bluuebunny/crossref_metadata_2025 huggingface dataset:
The Jet-Flap in Centrifugal Turbo Machines
Authors: Goldschmied F. R.
Published: April 2015

Increased flow and pressure rise at constant speed have been achieved for a centrifugal impeller by application of the jet-flap and of mechanical tip flaps to backward-curved airfoil blades. Flow increments up to 16 percent and pressure increments up to 36 percent have been obtained with a control efficiency of 85 percent. Peak total-to-total efficiencies of the basic impeller have been found to be over 88 percent. An experimental correlation has been found for radial jet-flap cascades between lift increment and jet thrust, cascade solidity, jet angle, and effective blade aspect ratio.
Jets, Props and Air Cushions: Propulsion Technology and Surface Effect Ships
Authors: Skolnick Alfred , Wachnik Z. G.
Published: April 2015

Following a brief review of the background and formulation of the jointly sponsored Navy/Commerce Department’s Surface Effect Ships (SES) Program, the paper offers a broad scope presentation on propulsion for SES, e.g., waterjets, supercavitating propellers, and lift fans. The problems associated with establishing the feasibility of successful designs and construction of such ships are considered, the status of development assessed and the efforts still remaining accordingly” defined. The paper deals primarily with the propulsion considerations of high speed ships using the air cushion principle in combination with vestigial rigid sidewall design.
Development of Fluidic Controls for Advanced Integrated Propulsion Systems
Authors: Johnson E. G.
Published: April 2015

Fluidic propulsion controls have been developed which provide improved modes of control by measurement and control of turbine inlet temperatures. By controlling the actual engine conditions improved performance, better engine protection and longer turbine life is possible. Comprehensive development programs by the Air Force Aero Propulsion Laboratory prove that fluidic controls can operate at 1200 F and are applicable to advanced turbojet propulsion systems.
Gas Turbines Versus Steam Reliability Analysis for a Warship Propulsion Plant
Authors: Benn D. H.
Published: April 2015

Methods of mathematical analysis are reviewed for defining and numerically computing the reliability of warship propulsion systems. Experimental analysis is made of a twin-screw all-gas-turbine plant design for a small warship and the results are compared with computed figures previously published for a geared-steam-turbine plant. It is apparent that relatively simple arrangement of components in subsystems is an inherent advantage of the gas turbine plant from the reliability standpoint and that this type of plant has a potential for high reliability. The analysis was made possible by the availability of component MTBF figures taken from past experience. It is hoped that this will encourage users of marine propulsion equipment to compile and present additional reliability statistics and possibly complete reliability analyses of propulsion plants currently in service.
Aircraft Fire Protection Developments by the Federal Aviation Administration (1940–1970)
Authors: Hansberry H. L.
Published: April 2015

Aircraft fire protection studies conducted by CAA/FAA from the DC-3 problems of 1940 to the most recent studies of the Boeing 720 and the Lockheed Jetstar are reviewed. The reasons for the changing emphasis from concern over powerplant fires in flight to concern over post-crash fires are discussed. Current studies of controlled flammability fuels, development of protection against burner-can burn-throughs, identification of interior materials of increased fire resistance and development of improved methods of crash firefighting are outlined.
Power Recovery From Gas Turbines: A Review of the Limitations, and an Evaluation of the Use of “Organic” Working Fluids
Authors: Luchter Stephen
Published: April 2015

Gas-turbine waste heat appears to be a valuable source of energy, yet the number of installations in which this energy is utilized is minimal. The reasons for this are reviewed and a typical nonafterburning cycle is examined for both steam and an “organic” working fluid. The power level range over which each is attractive is obtained, and the costs of each are compared on a relative basis.
Concept and Design of a 25,000-HP Heavy Duty Marine Gas Turbine
Authors: Junge R. M.
Published: April 2015

This paper reviews the design of a new two-shaft marine gas turbine that will be available in 1971. The engine can be supplied with continuous duty ratings of either 21,600 or 27,800 hp, firing residual oil. The rating duality is obtained by having two different compressors available.
Governor Control System for the TurboTrain
Authors: Long L. O.
Published: April 2015

