bluuebunny/crossref_metadata_2025 huggingface dataset:
Design Considerations for Heat Recovery System for DD-963 Class Ship
Authors: Katz Y. , Boyen J. L.
Published: April 2015

The advent of high-speed gas-turbine-powered naval vessels requires that new concepts in energy generation and conservation be employed This paper describes the heat recovery system designed for the U.S. Navy Spruance Class destroyers as applied to the ships service generator sets. Among the topics discussed in the paper are the water and steam system, controls, heating surface selection and configuration, water treatment, gas-side fouling, gas-side pressure drop, and heat transfer. The thermal power recovered is used to perform heating, distillation plant operations, and galley services, thereby reducing the fuel consumption required to perform these functions. The use of separately fired boilers to perform the required tasks would significantly increase the fuel consumption rate.
An Optimizing Design Point Program for Selection of a Gas Turbine Cycle
Authors: Conkol G. K. , Singh T.
Published: April 2015

As vehicles evolve through the concept phase, a wide variety of engines are usually considered. For long-life vehicles such as heavy armored tracked vehicles, gas turbines have been favored because of their weight and volume characteristics at high hp levels (1500 to 2000 hp). Many existing gas turbine engines, however, are undesirable for vehicular use because their original design philosophy was aircraft oriented. In a ground vehicle, mass flow and expense are only two areas in which these engines differ greatly. Because the designer generally is not given the freedom to design an engine from scratch, he must evaluate modifications of the basic Brayton cycle. In this study, various cycles are evaluated by using a design point program in order to optimize design parameters and to recommend a cycle for heavy vehicular use.
The Shaft Coupled Lift/Cruise Fan Propulsion System for Navy Multimission V/STOL Aircraft
Authors: Hudson S. M.
Published: April 2015

The Navy has promoted requirements for aircraft capable of operating from ships smaller than the CV class of large aircraft carriers. The subsonic roles within these requirements may be met by a multimission V/STOL aircraft powered by an integrated lift cruise fan propulsion system using advanced turboshaft engines and shafting for power distribution. General system requirements, unique features and characteristics, and special design considerations relating to V/STOL, such as propulsive lift control, engine sizing and engine out ratings, are presented.
Description, Output and Development Prospects of a 750 C Helium Direct Cycle Nuclear Power Plant With a Single Turbomachine and Intermediate Cooling
Authors: Tilliette Z. P. , Pierre B. , Jude P. , Chaboseau J.
Published: April 2015

The concept of a helium cycle nuclear power plant with a single turbomachine located outside the P.C.R.V. in a leaktight basement is being studied. Main features of the system are pointed out, as are the favorable aspects it offers for a satisfactory design of the plant, a high safety level, a good efficiency for electricity generation associated with a dry cooling tower and heat recovery in good conditions for heating or industrial purposes. Above all, the high technological credibility due to the temperature of 750 C is worth being emphasized. In this paper, a 750 C/800 MWe power plant (2000 MWt) with one intercooler is presented as an example of a possible first generation of gas turbine HTGR. Development prospects for higher power levels, 1000/2000 MWe, are also investigated, at first with one but also with two intermediate coolers, taking into consideration the somewhat higher-helium temperature. The net plant efficiencies, for electricity generation only, range from 40 to 45 percent.
Gas Turbine Salt Ingestion Analysis
Authors: Krulls G. E. , Lastella J.
Published: April 2015

Results of two series of tests are presented which were undertaken to determine the sodium ingestion patterns for barge mounted gas turbines of the Consolidated Edison Company of New York. Both fuel and air streams feeding the turbines were monitored continuously. It was found that on the average the fuel and air streams were well within specification limits even though the turbines were experiencing sulfidation. Short duration excursion levels well beyond specifications suggest that these are the real cause of sulfidation.
Gas Turbine Power Plants of Large Unit Capacity in Standard Construction
Authors: Lange K. H. , Heinecke H. J.
Published: April 2015

Contrary to the common practice in the U.S.A. it was usual in Europe to build Gas Turbine Power Plants individually. Kraftwerk Union AG now reports on a new pre-engineered standard concept which has been designed by its Engineering Department. This paper describes the pre-engineered concept and the standardization of components. Furthermore, it indicates the possibility of extending this standard plant to a KWU Exhaust Heat Recovery Plant.
Gas-Turbine Total Energy System for a Cement Plant
Authors: Green Leon
Published: April 2015

This paper proposes the use of a coal-fired, closed-cycle gas turbine to provide electric power and process heat to a “wet process” cement plant. Taking the example of a large plant requiring 100 million kilowatt-hours of electric energy per year, it is estimated that, by substitution of in-plant power generation for purchased electricity and use of reject heat for slurry dewatering, annual energy cost savings (at current rates) sufficient to pay off the capital cost of the installation between 5 and 15 years (depending upon the amount of that cost) could be realized. This degree of savings will increase as the price of power increases due to “normal” projected escalation of coal costs, plus the imposition of requirements for emission control equipment to meet stringent environmental quality standards. Because the fly ash from pulverized coal firing and the limestone sludge from a stack gas scrubber represent feed materials for the cement process, emission control does not constitute the burden on a cement plant that it would for an electric utility, but rather permits additional savings due to effective use of “waste” materials. Conservation of energy, material resources and the environment could thus be accomplished simultaneously.
FT4E: The Optimization of a Proven Modular Industrial Gas Turbine
Authors: Assard D. G. , Crouchley A. B.
Published: April 2015

