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The gas turbine or Brayton cycle offers many advantages over a conventional power plant, especially when installed in a cogeneration mode. These advantages include physically compact packages, high reliability, improved system economics and full operating flexibility to meet variable electrical/steam demand. Until recently, the primary disadvantage of the gas turbine cycle has been that internal burning of dirty fuels caused unacceptable erosion and corrosion of turbine blading. In the simple cycle gas turbine modified for indirect heating, the compressor discharge air passes through the tube side of a heat exchanger before passing on to the turbine. Heat is transferred to the air via the combustion products of alternative fuels passing through the shell side of the heat exchanger. This paper discusses the potential of the indirectly heated gas turbine burning wood in a cogeneration configuration with a back-pressure steam turbine.Copyright © 1980 by ASME

The paper covers development and operating experience of the Olympus TM3B, Tyne RM1A and RM1C engines in the Royal Navy over the period 1976 to 1978. Problem areas that have been identified and their solutions are discussed and lines of related research and development in the fields of Combustion, Materials, and Engine Health Monitoring are indicated. The paper concludes that the decision of 10 years ago adopt all gas turbine machinery for future surface warships is being thoroughly vindicated by experience.Copyright © 1978 by ASME

A series of duo-density silicon nitride gas turbine rotors have been prepared for testing and tested at Ford Motor Company. The paper reviews the duo-density fabrication process, and covers in detail the rotor preparation process, which includes machining, inspection, and cold proof spinning. The paper describes the hot spin test rig used for the hot testing of the rotors, and summarizes the results of the hot spin test program.Copyright © 1980 by ASME

This paper is a discussion of the methods of heavy fuel treatment for industrial gas turbines and the effects of fuel characteristics on washability. A summary of recent experience with burning heavy fuels by a typical industrial user is presented. The paper includes a discussion of the latest design improvements in fuel treating equipment and the resulting improvements in washed fuel quality. The effect of fuel parameters on system size, cost and performance is evaluated.Copyright © 1975 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 describes the design and development of the compressor and turbines of the British Leyland 2S/350/R truck engine. The design of these components has to meet the cycle requirements for efficiency and operating range on the one hand and have the ability to withstand the steady and vibratory stresses on the other. In addition the design has been influenced both by manufacturing methods and by the fact that the engine has to operate in an automotive environment. The paper discusses how these often conflicting requirements have been satisfied in the latest version of the engine.Copyright © 1974 by ASME

This paper describes the operating experience with the Westinghouse PACE 260 Combined Cycle Power Plant at Public Service Company of Oklahoma’s COMANCHE Station. This plant was the first PACE 260 unit to go into operation and had many new design features in the major components. The paper deals mainly with the problems that occurred and their solutions.Copyright © 1976 by ASME

This paper presents a description of the control and protective preliminary system designs for the gas turbine high-temperature gas-cooled reactor power plant (GT-HTGR). The purpose of these systems is the control and safe operation of the plant in accordance with utility practice for large nuclear generation stations, and in the event of an abnormal or accident condition to shut the plant down in an orderly manner and maintain it in a safe shutdown condition. The control system is designed to regulate reactor power, control electric load and turbine speed, control the temperature of the helium delivered to the turbines, and control thermal transients experienced by reactor internal components. In addition, it provides the required control and programming for start-up, shutdown, load ramp, and other expected operations. The control system also handles conditions imposed on the system during upset and emergency conditions, such as loop trip, reactor trip, or electrical load rejection. Under these conditions, reactor power and helium flow are reduced in order to minimize temperature transients imposed on reactor components. The transient analysis and control system selection process which has been used to establish the reference GT-HTGR control system is illustrated in this paper. The study demonstrates not only the design of adequate control, but also reduced severity of plant component design requirements imposed by transient events.

An earlier paper analyzed aeroengine fan flutter in terms of twin orthogonal vibration modes in the fan. This paper extends the analysis by incorporating variable aerodynamic phase lags between a blade motion and the resulting aerodynamic forces. The extended analysis predicts two independent kinds of flutter. If the total damping within each mode is negative, each mode develops a self-sustaining vibration at its own natural frequency. This was not predicted by the earlier twin mode analysis. Even when the damping in each mode is positive an interaction between the modes can cause flutter under some conditions. This behavior is basically of the form described in the earlier paper, but there are significant detailed changes when variable aerodynamic phase lags are introduced.Copyright © 1980 by ASME