The TurboTrain is an exciting venture introduced recently to the rail industry. Due to its unique configuration and unprecedented features, its background is outlined to underscore highlights of this revolutionary innovation to transportation. This is helpful to appreciate why the electric governing control system was devised for this application and why the proportional actuator was chosen. Equal distribution of traction load among the multiturbines at both ends of the train is effected and the switching of the auxiliary electric power unit at either end is facilitated. After the primary and secondary functions of the control system are outlined, the proportional actuator is then described and analyzed, followed by a detailed description and analysis of the electric governor control system.
The Use of Fire Tunnel Test Techniques in the Design of Concorde Powerplant
Authors: Talbot J. E. , Slater A.
Published: April 2015

In the very early design phases of Concorde Powerplant it was realized that the high airflows passing through the engine bay would pose significant problems in terms of the precautions necessary to withstand and extinguish fires within the powerplant. A better understanding of the conditions existing in the bay during fires would produce a rational approach to the problem for both the designer and the certifying authority. In order to obtain extensive coverage of all flight conditions it was necessary to depart from current practice and to construct a simulation of the engine and its environment thereby allowing a large number of tests to be carried out. Using this rig it has been possible, not only to prove the means of detection and extinguishing throughout the flight plan, but to obtain a considerable amount of generalized data for use in component design specifications.
Thermal Anisotropic Behavior in Graphite-Epoxy Composites
Authors: Winters W. E.
Published: April 2015

Preliminary evaluation of high modulus graphite fiber-resin composites in gas turbine engine hardware has revealed a high degree of residual stresses in such materials. These residual stresses are caused by the mismatch in thermal expansion of the reinforcement and the resin. An analysis indicates that the amount of residual stress can be closely related to the design of the composite construction as well as materials selection and processing. A model was designed for qualitatively evaluating the variables affecting the residual stresses. Several epoxy resin systems were evaluated and characterized for their ability to produce defect-free composites. It was found that resin shrinkage and resin-fiber bonding (transverse tensile strength) are contributors. Recognizing composite residual stresses, an intelligent approach can be taken to composite hardware design.
On the Theory of the Brayton Cycles
Authors: Gašparović N.
Published: April 2015

In the literature of the theory of gas turbine cycles certain views are expressed, which on critical examination can be shown to be incorrect. In particular with cycles incorporating intercooling or reheat the influence of the proportioning of the pressure ratios of the turbo-machines on the cycle efficiency and the specific work is frequently overlooked. Further questions relate to the definition of the performance of the heat exchanger in the Brayton cycle. The heat exchanger is usually defined by its effectiveness. However, it will be shown that effectiveness is not a satisfactory criterion of performance. This is particularly the case when changes in other cycle parameters or comparisons between different types of cycles (i.e., simple cycle with intercooled cycle) have to be evaluated. A better criterion is proposed in a parameter which is dependent upon the surface area of the heat exchanger.
Large Combined Cycles for Utilities
Authors: Hubert F. W. L. , Meima H. J. , Timmermans A. R. J.
Published: April 2015

Together with rapid development of the gas turbine technology a number of combined cycle arrangements have been proposed in literature. Characteristics of such installations are different from those of the installations normally used for similar application. The purpose of this paper is to determine how these characteristics compare in the case of a large utility power plant for a Municipal Electric Power Authority in the Netherlands. Factors as plant efficiency, fuel cost, investment and capital interest may differ from case to case and have to be reconsidered taking into account site location and economic factors.
Conventional and Nuclear Gas Turbines for Combined Power and Heat Production
Authors: Taygun Fikret , Frutschi H. U.
Published: April 2015

This paper mentions plants which have shown fundamental similarity of air and helium closed cycles. Existing air cycles have a proven economic performance record as total energy plants. They provide a basis for the development of the closed cycle gas turbine towards helium cycles of larger outputs. Plants of 50, 100, 500, to 1000 MW will make use of atomic energy in a direct cycle.
New Fuel for Naval Gas Turbine Engines
Authors: Carlton G. A.
Published: April 2015

