot stress on practical as-welded hardware.

B. Fatigue analysis [14]

a. Stress analysis tools described above used to develop transfer functions for

hot spot stress at 4 points at each end of each brace for various wave

frequencies and directions.

b. Wave climate is described in terms of directional scatter diagram. Each sea state is represented by Pierson-Moskowitz spectrum.

c. Short-term stress statistics are computed for each sea state at each hot

spot. These are accumulated to yield long term (annual) statistics.

d. Cummulative damage is computed using Miners Rule and AWS-X-modified S-N curve.

C. Fracture mechanics

Used mainly as a research tool to evaluate engineering procedures

48
6. Quality Assurance

A. Material procurement controls

Steel ordered by fabricator to ASTM, API, or AWS specifications. Structural

practice per ASTM- A6. Mill reports checked by owner's inspector.

B. Fabrication and processing controls

a. Major fabricators have independent, in-house quality control organization.

In addition, owner provides resident inspector and third-party

non-destructive testing.

b. Welding procedures are qualified per AWS Dl.l, with additional Charpy

requirements.

c. Welders are qualified per AWS Dl.l, with GAR required for tabular

connections.

d. Fabricators are evaluated by visiting team using AISC quality certification

program checklist.

C. Inspection

a. All welds are visually inspected.

b. Radiographic examination

Girth welds in jacket legs, piling, and structural braces--100 percent

Longitudinal seams in fabricated pi pe--spotcheck except that joint cans are checked 100 percent

Butt welds in truss members and girder tension flanges--up to 100 percent

as directed by inspector

c. Ultrasonic examination in fabrication yard

Tee welds in major tubular connections--100 percent

Deck truss joints and crane base tie-ins--up to 100 percent as directed by

i nspector

d. Ultrasonic examinations during offshore erection

Piling splices--up to 100 percent

Deck leg base connections--100 percent

Deck field splices--up to 100 percent

D. Proof testing

Members used to provide buoyancy or fluid storage are leak tested.

E. Traceability

Fabricator usually keeps track of the numbers used on a given job. Exact identity

of individual pieces depends on finding mill heat stamp.

49
F. Verification testing [15]

a. As research, selected platforms are instrumented to record sea state, wave

forces, deck motions member stresses, etc., permitting comparisons between

predicted and measured response.

b. Methods for periodic monitoring of structure natural frequencies hold promise

for detecting major loss of strength and stiffness. However, nonlinear

foundation or operational changes in deck mass can cause similar shifts.

Being used on a very limited trial basis.

C. Failure Mitigation Strategies [15]

A. Surveys

a. Yearly surveys include visual inspection for collision damage, splash zone corrosion, condition of deck, and effectiveness of cathodic protection.

b. More detailed surveys are conducted following exposure to severe loading

conditions, or every 5-10 years. This involves checking the condition of all

underwater braces, and spot checks in which marine growth is removed to permit detailed color photography for surface pitting, cracks at nodes, etc. Attempts at using oversold, undercal i brated, nondestructive techniques have

led mainly to false alarms.

B. Fail safe while manned

a. In the Gulf of Mexico, there is sufficient warning for hurricanes that

offshore platform personnel can be evacuated, and the wells secured against

leakage in the event of structural collapse. This is done as a practice of

long standing. For periods while the platforms are manned and the wells are

flowing, the maximum expected winter storm produces only 40 percent of the

design hurricane load. This leaves a considerable margin for undetected

damage.

b. In other areas like the north Sea, de-manning may not always be possible, and

a strategy comparable to the above remains to be developed.

C. Repairs

a. Techniques for underwater welding, hyperbaric chamber welding, and internal

grouting are available for repairing or upgrading members in offshore

structures when justified.

b. When structural deficiencies are found, the decision on whether or not to undertake repair attempts to make a rational trade-off between the cost of

repair and the benefits in terms of risk reduction.

50
References

1. United States Department of the Interior, Geological Survey, Conservation Division,

Gulf of Mexico Area, OCS Order No. 8, Platforms, Structures, and Associated Equipment,

effective October 1, 197G.

2. Recommended Practice for Planning, Designing, and Constructing Fixed Offshore

Platforms, API RP2A, 9th Edition (American Petroleum Institute November 1977).

3. Marshall, P. W., and Bea, R. G., Failure modes for offshore structures (Proc. B0SS'7G,

1 , Trondheim, Norway, August 1976).

4. Marshall, P. W., Design considerations for tubular joint design in offshore

construction, URC Bulletin 1^ (April 1974).

5. Carter, R. M., et. al . , Materials problems in offshore platforms (Proc. OTC, No. 1043,

May 1969).

6. Harrison, J. D., The selection of material to avoid fracture in large offshore

structures (Proc. OTC, No. 1909, May 1973).

7. Structural Welding Code, AWS Dl.1-75 (American Welding Society, 1975 edition with

revisions)

8. American Petroleum Institute, Recommended Practice for Ultrasonic Examination of

Offshore Structural Fabrication and Guideline for Qualification of Ultrasonic

Technicians, APT RP 2X, draft approved for letter ballot, June 1978.

9. Rolfe, S. T., and Barsom, J. M., Fracture and Fatigue Control in Stuctures

(Prentice-Hall, 1977).

10. Marshall, P. W., Failure modes for offshore structures--part II--fatigue, Methods of

Structural Analysis (ASCE Specialty Conference, Madison, Wise., August, 1976).

11. Marshall, P. W., Sherman, D. R., and Groff, W. J., Limit State Design of Tubular

Connections, Ibid., separate preprint.

12. Marshall, P. W., et al.. Preliminary dynamic and fatigue analysis using directional

spectra. Journal of Petroleum Technology (June 1977).

13. Marshall, P. W., A review of stress concentration factors in tubular connection. Shell

CE-32 Report (April 1978).

51
14. Marshall, P. W., and Kinva, R. K., Dynamic and fatigue analysis for deep water fixed

platform (paper presented at ASCE-EMD Specialty Conference, Raleigh, North Carolina,

May 1977).

15. Marshall, P. W., Philosophy for monitoring inspection and repair of fixed offshore

platforms (Proc. of MTS-IEEE Oceans '78, September 1978).

52
FLOATING NUCLEAR POWER PLANT

1. Overview

A. Codes and regulations

a. Nuclear Regulatory Commission (NRC) Regulations - Power Plant

b. U.S. Coast Guard Regulations - Support Barge

c. ABS Rules for Building and Classing Steel Vessels

d. American Welding Society Qualification and Certification Program

B. Scope

This summary is limited to the requirements for the support barge as discussin in [1].

2. Structural Design Conditions

A. Design life = 40 years

B. Loads

a . Dead load + live load

b. Wave action

c. Tornado

d. Earthquake

e. Fatigue

C. Service conditions

a. Water temp., 28.60 f (-2°C)

b. Air temp., -5°F (-21°C)

c. Water depth at site, 40-70 ft (12-21 m)

d. No drydocking

D. Safety factors

a. Stresses at extreme loading (dead, live, tornado, etc.)

<0.9oys

b. Fracture Control Plan developed to obtain very high level of structural

i ntegrity

c. Crack arrestors

5 :
3. Material

A. ABS-CS steel

a. Oyg = 34 ksi (234 MPa)

b. = 58-71 ksi (400-489 MPa)

c. Percent elong. = 24 percent in 2 in (51 mm)

B. Fracture toughness requirements

a. NOT = -30°F (-34°C)

b. DT = 250 ft lb (340 J) transverse at +30°F (-1°C) concepts such that

Klp/a^Q > 1.5 at 30°F (-1°C).

4. Qual ity Assurance

A. Welding procedure and performance

a. Section IX - ASME Code

b. Secton 30 - ABS Rules

c. USCG Marine Engineering Regulations, Subchapter F, Code of Federal Regulations 46 CFR57

B. Material procurement controls

a. Supplier qualification

Produce CS per ABS requirements and NOT -30°F (-34°C)

Establish dynamic tear transition curve.

b. Supplier quality controls

ABS requirements for grade CS

2 dynamic tear tests (transverse) per heat

2 NOT tests per plate, NOT -30°F (-34°C)

C. Weldment testing

a. Prequalification investigation (for each process)

Chemical and mechanical properties per ABS rules

Establish dynamic tear and Charpy V-notch transition curves for the weld,

HAZ, and base metal

Weld metal NOT < -30°F (-34°C)

b. Procedure qualification (in addition to ASME Section IX)

Dynamic tear energy > 250 ft lb (340 J) at 30°F (-1°C) in the weld

and HAZ NDT < -30°F (-34°C) in the weld metal

c. Production tests Toughness tests every 1000 linear feet (305 m) of weld by each process Dynamic tear (weld and HAZ) > 250 ft lb (340 J) at +30°F (-1°C) NDT

(weld and HAZ) < -30Op (-34°C)

54
D. Nondestructive exanination

Comprehensive in-house program approved by Coast Guard

References

Chazel , E. A., Deck, J., Rolfe, S. T., and Thompson, T. E., The structural requirements

including fracture control for the halls of the proposed coating nuclear pov^er plants.
LNG STORAGE TANKS

1. Overview

A. Codes applicable to storage tanks

a. API Standard 620: Recommended Rules for Design and Construction of Large,

Welded, Low-Pressure Storage Tanks [1]

b. API Standard 650: Welded Steel Tanks for Oil Storage [2]

B. Code applicable to LNG storage tanks

a. API Standard 620, Appendix Q: Low-Pressure Storage Tanks for Liquefied

Hydrocarbon Gases

C. Regulations

a. Federal none

b. State and local: may require conformance to API 620

2. Structural Design Conditions

A. Design life not specified

B. Loads

a. Pressure < 15 PSIG (0.1 MPa). Tanks are pressure rated and relief valves are

set at or below the pressure rating.

b. Weight of liquid 29.3 Ib/ft^ (.47 g/cm^) minimum for methane

c. Partial vacuum if probable

d. Supporting systems

Localized and general loads

Foundation conditions factored in

e. Superimposed loads

Attached equipment, piping, etc. Snow loads where applicable

Insulation and lining

Wi nd Earthquake

C. Temperature

a. Parts exposed to LNG: -270 F (-168°C)

b. Parts not exposed to LNG: lower of lowest one-day mean ambient temperature

plus 15°F(8°C), or vapor temperature if exposed to LNG vapor

56
D. Initial damage assumptions--none

3. Materials and Processes

A. Selection specifications

a. LNG containment materials

5Ni and 9Ni steels

AISI grade 304 and 304L stainless steels

3003-0, 5052-0, 5083-0, 5086-0, 5154-0, 5456-0, and 6061-0, T4 and T7 aluminum alloys

b. Parts not exposed to LNG Various ASTM, ISO, and CSA grades selected according to minimum temperature,

thickness, and product form

B. Allowable design stresses

a. Tension Lesser of 1/3 tensile strength or 2/3 yield strength for 5Ni and 9Ni steels

The Weld strength (95,000 psi , 655 MPa) sets the tensile allowable for 5Ni and 9Ni steel welds. Lesser of 1/3 tensile strength or 3/4 yield strength for 304, 304L, and aluminum alloys

b. Compression

Allowable stress for uniaxial compression in relatively thick wall, small diameter tanks (t-c/R > .0175) is 15,000 psi (103 MPa) for steel, where

t = thickness, c = corrosion allowance, and R = tank radius. For aluminum,

factor 15,000 by the ratio of the yield strength for the Al-alloy to 30,000.

