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In recent years, developments in the explosive welding process have demonstrated that the process has many areas of application in the turbine field. This is a result of the process’s capability to weld a wide variety of the metals and alloys which are being utilized in turbines as well as recent applications of the process to fabricate complex shapes and structures which are often encountered in turbine components. This paper describes the successful application of explosive welding to actual turbine components as well as areas in which the process has potential for application in the future. Applications included in the paper include the repair of damaged bearings and shafts, application of protective claddings to selected areas, fabrication of complex channelled structures, and the welding of laminated structures.Copyright © 1974 by ASME

The recent upsurge in the utilization of turbomachinery in the various industries has created a great interest in various educational programs in this area. The scope of engineering education in turbomachines is very broad. The undergraduate student and his initial relationship with this subject is only the first phase of this education. Extension coruses at various levels to the practicing engineer is another important phase. Graduate courses in this area with their inherent research projects rounds out the entire picture. The paper outlines the various courses of study for the different phases and also interrelates these phases to show how by an exchange of information the various groups might benefit from each other. The paper also deals with various basic research and educational test rigs which may be setup to benefit both graduate and undergraduate students.Copyright © 1974 by ASME

This paper presents information on the NREC core engine development program. The subject engine is a 100-hp, two-shaft gas turbine that is the low-power end of a family of engines up to 500 hp, both nonregenerative and regenerative. The major goal of the program has been the development of a low-cost small gas turbine engine (less than $5/hp to produce in quantities of 15,000/yr). Other objectives include low emissions (meeting the anticipated EPA standards for the markets of interest), relatively high performance (design point SFC = 0.7 for the simple-cycle engine and 0.4 for the regenerative version), and relatively long life (10,000-hr life at design power and a minimum service period of 500 hr). Items specifically covered in this paper include the following: (a) A description of the core engine concept. Frame size, regenerative, recuperative, and air compressor versions are discussed. (b) A technical description of the core engine concept. The salient low-cost features are identified. (c) The development program results. Some of the engine performance and manufacturing cost analysis results are given.Copyright © 1974 by ASME

This paper discusses the development of a 125-Mw combined cycle generating unit from the original developmental concepts to the initial operation. The initial justification, the evolution of the plant through design, and the actual construction are discussed. The actual construction site and the equipment utilized are described. A discussion of the cooling system and the licensing efforts that were required are also discussed. This paper also shows how this type of plant will provide a versatile, economical, mid-range peaking plant.Copyright © 1974 by ASME

This paper describes the construction and initial operation fo a 260-MW combined cycle power generating plant consisting of two gas turbines, each with its own heat recovery steam generator. The steam, which is generated at 1200 lb 950 deg in each of the boilers, is combined to feed a single cylinder axial exhaust steam turbine. The paper describes the major components and operating cycle, the control system and some of the initial startup problems.Copyright © 1974 by ASME

In May of 1960 La Fleur Enterprises, later to become The La Fleur Corporation, undertook the design of a closed-cycle gas turbine utilizing helium as a working fluid. The useful output of this machine was to be in the form of a stream of helium bled from the last stage of the compressor. This stream was to be used in a low-temperature refrigeration cycle (not described in this paper) and would be returned to the compressor inlet at approximately ambient temperature and at compressor-inlet pressure. The design of this machine was completed by the end of 1960 and construction was initiated immediately. The unit was completed and initial tests were made in the Spring of 1962. This paper covers the design philosophy as it affected the conceptual and preliminary design phases of the project and describes briefly the design of the various components. Photographs of these components and a flow schematic are included.Copyright © 1963 by ASME

This paper is a continuation of a previously presented paper, which described the over-all design of the major components of a mobile power unit. The present paper is concerned with the main power equipment only and offers a detailed description of the design features which were developed for this project and also provide the flexibility necessary to make this gas turbine suitable for other applications.Copyright © 1956 by ASME

The transporting of liquids and gases is a basic need of civilization. Many methods have been and are used, ranging from the Egyptian water jar to the modern pipe line. The method used in today’s economy depends on the kind and amount of fluid to be transported. Martinis are delivered in 2 ounce glasses by a waiter, whereas oil is transported by 6 to 16 inch pipe lines. For purposes of discussion in this paper we will assume that the requirements are such that the fluid must be delivered to a particular location at a uniform rate. Thus, with this assumption, the most economical method of transporting would be by pipe. If the pipe and valve circuit is to be designed for most economical installation and operation, there are several things that should be known at the outset. Paper published with permission.