This paper discussed the introduction of a new fuel into the Navy, the impact of this new fuel on gas turbine engines and means being taken by the Navy to evaluate this impact. Test methods and techniques for synthesizing some of the fuel characteristics and a comparison of current U.S. Navy fuel oils are presented.
A Marine Nuclear Power Plant Design Utilizing the Direct Brayton Cycles
Authors: Gathy Bruce S.
Published: April 2015

In this conceptual design the direct Brayton cycle is combined with a nuclear heat source and a waste-heat boiler to provide total power for a passenger ship. A steam power plant of an existing ship is replaced by a closed helium cycle. The cycle is developed and machinery components are selected based upon current manufacturing technology. Machinery, weight, volume, cost and plant efficiency are compared. This study showed that the direct Brayton cycle produced the same power at a lower weight and volume, at a higher cost and at a higher efficiency than the comparable steam plant.
Experience With Development Work and Manufacture of 100 MW Gas Turbine Plant at LMZ
Authors: Chervishev P. S. , Polischuk V. L. , Tatiankin A. P. , Fiveisky V. U.
Published: April 2015

The authors discuss initiation of gas-turbine building at the LMZ plant, noting the improvements in fuel and increases in gas-turbine sizes resulting from the cooperation of different production plants and research centers. The cooperative effort led eventually to the largest gas turbine (GT-100-750 sized at 100,000 kw) built at LMZ, manufactured and rig tested in 1967. Design features of the huge unit’s main parts are described, as is the manufacturing experience.
History of the Development of Light Weight Lift Jets
Authors: Bland M. J.
Published: April 2015

The growing interest in V/STOL aircraft will increase the pressure for efficient powerplants including lift jets and lift fans. The paper describes the progress that has been made in the development of lift jet engines and their design philosophy. Some of the problems encountered in the development of the RB 162 are discussed.
Governing and Monitoring of Gas Turbine Engine for Helicopters
Authors: Grandcoing J.
Published: April 2015

Pilots of modern aircraft have had to be provided with minimal operations in engine handling and controlling in order to devote themselves mainly to aircraft handling. Helicopter design has increasingly used the turbine engine governing system not only to control engine operation, but also to maintain a constant rotor speed, to pre-set the maximum power available in case of need, and to protect the rotating assemblies against overspeeding. This paper reviews the general requirements to be met by the helicopter engine governor system in multi- and single-engined craft with turbo-shaft or free-turbine engines (with the engine governor in the free-turbine model either controlled by the rotor speed governor or used to control rotor speed. Since the governor system has come to be considered an essential component of the helicopter and no longer as an engine component, the system must participate in general operation of the helicopter, allowing maximum performance over the entire flight envelope while requiring only minimal action and monitoring by the pilot.
Megawatts on Wheels
Authors: Thompson C. E. , Boland C. R. , Bernstein E.
Published: April 2015

The authors’ company has recently delivered three 17,000-kw mobile generating stations to American Electric Power Company. This paper describes the major activities, design criteria, design tradeoffs and tests which led to the development of these van-sized vehicles which are capable of travelling at speeds of 60 mph and made operational at a site in less than two hours after arrival.
Automatic Start-Up and Operation of Power Generating Plants With a Combined Gas-Steam Cycle
Authors: Aeberli W. A. , Darimont A. H.
Published: April 2015

This paper concerns two power stations using a combined thermal cycle where the heat of the exhaust gases is recovered in a boiler which delivers superheated steam to a steam turbine. After a description of the start-up process, it deals with a few typical problems which had to be solved in working out the automatic and semi-automatic control systems. It also describes auxiliary elements such as the control panel and the supervisory system. The choice between automatic and semi-automatic plants is discussed.
“Tag” Experience on Life Time of GT Hot Parts
Authors: Wagenbach F. , Keller B.
Published: April 2015

This article gives a short summary of the experience gained, on the life of gas turbine hot parts, by the authors’ two partner companies, Brown, Boveri and Sulzer. The subject will be discussed from the point of view of both operating experience and manufacturing methods for the particular components.
Worldwide Status of the Marine Gas Turbine: 1970
Authors: de Biasi Victor , Sawyer J. W.
Published: April 2015