Allowable stress for biaxial compression (again for tanks where

t-c/R > .0175) is 8,340 psi (57 MPa). For aluminum, factor 8,340 by the

ratio of the yield strength for the Al-alloy to 30,000.

For tanks with t-c/R _< .0175, allowable stresses are established on the basis

of stability considerations in accordance with formulas in API 620.

c. Combined stresses Tension tension--treat as tension

Tension compression--use biaxial stress chart in API 620 to compute stress reduction factor

d. Shear

Less than 80 percent of the maximum allowable tensile stress

57
Less than 80 percent of the maximum allowable tensile stress

e. Welded joints

Maximum allowable efficiencies of arc-welded joints specified 70 percent to 100 percent for butt welds and 35 percent to 70 percent for filled welds

depending on joint conf i guration and extent of radiographic inspection.

C. Minimum toughness requirements for 5Ni and 9Ni steels

a. Test temperature: 77K (-320°F)

b. Plates: 3 specimen set for each plate, transverse direction, 20 ft lb (27 J)

minimum average, 16 ft lb (22 J) minimum, .015 inch (3.8 mm) minimum lateral

expansi on

c. Structural shapes: 3 specimen set for each different shape in each heat treatment lot, longitudinal direction from the thickest part of the shape, 25

ft lb (34 J) minimum average, 20 ft lb (27 J) minimum, .015 inch (3.8 mm)

minimum lateral expansion

d. Forgings, piping, tubing: 3 specimen set for each heat included in any heat treatment lot, 25 ft lb (34 J) minimum average, 20 ft lb (27 J) minimum, .015 inch (3.8 mm) minimum lateral expansion

e. Subsize Charpy specimens. Impact energy requirements reduced by a factor

equal to the thickness reduction factor.

D. Minimum toughness requirements for welds

a. 5Ni and 9Ni steel weld metal Not required for the common, high nickel electrodes if deposited by the SMAW

or GMAW processes. For other processes, plate toughness requirements must be met on Charpy specimens taken from weld procedure qualification test plates.

b. 304 and 304L stainless steel weld metal

Not required for austenitic welds deposited by the SMAW or GMAW processes.

For other processes, 77K tests, 15 ft lb (20 J) minimum average, 12 ft lb (16 J) minimum and .011 inch (2.8 mm) minimum lateral expansion on Charpy

specimens taken from weld procedure qualification test plates.

c. 5Ni and 9Ni Heat Affected Zone (HAZ)

Plate toughness requirements must be met on Charpy specimens taken from weld

procedure qualification test plates. Notch located approximately normal to the plate surface such that as much HAZ material as possible is in the

resulting fracture.

Desi gn

A. Design for damage tol erance--not required
B. Standard details

a. Tanks have single vertical axis of revolution.

b. Design procedure given for tank walls, roofs, bottoms, knuckle regions, ring

grades, openings and reinforcements, structural members, bolted flange

connections, cover plates, and flush shell connections

c. Reinforcement of single openings, welded nozzles and other connections, flush

type shell connections

C. Joining practices

Welding practices, procedure qualification, and welder qualification per ASME

Section IX

5. Analysis

A. Stress analysis

a. Standard formulas for sizing sidewalls, roofs, bottoms, knuckle regions, and compression ring girders

b. Unit forces determined by statics using strength-of-material s approaches or numerical methods

B. Fatigue-none

C. Fracture mechanics-none

6. Qual ity Assurance

A. Material procurement controls

ASTM, ISO and CSA specifications

B. Fabrication and processing controls

a. Welding procedure and welders qualified to ASME IX

b. Welds identified by welder

c. Weld fitup, edge preparation, and cleaning requirements per API 620

d. Weather conditions for welding limited

Welding not done on wet surfaces

Welding not done in rain, snow, or high winds

Base metal temperature greater than 0 F (-18°C)

Preheat required for temperatures between 0 and 32 F (-18 to 0°C)

C. Weld quality requirements

a. Butt welds must be full penetration welds with complete fusion for the full length and free from undercuts, overlaps, and abrupt ridges or valleys.

59
b. Reinforcement limits specified

c. Radiograph acceptance standards per ASME , Section VIII, Division 1 (UW-51(b))

d. Ultrasonics-acceptance standards agreed to by purchaser and manufacturer

e. Liquid penetrant-acceptance standards per ASME, Section VIII, Division 1 (UA94,95)

D. Inspection

a. Qualified inspectors per API 620 requirements

b. Inspector assures compliance with engineering design and with the provisions

of API Standard 620

c. Radiography requirements

Complete for joints thicker than 1 1/4 inch (32 mm)

Complete for butt welds where the increased joint efficiency factor is used

in design except for circumferential welds in cylindrical or conical tanks

where only the intersections are radiographed (3 inches, 76 mm, on each side

of intersection)

Spot radiographing is required on intersections at various locations in the tanks.

E. Hydrostatic and pneumatic tests

a. Tanks are filled with water to the design liquid level and pressurized to 1.25 times the design pressure. Due to the low specific gravity of LNG,

exceptions to the procedure to avoid overloading the foundation or overstressing the tank are permissible. Allowable stresses during test are based on 80 percent of the yield strength for 5Ni and 9Ni steels and 90 percent of the yield strength for 304, 304L, and aluminum alloys.

b. Outer tanks in double-wall tanks are leak tested.

c. Proof tests are required for novel designs.

References

1. Recommended Rules for Design and Construction of Large, Welded, Low-Pressure Storage

Tanks, API Standard 620, American Petroleum Institute, Washington, D.C., Sixth Edition,

1978.

2. Welded Steel Tanks for Oil Storage, API Standard 650, American Petroleum Institute,

Washington, D.C., 1978.

60
STEEL BRIDGES

1. Overview

A. Codes

Standard Specifications for Highway Bridges-American Association of State Highway

and Transportation Officials (AASHTO)

2. Structural Design Criteria

A. Design 1 i fe-50-70 years

B. Loads-AASHTO Code (truck and lane)

a. Dead load

b. Live load (HS trucks)

c. Impact factor, wind

C. Initial damage assumption-none

D. Fracture critical members are designated as those tension components of a bridge

whose failure would be expected to result in the collapse of the bridge. These

members have special toughness requirements as noted below.

3. Materials and Processes

A. Selection specifications

AASHTO Materials Table (ASTM steel grades A36, A572, A588, A514)

B. Properties

a. ASTM tensile properties

b. Toughness values-see attached table of Charpy V-notch requirements for fracture critical members. For A36 (Oy^ = 36 ksi, 248 MPa) steel at 0°F (-18°C) service temperature, the minimum CVN impact requirement is 25 ft lb (340 J) at 70°F (21°C). Values are based on intermediate

loading rate and temperature shift. Similar values are specified for other

steel s.

C. Allowable stresses

a. Tension: oj ~ .55 o^g

b. Compression: <^.55 or buckling

61
4. Design

A. Damage tolerance-structural redundancy encouraged

B. Standard detai 1 s-fati gue categories A, B, C, D, E, F based on standard details

shown in AASHTO Specification

C. Joining Practices-AWS Structural Code [2]

5. Analysis and Design

A. Stress analysis-stress allowables, buckling criteria to withstand given truck and wind loading fatigue curves (S-N)

B. Fatigue analysis-based on categories of details and S-N curves when essentially

ag ~ 1/8 in (3.2 mm) and low da/dN

C. Fracture mechanics--not required

Concepts used in establishing toughness requirements

6. Qual ity Assurance

A. Material procurement--per applicable ASTM specification

B. Fabrication and processing

a. AWS Structural Welding Code [2]

b. AISC requirements [3]

c. AASFITO Fracture Control Plan [4]

C. Quality of workmanship required by AASFITO Code "workmanship and finish shall be equal to the best general practice in modern bridge shops."

D. Inspection

a. Butt welds-100 percent radiography

b. AWS Specifications

E. Proof testing-none

References

1. Standard Specifications for Highway Bridges, American Association of State Highway and

Transportation Officials, Washington, D.C., 12th Edition, 1977.
2. Structural Welding Code - Steel, AWS Dl.1-78, Anerican Welding Society, Hiani, FL,

. 1978.

3. AISC

4. Fracture Control Plan, Draft developed by the Structual Steel Design and Welding

Technical Committees of the AASHTO Subcommittee on Bridges and Structures in consort

with the Bridge Division of the Federal Highway Administration, April 1978.

