NBSIR 77-1288 (NASC-Navy)

Stress Corrosion Behavior of

K01-T7 Aluminum Alloy

Castings

B. T. Sanderson and W. F. Gerhold

Corrosion and Electrodeposition Section

Metallurgy Division

Institute for Materials Research

National Bureau of Standards

Washington, D. C. 20234

September 1977

D

Prepared for Naval Air Systems Command

Department of the Navy

Washington, D. C. 20360

NBSIR 77-1288 (NASC-Navy)

STRESS CORROSION BEHAVIOR OF

K01-T7 ALUMINUM ALLOY

CASTINGS

B. T. Sanderson and W. F. Gerhold

Corrosion and Electrodeposition Section

Metallurgy Division

Institute for Materials Research

National Bureau of Standards

Washington, D. C. 20234

September 1977

For Official Distribution Only

Prepared for Naval Air Systems Command

Department of the Navy

Washington, D. C. 20360

U S. DEPARTMENT OF COMMERCE, Juanita M. Kreps, Secretary

Or. Sidney Harman. Under Secretary

Jordan J. Baruch, Assistant Secretary for Science and Technology

NATIONAL BUREAU OF STANDARDS, Emeat Ambler, Acting Director
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STRESS CORROSION BEHAVIOR OF

K01-T7 ALUMINUM ALLOY CASTINGS

B.T. Sanderson and W.F. Gerhold

Reference : (a) Naval Air Systems Command, Department of the

Navy, request by AIR-5203-01.

Introduction

A new high strength aluminum casting alloy designated as K01-T7 has become available. Reference^ requested that NBS conduct tests to determine

the stress-corrosion behavior of this alloy in a marine atmosphere environment.

Material

Three K01-T7 aluminum alloy castings were obtained from Electronic

Specialty Company in Pomona, California. Two of these castings appeared to

be brackets and were identified as part number C740301-50. The third casting

was a flange marked C5T27377. All of the specimens were poured from the

same heat (ES 1). Nominal chemical analysis for this aluminum alloy include

the additions of Cu 4.8%, Ag 0.5%, Mg 0.25%, and Mn 0.25% (all weight percentages). Certification test data as furnished by the supplier appear in Table 1.

Specimen Preparation

Four test specimens were prepared from each of the two bracket castings

(part C740301-50). Two flat stress corrosion specimens were machined from

the base of each bracket and two round tensile specimens were machined from

the side of each bracket as shown in Figure 1. Fourteen round tensile

specimens were machined from the one aluminum alloy flange casting marked

C5T27377. Figure 2 illustrates the position of each specimen obtained from

the parent material. All specimens were taken from solid sections of the

castings and there were no visual indications of voids or flaws.

Mechanical Properties

Tests were performed by NBS to determine the mechanical properties of

the three K01-T7 aluminum alloy castings. These determinations (tensile
strength and yield strength) compare favorably with the mechanical test

results furnished by the supplier. All the mechanical tests performed

by NBS exceeded the minimum requirements as stated by the manufacturer.

The results appear in Table 2. The tensile properties as determined by

NBS were very similar for all three castings.

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Stress Corrosion Tests

Stressed and unstressed specimens were exposed in the marine atmosphere

’ at Kure Beach, NC [80 foot (24 m) lot]. A system of weights and levers

was used to obtain the desired stress on the flat stress corrosion specimens

while a constant strain system was utilized to obtain the applied stress

on the round test specimens. The specimens exposed in the marine atmosphere

were exposed with an applied stress equivalent to 0, 50, and 75% of the yield

strength of the alloy as determined by NBS. [60 Ksi (413.69 MPa)].

Results

Visual examination of the specimens after exposure in the marine atmosphere

revealed the presence of heavy adherent gray corrosion products with considerable

localized corrosion pits.

Both of the flat stress corrosion specimens which had been stressed

at 75% of their yield strength and exposed in the marine environment failed

after 37 and 249 days. A companion flat unstressed specimen which had been

exposed for the same period of time was removed from exposure along with the

failed sample. None of the round tensile specimens which had been exposed

unstressed or stressed at 50 and 75% of the yield strength of the material

had failed after 1160 days exposure in the marine atmosphere. In order to

obtain an indication of the effect of corrosion attack on the alloy, a

comparison was made of the tensile properties of unexposed specimens vs^.

those of specimens exposed to the marine environment. The values obtained
were then averaged and calculated as the percent loss in tensile strength due

to exposure in the environment. The results, given in Table 3, indicate a

small loss (from 1.6% to 11.2%) in tensile strength for the unfailed specimens

as a result of exposure.