This paper describes a solar receiver under development for the Department of Energy under contract to the Jet Propulsion Laboratory. The receiver is designed to be used with a single-point-focus, parabolic concentrator. The receiver accepts the concentrated solar radiation and uses it to heat the working gas of a small, open-cycle gas turbine to about 1500 F (815 C). The receiver employs a high-efficiency, metallic plate-fin heat transfer surface to effect this energy transfer. The paper discusses the thermal and mechanical design features of the receiver.Copyright © 1980 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 is a report on progress in the development of a control system for an automotive gas turbine engine. Contained in the paper is a description of the automotive gas turbine control requirements together with a description of the resultant electronic mechanization. Design characteristics of interface elements, such as fuel delivery system, variable area control actuators, and system sensors are discussed.Copyright © 1976 by ASME

In this paper, the authors describe construction and initial operating experience on two prototype gas turbine power plants located thousands of miles apart: Isefjordvaerket’s 140-MW plant at Kyndby, Denmark, built by Brown Boveri-Sulzer Turbomachinery (BST) and Northern States Power’s 200-MW plant at Blue Lake, Minnesota, built by Turbodyne Corporation (TBD). The paper provides a unique opportunity of comparing two approaches to a similar plant construction concept.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

The LARZAC 04 turbofan engine has been designed, developed and qualified by two French gas turbine engine companies linked by a controlling group known as Groupement Turbomeca-SNECMA. The LARZAC engine is in production for the Alpha Jet, a military aircraft developed by Avions Marcel Dassault-Breguet Aviation and Dornier GmbH. Teledyne CAE has an agreement to market, service and, optionally, to manufacture the LARZAC 04 in the United States and Canada and has designated this engine the Model 490-4. This paper addresses the criteria used to design the Model 490-4 and achieve high reliability and low maintenance cost. For example: (a) modular construction and how it reduces maintenance cost, (b) high reliability design and its payoff in low maintenance costs, and (c) the planned growth of the inspection intervals to achieve minimum Life Cycle Cost. Also addressed in this paper is the rugged design of the engine as proven by cyclic component tests, large and small bird ingestion, water and hail ingestion, short cycle testing and Simulated Mission Endurance Tests.Copyright © 1980 by ASME

The author describes the evolution of his company’s digital control approach to the Pegasus engine as applied to a single engined VTOL aircraft. The paper describes the digital control system being built by Dowty and Smiths Industries Controls Limited (DSIC). The design is based on extensive engine evaluation of different control configuration with electronic and hydromechanical back-up system. The paper describes the mechanical design, installation on the engine and the cooling of the system including the choice of basic packaging concept. It also discusses the rationale for the particular choice of back-up system and the reliability/safety of flight trade-offs involved.

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

The combination of pressurized fluidized bed (PFB) technology and the gas turbine - steam turbine combined-cycle power system offer a unique opportunity for the production of electric power at increased plant efficiency from the direct combustion of high sulfur coal and that is environmentally acceptable without stack gas cleanup. The concept offers the prospect of earlier commercialization than those systems requiring gasification or liquefication of coal to clean fels. This paper presents the design of a 500-MW commercial powerplant prepared in conjunction with the U.S. Department of Energy sponsored program for the design, construction, and operation of a coal-fired PFB/turbine electric pilot plant. The powerplant approach develops over 60 percent of the plant capacity by multiple gas turbine gas turbine-generators and the balance of the capacity by a steam turbine-generator. The paper describes the fluid bed process selection of an air heater cycle. With two-thirds of the compressor discharge air indirectly heated within an in-bed gas-to-air heat exchanger and one-third of the compressor air involved in the combustion process, technology requirements for hot gas cleanup and turbine protection are minimized. This approach, which offers a coal-pile-to-busbar plant efficiency of over 40 percent is superior to other concepts and contemporary plants in terms of plant arrangement flexibility, part-load performance, power availability, and provides a low risk in development toward commercialization in the 1980’s.Copyright © 1978 by ASME

LM2500 Engines have been in operation in U.S. Navy ships since September, 1975. This is an update of a previous ASME paper given in March, 1977, which presented the operational experience of the LM2500 to that time. Included in this paper will be the reliability achieved thus far plus the improvements that are projected from the ongoing component improvement program. The application of the engine to a wide spectrum of ships in 11 foreign navies is also covered.