63
Charpy V-notch Requirements for Fracture-Critical Members (a)

ASTM Designation Thickness, inches Zone 1 Zone 2^*^^ Zone 3^*^^

ft-lb (J) ft-lb (J) ft-lb (J)

A36

A572

Up to 4 in (102 mm)

Up to 4 in (102 mm)

mechanically fastened

25(34)

II at 70°F(12°C) 25(34)

II at 40°F(4°C) 25(34) at 10°F)

II

' Up to 2 in (51 mm)

II II II

A588 Up to 4 in (102 mm)

mechanically fastened

II II "

11 Up to 2 in (51 mm)

welded

II II II

II Over 2 in to 4 in (51-102 mm) welded

30(41) at 70°F(21°C) 30(41) at 40°F(4°C) 30(41) atlO°F(-12°C)

A514 Up to 4 in (102 mm)

mechanically fastened

35(48) at 0°F(-18°C) 5(48) at 0°F(-18°C) 35(48) at -30°C(-34°C

11 Up to 2-1/2 in (64 mm) welded

35(48) at 0°F(-18°C) 35(48) at 0°F(-18°C) 35(48) at -30°C(-34°C

II Over 2-1/2 in to

4 in (64-102 mm)

wel ded

45(61) at 0°F(-18°C) 45(61

at 0°F(-18°C) NOT PERMITTED

(a) The CVN-impact testing shall be "P" plate frequency testing in accordance with AASHTO T-243 (ASTM A673). When more than one flange or web is stripped from a larger plate, only the larger plate need be tested. The Charpy test pieces shall

be coded with respect to heat/plate number and that code shall be recorded on the

mill-test report of the steel supplier with the test result. If requested by the

Engineer, the broken pieces from each test (three specimens, six halves) shall be packaged and forwarded to the Quality Assurance organization of the State. Use

the average of three (3) tests. If the energy value for more than one of three

test specimens is below the minimum average requirements, or if the energy value

for one of the three specimens is less than two thirds (2/3) of the specified

minimum average requirements, a retest shall be made and the energy value obtained

from each of the three retest specimens shall equal or exceed the specified

minimum average requirement.

(b) Zone 1: Minimum Service Temperature 0°F (-18°C) and above

(c) Zone 2: Minimum Service Temperature from -1° (-19°C) to -30°F

(-34°C).

(d) Zone 3: Minimum Service Temperature from -31° (-35°C) to -60°F

(-51°C).

If the yield strength of the material exceeds 65 ksi(448 MPa), the temperature for the CVN value acceptability shall be reduced by 15°F (8°C) for each increment of 10 ksi

(69 MPa) above 65 ksi (448 MPa). The yield strength is the value given in the

certified "Mill Test Report."

64
LARGE ROTATING EQUIPMENT

for

Electrical Power Generation

1. Overview

A. Codes and regulations

Design practices are proprietary to the equipment manufacturers. There are no design codes or federal regulafions applicable.

B. Equipment

a. Steam turbine rotors and shafts

b. Generator rotors

c. Steam and land-based gas turbine

d. Discs and wheels

C. Scope

Due to the absence of design codes for large rotating equipment, this summary is

limited to general information of a non-proprietary nature.

2. Structural Design Conditions

A. Design life; 40 years

B. Loads

a. Centrifugal stresses due to rotation

b. Thermal stress

c. Bending of large shafts from dead weight

d. Shrink-fit stresses for discs

e. Stop-start fatigue cycle

f. Small amplitude vibration

C. Initial damage assumptions

a. Company specific

b. Generally based on operating experience, backed up by fracture mechanics

analysis

D. Safety factors

a. Company specific

b. Factor of 2 on yield strength is typical

65
3. Materials and Processes

A. Selection, specifications

a. Generator rotors--ASTM A 469

b. Turbine rotors and shafts--ASTM A 470

c. Turbine rotor disks and wheels ASTM A 471

d. Proprietary company specifications, more rigorous than the ASTM

specifications, may bo the procurement requirements.

B. Processes

a. Basic elctric furnace melting

b. Vacuum treated prior to or during pouring to remove objectionable gases,

particularly hydrogen

c. Forged using equipment with sufficient power to hot work the metal throughout

its section. The axial center of the forging is maintained common with the

axial center of the ingot.

d. Heat treatment--quench and tempered (A469 and A 471) or double normalized

(A47C)

0 . Stress rel i ef--requi red after rough machining

C. Properties

a. Minimum tensile and impact requirements in accordance with procurement

specification (ASTM or company)

b. Companies have ongoing material evaluations to qualify suppliers and to assess material variability.

D . A1 lowable stresses

Company specific

4. Design Practices

A. Based on successful operating history

B. Quality materials

C. Specified operating stresses

D. Minimal stress concentrati ons

66
5. Analysis

A. Stress analysis

a. Closed form methods

b. Finite element analysis

c. Photo elastic stress analysis

B. Fatigue analysis

a. Mainly conventional S-fl approach

b. Low cycle fatigue used to analyze discs

c. Fracture mechanics anal'ysi s--back up analysis and for in-service inspection

6. Qual ity Assurance

A. Material procurement controls

a. ASTM and company material specifications

b. In-house material eval uati on--check test not receiving inspection

B. Inspection

a. Ultrasonics (bore is critical region)

b. Magnetic particle

c. Defect limits are company specific

d. X ray where applicable, but generally parts are too big for x ray

C. Verification testing

a. Overspeed rotation tests

b. 20 percent overspeed--i ncreases stresses 40 percent

67
PRESSURE VESSELS

1. Overview

A. Codes

a. American Society of Mechanical Engineers (ASME) Boiler and Pressure Vessel

Code, Section VIII, Pressure Vessels

Division 1-applicable to vessels designed for pressures not exceeding

3,000 psi (21 MPa)-Factor of Safety against burst = 4

Division 2-Alternative Rules-more precise design and inspection procedures

are required than for Division 1-Pressures greater than 3,000 psi (21 MPa) are al lowed-Factor of Safety against burst = 3

2. Structural Design Criteria

A. Design life-not specified

B. Loads

a. Internal or external pressure

b. Impact, including rapidly fluctuating pressures

c. Weight of vessel and contents

d. Superimposed loads from other equipment

e. Wind loads, and earthquake loads where required

f. Reactions of supports

g. Effect of temperature gradients

C. Initial damage assumption-none

"All injurious flaws shall be removed"

D. Safety factors

3 or 4 on burst, depending on Division 1 or Division 2 rules

3. Materials and Processes

A. Only certain materials permitted as given by Code Material

Specifications, Section II Part A-Ferrous Materials

Part B-Nonferrous Materials

Part C-Welding Rods, Electrodes, and Filler Metals

68
B. Properties

Minimum tensile values as specified in Code

C. Special toughness reuirements

a. Carbon and low-alloy steels

Minimum Charpy V-Notch Impact Test Requirements for these steels vary from 10 to 20 ft lb (14 to 27 J) (depending on deoxidation) at minimum service

temperature. (Section VI 1 1 ,Di vision 2, AM-210)

b. Quenched and tempered ferritic steels

Minimum lateral expansion of 0.015 in (3.8 mm) at minimum service

temperature. (Section V 1 1 1 ,Di vi sion 2, AM-310) For service temperatures

below -20°F (-29°C), drop-weight NOT tests shall be made with NOT (no-break) to be at or below that temperature.

D. Allowable stresses

a. Section VIII, Division 2, Alternate Rules

Referred to as design stress intensity values, S^,. Design allowable values

are given in Section VIII, Division 2, Article M-6, "Material Design Data,"

for materials as a function of temperature. For example, SA-372 steel with a specified minimum yield of 35 ksi (241 MPa) and tensile of 60 ksi (413 MPa) has a design stress allowable ranging from 20(aj/3) ksi (138 MPa) at 100°F (38°C) to 17 ksi (117 MPa) at 650°F (349°C).

b. Section VIII, Division 1 Design allowable stress values given in UG-23--"Maximum Allowable Stress Values." For example. Table UCS-23 gives maximum allowable stress for SA-36

steel as 12.7 ksi (88 MPa). Minimum yield strength is 36 ksi (248 MPa) and minimum tensile strength is 58 ksi (400 MPa). The allowable stress is less

than oj/4 because SA-36 is a structural grade.

4. Design and Analysis

A. Design requirements specified in Code.

B. Thickness of vessel parts are established by formulas given in Code using the most severe combination of loadings and allowable stress intensities (also given in Code for each material) expected to occur.

C. Formulas are based on maximum shear stress theory of failure.

D. Standard details

Acceptable transition details presented in Code--Design Requirements

69
E. Fatigue evaluation

a. Specific rules are established for conditions when fatigue analyses are mandatory (Conditions A and B, Section VIII, Division 2, Alternate Rules,

AD-160)

b. Fatigue analysis based on S-N curves that have factor of safety of 20 on life

or 2 on stress.

c. Stress ranges for fatigue analyses are based on startup and shutdown, number

of operating pressure cycles, thermal stresses, and mechanical loading, e.g., piping reactions.

F. Experimental stress analysis shall be conducted to substantiate analysis of critical parts for which theoretical stress analysis is inadequate.

5. Quality Assurance

A. Material procurement

Section II, Material Specifications-same as ASTM material specifications

B. Fabrication and processing control

General fabrication requirements given in Section VIII, Article F-1, General

Fabrication Requirements and Section IX, Welding and Brazing Qualifications.

C. Inspection

Section V, Nondestructive Examination

Various methods (radiographic, ultrasonic, magnetic particle, liquid penetrant,

visual, eddy current, and leak testing) are specified to detect both surface and internal discontinuities.

D. Hydrotest

a. After all required heat treatments have been performed, the completed vessel

shall be sujected to either a hydrostatic test (Article T-3) or a pneumatic

test (Article T-4)

b. Hydrostatic test pressure to be not less than 1.25 times the design pressure

times the lowest ratio of design stress at the test temperature of the vessel

to the design stress at design temperature.

c. Pneumatic test can be used only if vessel cannot be filled with water. Required pneumatic test pressure shall be not less than 1.15 times the design

pressure times the lowest ratio of design stress at test temperature to design stress at design temperature.