This paper reviews the design of the latest version of the United Technologies FT4 modular industrial turbine. This FT4E design program was initiated early in 1976 and is scheduled for production in 1979. The broad experience of the FT4 is reviewed to show the basis for the design concepts and parameters that were the basis of the FT4E program.
The Dynamic Behavior of Nuclear Helium Turbine Plants During By-Pass and Pressure Level Control Operations
Authors: Hewing G. , Förster S.
Published: April 2015

This paper describes studies on the operating and control behavior of nuclear helium turbine plants. The aim of these studies is to prove that the requirements of the grid can be met by the power plant without undue operating conditions. This work refers to a non-integrated plant design which has been developed in the framework of the German HHT-Project. Essentially the following control modes are investigated: Gas injection and discharge at various points of the circuit; opening and closing of by-passes; and control of loss of load with the aid of by-passes. The gas injection and discharge gives relative slow power changes but favorable efficiencies at part-load. With gas injection on the HP-side the power output rises faster than would correspond with the increase of inventory. This behavior can be used advantageously for frequency maintenance as described in the paper. The by-pass control is characterized by rapid power changes in connection with unfavorable part-load efficiencies. The associated pressure-gradients are inside of tolerable limits. The loss of load from full load as the most extreme operating case can be met by by-pass control with Pl-controller. One can establish that the plant can fulfill all investigated operating requirements without undue operating conditions.
The Variable Geometry in Supersonic Compressors
Authors: Breugelmans F. A. E.
Published: April 2015

A flexible inlet guide vane has been designed for an independent control of the pre- or counter-swirl condition over the blade height. This model has then been investigated with a Mach 2 supersonic rotor and proved to produce large variations of the design mass flow and pressure ratio with 6 percent loss in efficiency for the preswirl conditions.
Experimental Investigations of Supersonic Cascades Designed for High Static Pressure Ratios
Authors: Fuchs R. , Starken H.
Published: April 2015

The outlet conditions of supersonic compressor rotors designed for very high total pressure ratios can be highly supersonic (impulse rotors). Then the following stator blade row has to build up high static pressure ratios at supersonic inlet conditions. This paper describes part of a research work which should answer, if it is at all possible to realize such high static pressure ratios in a cascade. Cascades with convergent-divergent blade passages were designed and optimized by boundary layer calculations. In a first step no flow turning was incorporated in the blade sections. A three-shock-type cascade was found to be an optimum design The wind tunnel measurements resulted in static pressure ratios of the order of 6 and total pressure ratios of 0.77 at inlet Mach numbers of 2.2. In a second step the flow turning to axial direction was realized. For that two types of cascades were built and tested. One was a tandem type cascade and the other a single row cascade. The experiments at inlet design conditions resulted in static pressure ratios of the order of 6.5 and total pressure ratios of 0.72.
Design Properties of Silicon Nitride for High Temperature Gas Turbine Application
Authors: Uy J. C. , Williams R. M. , Swank L. R.
Published: April 2015

Engineering properties useful in design are presented for both hot pressed and reaction sintered silicon nitride. In particular, the statistical nature of strength properties is discussed from the standpoint of cause of strength scatter, effect of sample preparation and test procedure, Weibull statistical analysis, and the application of Weibull strength parameters.
Emissions and Performance of Catalysts for Gas Turbine Catalytic Combustors
Authors: Anderson D. N.
Published: April 2015

Three noble-metal monolithic catalysts were tested in a 12-cm-dia combustion test rig to obtain emissions and performance data at conditions simulating the operation of a catalytic combustor for an automotive gas turbine engine. Tests with one of the catalysts at 800 K inlet mixture temperature, 3 × 105 Pa (3 atm) pressure, and a reference velocity (catalyst bed inlet velocity) of 10 m/sec demonstrated greater than 99 percent combustion efficiency for reaction temperatures higher than 1300 K. With a reference velocity of 25 m/sec the reaction temperature required to achieve the same combustion efficiency increased to 1380 K. The exit temperature pattern factors for all three catalysts were below 0.1 when adiabatic reaction temperatures were higher than 1400 K. The highest pressure drop was 4.5 percent at 25 m/sec reference velocity. Nitrogen oxides emissions were less than 0.1 g NO2/kg fuel for all test conditions.
Propulsion Gearing Transmission Systems for Guided Missile and Standard Frigates of the Royal Netherlands Navy
Authors: Kerpestein J. B.
Published: April 2015