Reviews the world trends since 1966 in the application of gas turbines on both naval and merchant ships. States that the total horsepower increased from 1.9 to 5.8 million in a four-year period, with some 5.5 million horsepower in propulsion. Indicates a definite growth in commercial use from 100,000 to 390,000 hp. Attributes the significant gain in total power due primarily to the availability of proven engines, that are competitive with other prime movers, in the 20,000 hp and above size. Predicts significant increase in use of the marine gas turbine for naval as well as merchant ships when the overall ship, its utilization and supporting shore facilities are considered jointly.
Optimization of Performances of Gas Turbines With Centrifugal Compressors for Pipelines
Authors: Revzin B. S.
Published: April 2015

Some problems arising from the development of gas pumping units including gas turbines and centrifugal compressors, and particularly problems resulting from the tendency of increasing the pipeline diameters and gas pressure are considered. An operating experience with gas turbines GT-6-750 installed at the natural gas transmission lines is described.
Material and Fabrication Development and Application Studies of Aluminum-Boron-Stainless Steel Composites
Authors: Christian J. L.
Published: April 2015

The recent development of a new composite material with superior properties for structural applications is described. The development consisted of selection of matrix and filament materials, the fabrication of a number of composite panels qualification testing, evaluation of secondary fabrication methods and design application studies. It was demonstrated that the new composite material, aluminum-boron-stainless steel (A1-B-SS), could be made in various forms, shapes and sizes, that it possessed very desirable mechanical and physical properties, and that it could be satisfactorily cut, machined, formed and joined by a variety of methods. The potential weight savings (typically 30–45 percent) and other attractive properties make the A1-B-SS composite particularly promising for a number of structural applications.
Surface Studies in Tribological Research and Failure Investigation
Authors: Scott D.
Published: April 2015

Progress in wear prevention can be aided by a better understanding of the mechanisms of surface failure. Changes in topography, chemical nature and physical properties of surfaces subjected to sliding, rolling, abrasion, corrosion, deformation and repeated stressing have been studied. Optical and electron microscopy and electron probe micro-analysis have been used to obtain information for the elucidation of failure mechanisms and their controlling factors. The paper reviews some of this work which has been carried out in recent years in NEL mainly from the technological point of view.
Maintenance of Marine Gas Turbine Engines
Authors: Siemietkowski J. S.
Published: April 2015

Marine gas turbines have been in the U.S. Navy since 1951. At present there are approximately 386 engines including both main propulsion and electric power generation in all types of craft. The maintenance of those engines is performed under a three-level concept, those being organizational, intermediate, overhaul. (Depot.) The lack of a large-scale commitment of gas turbines to the Fleet until mid-year 1969, prevented the establishment of a comprehensive maintenance program. For that reason, manufacturers recommendations rather than firm operating experience, are initially dictating the level of maintenance to be performed at specified intervals.
Bid Boland Compressor Station: IGAT
Authors: Polloway Ed
Published: April 2015

This paper outlines the design basis of a key gas compressor station of the IGAT system in Iran. The factors affecting the selection of the prime mover and compressor are presented, and the control philosophy for their operation is discussed. The effect on compressor station operation during upset conditions at an adjacent gas treatment plant, and vice versa, are also considered.
A Rational Determination of Permitted Usable Lives for Gas Turbine Engine Components
Authors: Salt T. L.
Published: April 2015

The specification of permitted usable lives, or as they are frequently called “life limits,” is an F.A.A. requirement for critical aviation gas turbine rotating components in commercial use (1). To establish these life limits in a consistent conservative manner, a statistical analysis is necessary to assimilate the many variables involved. The most important parameters are the expected component deterioration with use, the characteristics of this use and the chosen overhaul times and maintenance procedures. Considerable effort has been expended in the aircraft engine industry to obtain better recordings of actual engine operation and environment. A paper by Hohenburg (2) which was principally concerned with such monitoring devices did, however, state “Users of engines must make decisions on when to perform maintenance, to overhaul, or to retire engines from service …. There is a substantial requirement for rational determination of maintenance and retirement intervals.” This paper demonstrates such a rational approach in the form of computer program SMILE (Statistical, Maintenance, Inspection and Life Evaluation). It compares, on the basis of estimated risk, alternative choices of life limits by including all the principal parameters involved. An example makes a comparison of a component with early crack initiation and substantial propagation before failure with an alternative design having late crack initiation but virtually infinitely fast propagation. It shows how a life limit may be considered redundant but necessary in the first case and essential in the second. The alternative risks with specified permitted usable lives will be estimated for each design.
A New 4500-HP Gas Turbine for Pipeline Industrial Service
Authors: Oliver R. R. , Fraschetti F.
Published: April 2015