The gas turbine is rapidly becoming the dominant means of propulsion in surface ships of the Royal Navy, as more ships of existing classes are built and as new gas turbine ships come into service. The paper describes recent operating experience, and the introduction of the uprated RM1 C Tyne engine to service. The principles of upkeep, engine health monitoring, and life extension being followed by the Royal Navy are discussed. The paper includes a review of the progress of the development program for the SM1 A Marine Spey engine for ships of the Royal Navy in the 1980s.Copyright © 1980 by ASME

The Westinghouse PACE 260 combined cycle control system was first shipped to the field January 1973. It was shipped to the Comanche Site of Public Service of Oklahoma, at Lawton, Okalhoma, Fig. 1, to control the Westinghouse prototype combined cycle plant. Since then, nine other PACE 260 control systems have been shipped to other combined cycle plant sites. The PACE control system was a new system controlling a new process, the combined cycle. Problems were experienced and problems were solved. At this date, all the control system functions, both analog and digital, have been field tested and are functioning. This paper discusses the experiences at the installed PACE 260 combined cycle plants which were on line producing megawatts at the time this paper was written. The sites are: Dos Bocas and Gomex Palacio in Mexico for the Mexico Commission Federal de Electricidad; El Paso, Texas for El Paso Electric; and Comanche for Public Service of Oklahoma. Changes were made to the process, to primary sensors, final control elements and to the control system. This paper discusses some of these changes, the reason for them, and the effects of implementing them.Copyright © 1976 by ASME

This paper considers the major interfaces between the main propulsion gas turbine and its environment in the ship. Both hardware and software interfaces are recognized and accent is placed on the designer’s approach to them. The importance of proper appreciation of design restraints and requirements is underlined. The various problems are general, and have been listed and discussed in summary form. Their solution can be sought with vigor only when applied to the particular case of a given gas turbine in a firmly projected ship. Thus the paper discusses problems and asks questions; it does not offer any general solutions.Copyright © 1974 by ASME

A joint General Electric and Electric Power Research program is nearing completion after six years of water-cooled turbine technology development. The first two years were devoted to preliminary combined gas and steam turbine cycle studies and preliminary gas turbine combustor and turbine hot section design studies. Beginning in 1976, the major emphasis has been on resolving areas of critical technology toward the application of water cooling to the heavy duty commercial gas turbine. Earlier papers, ASME 78-GT-72 and 79-GT-72, presented preliminary results for development tasks which investigated phenomena associated with application of water cooling to turbine hot section nozzles, buckets and flowpath components for operation at increased turbine firing temperature. This paper presents results obtained from mid-1978 through 1979, and deals primarily with near term application of water cooling technology to the commercial gas turbine operating on heavy residual oil or coal derived liquid fuels. Water cooling in the near term offers the promise of significant reduction of both hot corrosion and ash deposition at the turbine first-stage nozzle.Copyright © 1980 by ASME

The paper describes a digital electronic engine control system being built by Dowty and Smiths Industries Controls Limited (DSIC) to demonstrate the control features required for the next generation of helicopters and their power plants. It is engine mounted, fuel cooled and of lightweight design. The paper describes the mechanical design, the installation and the cooling of the system including the choice of the basic packaging concept. It also discusses the safety of flight aspects of system operation. Finally, the paper discusses how the design can be modulated to increase/reduce the capability of the system and thus, the more effectively to cover a range of requirements.Copyright © 1980 by ASME

The Gas Turbine High Temperature Gas-Cooled Reactor combines a helium-cooled reactor core of established design with a closed-cycle helium turbine power-conversion system. This paper discusses the design considerations which mitigate the consequences of failure of the rotating machinery located within the reactor vessel. The methods of analysis and summary of results are presented for the failure modes of most concern. The spectrum of potential incidents which have been evaluated include turbine blade, rim, and disk failures. The requirements and design methods for rotor containment are discussed. The turbomachine maintains a pressure ratio of about two between the high and low pressure portions of the loop; postulated failures can, therefore, lead to rapid rates of pressure change. The preliminary evaluation of this internal pressure equilibration is presented.