This paper describes the design of and operating experience with modern propulsion gearing transmission systems for the gas turbine driven Guided Missile and Standard Frigates of the Royal Netherlands Navy. From the staff requirements and the general ship design, established by the Royal Netherlands Navy, the Rijn-Schelde-Verolme Group of the Netherlands performed the further development and the design of these frigates which are building at their Royal Schelde Yard. Royal Schelde designed and manufactured also the gearing transmission systems involved. The paper reviews the initial considerations and the development of the gearing transmission system design. A review of shore test and sea trial results and an overall appraisal of the gearing transmission system performance to date is given. The paper is complementary to the paper “COGOG Propulsion Installations in Guided Missile and Standard Class Frigates of the Royal Netherlands Navy” (ASME Paper No. 77-GT-68) by Capt. P. van Staalduinen, Royal Netherlands Navy. Both papers can also be considered separately as contributions to their own specific domain of today’s naval propulsion engineering.
COGOG Propulsion Installations in Guided Missile and Standard Class Frigates of the Royal Netherlands Navy: A Review of the Development From the Specific Design Philosophies to the Actual Technical, Personnel and Maintenance/Logistic Management in Service
Authors: van Staalduinen P.
Published: April 2015

This paper gives a brief survey of the overall design philosophies of the Olympus/Tyne twin shaft propulsion plants in the unmanned engine rooms of the Guided Missiles and Standard class frigates of the Royal Netherlands Navy, including the installation’s major auxiliaries, electronic control system, solid state surveillance and data recording equipment Complimentary to this paper is the paper by J. B. Kerpestein of Royal Schelde entitled, “Propulsion Gearing Transmission Systems for Guided Missile and Standard Frigates of the Royal Netherlands Navy” (ASME Paper No. 77-GT-67). The author further outlines briefly current ship operating experience and the reorganization undertaken by the RNN to satisfy the requirements for personnel training and technical and logistic support of the gas turbines.
Experimental Analysis of a Hybrid Ceramic-Wrought Superalloy Turbine Rotor
Authors: Carruthers W. D. , Walker B. H. , Vanwanderham M. C.
Published: April 2015

The successful design of ceramic components for gas turbine applications requires experimental and analytical failure analyses of failed components, the correlation of failure modes with material data, and the evolution of design criteria and material characterization requirements for that component. This paper discusses the establishment of experimental strain rupture life prediction data for a hybrid ceramic bladed-wrought superalloy turbine rotor. Also presented is the correlation of these data with an experimental failure analysis and the effect of this analysis on subsequent rotor designs.
Some Measured and Calculated Effects of Forward Velocity on Propeller Noise
Authors: Pegg R. J. , Magliozzi B. , Farassat F.
Published: April 2015

The results of a program investigating the sources of noise in unshrouded propellers under forward flight conditions and a comparison with theory are reported. Tests were conducted using an instrumented three-bladed propeller installed on a turbine-powered, twin-engine, general aviation airplane. Measurements included far-field noise on the ground and on the aircraft wing tip, propeller blade surface pressures, atmospheric turbulence, and aircraft operating conditions. The primary result of the full-scale flight tests was to confirm that foward-flight propeller noise levels are lower than those experienced under static conditions and that the most significant reductions occur at the mid-frequencies which dominate perceived and A-weighted noise levels. Analytical techniques have been used to predict the observed experimental trends and to provide further insight into the noise generating mechanisms. Correlation with experimental data is shown to be good at low frequencies under static conditions and at all frequencies in forward flight. It is tentatively concluded that propeller noise generation in flight may result from steady loads (including blade thickness effects). Under static conditions, the principal noise source appears to be the intersection of the propeller with persistent turbulent eddies passing through the propeller disk.
Gas Turbine Installations for Air Cushion Vehicle Lift and Propulsion Power: The AALC JEFF Craft
Authors: Smith C. H.
Published: April 2015

The U.S. Navy is currently developing a radical new concept in the ship-to-shore transportation of equipment and personnel. The Amphibious Assault Landing Craft (AALC) program is the Navy’s advanced development effort in this area. One of the craft being developed under this program, the high performance air cushion vehicle (ACV) JEFF Craft, is the mainstay of this concept. Two contractors, Bell Aerospace and Aerojet Liquid Rocket Company are about to begin systems checkout and shakedown tests on the first advanced development crafts, the JEFF (A) and JEFF (B). This paper discusses the installation features of the Lycoming TF40 Marine Gas Turbine, which provides the lift and propulsive power for both craft. In particular, the intake and exhaust, electrical and control, mounting, starting, and lube and fuel systems interfaces are examined and compared.
Torsional Flutter in Stalled Cascade
Authors: Yashima S. , Tanaka H.
Published: April 2015

Applying free streamline theory and singularity method, a theoretical study is developed for the torsional flutter problem in fully stalled cascade. Aerodynamic moment acting on a vibrating blade is calculated for some cascade conditions. Computational results show that critical reduced frequency is much higher in the case of stalled cascade than unstalled one and affected by the position of pitching center. Experiments were carried out using a water tunnel with a linear cascade, and the unsteady moment acting on the vibrating blade was measured. Computational and experimental results show fairly good agreement.
The V.P.I. Gas Turbine and Turbomachinery Research Laboratory
Authors: O’Brien W. F. , Jones R. R. , Moses H. L. , Sparks J. F.
Published: April 2015