After giving a brief survey of some of the salient design features of the Mark TA 750/1000-kw gas turbine, an account is given of some of the different categories of application found for this machine on all six Continents of the World, indicating the economic factors which have led to the selection of gas turbines rather than alternative types of prime mover. The main portion of the paper deals with the operating experience which has been obtained on turbines burning natural gas, distillate, and crude oil fuels. The operation of twenty-nine Mark TA turbines which are now in service has been noteworthy for its complete freedom from blade breakages or other major failures. The few service troubles which have arisen, in nearly all cases, have been concerned with the operation of auxiliary equipment, and further development work is actively in progress on these items, in conjunction with the specialist manufacturers concerned, where necessary. The paper ends with an assessment of likely future trends in the application of medium-power gas turbines. Attention is given to the integration of the turbine with packaged assisted circulation boilers in order to provide compactness and flexibility of output.Copyright © 1958 by ASME

A test was conducted to explore the dynamic mechanical characteristics of a gas turbine-reciprocating compressor system, to define its optimum running conditions, and to verify the analytical results presented in ASME Paper 68-WA/GT-4. This paper summarizes the results of that test.Copyright © 1970 by ASME

This paper is based mainly on theoretical and experimental work done as part of the research program on turbine blade cooling at the National Gas Turbine Establishment. After describing the effects of increased trailing edge thickness on turbine efficiency, the bulk of the paper is concerned with the losses caused by the cooling air. A simple theoretical method for calculating the pressure losses caused by discharging the spent coolant into the main gas stream is described and the available experimental results used for comparison. Reasonable agreement for the loss of efficiency is obtained. The results of some cascade tests on transportation cooled blades are also included.Copyright © 1969 by ASME

This paper reviews the limitations today’s superalloys exercise on the realization of the potential of the gas turbine engine. Ceramic materials are suggested as a means of achieving lower cost and higher turbine inlet temperature in small gas turbine engines. The paper serves to introduce ceramic materials and processing techniques and identifies silicon nitride, silicon carbide and lithium-alumina-silicate as promising materials for high temperature turbine engine components.Copyright © 1970 by ASME

This paper describes the high speed cascade program underway at the von Karman Institute Turbomachinery Laboratory in Belgium. The primary purpose of the program is to contribute to the understanding of turbomachinery flow problems at transonic and supersonic speeds. Supersonic axial flow rotor blade sections and subsonic stator blade sections are investigated in a high speed cascade facility. The paper describes the cascade facility, instrumentation, and blade sections investigated. The aerodynamic flow through high subsonic and supersonic cascade blades is discussed, and some data obtained in the cascade tunnel are compared with those obtained in a rotating machine. Several major problems of high speed cascade testing are discussed, although a final solution is not always presented.Copyright © 1968 by ASME

This paper describes a recommended design and development procedure for reducing the possibility of vibrational problems in the blading of axial turbomachinery. The recommendations that are presented are based upon a study undertaken for the Bureau of Ships, United States Navy, under Contract No. NObs-92089.Copyright © 1966 by ASME

At the 1962 and 1964 ASME meetings, Allison submitted papers describing the possibilities of industrializing the T56 aircraft engine and the applications of the 501 gas turbine to industrial operations. Since 1964, Allison has been evaluating a prototype electrical power and steam generation set which has operated for approximately 20,000 hr. This paper describes the test program and the results obtained. Operating data from various engine configurations using natural gas and diesel fuel, four lubricating oils, two types of air-inlet filters, and a Harrison special high heat transfer rate exhaust gas steam boiler are also presented.Copyright © 1967 by ASME