This paper describes the performance and mechanical design of a 4500-hp, two shaft heavy duty simple or regenerative cycle gas turbine. This machine resulted from an international cooperative effort of the joint authors’ respective companies. Initially planned for gas pipelines and process applications, a line of load compressors has been integrated into the single package design. Options include indoor or outdoor models and geared or direct mechanical output for applications not served by the integral compressor models. A variable area load turbine nozzle assures maximum efficiency over a wide range of load, speed, and amibient conditions.
Engine Rotor Matching for Tip Propulsion of Large Helicopters
Authors: Amer K. B. , Sullivan R. J.
Published: April 2015

This paper presents the results of engine/rotor matching studies for a pressure-jet tip-propulsion system for a large helicopter. When matching engine/airplane characteristics, it is standard practice to study the effects of cycle pressure ratio, turbine temperature, and fan bypass ratio. For a helicopter pressure-jet tip-propulsion system, in addition to engine cycle studies a more sophisticated matching analysis must be conducted because of the interacting effects of rotor characteristics (radius, chord, tip speed, airfoil thickness ratio) on propulsive efficiency as well as on weight and aerodynamic efficiency. The results of the study are compared with results for conventional shaft-drive propulsion systems for a short-range heavy-lift helicopter mission.
Gas Turbine Applications in the U.S. Electric Utility Industry
Authors: Lokay H. E. , Seglem C. E.
Published: April 2015

This paper presents the general planning economics and types of applications for the gas (combustion) turbine generating plants in the U.S. electric utility industry. A typical generation planning study indicates 10 to 20 percent of new generation additions can economically be peaking type units. General observations of gas turbine operating requirements and practices are presented for existing gas turbine applications.
Long-Time Operating Experiences With Oberhausen Closed-Cycle Gas-Turbine Plant
Authors: Deuster Gerhard
Published: April 2015

Calculations made prior to building the Oberhausen closed-cycle gas-turbine plant have been fully confirmed after nine years of operation. Operating experiences reviewed are (a) with the air heater, including radiation parts, convection part, brickwork, and double-jacket pipe; (b) with the machine set, including LP and HP compressors, turbine, and gearing; (c) with the heat-exchanging units, including heat exchanger, precooler, and intercoolers; (d) deceleration and acceleration of the machine to/from cold state. Breakdowns and failures referred to were of the sort that can be avoided both safely and cheaply by applying the experience we have now accumulated.
Environment Problems Affecting Helicopter Engine Operation
Authors: Arribat J. C.
Published: April 2015

One of the advantages of the helicopter is to be able to undertake in roles, which for other vehicles would prove to be difficult and even impractical. When performing flying crane duties, rescue flights or military operations, it has to fly very close to the ground or the sea, land on unprepared fields and this, in open country, in the mountains or in the desert. It is, relative to the fixed wing aircraft, what the “Jeep” is to a passenger car, and due to this, it has more acute environment problems than other types of aircraft. The engines, being one of the more vulnerable components, must be protected against the attack of the environment. This subject being very large, it will be limited to three environment problems which are the most important for helicopter engines: salt spray, dust and ice. The solutions — adopted by Sud Aviation, in close collaboration with Turbomeca, for its helicopters — are presented. The case of piston engines, we shall deal with gas turbine engines only.
Design and Development of a 12,500-Hp Gas Turbine
Authors: Austin C.
Published: April 2015