Metallography

I Sections were obtained from areas at and adjacent to the fracture surfaces

of the failed specimens for metallographic examination. In general, the microstructure for both specimens revealed a uniform grain size and the presence of

intermetallic precipitates at the grain boundaries (Figure 3). Metallographic

examination of areas at the fracture showed that the fracture surface was

both intergranular and transgranular (Figure 4) with no evidence of secondary

cracking.

Conclusions

The results obtained from stress corrosion tests on K01-T7 aluminum

alloy indicate that the alloy may be subject to stress corrosion. Examination

of failed (37 and 249 days) specimens, which had been stressed by the constant

load method, showed that the fractures were both transgranular and intergranular

in nature. Other specimens stressed by the constant strain method had not

failed after 1160 days of exposure. Both of the failures which occurred

during exposure in the marine atmosphere were from specimens removed from

the brackets. However, these were the only specimens exposed utilizing a

constant load system. The alloy also exhibited a considerable amount of

shallow surface pitting which was accompanied by heavy adherent gray corrosion

products. Since the number of specimens tested was limited by the amount of

material available, due consideration should be given to further testing of

this alloy under constant load conditions at the same and lesser applied

stresses.
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Table 1

Certification Test Data as Furnished by the Supplier

Casting

Identification

Alloy Heat

No.

Yield

Strength

KSI (a)

Tensile

Strength

KSI (a)

Percent

Elongation

C5T27377 K01-T7 ES 1 58.7 62.9 5.0

C740301-50 K01-T7 ES 1 62.4 66.7 4.0

Minimum K01-T7 50.0 60.0 3.0

Requirements

^1 KSI = 6.8948 MPa.

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Table 2

Results of Mechanical Tests Performed by NBS

Material Tensile Strength

Ksi (a)

Yield Strength

Ksi (a)

Bracket #1

C740301 -50

65.6 60.8

Bracket #2

C740301-50

65.7 60.7

Flange

CST 27377

62.4 59.8

K01-T7

Minimum

Requirements

60 50

(a)

1 Ksi = 6.8948 MPa.
Table 3

Specimen

Origin

Brackets

C740301-50

Flange

CST 27377

(a)

l Ksi =

Average Loss in Tensile Strength from Exposure

Exposure

time. Marine

Atmosphere

Applied Stress

during Exposure

% of Yield Strength

Tensile

Strength

Ksi (a)

Yield

Strength

Ksi (a 1

Percent Loss

in Tensile Strength

from Exposure

unexposed - 65.6 60.6 -

37 0 64.6 57.1 1.6%

249

37 75 failed failed

249

unexposed - 62.4 59.8 -

1160 0 56.8 9%

1160 50 58.6 54.4 6.1%

1160 75 55.4 52.2 11.2%

6.8948 MPa.

Figure 1. Drawing of bracket casting

(C740301-50) showing origin

of test specimens.
Figure 2. Drawing of flange casting

( C5T27377 ) showing origin

of test specimens.
Fiqure 3. Microstructure of K01-T7 aluminum alloy. Etched,

Keller's, etch. X50.

Figure 4 Fracture surface of failed K01-T7 aluminum alloy specimen

after exposure for 37 days. Fracture is both intergranular

and transgranul ar. Etched, Keller's etch. X50.

NBS-1 14A (REV. 7-73)

U.S. DEPT. OF COMM.

BIBLIOGRAPHIC DATA

SHEET

1. PUBLICATION OH RLPORT NO.

NBSIR 77-1288 (NASC-Navy)

2. Gov't Accession

No.

3. Recipient’s Accession No.

4. TITLK AND SUBTITLE

Stress Corrosion Behavior of KQ1^T7 Aluminum Alloy Castings

5. Publication Date

6. Performing Organization Code

j7. AUTHOR(S)

B.T. Sanderson and W.F. Gerhold

8 . Performing Organ. Report No.

9. PERFORMING ORGANIZATION NAME AND ADDRESS

I NATIONAL BUREAU OF STANDARDS

DEPARTMENT OF COMMERCE

WASHINGTON, D.C. 20234

10. Project/Task/Work Unit No. 3120410

11. Contract/Grant No.

2. Sponsoring Organization Name and Complete Address (Street, City, State, ZIP)

Naval Air Systems Command

Department of the Navy

Washington, D.C. 20360

13. Type of Report & Period Covered

14. Sponsoring Agency ('ode

5. SUPPLEMENTARY NOTES

5. ABSTRACT (A 200-word or less factual summary of most significant information. If document includes a significant

bibliography or literature survey, mention it here.)

Tensile specimens of K01-T7 aluminum alloy were stressed at fifty and seventyfive percent of the alloy’s yield strength and exposed in a marine atmosphere

environment. Specimens stressed by the constant load method failed after 37 and

249 days. The K01-T7 aluminum alloy may be subject to stress corrosion in a marine atmosphere environment.

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

)

Alloy; aluminum; atmosphere; castings; marine; mechanical

properties; stress corrosion.

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