As the value of natural gas began to rapidly escalate in recent years, a number of old concepts for improved gas turbine pipeline station fuel consumption have been analyzed. These concepts include the use of diesel starting devices, inlet air evaporative coolers, higher effectiveness regenerators, steam injection, combined steam and gas turbine cycles, optimum loading of the gas turbine, and more frequent changing of compressor impellers. This paper reviews these concepts in anticipation of higher fuel costs and offers a brief analysis of economic gains.Copyright © 1976 by ASME

The fundamental advantage of the reprogrammable general-purpose digital computers is their ability to perform accurately and repeatably calculations of any complexity. In practical terms, the computing task determines the size of program memory required and the run time of the calculations. The former affects cost; the latter affects the real-time performance for control applications. This paper discusses how and to what extent these advantages can be implemented assuming that the “digital computer” is a microprocessor plus semiconductor memory and that the applications are naval and industrial gas turbines. Examples are drawn from engine tests that have used a medium-speed microprocessor.Copyright © 1976 by ASME

Energy costs can be reduced in most large process plants by the use of turbines to supply power and heat. Performance characteristics of gas turbines, gas turbine exhaust heat boilers and combined gas-steam turbine cycles, plus the typical heat balance diagrams included in this paper will help the reader visualize economic applications for turbines in different industrial plants. The effect different fuels have on gas turbine maintenance (costs and downtime) and other application parameters are included. The information provided will permit the user to assess his own situation and then select the most economic fuel for a specific gas turbine application.Copyright © 1974 by ASME

Electronic controls are being used on more gas turbine engines today than ever before. Part of this has been due to the proven capability of electronics, and part has been due to the increasingly complex tasks that controls have been required to perform. Unfortunately, for industrial gas turbines, there has been little coordination between the various aspects of the total system: control, sequencing, monitoring, and annunciation. This paper describes a control system which has integrated all those functions into a hierarchical system that is both powerful and reliable. The key elements of the system are a microprocessor controlled programmable sequencer and a proven modular analog control system. A gas pipeline application will be explored in detail.Copyright © 1978 by ASME

This paper shows how the significant developments available today can bring digital controls within the price range of all but the very simplest control systems and at the same time provide very significant flexibility not possible hitherto, except in the most complicated installations. New development in the form of the microprocessor chip has made it possible to design digital fuel controls at a cost equivalent to current analog systems. These developments free the control system designer from many of his previous limitations, but they also impose new constraints.Copyright © 1975 by ASME

The paper describes the development and initial field experience with a new high efficiency 26,000/30,000 hp gas turbine. Exhaust heat from the power turbine was used to boost the installation thermal efficiency and provide icing protection for the inlet. Wherever possible, proven power turbine design concepts were combined with the advances of a “second generation” aircraft derivative gas generator to produce a reliable machine which was introduced with a minimum of development time. To assure field success, a special test facility was constructed and the unit subjected to a full load mechanical and performance test under simulated field condition.Copyright © 1980 by ASME

Studies sponsored by the U. S. Department of Energy (DOE) have indicated that the combined cycle, incorporating an open cycle gas turbine having a Low Btu gas (LBG) fueled combustor operating at temperatures over 2600 F and a closed cycle steam turbine can produce cost competitive electric power from gasified coal. For increased efficiency, the coal gasification system would be integrated with the gas turbine which supplies the compressed air for the coal gasification system, and the steam turbine which supplies the steam for the gasification system. The coal gasifier would provide a pressurized low heating value (LBG) fuel (at the order of ISO Btu/SCF (5590 kJ/m3) for combustion in the gas turbine engine. Under DOE sponsorship, one of the gas turbine engine components being investigated both analytically and experimentally, is the LBG fueled combustor. This paper describes the LBG configuration background technology utilized in the design of the combustor and the test program outline for substantiation of the design approach.Copyright © 1980 by ASME

This paper considers the problem of the unbalanced rotating turbine as a single degree of freedom system, wherein the principal mode of vibration is a translation in the direction of the machine supports. The distance from the center of mass of the rotating mass to the geometric axis, also known as the effective eccentricity, is modeled as a random variable. The expression for the root mean square response of the rotating machine is derived and related to the statistical analog for the deterministic expression for the foundation force. These results are numerically compared to their equivalent deterministic values.Copyright © 1976 by ASME

Certain types of failure in aircraft gas turbines can have effects which prejudice the safety of flight of the aircraft in which they are installed. The failures can be directly caused by software deficiencies in a digital engine control. The paper reviews the basic issues in achieving software safety of a level required for certification and discusses the effects of these issues. The discussion addresses particularly choice of language; specification, design validation and test procedures throughout the life of a given set of control software.Copyright © 1980 by ASME