A recently completed facility for high-speed turbomachinery and gas turbine related research is described. A test cell houses a 3000 hp turboshaft engine which is capable of driving research rotors in a direct-coupled mode at speeds to 17,000 rpm. Gearboxes provide for reverse drive and speeds from 8000 to 24,000 rpm. An automatic governing system controls gas generator and load speeds, and provides overspeed protection. Research instrumentation includes on-rotor telemetry equipment for transmission of data from research rotors.
Ammonia Turbomachinery Design Considerations for the Direct Cycle Nuclear Gas Turbine Waste Heat Power Plant
Authors: McDonald Colin F. , Vepa Kosla
Published: April 2015

This paper describes the turbomachinery design considerations for a supercritical Rankine cycle waste heat power conversion system for use with the large helium closed-cycle gas turbine nuclear power plant under development by General Atomic Company. The conceptual designs of the ammonia turbine and pump are presented. The high density working fluid in the ammonia turbine results in small blade heights and high hub-to-tip ratios due to a combination of the properties of ammonia and the high degree of pressurization, particularly at the turbine exit. With the molecular weight of the ammonia working fluid being very similar to steam, the double-flow, multistage axial ammonia turbine bears a strong resemblance to modern steam turbines. Conceptual design work has been done in sufficient detail to support component cost estimates for the balance of plant economic studies. While an extensive design program is needed for the ammonia turbine, existing technology from the power generating and chemical process industries is generally applicable; and, with specialized design attention, the goal of high turbine efficiency should be realizable. The design studies have been specifically directed toward a nuclear closed-cycle helium gas turbine plant (GT-HTGR); however, it is postulated that the turbine design considerations presented could be applicable to other low temperature power conversion systems such as geothermal or industrial waste heat applications.
Operational and Maintenance Experience of an Industrial Type 14-MW Gas Turbine
Authors: Werner H. , Ekman S. , Boltshauser H.
Published: April 2015

The GT35, originally planned as a new step in the author’s jet engine development program, is a lightweight industrial gas turbine. This paper describes the operation, maintenance procedures, costs, problems and cures of several plants located in Sweden, Venezuela, Holland, Turkey and Algeria.
Considerations Concerning the Layout of Nuclear Helium Turbine Power Plants With Optimum Economy
Authors: Bammert K. , Krapp R. , Reiter U.
Published: April 2015

The essential design parameters of HHT plants and various principles of arrangement are investigated with regard to their influence on the economy. On the basis of these considerations, and taking into account the development of HHT plant components in West Germany, a low-cost HHT plant concept is developed. By means of this layout, the possibilities of the utilization of waste heat are discussed. The results are compared with existing plant concepts.
Effect of Water-Cooling Turbine Blades on Advanced Gas Turbine Power Systems
Authors: Johnson B. V. , Giramonti A. J. , Lehman S. J.
Published: April 2015

A study was conducted to determine what benefits in cycle efficiency and performance could be obtained with water-cooled gas turbine blades. Water cooling was compared against various degrees of air cooling and the ultimate limit of no cooling. Performance studies were conducted for both combined gas turbine-steam cycles and simple gas turbine cycles with temperatures at the inlet to the first turbine blade row from 1478 K (2200 F) to 1922 (3000 F) and compressor pressure ratios from 12 to 28. Results for both types of cycles indicated that absolute efficiencies 1 to 3 percentage points greater and power output per unit airflow 5 to 25 percent greater than could be obtained with water-cooled blades compared to air-cooled blades. For a given cooling scheme and pressure ratio, highest efficiencies were obtained at 1700 K (2600 F) for the simple cycle and 1922 K for the combined cycle.
Cooling Considerations for Design of a Radial Inflow Turbine
Authors: Hamed A. , Sheoran Y. , Tabakoff W.
Published: April 2015

A numerical study to determine the temperature distribution in the rotor of a radial inflow turbine is presented. Internal cooling passages are modeled in the present formulation in order to carry out solid and coolant temperature computations simultaneously resulting in a considerable computer time savings. The stresses due to centrifugal and thermal loadings are determined in an actual rotor and the effect of cooling design on its mechanical integrity is discussed.
The Need for Cost/Benefit Analysis When Developing Environmental Standards
Authors: Zeltmann E. W.
Published: April 2015

The last seven years have seen a special awareness of the need for environmental clean-up throughout the entire U. S. society. Confrontations between regulator and regulatee have, as a result, been acrimonious and numerous, with decisions on various projects remaining seriously delayed or completely unresolved. This paper suggests that environmental/energy disagreements be settled through careful use of cost/benefit analyses. Several examples are cited, and emphasis is placed on making decisions in a timely fashion.
Stingray Pipeline Automated Measurement and Control System
Authors: Murry L. D. , Lue D. D. C.
Published: April 2015