The Alberta Gas Trunk Line’s new 20,000-hp gas turbine compressor set is one of the largest and most modern aircraft derivatives available to industry to date. This paper describes the various aspects of station and unit design for the compressor package. The additional operational flexibility gained as a result of adding this unit to our existing 12,500-hp station is described. The paper will also present a description of the station’s control system, including unit controls, surge controls, and other features of the instrumentation. Trunk Line is concerned with keeping the availability of the unit high, and as such, the paper will describe some features which help keep downtime to a minimum.Copyright © 1972 by ASME

Prototype gas turbines must have higher power and efficiency than their forerunners and therefore include new technologies and designs. A high reliability of the new gas turbine can be reached by careful evaluations of operating experience and by the choice of well proven elements for the new design. The first year’s operating experience with several prototype gas turbines, put into operation in the last decade, is given in the paper. It shows what kind of problems have been met in the past. All machines have given satisfactory service. This paper gives gas turbine users an assessment of the risks of running a prototype gas turbine.Copyright © 1973 by ASME

This paper gives a brief description of the Volvo experimental turbine, its working cycle, its basic components and their relative arrangement as well as some of the basic thinking behind the selection of the same. The paper also gives a short description of the new concept of a dual-geared power turbine, the combined reduction gear and high-speed hydrodynamic retarder, as well as some other new features incorporated.Copyright © 1962 by ASME

This paper discusses the factors involved in selecting the multiple free-turbine module arrangement for high-capacity, gas-turbine peaking units, and describes the design of the Pratt and Whitney Aircraft 121-Mw peaking unit being installed by Public Service Electric and Gas Company at the Sewaren Station.Copyright © 1964 by ASME

This paper is concerned with the experimental investigation of vibration in aircraft jet-engine rotating compressor disks of two different configurations. The blades in the first configuration were small, with relatively low mass, and had an insignificant effect on the disk vibration except for centrifugal loading. The second configuration had relatively large blades which resulted in combined blade and disk modes. The test techniques, test results, and examples of some known phenomenon as they occur in lightweight aircraft jet-engine disks are discussed.Copyright © 1965 by ASME

The proposed gas turbine engine represents a combination of a turbo-supercharger with a Comprex pressure exchanger. The engine is expected to have without recuperator a fuel consumption comparable to gasoline reciprocating engines. The availability of high quality low cost turbomachines as a result of the turbocharger development on the one side and the knowledge of non-steady flow machine technology acquired in the development of Comprex supercharger make this engine combination promising in the sizes of 50 to 100 KW output. The paper will give informations on thermodynamic parameters. The proposed arrangement of engine-components will be shown.Copyright © 1974 by ASME

A hydrodynamic gas bearing was developed for an automotive gas turbine whose output power and revolutions were 30 PS and 86,000 rpm, respectively. Experiments were performed on this gas bearing to clarify the relation among the load, film thickness and revolutions. Also, endurance tests was performed for wear during starts and stops. This paper describes these results.Copyright © 1974 by ASME

This paper reviews the basic researches of high temperature turbines. These researches include: the performance estimation of a turbo-fan engine with an air-cooled turbine; the relation between the spanwise distribution of cooling effectiveness and the life of the air-cooled turbine blade; experiments of film cooling on the leading edge and on the reduction of unsteady thermal stress in the air-cooled turbine blade; and a new construction of the air-cooled turbine blade. Also discussed are the two-dimensional cascade tests of air-cooled turbine blades by the low-speed and high-speed wind tunnels. Full-scale tests for the high temperature turbine including aerodynamic and thermodynamic investigations of air-cooled axial flow turbines are shown.