This paper outlines the major design considerations and development experience of a 12,500-hp dual-shaft gas turbine. The unit uses an aircraft derivative gas turbine as the gas generator and is designed to operate in an attended or unattended station without external electrical power above 60 per cent of design speed. Proven power turbine design concepts were combined with the advantages of a variety of highly developed gas generators to produce a reliable machine which could be introduced with a minimum of development time. A special test facility was constructed to subject the unit to a full load test under conditions which simulated field operation.
Design Considerations in Inertia Welding of Turbocharger and Gas Turbine Components
Authors: Weiss C. D. , Moen L. J. , Hallett W. M.
Published: April 2015

This paper begins with a statement of the acceptance and use of inertia welding in the gas turbine field. A short explanation of the inertia welding process follows. Categories of welds discussed are solid inertia butt welds; tubular inertia butt welds; and angular-annular inertia butt welds. An example of the first category is a bimetallic engine valve. The second category is typified by steel shafts joined to superalloy rotors for turbines. The joining of wrought superalloy disks to cast superalloy blade rings to produce a composite wheel comes into the third category. The effect of welding parameters on strength and microstructure, as well as design and process changes required for inertia welding are related. In conclusion, basic considerations for utilization of inertia welding are expressed.
A Turbine-Speed, Main-Engine Fuel Pump
Authors: Johnson H. T.
Published: April 2015

This paper describes the design and experimental evaluation of a vane-type fuel pump that has operated successfully at speeds up to 49,500 rpm and outlet pressures up to 900 psig. The objective of the research was to produce a main-engine fuel pump for small gas-turbine engines capable of operating at engine shaft speed in order to reduce the bulk and complexity of the required gear drive train. The pump has a design JP-4 turbine-fuel flow rate of 2000 lb/hr at 650 psig. The successful completion of a 200-hr endurance run has verified that the high-speed capabilities have been achieved without sacrificing pump endurance life.
Experience With Gas Turbines as Prime Movers for Underground Storage of Natural Gas
Authors: Bonner R. C.
Published: April 2015

Aircraft-type gas turbines have been used by Consumers Power Co. to provide power for the injection of natural gas into underground storage for the past five years. Special controls, auxiliary and driven equipment are required for this unique application. Operating experience has prompted numerous refinements as well as providing information for maintenance and economic planning. The paper describes the basic design of the engine-compressor units for a remotely controlled, unmanned compressor station as well as highlights from the operating experience with this application.
Marine Installation of a Gas Fired Turbine for Cryogenic Gas Processing
Authors: Gee C. F.
Published: April 2015

The development of the cryogenic turbo-expander type plant as applied to natural gas processing for the recovery of ethane and heavier hydrocarbons is traced briefly. Integration of a large gas fired turbine into this process for a marine installation is discussed. Design considerations are outlined and operating experience is reviewed.
Lightning Protection Approaches for Gas Turbine Controls
Authors: Robb J. D.
Published: April 2015

The trend toward electronic controls for turbine engines because of their flexibility in meeting the requirements of the more complex gas turbine operating cycles suggests possible problems in view of the minor electrical malfunctions routinely experienced by jet transport aircraft. High by-pass ratio turbine engines can provide a possible close coupling path for surges into engine control wiring and approaches to alleviate this possible problem are suggested, including component arrangement, shielding approaches, the use of protection devices and thorough surge testing of the developed systems.
Inertia Welded Jet Engine Components
Authors: Stalker K. W. , Jahnke L. P.
Published: April 2015

The fabrication of jet engine rotors by joining simple disk and ring shapes offers both weight and cost advantages; however, the metal joints must have excellent and completely reproducible mechanical properties. Inertia welding achieves this since it is a solid state joining process which forges the two parts together under an automatically controlled situation. The parameters for inertia welding jet engine nickel and titanium alloys are discussed. The cost and weight advantages occurring from elimination of mechanical joints and better material utilization are identified. Several typical applications are described.
A Design Method and the Performance of Two-Dimensional Turbine Cascades for High Subsonic Flow
Authors: Uenishi A.
Published: April 2015