This paper discusses the Stingray Pipeline automated measurement and control system installed by Teledyne Geotech early in 1976. The system includes computer control and monitor of two Stingray natural gas compressor stations with a communications interface between the stations and the Stingray gas control center (GCC) located in Houston, Tex. Each station contains turbine/compressor units, with one station located onshore and the other station being an offshore facility. Included is a description of the system, the system functions and capabilities, and interrelationships between the stations and GCC. Advantages and disadvantages of the system are also discussed.
Influences on the Fuel Economy of an Automotive Gas Turbine
Authors: Köhler M. , Walzer P.
Published: April 2015

A previous simulation of a metallic gas turbine has predicted a fuel economy of 18 mpg in a 1550-kg car Using this engine as reference, the influences of component efficiencies, variable geometry, maximum pressure, temperatures, and output power are analyzed, A fuel economy of 24 mpg could be attained with this metallic engine, if new heat exchanger matrices, ceramic turbine shrouds, materials with somewhat higher temperature capability for turbines, and heat exchanger can be developed and a moderate reduction of car performance is accepted.
Technical and Economic Objectives for the Development of Advanced Combined Cycles for Use With Coal-Derived Fuels
Authors: Fraize W. , Lewis J.
Published: April 2015

The High Temperature Technology (HTTT) Program of the U. S. Department of Energy (DOE) is attempting to develop the “technology readiness” necessary for utility implementation of advanced combined-cycle power systems operating on coal-derived fuels. To be successful, this HTTT Program should lead to a utility power system which is economic, efficient, environmentally acceptable, and timely in its commercial availability. This paper examines these issues, and attempts to define technical and economic objectives for development of an advanced combined cycle.
Future Prospects for Naval Propulsion Gas Turbines
Authors: Armstrong F. W. , Philpot M. G.
Published: April 2015

The continuing evolution of gas turbine propulsion systems for naval vessels is discussed. Following a brief historical survey, the reasons for the current practice of using adapted aero-engines are reviewed. The forward prospect for naval power-plants is then examined in the light of the progression of aero-engine technology and the trends in major cycle parameters. The extent to which these can be exploited in marine propulsion engines is assessed. Finally, some elaborations of the simple-cycle engine which might be suitable for naval applications are considered.
Erosion and its Effect on a Water-Cooled Turbine
Authors: Freedman Max
Published: April 2015

Erosion tests were run to obtain data for designing a water-cooled gas turbine collection shroud. All tests utilized a coherent stream of water ejected from a static nozzle against stationary small block specimens. Twenty-one tests were run with aluminum specimens and 16 more tests with other materials. The impact velocity was varied from 165 to 270 m/s (540 to 890 fps). The impact angle was varied from 10 to 90 deg. The mass loss rate results generally show four erosion regions, which are consistent with the literature. A correlation between regions two and four was found. Aluminum specimen erosion rate was found to be unexpectedly high with impact angles of 10 deg and moderate-to-high impact velocity. No report of previous liquid erosion work at impact angles less than 30 deg was found; since it is expected that water-cooled gas turbines will operate at impact angles of about 15 deg, erosion in this low impact angle region should be studied. If the correlation between erosion regions two and four can be quantized, then very short-time tests could be used to predict long-term erosion at minimal cost.
Wide Range Operation of Advanced Low NOx Aircraft Gas Turbine Combustors
Authors: Roberts P. B. , Fiorito R. J. , Butze H. F.
Published: April 2015

Over the past three years, Solar Turbines International, an Operating Group of International Harvester, has been engaged in characterizing the NOx emissions and operation of two particular types of lean, premixed combustors, namely the Jet Induced Circulation (JIC) and Vortex Air Blast (VAB) configurations and was concerned primarily with the NOx emissions at a simulated high-altitude, supersonic cruise condition. The VAB combustor demonstrated the capability of meeting the NOx goal of 1.0 g NO2/kg fuel at the cruise condition (Tin = 833 K, Pin = 5 atm, Tout = 1778 K). In addition, the program served to demonstrate the limited low-emissions range available from the lean, premixed combustor. A follow-on effort, the results of which form the basis of this paper, was concerned with the problem of operating these lean, premixed combustors with acceptable emissions at simulated engine idle conditions. Various techniques have been demonstrated that allow satisfactory operation on both the JIC and VAB combustors at idle (Tin = 422 K, Pin = 3 atm, Tout = 917 K) with CO emissions below 20 g/kg fuel. These include degrees of variable geometry, fuel switching and fuel-staging designs. The VAB combustor was limited by flashback/autoignition phenomena at the cruise conditions to a pressure of 8 atm. The JIC combustor was operated up to the full design cruise pressure of 14 atm without encountering an autoignition limitation, although the NOx levels, in the 2 to 3 g NO2/kg fuel range, exceeded the program goal.
Flow in an Annular Axial-Radial Diffuser
Authors: Šťastný M. , Feistauer M.
Published: April 2015