Flow data taken directly from turbomachine rotors are valuable, but the instrumentation problems are difficult. Information must be transferred from high-speed rotors, and the measurements require miniature transducers that can operate in high-acceleration environments. Recent advances in electronics, particularly in integrated circuitry, have permitted the design of miniature radio-telemetry systems for the transmission of data from rotors to stationary measurement equipment. Measurements are obtained without physical contact with the rotor, eliminating a principal problem. The present paper describes the design of a six-channel telemetry system for on-rotor research in turbomachinery.Copyright © 1974 by ASME

This paper describes a complete training program for an actual industrial plan that generates all of its own 80–90 Mw electrical power load and a great deal of the process steam with gas turbines. Enough information is presented to permit designing a course for most industrial generation and distribution systems including specific and detailed information of material and equipment required.Copyright © 1974 by ASME

This paper describes the application of the ceramic regenerator to the British Leyland truck gas turbine. Aspects of mounting, driving and sealing the heat exchanger disk are covered with particular reference to the single disk version of the 2S/350/R engine.Copyright © 1974 by ASME

This paper reviews the methods for predicting boundary-layer behavior on flat and curved surfaces under conditions experienced in gas turbine engines and the resultant heat transfer to the turbine rotor blades. Particular attention is given to the effects of streamwise pressure gradient and the intensity of mainstream turbulence on transition phenomena. The time-mean heat transfer across a boundary-layer under unidirectional oscillatory mainstream flow, such as might be initiated in a combustion chamber, is considered. The relevance of flat plate predictions and correlations to rotating turbine blades is also discussed.Copyright © 1974 by ASME

This paper describes the step-by-step procedure involved in solving a noise-control problem associated with the use of a J47 turbojet as a fixed-plant turbine-generator. Noise-reduction requirements for the turbine exhaust and intake are computed to satisfy both a hearing-loss criterion and a speech communication criterion. An impervious enclosure or a resilient wrapping, a lined 90-deg bend, the directive nature of one of the sources, and a muffler of acoustic baffles are utilized in solving the problem.Copyright © 1963 by ASME

Gas turbines with turbine inlet temperatures of 2500 to 3000 F are planned for the future. A critical element of the advanced controls needed for a turbine of this type is the turbine inlet temperature sensor to protect vital engine hardware and the registration of gas temperature for power controls. The paper discusses the requirements for high temperature sensor advancements, since currently developed sensors have short life, slow response, and are not sufficiently accurate. Considerable discussion is devoted to the capabilities of two different types of thermocouples and a radiation pyrometer to sense turbine hardware. Innovative concepts, such as a gas collimator lens, the use of fiber optics to avoid environmental test temperature, effects of combustion gases on radiant intensity, and emissivity changes on indicated temperature are discussed.Copyright © 1969 by ASME

This paper describes the design and development of a new series 3000 two-shaft regenerative and simple cycle gas turbine for mechanical drive applications. Technical advances in the areas of aero-thermal, mechanical, controls, and materials design were combined to produce a machine with a regenerative cycle thermal efficiency of 32%. Increased automation and adaptability to remote control were provided by a new solid state control system and high pressure hydraulics.Copyright © 1969 by ASME

The present design study was part of a program undertaken for the purpose of determining the feasibility, establishing the development requirements, and estimating the cost of a turbocirculator to provide the pumping power for a 1000-MWe High Temperature Gas Cooled Reactor (HTGR). Methods were developed for the optimization of the thermodynamic cycle and the design point of the turbocirculator components. A comparison of a turbocirculator to other ways of pumping helium in a HTGR is also shown in this paper. A design of the machine with its associated bearing and seal system and gas conduits was carried out. An important feature of this design is incorporation with the other components of the nuclear steam supply system within the prestressed concrete reactor pressure vessel.Copyright © 1970 by ASME

This paper will discuss the specific development of the plate-fin type of recuperator utilized on the Ford Motor Company’s 16:1 pressure ratio, gas turbine engine.Copyright © 1969 by ASME

Until two or three years ago, the conventional method of getting canned, glassed, or packaged goods to market was to load them into a top-opening regular printed and slotted corrugated case. The packaging operation itself had become pretty well automated through use of drop type and push in equipment. Some had completely automated the system with automatic case openings positioning and gluing and sealing machines. By far the bulk of the packing industry was still in the semi-automatic stage of manual case opening and placing the case on the packer funnel to complete the loading cycle, prior to discharge and conveying to the gluer. Paper published with permission.