E. Safety valves set approximately 10 percent above the operating pressure.

70
6. Fracture Mechanics Analysis

Not used in Section VIII, Pressure Vessels. Fracture mechanics i_s_ used in

Section III, Nuclear Power Plant Components.

71
NUCLEAR PRESSURE VESSELS

1. Overview

A. Codes and Regulations

a. American Society of Mechanical Engineers (ASME) Boiler

and Pressure Vessel Code - Section III - Nuclear Power

Plant Components

b. Nuclear Regulatory Commission (NRC)

2. Structural Design Criteria

A. Design life - not specified (fatigue curves ~ 25 years)

B. Loads

a. internal and external pressure

b. impact loads, including rapidly fluctuating pressures

c. weight of the component and contents

d. superimposed loads such as other components, operating

equipment, etc.

e. wind loads, snow loads, earthquakes

f. reactions of supporting lugs, rings, etc.

g. temperature effects

C. Maximum shear stress theory

a = 1/2 (a - a ) max 1 3

Generally o <

max

at operating temperatures

Example: carbon steel - a =24 ksi (165 MPa), a = 45 ksi (310 MPa) ys u I c

max = 15 @ 100°F (38°C)

14.2 @ 30QOF (1490c)

12.9 @ 50QOf (260°C)

11.5 @ 700Of (3710c)

D. Detailed stress report showing stress analysis is required for normal

stress, shear stress, bending stress, secondary stress, thermal

stress, and fatigue stresses.

72
E. Safety factors:

Primary stress 3 based on ultimate

Fatigue - use fatigue design curves based on FS = 2

on stress level for no initiation in actual tests.

Fracture - very large based on assumed flaw depth of 1/4 wall

wall thickness (see section on damage tolerance).

Materials and Processes

A. ASTM and SA grades.

B. Properties - Minimums specified by Code and tested by manufacturer

according to ASME Code - NB-2000, Material

C. Fracture Toughness Requirements

a. Drop weight tests to determine NDT according to ASTM E-208-60 standard

b. Charpy V-notch tests according to ASTM SA-370

c. Requirements for toughness levels described in Article G-2000 (copy

attached)

1.

Establish RT j^^^( reference NDT temperature)

2. Establish - reference critical stress intensity factor

IR for dynamic loading for all operating temperatures

3. Use CVN impact test results to verify

4. Assume surface flaw depth of 1/4 wall thickness

5. Calculate appl ied stress intensity factors at all operating

level

1) = stress intensity factor due to membrane stress

2) = stress intensity factor due to thermal stress

It 6. To establish allowable pressure at any operating temperature.
4 . Quality assurance

A. ASTM and SA material requirements

B. Actual tension, CVN, NOT tests by manufacturer

C. Preparation of Materials Report and Stress Report

D. ASME Fabrication Requirements NB-4000 includes procedure

qualification tests, radiography, ultrasonic, and magnetic

particle testing, weld production tests of weld metal and

heat affected zone, specified repair procedures, etc.

5. Verification testing

A. Hydrotesting at 1.25 times system design pressure

B. Use of pressure gages

C. Periodic in-service inspection according to ASME

Section XI - Division 1 -

D. a. Owners responsibility

b. NRC control

c. Examination and inspection

d. Standards for Examination Evaluation

e. Repair Procedure

f. System pressure tests

g. Records and reports

h. Replacements

74
GAS AND OIL PIPELINES

1. Overview

A. Codes

a. Liquid Petroleum Transportation Piping Systems ANSI B31.4 [1]

b. Gas Transmission and Distribution Piping Systems ANSI B31.8 [2]

c. Standard for Welding Pipe Lines and Related Facilities API Std. 1104 [3]

B. Regulations

a. Transportation of Liquids _by Pipeline 49 CFR 195 [4]

b. Transportation of Natural and Other Gas by Pipeline: Minimum Federal Safety

Standards, 49 CFR 192 [5]

C. Practices

a. Material procurement specification: Requirements on line pipe quality

specified by owner companies frequently exceed the minimum requirements of

the applicable codes and regulations.

b. Nondestructive testing of field welds: Federal regulations require

inspection of from 10 to 100 percent of each day's field butt welds, the

percentage depending on location (e.g., 10 percent in isolated locations,

100 percent under highway crossings). In practice, 100 percent inspection is frequently required by the owner company and/or by federal regulatory

authorities.

c. Crack arrest: Although not required by codes and regulations, many owner companies require crack arrest capabilities in gas pipelines. This is generally achieved by specifying minimum toughness requirements sufficient to avoid long running cracks or by specifying use of mechanical crack arrestors

at intervals along the line.

D. Scope Fracture control practices are summarized for large diameter (> 12 inch, .3 m)

steel pipelines for transportation of oil and gas. Codes and regulations have

additional provisions for non-ferrous and plastic pipe, and for small idameter

pipe.

2. Structural Design Conditions

A. Design life: not specified. Determined by size of oil/gas reservoir.

Trans-Alaska Pipeline has a design life of 30 years. Other pipelines have been in operation longer than 30 years.

75
B. Loads

a. Internal design pressure

b. External design pressure

c. Fluid expansion effects

d. Dynamic effects

Impact

Wi nd Earthquake

Vibration

Subsidence

Waves and Current

e. Weight effects

Live loads--] iquid transported plus ice and snow Dead 1 oads--wei ght of pipe, components, coatings, backfill, and unsupported

attachments

f. Thermal expansion and contraction

g. Relative movement of connected components

h. Surge pressure--surge pressure has less than 20 percent design pressure.

C. Initial damage assumptionsd

a. Oil pipelines: none

b. Gas pipelines: Frequently owner specifications require crack arrest capability. Thus, the pipeline is designed to arrest a through-thickness

crack that exceeds critical size at design pressure.

D. Locations

Design pressures (gas lines only) and inspection frequency are functions of location. For gas lines, the class location unit is an area that extends 400 yards (366 m) (B31.8) or 220 yards (201 m) (49 CFR 192) on either side of the

centerline of any continuous one-mile length of pipeline. For gas lines, four classes are defined

as a function of population density and degree of development. For oil lines,

pollution potential is also considered.

E. Design temperature

a. Oil: Design stress constant for -20°F<T<+25°F (29°C < T < -4°C).

b. Gas: Temperature derating factor used for T > 250°F (121°C)

Gas Temperature Derating factor

T 250°F (121°C) 1.000

300°F (149°C) .967 350°F (176°C) .933 400°F (204°C) .900 450°F (232°C) .867

76
For immediate temperatures, the derating factor is determined by

i nterpol ation.

c. Low temperature service: cautionary notes regarding brittle fracture

3. Materials and Processes

A. Selection, specifications

a. Line pipe generally conforms to API specifications.

API 5L Steel (seamless and welded) line pipe

API 5LS Steel (special welded) line pipe

API 5LU Steel (seamless and welded) ultrahigh test heat treated line

pipe

API 5LX Steel (seamless and welded) high test line pipe

b. Materials for components generally conform to ASTM specifications.

B. Properties

Allowable stresses for design based on the specified minimum yield stress (SMYS).

C. Allowable stresses

S = (SMYS) X F X E X T where S = allowable stress

F = design factor

E = weld joint factor

T = temperature derating factor for gas lines (see 2.E.b.)

a. F-values

Oil pipelines: F = .72 unless pipe has been cold worked to meet SMYS and subsequently heated, other than by welding, to 600°F (315°C) or more.

For latter case, F = 0.54.

Gas pipelines: F is a function of location.

Class 1 F = 0.72

Class 2 F = 0.60

Class 3 F = 0.50

Class 4 F = 0.40

b. E-values

For all commonly used API 5L, 5LS, or 5LX pipe, E = 1.00. For API 5L pipe

that is furnace butt welded, E = 0.65 and furnaced lap welded, E = 0.80.

c. Surge pressures must not raise the stress more than 10 percent.

d. Allowable stresses--other than tension

Compression = tension allowable

Shear = 45 percent SMYS Bearing = 90 percent SMYS

77
e. Structural supports

Tension (and compression) 66 percent SMYS

D. Minimum toughness

a. API requirements depend on specifications and strength level, e.g.,

API 5LX-65--base metal requirements, none on welds or HAZ. Transverse shear

energy: 50 percent ave, 35 percent min at O^C or +10°C, 2/3 size

specimens

b. Specific pipelines have more stringent requirements, e.g., Trans-Alaska

Pipeline system.

Toughess on 5LX 65 pipe (full-size specimens longitudinal)

Base metal 50 ft lb (68J) at -10°C (Ave of 3), 35 ft lb (48J) min,

50 percent shear

Weld 30 ft lb (41J) at 0°C (Ave of 3), 20 ft lb (27J), min

HAZ 30 ft lb (41J) at -Oc (Ave of 3), 20 ft lb (27J), min

4. Design

A. Design for damage tolerance

Oi 1 --none Gas--crack arrest

B. Standard details

a. Straight pipe

Dimensional limits specified to assure good joint fit-up

b. Curved pipe

Pipe bending limits specified

c. Intersections, closures, ranges, reducers, and elbows

Design procedures standardized

d. Fittings, valves, and flanges

Standard components used

C. Joining practices

a. Acceptable butt-welded joint designs are standardized.

b. Attachment details for flanges recommended in B31.4

c. Details for reinforcement of openings specified

78
5. Analysis

A. Straight pipe and bends

t = P-jD/2S where t = wall thickness

= internal pressure

D = pipe diameter (nominal outside diam.)

S = allowable stress value.