The subject-matter of interest is an annular, axial-radial diffuser with a small relative length. The diffuser is intended for the outlet of flow from the last turbine stage. Investigated are possibilities of a theoretical solution to the flow in a diffuser, based on a potential flow in the stream core and on the viscous flow in the boundary layer. Compared are two methods of solution to the potential flow in the given diffuser: a numerical calculation and a method of electrical analogy. By the method of calculation investigated are the influence of compressibility of the flowing medium upon the potential flow, and the influence of viscosity within the boundary layer. Given are the main data about a wind tunnel necessary for the research into the diffusers and the exhaust chambers, and experimental information gained in measurements taken on the diffuser. Comparison is made about the results of experiments and calculations. Pointed out is the influence of the exhaust chamber upon the diffuser. In an operating turbine, the flow in a diffuser is significantly influenced by the regime of flow in the last stage. Given are the results of the experimental research into the velocity field at the inlet into the diffuser depending on the aerodynamic loading of the last stage, and described are flow conditions within the diffuser with the turbine running idle when the last stage is in windage operation.
Erosion Study in Turbomachinery Affected by Coal Ash Particles
Authors: Tabakoff W. , Kotwal R. , Hamed A.
Published: April 2015

Turbomachinery operating with coal particles or using pulverized coal as fuel are exposed to erosion. The problem of predicting erosion in rotating machinery is very complex. The present paper describes the test facility which is designed in such a way that the aerodynamic effects are an integral part of the erosion test parameters. Some results from the alloys studied (aluminum, stainless steel, and titanium) in this investigation are reported.
A Proposed Scheme for Computer Aided Design and Manufacture of Radial Turbine Rotors
Authors: Benson R. S. , Fisher U.
Published: April 2015

A scheme for the computer-aided design and manufacture of a radial turbine rotor is described based on a package developed by the University of Manchester Institute of Science and Technology. Starting with a one-dimensional calculation, the overall dimensions of the rotor are determined for a specified performance. From these data, the detailed dimensions of the blade profile are evaluated. These are then processed as input data for stress calculations and flow analysis in the blade passages. Interaction between the designer and the program at a number of points enables an optimal design to be achieved. As an aid to assessing the design, a rotating pictorial view of the rotor may be presented on the visual display unit The final output may be in the form of working drawings, blade profile dimensions, or tapes to assist in the preparation of patterns for castings, dies for forging, jigs and templates for machining or straight input to N.C. Machines. Illustrations of the accuracy of the flow analysis methods and typical outputs are given.
The Centaur Engine: Operational Progress Report
Authors: Emmerson C. W.
Published: April 2015

The Centaur engine, introduced by Solar in 1970, pioneered the application of turbine power in the 3000- to 4000-hp class for the oil and gas industry. Today, with over 500 units operating in some of the toughest industrial environments in the world, the documented reliability of the basic model continues to improve, surpassing original life objectives. Many changes have been made to the Centaur engine since 1970. This paper deals specifically with those based on field operating experience. Each modification is described in terms of the field experience, both before and after the change, the in-house and/or field test program, and the qualification testing involved. The scope of the discussion includes modifications applied throughout the major components of the engine. Of particular interest are the changes incorporated due to operation in arctic environments. Other modifications were made in response to specific problems encountered in unusual or particularly abusive service. The overall effect has been to greatly strengthen the engine improving both durability and reliability in the industrial working environment it serves.
Flame Characteristics of a NASA Contra Swirler Module
Authors: Thompson D. , Chigier N. A. , Ungut A.
Published: April 2015

The structure of unconfined propane flames stabilized on a NASA contra-swirl can has been examined. A wide range of flame types may be stabilized. The structure depends on reference velocity and fuel-air ratio, and photographic illustrations of representative examples of each flame type are shown. A highly compact flame is obtained over a narrow band of fuel-air ratios, within the total range over which flames may be stabilized at high reference velocity (27.8 m/s) (91.2 ft s−1). The compact structure can only be obtained with careful fuel nozzle location. Chemical concentration (major products and NO) profiles, temperature profiles, and sodium chloride seeding experiments all confirm the visual impression of compactness. A flame with 50 percent greater propane throughput has a much less compact structure, which is reflected in lower maximum temperature, much more complex chemical concentration distributions, and a more diffuse recirculation boundary as observed by sodium chloride seeding than in the compact flame. Each of these flames has not only an evident axial recirculation core, but also a toroidal recirculation region over the bluff region between the inner and outer swirlers. In contrast, laser Doppler velocimetry measurements carried out on a flame with lower reference velocity (5.65 m/s) (18.5 ft s−1) do not indicate the presence of a secondary recirculation region in this flame.
Full Authority Digital Electronic Control: Highlights of Next Generation Propulsion Control Technology
Authors: Barclay B. A. , Lenox T. G. , Bosco C. J.
Published: April 2015

This paper describes the results of Pratt & Whitney Aircraft preliminary design studies for a full authority digital electronic control (FADED) system with capability for controlling an advanced variable cycle gas turbine engine in an advanced supersonic Navy fighter-type aircraft application. The FADEC system concept which resulted from these studies features essentially fail-operational fault tolerance capability for non-augmented operation through the use of redundant sensing, computation, and command paths; parameter synthesis; and self-test techniques. Incorporation of advanced electronic circuit technology and minimization of complex hydromechanical hardware projected to result in over 43 percent reduction in life cycle cost, 41 percent reduction in acquisition cost, 26 percent reduction in weight, and 130 percent improvement in piece part reliability, relative to a system configuration with latest current production control technology.
Training in the Gas Turbine Field in Belgium, in France, in Italy
Authors: Boudigues S.
Published: April 2015