To exploit the regenerative gas-turbine cycle to the fullest possible extent requires an extremely high degree of heat exchange. Presently, the rotary heat exchanger is the only type which can be designed with the high thermal effectiveness necessary and yet remain practical from a size and cost standpoint. The mechanical nature of the rotary heat exchanger is such, however, that some leakage of high-pressure fluid to the low-pressure side will always occur. The fact that in the past this leakage could not be held to workable values has prevented commercial acceptance of this type unit. Consequently, The Air Preheater Corporation set up an intensive program aimed at developing an acceptable sealing means which would remove this one objection to an otherwise highly desirable piece of equipment. While this development program, at time of writing, is far from complete, results to-date have indicated that sealing of the rotary design can be accomplished, and based on quantity production, costs of a turbine plant equipped with a rotary heat exchanger would be attractive commercially. Included in the development program was the design and construction of a prototype unit for a 3000 hp turbine plant. While erection of the prototype unit is complete, no testing has been done at time of writing. The purpose of this paper is to emphasize the advantages of the regenerative cycle, generally, and more specifically, to show why the rotary type is most promising, particularly in the high effectiveness range. In addition, certain data pertaining to the design of the prototype unit are also presented. A future report will present results obtained from the prototype test program.

Advancing turbine engine technology requires air-cooled turbines. Cooling mechanisms applied must be exploited in a practical manner to obtain maximum cooling effectiveness. Cooled turbine stator and rotor blade design requires rigorous analysis supplemented by verifying experimental data. Problem definition, analysis techniques, material application, cascade and engine testing, and correlation of data are presented for air-cooled turbines. Convection, impingement, film, transpiration, and combined cooling mechanisms are reviewed.Copyright © 1965 by ASME

This paper describes the results of a design study of a family of steam turboalternators for a potential terrestrial low power reactor power plant. The criteria were small size, very high reliability, and as high an efficiency as possible. The use of water lubricated bearings and of 400-Hz power were fundamental to the design. The results indicate feasibility of a single basic design over the power level range of from 30 to 2000 kwe.Copyright © 1969 by ASME

Increased emphasis is being placed on the regenerative gas turbine cycle, and the utilization of waste heat recovery systems, for improved thermal efficiency. For such systems there are modes of engine operation, where it is possible for a metal fire to occur in the exhaust heat exchanger. This paper is intended as an introduction to the subject, more from an engineering, than metallurgical standpoint, and includes a description of a series of simple tests to acquire an understanding of the problem for a particular application. Some engine operational procedures, and design features, aimed at minimizing the costly and dangerous occurrence of gas turbine heat exchanger fires, are briefly mentioned.Copyright © 1969 by ASME

This paper discusses the common needs of different industrial-marine gas turbine systems for flexible power transmission coupling shafts and shows how the flexible diaphragm coupling has been successfully applied to such gas turbines as the TPM FT-4, G. E.’s LM2500 and several others. Most aircraft derivatives and the larger industrial gas turbines require lightweight, maintenance-free, quiet flexible couplings. The diaphragm coupling will fill this need if properly designed and applied. Materials and methods of making preliminary natural frequency calculations and computer modeling of the diaphragm coupling are also discussed.Copyright © 1973 by ASME

This paper discusses the application of the two-shaft gas turbine to oilwell stimulation pumping through the successful design and manufacture of a mobile mounted 2000-hp pumper, using two 1000-hp turbines. The design is discussed from the standpoint of: functional requirements; operational requirements; power train design; control requirements and design; auxiliary systems; and field operating experience. The pumper was put into operation in October 1968 and after one year of experience it was judged successful in terms of reliability and reduction of maintenance and operating costs. Two more pumpers are now planned and scheduled for completion in March and June 1970.Copyright © 1970 by ASME

This paper describes the design of a new boiler incorporating advanced features in gas turbine heat recovery. The basic requirements such as size, adaptability, and cost are listed and design parameters covering these requirements are given. Illustrations of the heat-transfer surface and boiler module are accompanied by typical curves showing heat recovery and pressure loss. The author summarizes with an outline of the advantages of this new boiler design.Copyright © 1967 by ASME