A brief history on the application, start-up and operation of two gas turbines with waste heat recovery boilers in a combined energy cycle, integrated with an existing power plant to provide the total energy needs for a major chemical manufacturing complex. This paper describes an installation with some unique design features to provide for maximum cycle efficiency and reliability and discusses the major problems and difficulties experienced in putting this complex energy plant into operation.Copyright © 1974 by ASME

Occasionally, gas turbines are subjected to random ice ingestion, but due to the illusiveness of the ice, varying weather patterns, and intake and plenum systems ahead of the gas generator intake, it has been almost impossible from field experience to tabulate precise data, for design criteria for future equipment. The paper covers some of the research and development work which has been carried out to determine the varieties and size of ice being ingested, the effects on compressor components, and use of such data for existing equipment, and future gas generator designs. Intake and plenum designs past and future are briefly reviewed. It would appear there are solutions to substantially reduce icing incidents on most of the existing equipment, certainly costly incidents, and on future equipment, the problems should be eliminated.Copyright © 1976 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

Evaluation of power transmission shafting for high-speed balancing has shown that when axial torque is applied, the imbalance response is altered. An increase in synchronous excitation always occurs if the axial torque level is altered from the value used during balancing; this was the case even when the shaft was balanced with torque applied. The twisting of the long slender shaft produces a change in the imbalance distribution sufficient to disrupt the balanced state. This paper presents a review of the analytic development of a weighted least squares approach to influence coefficient balancing and a review of experimental results. The analytic approach takes advantage of the fact that the past testing has shown that the influence coefficients are not significantly affected by the application of axial torque. The 3.60-m (12-ft) long aluminum shaft, 7.62 cm (3 in.) in diameter was run through the first flexural critical speed at torque levels ranging from zero-torque to 903.8 N-M (8000 lb-in.) in 112.9 N-M (1000 lb-in.) increments. Good comparison was achieved between predicted and experimental results.

Liquid fuel treatment systems are available in a variety of types and sizes for various kinds of fuels. It is the purpose of this paper to make sense out of this maize of equipment and develop a systematic approach to component selection. In addition, the equations for calculating washing system efficiencies are presented as well as some new ideas in control systems and fuel analysis techniques. A gas turbine user should look at the total fuel history from refinery to exhaust stack as a part of the systems engineering work performed in the planning stages of a gas turbine or combined cycle installation.Copyright © 1975 by ASME

In 1967, IHI engaged in developing a gas turbine for high speed railcars as an industrial application of the aero gas turbine CT58. Since then, IM100-1R and IM100-2R engines, derived from CT58’s, have been tested on the bench and on experimental railcars by the Japanese Rolling Stock Manufacturers association (JRSMA) and the Japan National Railway (JNR). In this paper, a brief history of development tests for gas turbine railcars, problems and improvements in applications of the IM100-1R and -2R for prime mover of the railcar are described.Copyright © 1974 by ASME

During recent years, the use of gas turbine driven compressors for natural gas liquefaction has been getting increased attention. This paper will describe the application of lightweight Modular Industrial Turbines to conventional liquefaction processes.Copyright © 1980 by ASME

Noise technology requirements are surveyed for several future aircraft powerplants. The applications considered range from growth verions of current production engines to future advanced supersonic transport applications. Although a variety of complex and challenging noise-suppression problems are identified, a sampling of several basic problems common to a variety of engine designs are discussed in more detail. Among these are: the prediction of fan noise generation and propagation in treated ducts, the use of mixer nozzles to reduce jet exhaust noise, and the prediction and absorption of combustion noise. Discussed in the paper are analytical and experimental approaches applicable to solving these problems.Copyright © 1976 by ASME

Utilizing and converting of existing low temperature and waste heat sources by the use of a high efficiency bottoming cycle is attractive and should be possible for many locations. This paper presents a theoretical study on possible combination of an organic Rankine-cycle turbine power plant with the heat pump supplied by waste energy sources. Energy requirements and system performances are analyzed using realistic design operating condition for a middle town. Some conversion systems employing working fluids other than water are being studied for the purpose of proposed application. Thermodynamic efficiencies, with respect to available resource, have been calculated by varying some system operating parameters at various reference temperature. With reference to proposed application equations and graphs are presented which interrelate the turbine operational parameters for some possible working fluids with computation results.Copyright © 1980 by ASME