B. Expansion and flexibility

$L = Ea(T2-T]^) -vS^

S|_ = longitudinal compressive stress

E = Young's modulus

ct = Linear coefficient of thermal expansion

V

= Poisson's ratio = 0.30 for steel

T]^ = Temperature at time of installation

T

2 = Operating temperature

= Hoop stress due to internal pressure

6. Qual ity Assurance

A. Material procurement controls

API and supplemental owner-company requirements on strength, toughness, hardness,

chemistry, dimensional tolerances, and inspection

B. Fabricating and processing controls (per API 1104)

a. Weld procedure qualifications

b. Welder qualifications

c. Controls on repair and removal of defects

d. Controls on weld joint design, preparation, and alignment

C. Inspection

a. Methods: commonly visual and radiography

b. Frequency: function of location (see 2.D).

c. Standards of acceptability (per API 1104)

d. Qualified inspectors and procedures required

D. Pressure testing

a. Oil pipelines

For operating stresses < 20 percent SMYS, pneumatic leak test at 100 psig(0.7

MPa] is satisfactory.

79
For operating stress > 20 percent SMYS, hydrotesting equivalent to not less than 1.25 times the internal design pressure at that location is required,

b. Gas pipelines

For operating stresses < 30 percent SMYS but > 100 psig (0.7 MPa), leak tests

requi red For operating stresses > 30 percent SMYS, hydro or pneumatic testing required

at test pressures specified as a function of location:

Class 1: Test pressure exceed 1.1 x m.o.p. (maximum operating pressure)

Class 2: Test pressure exceeds 1.25 x m.o.p.

Class 3 and 4: Test pressure exceeds 1.40 x m.o.p

7. Operation and Maintenance Procedures

A. Written plan for operating, maintenance, and emergency

a. Operate and maintain facilities in accordance with the plan.

b. Keep records necessary to administer the plan properly.

c. Modify the plan as required by changes in population density or operating

conditions.

B. Elements of the plan

a. Surveillance and patrolling

b. Repair procedures

c. Testing of repairs

d. Leak records

e. Failure analysis

f. Procedures for abandoning facilities

g. Changes in class location

h. Valve maintenance

i . Corrosi on control

j. Emergency plans

k. Review procedure for proposed changes in operating conditions.

l. Liaison with local authorities

m. Pipeline markers

n. Maintenance of pressure limiting and pressure regulating stations

References

1. Liquid Petroleum Transportation Piping Systems, American National Standards Institute,

ANSI B31.4, American Society for Mechanical Engineers, New York, 1974.

2. Gas Transmission and Distribution Piping Systems, ANSI B31.8, American Society for Mechanical Engineers, New York, 1975.

30
3. Standard for Welding Pipelines and Related Facilities, API Standard 1104, American

Petroleum Institute, Washington, D.C., 13th Edition, 1973.

4. Transportation of Liquids by Pipeline, Part 195, Title 49, Code of Federal

Regulations, 1978.

5., Transportation of natural and Other Gas by Pipeline: Minimum Federal Safety

Standards, Part 192, Title 49, Code of Federal Regulations 1978.

81
PRESSURE PIPING--POWER AND CHEMICAL INDUSTRIES

1. Overview

A. Codes

a. Power Piping, ANSI B31.1 [1]

b. Chemical Plant and Petroleum Refinery Piping, ANSI B31.3 [2]

B. Regulations

a. Federal: none

b. State and local; may require conformance to B31 codes

2. Structural Design Conditions

A. Design life--not specified

B. Loads

a. Internal pressure

Static head plus sustained fluid operating pressure

b. External pressure

Maximum differential pressure

c. Ambient effects

Fluid expansion/contraction due to heating/cooling

d. Dynamic effects

Impact (e.g., water hammer effect)

Uind--same as specified for buildings

Earthquake--not concurrent with wind

Vibration

Discharge reactions

e. Height effects

Life load: medium plus snow, ice

Dead load; system weight and permanent loads

f. Thermal expansion and contractoin

Duo to reactions, temperature gradients, and differential thermal expansion

g. Effects of support, anchor, and terminal movements

C. Initial damage assumption: none

D. Temperaturo--B31 .1

a. Fluid temperature unless shown to be lower

b. Heat exchanger piping; highest temperature expected in that section of the

82
Piping from fired equipment: design temperature based on continuous (not

peak) operating condition

c

E. Temperature--B31 .3

a. Design temperature: most severe condition of coincident pressure and temperature (i.e., not peak)

b. Uninsulated piping, T < 100°F (38°C)

Piping temperature equals fluid temperature

c. Uninsulated piping, T 2 100° (38°C)

Component

Metal Temperature

(percent of fluid temperature)

95 percent

90 percent

85 percent

80 percent

100 percent

d. Insulated (internal) piping

Based on heat transfer calculations

e. Insulated (external) piping

100 percent of fluid temperature

Thin wall components

Flanged fittings and flanges

Lap joint flanges

Bolting

Nonmetal lie piping

3. Materials and Processes

A. Selection specifications

a. Materials specifications listed in respective codes

b. Uni isted materials

B31 .l--al 1 owabl e stress must be assigned by B31.1 prior to use.

B31 .3--al lowable stress must be established in accordance with the allowable

stress basis of the B31.1 code.

B. Limitations on materials

a. Steels

Temperature limits to avoid graphitization

Carbon content limits (C _< 0.35 percent) to improve weldability

b. Cast irons

Specific limits placed on usage of cast iron, malleable iron, ductile iron,

and high silicon iron regarding temperature, pressure, and impact

c. Nonferrous metals

Cautionary note regarding fire hazard and galvanic corrosion

B3
d. Welding

Not permitted in ductile iron or on aluminum alloy castings

C. Allowable stress basis--basic allowable stress values at temperature shall not exceed the lowest of the following (property x factor):

Factor

Property B31.1 B31.3 B31.3

Specified minimum tensile strength at room temperature 1/4 1/3 1/4

Tensile strength at temperature

Specified minimum yield strength at room temperature

1/4 1/3 1/4

Ferrous 5/8 2/3 5/8

Nonferrous 2/3 2/3

Yield strength at temperature

Ferrous 5/8 2/3 5/8

Nonferrous 2/3 2/3

Average stress for a creep rate of .01 percent/1000 h 1.0 1.0 1.0

Average stress for rupture at 100,000 h 2/3 2/3 2/3

Minimum stress for rupture at 100,000 h 4/5 4/5 4/5

Notes: 1. For austenitic stainless steels and certain nickel alloys allowable stresses

up to 90 percent of the yield strength at temperature may be used if the

added deformation is not deleterious.

2. For heat treated bolting materials, a factor of 1/5 is used on specified

minimum tensile strength at room temperature.

D. Properties

a. Strength vs. temperature: Trend curves are from ASME Boilder and Pressure

Vessel Code. These curves are factored in accordance with Part C above to derive allowable stresses. Section VIII, Division 1 factors are used for

ANSI B31.1 and Section VIII, Division 2 factors are used for ANSI B31.3.

b. Minimum toughness requi rements

84
Specified Minimum Tensile

Strength

Carbon and low alloy steels

0^3 1 65 ksi (448 MPa)

65 (448 MPa) < < 75 ksi (517 MPa)

75 (517 MPa) < < 95 ksi (655 MPa)

a >95 ksi (655 MPa) ts ~

Stainless steels

4. Design

Charpy Impact Energy, ft lb (J)

Killed Steels Other Steels

Ave Min Ave Min

13 (18) 10 (14) 10 (14) 7 (10)

15 (20) 12 (16) 13 (18) 10 (14)

20 (27) 15 (20) —

Lateral Expansion, inch (mm)

0.015 (3.8)

0.015 (3.8)

A. Design for damage tolerance —formalized procedure not specified, however, B31.3

states: "Provisions shall be made to contain or safely relieve any excessive

pressures to which the system may be subjected, e.g., ambient influences, improper

operation, and failure of control devices."

B. Standard detai 1 s--code or ASTM specification requirements for:

a. Reinforcements

b. Closures

c. Flanges and blanks

d. Reducers

e. Valves, fitting, etc.

C. Joining practices

a. Welding: practices, procedure qualification, and welder qualification per

ASME, Section IX b. Brazing: qualification per ASME, Section IX, Part QB

5. Analysis

A. Stress analysi s--standard formula for:

a. Straight pipe under internal pressure

b. Intersections

c. Piping components

d. Sustained loads, thermal expansion, flexibility

e. Reinforcements

85
B. Fatigue analysi s--the allowable stress range for expansion stresses is reduced by

a factor, f, for cyclic conditions, where f is a function of the numer of full

temperature cycles:

Stress range reduction factors, f

Temperature cycles, N Factor f

M < 7000 1.0

7000 to 14,000 0.9

14.000 to 22,000 0.8

22.000 to 45,000 0.7

45.000 to 100,000 0.6

Over 100,000 0.5

C. Fracture mechanics analysi s--none

6 . Qual i ty Assurance

A. Material procurement control S--ASTM specifications

B. Fabrication and processing controls

Weld procedure and welder qualifications per ASME IX

C. Inspecti on--to assure compliance with engineering design and with the requirements

of B31.1

Responsibility of the owner Code compliance verified by authorized code inspector

Certified inspectors

D. NDE of wel ds--acceptance standards given

Visual

Magnetic particle per ASME V, Article 7 Liquid penetrant per ASME V, Article 6 Radiography per ASME V, Article 3 Ultrasonic per ASME V, Article 5

86
E. Leak testi ng--boi 1 er external piping to be in compliance with ASME I requires

hydrotest per ASME Section PC-99

Leak testing per requirements of owner

o _< 90 percent in all leak tests

References

1. Power Piping, American National Standards Institute, ANSI B31.1, American Society of

Mechanical Engineers, New York 1977.

2. Chemical Plant and Petroleum Refining Piping, ANSI B31.3, ASME, New York, 1977.

87
USAF AIRCRAFT

Overview

Source. AIAA Workshop on Analysis o-i" USAF Aircraft Structural Durability and Danage

Tolerance, Washington, D.C., April 1978.