This paper deals with a hodograph method for design of turbine cascades in high subsonic flow and an approximate solution to a gas, specific heat ratio γ = −1 (the Karman-Tsien approximation) and γ > 1 (the gas obeying the adiabatic law). Numerical examples and a comparison of theoretical and measured pressure distribution for profiles designed by this method are given. Further, a better criterion for design to improve cascade efficiency is also presented.
Performance Evaluation of a 2.1-MW Gas Turbine Generator Set Using Computerized Data Acquisition
Authors: Torpey P. J. , Smith W. L.
Published: April 2015

A gas turbine generator set intended for use as an emergency power source has been evaluated and tested using a computer controlled data acquisition and processing system. At 1-sec intervals during startup, transducer devices monitor such items as turbine inlet temperature, compressor discharge pressure and speed. While operating under normal or steady-state conditions, a total of 65 parameters are logged at 5-min intervals. In addition, power, specific fuel consumption and efficiency are calculated every 5 min. Computer output is in engineering units (deg F, psi, cfm, etc.). The computer programming language is structured with Fortran-like arithmetic and formatting capabilities. Analog-to-digital conversion is accomplished by an integrating digital voltmeter and switching via a 200-channel reed relay scanner. Two teletypewriters, a programmable clock, and 64,000 words of disk storage comprise the rest of the major hardware. For this project 4096 words of computer core were implemented. A turbine development program conducted with this computerized data system can be completed by a single appropriately trained individual in approximately half the time required by a team of three or four using conventional data gathering methods.
Liquid Distributions of a Low Pressure Drop Injection System: Gas Turbine “Vaporizer” Design
Authors: Alperi R. W. , Hoffman J. S.
Published: April 2015

Low pressure drop fuel injectors for jet engine combustors are currently being considered. In this respect, the general problem considered in this paper is the flow variables affecting the distribution of a low pressure drop, low velocity stream of liquid which is convected by a concentric airstream against a concave hemispherical cap similar to possible fuel injectors designs (Fig. 1). Experimental results from a plexiglass model of the injection system are presented. The experimental results indicate that for a centrally located liquid stream injector (less than 1/16 in. from the true center), the momentum ratio between the liquid and air streams is the predominant factor which influences uniform fuel distributions. More uniform distributions are obtained with higher liquid-to-air momentum ratios. For larger injector eccentricities, the liquid distributions exhibit variable tendencies depending on the range of the momentum ratio.
A Numerical Technique for the Calculation of Transonic Flows in Turbomachinery Cascades
Authors: Gopalakrishnan S. , Bozzola R.
Published: April 2015

A numerical technique is presented for the calculation of steady inviscid transonic flows in turbomachinery cascades, wherein both subsonic and supersonic regions co-exist. The problem is posed in the time-dependent form and the aysmptotic solution at large times provides the solution of the steady physical problems. The solutions for a hyperbolic nozzle cascade and two turbine cascades are compared with other analytical solutions and with an experimental result. The agreement appears to be very good. Some preliminary results are presented for a flow containing an oblique shock and its reflection. The computed results compare satisfactorily with the exact solution.
A Fluidic Fuel Control Valve for Turbine Engines
Authors: Wilcox R. L. , Shadowen J. H.
Published: April 2015

A fluidic valve, consisting of a swirl chamber with tangential and radial inlets and a single outlet, has been used to provide uniform fuel distribution to the nozzles in an annular combustor designed for a small turbine engine. The fuel nozzles were of the air atomizing type, with large flow passages for contamination tolerance. Pressure drop across the nozzles was too small at low fuel flows to overcome hydraulic heat effects and uniformly distribute the fuel to the nozzles. A fluidic valve installed in series with each nozzle provided sufficient pressure drop to distribute the fuel at low flow rates without requiring exceptionally high fuel pressures at large flow rates. The fluidic valves were fed by a dual man fold fuel system. Fuel flow was divided between the two manifolds, which were connected separately to the tangential and radial inlets of the fluidic valves, by a pressure relief valve. The flow schedule of the system was similar to that of a dual orifice pressure atomizing fuel system. Turn down requirements of the system were 40:1.
Metal Matrix Composite Fabrication Procedures for Gas Turbine Engine Blades
Authors: Alexander J. A. , Parks E. G. , Melnyk P.
Published: April 2015