The Gas Turbine High Temperature Gas Cooled Reactor (GT-HTGR) power plant combines the existing HTGR core with a closed-cycle helium gas turibne power-conversion system directly in the reactor primary circuit. An integrated design concept in which the reactor core, turbomachinery, heat exchangers, and entire helium inventory are enclosed within the prestressed concrete reactor vessel (PCRV) was selected on the basis of both safety and economic reasons. Th layout of the power-conversion loop (PCL) components, with envelope restraints associated with installation in cavities in the PCRV, and development of the primary system gas flow paths are discussed. This paper outlines the studies which led to the selection of the primary system for an integrated type of plant embodying multiple gas turbine loops. With orientation and configuration of the major components in the PCL forming the basis of these studies, some of the preliminary design considerations for the turbomachinery, heat exchangers, and other components are discussed. The high potential for further improvement in plant efficiency and capacity, for both advanced dry-cooled and waste heat power cycle versions of the direct cycle nuclear gas turbine, is also discussed.Copyright © 1976 by ASME

A program to design, construct and operate a pilot electric plant using a pressurized fluidized bed (PFB) combustor burning high sulfur coal to produce electricity at competitive costs and in an environmentally acceptable manner is proceeding under DOE sponsorship. Three components were identified needing experimental test data to validate the selected design configurations or material selections. These components included: (a) PFB in-bed heat exchanger tubes, (b) hot gas cleanup system, and (c) turbine blades. R&D test programs utilizing laboratory rigs, commercial fluid bed reactors, and a large scale PFB technology rig were conducted for a cumulative test time of over 10,000 hr. Design criteria and configurations were selected and verified. This paper presents the results of the technology development presents the results of the technology development tests. Also, the large scale PFB technology rig design and test program are presented. The results of operating a small gas turbine coupled to the PFB combustor and hot gas cleanup system within this technology rig are discussed.Copyright © 1980 by ASME

This paper briefly reviews the technical capabilities of the NAFP and several facilities that will support future aerospace RDT&E. It explores the subject of increasing test facility utilization and their international use.Copyright © 1978 by ASME

There has been an increased concentration of effort recently in the understanding of the complex flow in centrifugal turbomachines, especially industrial machines. Although it is impossible at this time, to model all the phenomena existing in a real machine, it is felt that a systematic approach which makes use of recent advances in computational fluid dynamics, and extends these as further developments occur, will significantly improve our understanding of the flow, and our ability to predict performance and improve efficiency. In this paper, a new general finite difference technique for solving the flow field in the hub-to-shroud plane of any component of a centrifugal turbomachine is described. The technique uses a quasi-orthogonal finite-difference net, and solves the resulting system of equations using a matrix method. Thus the technique offers a stable, accurate computational method, combined with a fixed grid which may be simply applied to the most complex annular passage shape. The results for three numerical examples are presented, a radial to axial inlet, a vaneless radial diffuser and an interstage return bend.Copyright © 1975 by ASME

The operation of gas turbines during conditions of extreme cold weather can present a variety of problems. Foremost among these problems is the potential for snow and ice buildup in the air intake system which can cause restrictions or interruptions in operation and possible ingestion damage to the axial compressor section of the gas turbine. Other cold weather operating problems include cold lubricating oil and oil system blockages following periods of shutdown. Major maintenance on the equipment becomes very difficult, if not impossible, during conditions of extremely cold weather unless the work can be carried out in an adequately heated building. This paper expands on these problems and others and outlines methods which have been developed to deal with them. Its content could be of benefit to design engineers engaged in preparing specifications for gas turbine equipment to be used in cold climates.Copyright © 1976 by ASME

The Canadian Government, Ministry of Transport, initiated a Study of the Application of Gas Turbines to Canadian Coast Guard Vessels in 1972, which was completed in early 1974. This paper discusses the results of our findings and also new data now being used in design studies for heavy Icebreakers of Polar Class.Copyright © 1975 by ASME

This paper presents progress in the development of silicon nitride ceramic turbine stators and rotors as part of the ARPA/Ford program to apply ceramics to a small vehicular gas turbine engine. It reviews the benefits of increasing engine operating temperature by adopting ceramics. Design of ceramic stators and rotors is discussed, together with results of stress and heat transfer analyses. Progress in fabrication methods is reviewed and pertinent silicon nitride property data are presented. Methods of thermal testing ceramic turbine stators are discussed, as well as how this testing has influenced interations in stator design. Results of testing stators in a high temperature turbine engine are reported. Spin testing of ceramic turbine wheels is reviewed with special reference to the importance of flaw detection and the types of rigs used for cold and hot spin testing.Copyright © 1975 by ASME