A. Standards and specifications

a. Aircraft Structural Integrity Program

riIL-STDIl-1530A

b. Specifications for Airplane Strength and Rigidity

MIL-A-8860 series

c. Airplane Damage Tolerance Requirements

HIL-A-83444

B. Systems experience with fracture mechanics

a. flew aircraft

Contract-specific requirements

A-10 and B-1

flIL-STDfl-1530A requirements

F-15; by contract modification (ECP)

F-IG. original contract requirement

b. Fleet ai rcraft--for inspection and modification planning

Evaluations completed

F-4 C/D, F-4E, A-7, C-5A, C141 A/B , F-111, and B-52

Evaluations in progress

T-38, E-3A, F-5E/F, KC-135, SR-71, T-39, F-5A/B

Evaluations being started

C-130, B-52C/H

c. Engine Structural Integrity Program (ENSIP)

EflSIP still under development

Tentative EflSIP requirements being used to evaluate F-lOO engines

C. Summary of pre-1970 approach

a. Design and analysis

Fatigue analysis used to evaluate both durability and damage tolerance. Moan

life was predicted using conventional S-fl data. Miner's rule for damage

accumulation, and a block spectrum. A scatter factor of 4 was used to predict minimum life, i.e., mean life/4. The scatter factor was assumed to

account for the influences of initial quality level, environment, and

material variability.

88
b. Full seal G testing

A production airplane vjas fatigue tested using a block spectrum for the

equivalent of 4 service lives. Completion of the test v;ithout failure

constituted proof of compliance to the aircraft structural integrity

requi rements . Test scheduling v;as not related to aircraft production

schedules. Tear-dov/n inspection of the test article was not generally

requi red.

c. Force managGment--i nspecti on and modification

The basic promise of force management was that safe life = 1/4 of test life.

Inspections, modifications, and repairs were scheduled for 1/4 of test failure time. Inspection and maintenance times were adjusted for aircraft

usage based on service life monitoring programs.

D. Problems with pre-1970 approach

a. Safe-life approach didn't always work for safety and durability.

b. High strength, flaw sensitive, stress corrosion susceptible materials not precluded

c. High stress levels not precluded

d. Full scale testing did not; reflect developmental nature of test,

include damage tolerance tests,

use flight-simulation loading profiles, ensure timely data acquisition, and ensure critical data area identification by tear-down inspection.

e. Force management procedures need updating, i.e., fracture mechanics approach

f. Poor correlation between test and service

E. Summary of problems with pre-1970 aircraft

a. Severe usage

TAG T-38, F-5A/B

b. High stress levels--general

C-5A wing, KC-135 wing

c . High stress 1 evel s--l ocal

TAG T-38, F-5A/B, F-4G/D

d. Poor material toughness

B-52 D wing, F-111 wing fittings. KG- 135 wing

G. Marginal initial quality

TAG T-38, F-5A/B, G-5A wing, F-111 wing fittings

f. Lack of damage tolerance

TAG T-38, F-5A/B, B52D wing, F-111 wing fittings, F-4G/D

9- Late testing

G-5A, F-111

89
h. Test spectrum problems

KC-135, F-4C/D

Structural Design Conditions

A. Design life

a. Stipulated in contract established by force planners

b. Typical values

Fi ghters Bombers Cargo/Transport

Years of service 20 25 25-30

Flight hours 8,000 15,000 30,000

Humber of f 1 i ghts 6,000 3,000 6,000

Humber of landings 8,000 5,000 5-10,000

Fuselage pressurizations 8,000 5,000 5-10,000

B. Loads

aExceedance data in MIL-A-886GB specification

b. Mi ssi on profiles and mission mix in contract, per force planners

c

Specifications for airplane strength and rigidity

8860. General specification for ... 8861; Flight loads

8862. Landing and ground handling loads

8865. Miscellaneous loads

8866; Repeated loads and fatigue

8867; Ground tests

8869; Huclear weapons effects

8870. Flutter, divergence, and other aeroolastic instabilities

8892; Vi brati on 8893; Sonic fatigue

C. Environment

a. MIL A 886GB--desi gn chemi cal /thermal environment spectra

The chemical and thermal environment anticipated during aircraft service is

characterized during aircraft design. Intensity, duration, frequency of occurance of all exposures to chemicals, and temperatures are included.

b. MIL A 8867B--envi ronment simulation requirements for tests

Material and joint allowables tests--eval uate chemical and thermal effects

Full scale tests--simul ate chemical and thermal environment as deemed

necessary based on allowables tests

90
D. Initial damage assumptions

Specified in MIL-A-83444 (2 July 1974) Airplane Damage Tolerance Requirements

a. Durability requirements (assumed initial quality level)

Cracks equivalent to an .005 inch (.13 mm) radius corner flaw are asssumed to exist at each location in the structure.

A larger initial flaw size may be required by the USAF if warranted by the

initial quality data for the fastener holes in question. To establish

inspection and maintenance schedules for aircraft in service, it is frequently necessary to establish the initial quality level by using

fractographic methods to track flaw growth back to time zero.

b. Damage tolerance requirements (rogue flaw)

Type of Structure Flaw Location Thickness,

inch (mm)

Flaw Type Flaw Size

inch (mm)

Safe crack growth at hole (one side) T^.05 (1.3) Through crack L = .05 (1.3:1

II II T>.05 (1.3) Corner crack L = a

= .05 (:i.3)

II away from holes T<.125 (3.2) Through crack L = .25 (6.4:1

II II T>.125 (3.2) Surface crack L = 2a = .25 (6.4)

Fail safe at hole (one side) T£.02 (.5) Through crack L = .02 (.5)

M II T>.02 (.5) Corner crack L = 2a = .02 (.5)

II away from holes T_<.05 (1.3) Through crack L = .10 (2.5:1

II M T>.05 (1.3) Surface crack L - 2a = .10 (2.5)

Corner cracks are quarter circular; surface cracks are semi-circular

L = crack length

a = crack depth

c. Continuing damage

When crack growth terminates due to structural discontinuities or element

failure, cracking is assumed to proceed at the most critical location of the

remaining structure. The initial flaw size at this location is a .005 inch

(.13 mm) radius corner crack at the edge of a hole or a .10 inch (2.5 mm)

deep semicircular surface flaw, whichever is worst. Since this flaw is assumed to exist in the initial structure, it has grown by an increment, Aa,

prior to termination of crack growth in the adjacent structure.

d. Remaining structure damage--fai 1 -safe structures

Dependent configurations (structure where a common source of cracking exists

in adjacent elements due to the nature of the fabrication procedures). The

91
flaw size at the time of element failure is the initial rogue flaw size of

2.D.b. plus the increment of crack growth, Aa, prior to element failure.

Independent configurations (structure where common source of cracking

unlikely). The flaw size at the time of element failure is the continuing

damage flaw size of 2.D.C.

Crack arrest structure (structure where unstable rapid crack propagation is arrested within a continuous area of structure and subsequent growth is slow

enough to permit detection prior to complete failure). Flaw size in

remaining structure depends on configuration. Two examples are: 1) for

conventional skin-stringer structure, 2 panels and the central stringer are assumed to be totally cracked, and 2) for tear-strap configurations, the

crack extends to the tear strap on each side of the stringer plus the

stringer is broken.

e. Flaws assumed to exist after in-service insection

Type of Inspection Flaw Location Thickness,

inch (mm)

Flaw Type Flaw Size

inch (mm)

Equivalent to initial

inspection: Same as initial damage per 2.D.b

NDI, No fastener

removal

Close visual inspection

Non-i nspectable

at hole (one side) T<.25 (6.4) Through crack L * = .25 (6.4)

II T>.25 (6.4) Corner crack L *= .25 (6.4)

open areas T<.25 (6.4) Through crack L = .5 (12.8)

It T>.25 (6.4) Surface crack L = 2a = .5 (12.8)

Accessible areas all T Through crack L = 2 (51)

initial damage plus growth increment Aa prior to inspection

L* = uncovered length, i.e., beyond fastener head, nut, etc.

E. Safety factors

a. Static strength: factor of 1.5 on load

b. Fatigue (durabi 1 ity) : None, formerly a scatter factor of 4 on life.

Currently, economic life of the airframe must exceed the design service

life.

c. Safe crack growth: factor of 2 on inspection interval

Due to the damage assumptions required after inspection, it is sometimes

easier to qualify structure as non-i nspectable, which requires a factor of

safety of 2 on design life.

92
3. Materials and Processes

A. Selection

Based on concept/wei ght/matori al /cost trade studies, i.e., not a set list as in some codes

B. Properties

a. MIL-HDBK-5 (also-17 and-23 for plastics and composites)

b. Fracture mechanics properties. MCIC-HDBK-01

c. Contractor data: additional tests as required

d. Other sources: require approval by DSAF

C. Specifications

Developed by contractor. Approved by USAF

4. Design and Analysis

A. Design for damage tolerance

a. Slow crack growth structure: Design concepts where stress levels are limited

to assure that cracks will not grow to critical size during specified periods

of usage which depend on degree of inspectabi 1 ity.

b. Crack-arrest fail-safe structure: Structure designed such that unstable,

rapid propagation is stopped within a continuous area of structure and

subsequent growth is slow enough to permit detection prior to complete

fai lure.

c. Multiple load-path, fail-safe structure: Structure designed in segments such

that localized damage is contained within one or two segments and the

remaining structure exhibits slow crack growth and provides sufficient

strength to the subsequent inspection.

B. Joints

a. Design development and joint allowables tests are conducted on representative

joints (mechanically fastened and welded) to establish static strength and to verify crack growth analysis models that will be used for durability and

damage tolerance evaluations.

b. The beneficial effects of interference fasteners, cold expanded holes, joint

clamp-up, and other specific joint design and assembly procedures may be used

in achieving compliance to the flaw growth requirements of MIL-A-83444.

93
C. Stress analysis

a. Consists of the analytical determination of the stresses, deformations, and

margins of safety resulting from the external loads and temperatures imposed

on the airframe.

b. Used to verify airframe strength, provide stresses for fracture mechanics

analysis, identify critical components for fracture control and for design

development tests, and to select loading conditions for structural testing.

It is also used as the basis for material review actions, for determination

of the adequacy of structural changes, and for assessing the significance of new loads due to changed service requirements.