This paper gives a brief description of a circumferentially oriented modular gas turbine recuperator. The basic module is of the plate-fin type, and is made from an assembly of radially tapered secondary surfaces to form a segmental matrix with a counterflow fluid configuration. The removable modules are integrated with the axial turbomachinery to form a compact package. Some of the economic, design, manufacturing, and performance experiences gained during the development of this heat exchanger are discussed in detail.Copyright © 1968 by ASME

The objective of the research and development program reported by this paper was to decrease the specific fuel consumption of a small gas-turbine engine by means of an increase in pressure ratio alone. Development of a centrifugal compressor is presented, with a general description of equipment, methods, and special problems met during the tests. Results showed the required decrease in specific fuel consumption and pointed up the advantages of a straightforward development program.Copyright © 1956 by ASME

A rotor-mounted radio telemetry instrument system for measuring surface pressures on the rotating blades of an axial-flow compressor was developed and tested. The paper describes the design of the instrument system and several tests to establish its accuracy. Measurements of average and fluctuating surface pressures were reported. Measured pressure levels were found to agree with theory and available experimental data.Copyright © 1973 by ASME

Advances in gas turbine engine technology have made possible small, lightweight, very high-speed engines. Plans for future units promise a continuation of this trend. Accessory technology has not made comparable advances to date. The low-speed capability of presently available accessories threatens to severely penalize the specific weight and volume of anticipated small engine packages. This paper describes the design analysis and laboratory evaluation of a vane-type fuel pump designed to operate at gas-turbine-shaft speed. Techniques required to attain these speeds without sacrificing endurance in the vane-type pump are discussed.Copyright © 1969 by ASME

This paper reflects on the design considerations for naval gas turbines in terms of duty profile operating requirements and the basic parameters of engine design. The degree of compromise of weight, efficiency, and engine life should reflect the specific application requirements.Copyright © 1956 by ASME

This paper presents a review of the progress made by the investment casting foundries in producing integrally-cast airfoil components for small gas-turbine engines. The casting process, from pattern production to the final inspection operations, is discussed in detail. Suggested dimensional tolerances, based on the present state of the art, are included. Finally, the properties and casting characteristics of various alloys commonly used for internal components are presented.Copyright © 1962 by ASME

This paper discusses the economic and technical considerations involved in the decision of a large chemical complex to install on-site power generation; why the gas turbine with waste-heat recovery for process steam generation was determined to be the optimum approach; and the reasons for selecting the aircraft-type gas turbine for this particular application. A brief description of plant components and operation is also included.Copyright © 1967 by ASME

This paper presents a unique application of two 14,200-hp gas turbines and their associated waste heat-recovery boilers in a refinery modernization program. It summarizes economics, design, and operating experience. Special emphasis is placed on three unusual features: (1) oversized starting turbines used as helpers; (2) control of two drivers with one governor; and (3) use of gas-turbine exhaust as combustion air, backed up by a forced-draft fan running at full speed against a closed damper.Copyright © 1964 by ASME

Designers of axial flow compressors have always been alert to the effects of tip clearance. The literature contains some simple theories and many tests of specific machines. There has been a tendency to presume that these test results are valid for compressors in general. Certainly a general rule is needed for the great variety of designs found today. Some types, among them generator cooling blowers and wind tunnel blowers, may require large tip clearances so accurate prediction is essential to success. Enough data have now accumulated to permit attempts at generalization. Leroy H. Smith, Jr. provided a starting point with his 1958 paper. This one adds more data, carries the analysis of data further, and points out practical need for further experiment.Copyright © 1960 by ASME

Facets of safety of operating personnel, the public and equipment are presented in this paper which is one of a series covering all subjects of the proposed gas turbine procurement standard. Information is furnished to provide guidance in the preparation of gas turbine purchase specifications. Comments and suggestions are welcomed by the authors in order to improve this material and produce a more useful standard.Copyright © 1972 by ASME