More than the terrestrial gas turbine, the aeronautical gas turbine has necessitated to teach this converter of energy in Belgium, France, and Italy. In these three countries, training in the gas turbine field takes place in the higher education with modalities which vary from one country to another, but as a result of this training, these three countries get engineers who satisfy the requirements of the industrialists.
The Gas Turbine Waste Heat Recovery System and the U.S. Navy
Authors: Marron H. D. , Carleton R. S.
Published: April 2015

This paper will discuss the current status of the gas turbine waste heat recovery systems in the U.S. Navy. This will include discussions of the auxiliary systems currently operational on the SPRUANCE Class Destroyers as well as the combined-cycle cruise propulsion systems currently planned for development initiation in FY’78. The major emphasis of the discussion will be to detail the rationale and to identify the basis upon which the U.S. Navy arrived at a decision to develop combined cycle systems to be available for non-nuclear combatant ship cruise propulsion for the mid 1980’s. The design concepts considered feasible for these applications will be discussed as well as an overview of the development program to completion.
Influence of Geometric Effects on the Aspect Ratio Optimization of Axial Turbine Bladings
Authors: Rist D.
Published: April 2015

In order to illustrate optimization possibilities, the cooled axial turbine stage has been investigated regarding aerothermodynamics. Aims of the study are: (a) to estimate the range of the aspect ratio in which the aerothermodynamic efficiency, under comparable conditions, is not less than 0.2 percent under the best value in order to acquire tolerances for the best possible blading design when considering other design and aspects; (b) to acquire the relationship of the turbine loss coefficients and efficiencies to the absolute size of the flow channels, i.e. (also) to the hot gas flowrate. This is important for fair comparison of smaller and larger machines as well as for realistic judgments and prognosis pertaining especially to small units.
Advanced Industrial Turbine Gear Calculation Methods
Authors: Hirt Manfred
Published: April 2015

Calculation of industrial turbine gears is more than calculation of load capacity concerning Hertzian pressure, bending stress, and scoring phenomena. It also includes, for example, a complete vibration analysis of the gear, shaft, and bearing systems. Some newer methods used in the German practice for these calculations and also for determining exact tooth width corrections and some aspects of the new ISO calculation methods are discussed.
Investigation of an Axial Flow Compressor With Variable Reynolds Number and Inlet Casing Geometry
Authors: Becker B. , von Schwerdtner O. , Günther J.
Published: April 2015

In the course of developing the compressor of a 100-MW gas turbine, extensive measurements took place on a test compressor provided with the four front stages scaled down to 1:4.63. The performance investigations have been supplemented by measurements of flow distribution down- and upstream of the blading, as well as at various intermediate axial positions. The test stand, operating in a closed circuit, allowed for the variation of the Reynolds number by changing the pressure level. The geometry of the inlet casing was variable as well, thus enabling the comparison of results with axial, two- and one-sided inlet flows. In this connection, the vibrational behavior of the rotating blades, besides the aerodynamics of the compressor, have been investigated. In case of the inlet casing with a two-sided inflow, additional flow field analyses have been performed using a model without compressor blading. The theoretical results calculated under the assumption of a rotational-symmetric flow, as well as the measurements at the gas turbine compressor itself, are used for comparison. The gas turbine compressor operating with a mass flow of 483 kg/s at ISO-conditions and a pressure ratio of 10 is running in the highest performance range of single-shaft compressors in operation today.
Radial Vaneless Diffusers: A Re-Examination of the Theories of Dean and Senoo and of Johnston and Dean
Authors: Inoue M.
Published: April 2015

There are two different, but well-known, theories for calculating the mixing process of the distributed flow discharged from the impeller into the vaneless diffuser. One is by Dean and Senoo, the other by Johnston and Dean. It is intended in this paper to make clear the reason for these two theories predicting similar total pressure losses. The mixing process in the vaneless diffuser, based on the Dean and Senoo theory, is re-examined. It is found that the mixing of the flow is greatly accelerated by wall friction and shear force acting between wake and jet, and it causes the large loss at the diffuser inlet. Nevertheless, the reversible work exchange makes a significant contribution to the mixing out of the flow compared with the stationary jet and wake pattern.
Radial Compressor Development as Dictated by the Requirements of Large Turbochargers
Authors: Stanley R. E. , Akers D. J.
Published: April 2015

The basic demands which are placed upon turbocharger compressors operating with maximum air-mass-flows from 1.0 kgs −1to 30.0 kgs −1are outlined. A review is made of the natural development which has taken place with one European manufacturer of turbochargers since 1948, and comments are made as to the possible trends in turbocharger compressor development in the future. A compressor type is selected for investigation, and sufficient design and performance data are presented to enable its general use as a baseline computer performance prediction test case. Compressor design and performance parameters, which are of interest to the turbocharger compressor designer, are also reviewed.
Research of the XF3-1 Turbofan Engine
Authors: Kohzu M. , Chinone H. , Miyake M. , Murashima K. , Yamanaka K. , Ishigaki T.
Published: April 2015