D. Fatigue (durability) analysis

a. Consists of the semi-empirical determination of the growth behavior of small

flaws assumed to exist at critical locations throughout the structure due to application of the design service loads spectra. The analysis must account

for load sequence and environmental interactions, material property

variations, and analytical uncertainties.

b. Used to verify that the economic life of the airframe exceeds the design

service life. This is accomplished by conducting the analysis between the

limits of flaw sizes representative of the initial quality level (the minimum

allowable initial flaw size is a .005-inch (.13 mm) radius corner crack on one side of a hole) and flaw sizes that are readily repaired during depot

level inspections. Generally the limiting flaw size is the maximum growth

that can be eliminated by oversizing the hole to the next fastener size,

generally about .030 inch (.76 mm).

Fracture mechanics (damage tolerance) analysis

a. Consists of the same flaw growth analysis used in 4.D.a except the initial

flaw sizes are relatively large (rogue flaws) as summarized in 2.D.b.

Initial flaws sizes and residual strength requirements are specified as a function of design concept (fail-safe or not) and inspectabil ity.

b. Used to verify the safety of the airframe from potentially deleterious

effects of initial defects caused by material manufacturing or processing

malfunctions. The analyses are used to calculate critical flaw sizes,

residual strengths, safe crack growth periods, and inspection intervals.

Fail-safe crack-arrest analysis

a. Consists of the analytical determination of the stress intensity factor as a function of crack length for a stress level corresponding to the lesser of

design limit load or the maximum credible load multiplied by a dynamic factor

(DF = 1.15 unless test or analytical data indicate otherwise).

94
b. Used to verify that crack arrest will occur in the configuration being

evaluated for the specified level of initial danage and further to verify

that subsequent fatigue crack growth will be slow enough to permit detection

pri or to failure.

G. Fail-safe multiple-1 oad-path analysis

a. Consists of the analytical determi nati on of the stresses and deformations

caused by failure of a load path under specified loading conditions

b. Used to verify that load path failure will not cause complete structural

failure and further to verify that fatigue crack growth in the remaining

structure will be slow enough for specified initial flaw conditions to permit

detection prior to failure

5. Qual ity Assurance

A. Material procurement controls

a. Material specifications prepared by contractor and approved by USAF

b. Minimum fracture toughness requirements are specified for materials to be

used to manufacture fracture-critical parts. The specified toughness must

equal or exceed the value used in design and analysis.

B. Fabrication and processing controls

a. Fastener installation procedures must be qualified to demonstrate that the

assumed initial quality levels and that the beneficial effects of fatigue

resistant fastener systems are valid.

b. Processing specifications are required to assure the processing conditions do

not degrade material toughness to a level below that used in design.

C. Inspection

a. NOT demonstration program; Exceptions to the initial flaw size requirements

of 2.D.b must be justified by an IlDT demonstration program which verifies

that all flaws equal to or greater than the design flaw size will be detected

to the specified reliability and confidence levels. The demonstration shall

be conducted using production conditions, equipment, and personnel; and the

procedures employed must subsequently be used as production inspection

requi rements

b. For each f racture-cri ti cal part, a specific inspection plan must be approved

by the USAF and used in production.

D. Traceability

Traceability is required for all fracture-critical parts that receive processing

and fabrication operations that could degrade the design material properties.

95
6 . Ful 1-Scalc Testing

A. Static tests

a. Consists of a series of laboratory tests conducted on an instrumented

airframe that simulates the loads resulting from critical flight and ground

handl i ng conditions

b. Used to verify the design ultimate strength of the airframe and to verify the

stress analysis results by correlating strain survey results with analytical

predictions

c. Scheduled to bo completed such that the flight test program can be conducted

on schedule, i.e., until test completion, flight test aircraft are restricted

to 80 percent of limit load.

B. Fatigue (durability) tests

a. Consists of the repeated application of the flight-by-flight design service

loads/environment spectra. Cycling is continued for a minimum of two

lifetimes or until the economic life is reached. Subsequently the test

article may be subjected to a teardown inspection, may be used for the damage

tolerance tests, or may be cycled more to establish life or usage extension

limits.

b. Used to verify that the economic life of the airframe exceeds the design

service life, to identify fatigue critical components (hot spots) and to

provide a basis for establishing special inspection and maintenance

requi rements

c. Scheduled such that one lifetime of testing is completed prior to the full

production go-ahead decision and two lifetimes are completed prior to delivery of the first production airplane.

C. Damage tolerance tests

a. Consists of a series of tests on full-scale articles with specified levels of

induced damage that approximate the initial damage conditions and residual

strength requirements used in design. Test articles include component test

specimens and the static and durability test articles. Generally a separate

test article specifically for damage tolerance testing is not required.

b. Used to verify the damage tolerance (and the analysis thereof) of the

fracture critical parts

c. Scheduled to follow other major test programs in order to use the same test

articles

96
D. Flight and ground operations tests

A series of tests are conducted on early aircraft, usually KDT and E aircraft to verify the airfrane safety. These include.

a. Flight and ground loads survey

b. Dynamic response tests

c. Sonic durability tests

d. Flight vibration tests

e . FI utter tests

f. Ground vibration tests

g. Structural rigidity tests.

97
NASA SPACE VENICLES

General Sources. "Structural Design Criteria Applicable to a Space Shuttle," NASA SP-8057,

January 1971.

E. ri. Ehret, "Material Control and Fracture Control Planning for the Space

Shuttle Orbiter Program," in Structural Integrity Technology, ASME , 1979.

1. Overvievj

A. Scope

This review is limited to the fracture control plan for the Space Shuttle

required by the "Space Shuttle Flight and Ground System Specification,"

Document JSC 007700, Volume X, Revision B, Johnson Space Center, Houston,

Texas. This document covers fracture control in a single paragraph which

is shown below:

3. 2. G. 1.8 Fracture Cont rol . In addition to the ultimate factors of

safety presented in paragraph 3 .2 .2 .1 .5 .2. , designs for primary structure,

windows, glass components of other subsystems, and tanks shall consider

the presence of sharp cracks, crack-like flaws, or other stress

concentrations in determining the life of the structure for sustained

loads and cyclic loads coupled with environmental effects. Parts determined to be fracture critical, including all pressure vessels*, shall

be controlled in design, fabrication, test, and operation by a formal,

NASA-approved fracture control plan as specified in SE-R-006, "JSC

Requirements for Materials and Processes."

*For the purpose of this paragraph, a pressure vessel is defined to be a component designed primarily for the storage of pressurized gases or

1 iquids.

The Fracture Control section (2.4) of "General Specification, NASA JSC

Requirements for Materials and Processes," Document SE-R-0006, Revision B,

March 29, 1976, is also reproduced less examples of organizational

responsibilities below.

FRACTURE CONTROL REQUIREMENTS

Structural failures due to crack-like flaws shall be prevented on parts

designated as critical to vehicle and crew survival by the application of

fracture control to those parts. The identification of fracture critical

98
based on the parts function, load environment, life analysis material,

and accessibility for inspection during fabrication and operation of the

vehicle. Typical characteristics of a fracture control part are.

a. Failure of the part will cause loss of the vehicle or crow.

b. Predicted operational stresses are a significant fraction of

critical stress considering the load, environment, and life

requirements of the part.

c. The part is not routinely accessible for preflight inspection.

FRACTURE CONTROL PLAN

A fracture control plan shall be developed to provide for the

fol 1 owi ng.

a. Identification of components selected for fracture control on the

basis of critically to structural f 1 i ghtworthi ness and

susceptibility to cracking or fracture.

b. Definition of organization responsibilities and procedure relevant

to fracture control.

c. Maintenance of a continuing quality assurance activity.

d. Appropriate review, performance appraisal, and control by

management

The fracture control plan shall treat all organizations and disciplines

which affect fracture control, and shall be approved by NASA prior to

implementation.

The two NASA documents that cover the fracture control requirements for the entire

Space Shuttle system are quoted because of their importance, brevity, and limited

availability. These few paragraphs indicate how NASA implements fracture control

for an incredibly complex system. In the NASA approach, the details of the

fracture control plan for each major subsystem are prepared by the contractor for

that subsystem and must bo approved by NASA prior to implementation.

A further limitation on this review is that NASA treats fracture control as part

of an overall systems specification that includes many other requirements that

contribute to structural integrity. Fracture control is simply the set of extra requirements needed to assure that "structural failures due to crack-like flaws

shall be prevented in parts designated as critical to vehicle and crow survival."

99
Ovorall structural integrity of the Space Shuttle is primarily assured by analysis

supplemented by tests to verify the analysis methods. Some full-scale testing is

required to demonstrate capability to v/ithstand the design loads and environment.

NASA's requirements for structural certification of the Space Shuttle System are specified in the Shuttle Master Verification Plan, NASA Johnson Space Center,

Report JSC-07700-10-MVP-01, May 15, 1973.

B. Subsystem fracture control plans

a. Space Shuttle Orbitor

Rockwell International, Space Revision Report SD73-SH-0082A , September 1974

b. Space Shuttle, Main Engine

Rockwell International, Rocketdyne Report RSS-8589-2, September 1977

c. Space Shuttle External Tank

Martin Marietta, Michond Assembly Facility Report MMC-ET-SE13-C

December 1, 1976

d. Space Shuttle Solid Rocket Motor

Thiokal, Uasatch Division Report T11R-10184(DC) , Revision B, May 18, 1977

NASA, Marshall Space Flight Center Report SE-020-002-2H , June 17, 1974.

C. Fracture critical parts

The requirements of the fracture control plan are applicable to parts identified

as fracture critical. The selection logic for fracture-critical parts is shown in

figure A-1.

Structural Design Conditions

A. Design life--100 missions

B. Loads

All static and dynamic loads and pressures acting on the structure are determined

and distributed throughout the structure by rational analysis. Loads encountered

in each of the operational phases (launch, space, reentry, atmosphere, flight,

etc.) must be accounted for.

C. Environment

The structure must meet all the required design characteristics after (or during,

as applicable) exposure to all credible environments. Thermal, chemical, and

natural (rain, hail, blowing sand, etc.).

100
D. Initial damage assumptions

a. Initial crack-like flaws are assumed to exist throughout the structure. The

initial flaw size assumed in analysis is a function of the inspection

method.

b. Standard NDE flaw sizes

Flaw sizes detectable with a 90 percent probability of detection and a 95 percent confidence level by inspectors certified to Level II of MIL STD 410 working to applicable aerospace industry and military standards.

These flaw sizes are assumed in routine fracture mechanics analyses.

c. Special NDE flaw sizes

Flaw sizes detectable (cigain with 90/95 statistics) by most-qualified

inspectors using part-specific inspection procedures. These flaw sizes are assumed in the fracture mechanics analysis of specified parts where special

NDE procedures are used.

d. NDE capabilities

Inspection method

Penetrant or magnetic

particle

Ultrasonics

Flaw type

Surface flaw

(Depth X length)

Embedded flaw

(di ameter)

Standard NDE

0.19 X 0.38 cm (0.075 X 0.150 in.)

or equivalent area

0.254 cm (0.100 in.)

Special NDE

0.063 X 0.127 cm

(0.025 X 0.050 in.)

or equivalent area

0.12 cm (0.047 in.)

Radiographic Surface or embedded

(depth X length)

0.7 X 1.4t

Min length = 0.38 cm (0.150 in.)

0.6 X 1.2t

Min length = 0.127 cm

(0.050 in.)

t = thickness

E. Safety factors

Recommended values (NASA SP-8057) for application to mechanically induced loads

and pressure (i.e., not thermally induced). Limit load is defined as the maximum

load expected to act on a structure in the expected operating environment. Limit

pressure is the maximum differential pressure expected to occur in service.

a. General unpressurized structure

1.5 on limit load results in o(stresses) < (ultimate tensile

strength). 1.0 on limit load results in a < (yield strength)

b. Pressurized structure

1.5 on limit load applied at limit pressure results in a < a^^j.

101
2 on limit pressure applied at zero load results in a < 1.0 on limit load results in a < o^-y.

c. Main propellant tanks

1.4 on limit pressure results in a <

1.1 on limit pressure results in a <

d. Pressure vessels

2.0 on limit pressure results in a < a^^j.

e. Fati gue--factor of four on mission cycles

3. Materials and Process

A. Selection

a. A list of approved materials is maintained by the integration contractor

(Rockwell International).

b. Selection of structural materials from this list is based on specified

materials selection criteria (Rockwell International Shuttle Specification

MF0004-003, September 20, 1974).

B. Properties

a. Sources: approved by NASA, such as MIL HDBK-5A or test data developed by

the contractor

b. "A" allowables (99 percent nonexceedance with 95 percent confidence) used for

single load path structure

c. "B" allowables (99 percent nonexceedance with 90 percent confidence) used

for redundant structure

d. Fatigue and fracture mechanics data approved by NASA

102
c. Specifications

Developed by contractor. Approved by flASA

4. Design and Analysis

A. Design for damage tolerance

Fracture critical parts shall be designed using sound and established design

procedures which include considerations for minimizing eccentricities and stress

concentrati ons , providing access and clearance for in-service inspections and

tests, and part documentation and identification requirements.

B. Joints

a. Design and analysis verified by test

b. The beneficial effects of interference fasteners, cold expanded holes and

other K-reduction joint design and assembly procedures may be used in

achieving compliance to the flaw growth requirements.

c. Uel ds--scl cction of materials and welding methods is based on consideration

of the effect of welding on the operational capability of the parts

concerned.

C. Stress analysis

a. Consists of the analytical determination of the structur-al response to the

critical loads, environments, and temperatures anticipated during the service

life of the vehi do.

b. Used for the following.

1) To define the critical combination of loads, conditions, material

properties, and interactions which determine the stress levels and

margins of safety for all structural components,

2) To show that deformations do not cause degradation of vehicle

performance,

3) To establish vehicle strength and operating restrictions, and

4) To determine stresses for the fatigue and fracture mechanics analyses.

D. Fatigue analysis

A conventional fatigue analysis (i.e., no assumed initial flaw) is conducted to determine by analysis and subsequently verify by test that all structure vital to

the integrity of the vehicle or the safety of personnel has a safe life that

exceeds by at least four times the specified service life.

103
E. Fracture nechanics analysis

All prinary structural parts arc analyzed to verify that the assumed initial flaws

do not propagate to critical length during a mininuin of foiir service lifetimes,

nominal part dimensions, fatigue crack growth rates, minimum fracture toughness

values, and semiempi rical retardation models are used in the analysis. If the

crack-growth life with standard TIDE flaw sizes does not exceed four lives, the

part is fracture critical and special TIDE is required and smaller initial flaw

sizes may be assumed (section E.O.d). If the part still does not exceed four

lives by analysis, the part must be redesigned or the analysis modified to reduce

conservatism on the basis of directly applicable tost results. If the part cannot

be redesigned or successfully reanalyzed, the design life of the component may be

reduced below that of the system and mandatory inspection intervals established.

Quality Assurance

A. Materials and processes

a. General specification (IIASA requirements)

b. Material specifications, prepared by contractor and approved by NASA

c. Process specifications; required for fabriction activities such as welding,

bonding, chemical processing, and heat treatment.

B. Inspection

a. NDE demonstration program. Special NDE flaw sizes (Z.D.d) require an HDE demonstration program to determine the minimum flaw size that can be detected

90 percent of the time with a 95 percent confidence.

b. Part specific FIDE. A specific inspection procedure must be established for

each fracture-critical part.

C. Other quality assurance responsibilities

a. Receiving inspection

b. Quality reviev/ and reporting

c. Failure documentation

d. Traceability

e. Personnel certification

D. Proof testing

a. Mandatory for all pressure vessels

b. Optional for establishing initial flaw sizes. In practice, this option is not too attractive because of the high toughness and thin section sizes of

most of the structural members.
6 . Qua! i fi cation Tests

Extensive qualification testing is required to verify the analysis procedures used in

design and to dornonstratc the capability of the structure to withstand the design loads

and environment.

A. Static tests

a. Limit conditions, to demonstrate that detrimental deformation does not occur

at limit loads and pressures

b. Ultimate conditions; to demonstrate that rupture or collapse does not occur

at ultimate load and pressure

c. Combined conditions

Loads and pressure

Loads and thermal effects

B. Life tests

a. Fatigue tests; to demonstrate safe life for four service lives

b. Fail-safe tests, to demonstrate damage tolerance and residual strength where

applicable

C. Flight and ground tests

a. Static elasticity--di vergence

b. Dynamic aeroel asti city--fl utter

c. Vibration

d. Shock

e. Thermal

105
PLANE-STRAIN

FRACTURE

TOUGHNESS

D.

-400

TEMPERATURE, “F

-200 -100 0

I I r

TEMPERATURE, °C

80

60

-40

-20

e

•I

•r“00

Fig. 1 The Effect of Strain Rate on the

Fracture Toughness of a Structural Steel

106

PLANE-STRAIN

FRACTURE

TOUGHNESS
CHARPY V-NOTCH ENERGY, ft. lbs.

0 20 40 60

Fig. 2 Critical Crack Length as a Function

of Charpy V-Notch Toughness for a Specific

Type of Size of Line Pipe

107

CRITICAL

DEFECT

LENGTH

(2c)-in
COMPLETE

NORMAL

STATIC

AND

FATIGUE

ANALYSIS co 0)

•r"

u

4-> fO a Q.

cu oo

OJ O) CO

+-> O)

<4-

4->

O

s- (/) o +-> S-

(O E DfC

s- r—

C71 03

fO

O

Q -l-i • r— a S-' *r“ ocno O) _i S-3

-l-> 1— o 1 03 <C s- u_ m CDM-o

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108
NBS-114A (REV. 8-78)

U.S. DEPT. OF COMM. BIBLIOGRAPHIC DATA

SHEET

1. PUBLICATION OR REPORT NO. NBSIR 79-1623

Z. Acc$$Si(on No.

4. TITLE AND SUBTITLE 5. Publication Date January 1980

FRACTURE CONTROL PRACTICES FOR METAL STRUCTURES

7. AUTHOR(S) 8. Performing Organ. Report No.

H. I. McHenry and S. T. Rolfe

9. PERFORMING ORGANIZATION NAME AND ADDRESS

NATIONAL BUREAU OF STANDARDS

DEPARTMENT OF COMMERCE

WASHINGTON, DC 20234

11. Contract/Grant No.

12. SPONSORING ORGANIZATION NAME AND COMPLETE ADDRESS rsfreer. City, St^te, ZIP)

David Taylor Naval Ship Research & Development Center

Annapolis, MD 21402

13. Type of Report & Period Covered

15. SUPPLEMENTARY NOTES

I I Document describes a computer program; SF-185, FIPS Software Summary, is attached.

16. ABSTRACT (A 200^word or leas factual aunmtary of most significant infonnation. If document includes a significant bibliography or

literature survey, mention it here.) Fracture control practices are the engineering procedures and requirements

that contribute to the prevention of fracture in metal structures. These

practices are identified as the elements of fracture control and each

element is defined and described. The systematic application of these

practices to the prevention of fracture in a particular structure is accomplished

by either the code approach or the performance specification approach to

fracture control. In these two approaches, the consideration given to each

of the elements of fracture control is discussed and illustrated with

examples for specific types of structures. Selected practices that may be

of use in Naval systems are discussed. An Appendix contains detailed

summaries of the fracture control practices used in each of thirteen classes

of metal structures, including ships, offshore structures, bridges, cryogenic

tanks, pressure vessels, piping, power generation equipment, and aerospace

structures.

17, KEY WORDS (six to twelve entries; alphabetical order; capitalize only the first letter of the first key word unless a proper name;

separated by semicolons)

Fracture Control , Fracture Mechanics, Mechanical Properties,

Quality Assurance, Stress Analysis, Structural Safety

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