A research program of low bypass ratio small front fan engines has been in process at Third Research Center of Technical Research and Development Institute of Japan Defence Agency since 1975. The final target of this program is the development of the propulsion engine for the high subsonic small aircraft. As the first phase of this program, the bench test engine XF3-1 was manufactured and the basic studies of the overall engine matching performance and the effect of each component on the engine performance have been carried out. This paper describes the XF3-1 engine, reviews the status of the research and presents the major engineering progress attained through the research.
Synthetic Fuels Derived From Coal for Marine Applications
Authors: Gatzoulis Juliani
Published: April 2015

This paper presents a summary of work which is being conducted in the United States in the area of synthetic fuels derived from coal for marine applications, and also gives an overview of the current supply and demand for oil fuels and defines the impact of this picture on the future fuel needs of the maritime and naval communities.
The Application of Low Cost Manufacturing Technology to a Turbine Gas Generator
Authors: Due H. F. , Buchanan E.
Published: April 2015

The Low Cost Gas Generator (LCGG) program addresses the task of designing and demonstrating gas generator components with low cost as the primary objective. The components are sized to provide a turbojet engine configuration in the 9000-N thrust class (SLS, 288 K) and are applicable to a turbofan engine. By demonstrating these components in the actual engine environment, as a turbojet, a solid base will be established for transitioning this technology into engineering development as specific firm mission requirements become available. The program is sponsored by the U.S. Air Force Aero Propulsion Laboratory and consists of three phases covering a 39-month period as follows:

Phase I – Preliminary Design (7 months)

Phase II – Component Detail Design, Fabrication & Testing

Phase III – Gas Generator Design, Fabrication & Testing (1 2 months).

The Phase I portion of the program was completed in December 1976 and the results are discussed in this paper. The Phase I, preliminary design, consisted of performing cycle analysis, aero-thermo analyses, mechanical design, and manufacturing analyses to determine the best turbine engine configuration which satisfied the program objectives. The results of Phase I indicate that a turbojet in the 9000-N thrust class can be produced for approximately 2.4 $/N SLS thrust (1976 dollars) by making maximum use of casting technology and mechanical design simplicity. The SFC is 10 to 20 percent higher than existing engines in the same thrust class; however, the thrust to weight is comparable or better than engines used for RPV, missile, or drone applications.
Test Results of a New Distillate Fuels Purification System
Authors: Prem L. L. , Meyer R. H.
Published: April 2015

Seven hundred gallons of jet fuel, stored at the Hartford Electric Light Company’s South Meadow station, had been contaminated with living organisms, water, loose solids, and foreign material. The fuel was treated with the Electrocoalescer Fuels Purification System, and all but traces of the contaminants were removed. The gas turbines, fed by this purified fuel, performed faultlessly during the recent cold-snap crisis. The operating cost of this purification process was estimated to be not more than 0.6¢ per gallon.
Performance Investigations of Large Capacity Centrifugal Compressors
Authors: Mishina H. , Gyobu I.
Published: April 2015

An experimental investigation concerning the optimum relative velocity distribution within impellers, the optimum diffusion ratio of vaned diffusers and the optimum circumferential area distribution, sectional shape of scrolls was carried out using high specific speed shrouded impellers with backward leaning blades. A performance design procedure based on loss analysis and quasi-three-dimensional flow analysis was also developed and modified by introducing experimental results. The design procedure was applied to a 7900-kw four-stage air compressor to demonstrate the usefulness. Field test results of the complete machine showed that the maximum isothermal efficiency was 75 percent with the pressure ratio of 5.96 and the flow rate of 29.3 m3/s.
Direct Blade Force Measurements in Transonic Cascade Flows
Authors: Patel B. R. , Desai K. J.
Published: April 2015

The variations of the aerodynamic forces and moments on a turbine blade section with varying operation conditions are required for determining the blade flutter characteristics. Also, it is desirable to observe blade performance which is independent of local pressure measurement by using a lift/drag force measuring technique. This paper describes a force measurement system which directly measures these aerodynamic forces and moments acting on a blade section in a transonic linear cascade. The experimental results obtained using this system are compared with those derived from blade pressure distributions, downstream probe traverses, and theoretical calculations. Good agreement is shown between the various methods. Future areas of application for this system are also discussed.
One Manufacturer’s View of Gas Turbine Service
Authors: McLean H. D. , Delaney E. F. , Patterson J. R.
Published: April 2015

This paper describes full gas turbine services in support of owners operations in terms of availability, reliability, and maximum economic return on investment. The scope of the paper is the strategy of one manufacturer to provide service for the entire life of the turbine from installation through final retirement. Included is a detailed description of factory design engineering and parts support, on-site service, and field engineering and local specialized repair facilities.