Metal matrix composites constitute an attractive class of materials which must be considered as serious candidates for application in advanced gas turbine engines. Materials development programs have been successful in fabricating and characterizing metallic composite materials. Demonstration programs have shown that aerospace structural components can be fabricated from them. This paper deals with the application of the diffusion bonding process to the formation of a complex shape such as a gas turbine engine fan blade from titanium or aluminum matrix composites. It deals with the route to volume producibility rather than with the documentation of progress to date.
Operating Concept for a 240-MW Combined Cycle Intermediate Peaking Plant
Authors: Berman P. A.
Published: April 2015

This paper describes the design of a combined cycle power plant for intermediate peaking with particular reference to design features resulting in simplified control and operation.
A Fuel for Total Energy
Authors: Tintori J. , Schiefer R. B. , Taylor J. R.
Published: April 2015

With increasing international competition and the formation of the common market, a large chemical company producing chlorine and soda decided that it was imperative to reduce to a minimum the costs of its electricity and steam requirements without loss of reliability of supplies. After several schemes had been carefully costed it was concluded that a total energy scheme using packaged ags turbines, burning an economic oil fuel particularly suitable for high temperature machines should be adopted. The gas turbines exhaust through natural circulation heat recovery boilers to produce sufficient steam to meet all the process requirements. This paper reviews the uses of gas turbines in total energy systems, describes the actual fuel adopted, and gives a comprehensive description of the particular plant installed. Some notes on the plant performance up to the time of the submission of the paper are also included.
Reduction of Nitrogen Oxides From Gas Turbines by Steam Injection
Authors: Dibelius N. R. , Hilt M. B. , Johnson R. H.
Published: April 2015

This paper describes the results of tests to determine the effects of steam injection on the production of nitric oxide in gas turbine combustors. When the steam injected into the compressor discharge was 2 percent of the total air flow, the oxides of nitrogen were reduced to 50 percent of what they were with no steam injection for a given load in a gas fired machine. When the steam flow was increased to 4 percent the oxides of nitrogen dropped to 25 percent of the value with no steam.
Thrust Bearings for Power Gas Turbines
Authors: Leopard A. J.
Published: April 2015

The design requirements of thrust bearings for power gas turbines are discussed with reference to designs which have given satisfactory service. The shortcomings of these designs are analyzed both from the point of view of efficiency and that of service experience. The development of a new system of lubrication designed to overcome these shortcomings is outlined. It is shown that this system, when applied to tilting pad thrust bearings in power turbines, can result in a simpler bearing assembly with increased load capacity and substantially ower power losses.
A New Method for the Calculations of Blade Loadings in a Radial Flow Compressor
Authors: Boyce M. P. , Bale Y. S.
Published: April 2015

The paper outlines a quasi-three-dimensional approach based on the solution of the entire inviscid momentum and energy equations in the meridional and blade-to-blade plane to calculate the blade loading in a radial flow turbomachine. The method is outlined in detail so as to enable the reader to adapt it for use on his computer. The flow in the compressor is considered to be nonhomentropic with variations of thermodynamic properties at the inlet. A comparison of various inlet distributions is shown and this illustrates the usefulness of this method. Calculation of the velocity on the trailing and driving faces of the blades is obtained. Pressure and temperature distribution throughout the flow passage considering an actual process is also outlined.
Sensor for the Control of Vehicular Gas Turbine Combustors
Authors: Lynn W. R.
Published: April 2015

The unique control problems associated with vehicular gas turbine engines are forcing the requirement for more direct measurement and control of vehicular gas turbine operating parameters. Two of the most important parameters are gas generator turbine inlet temperature and engine flameout. The major problem controlling these parameters has always been the lack of low cost sensors with sufficient accuracy and response for closed loop control along with the life required for economical operation. Two sensors have been developed which have the necessary response and accuracy for application to vehicular gas turbine controls. These sensors are also rugged and reliable and will provide the required long life. A fluidic temperature sensor measures turbine inlet temperature and an ultraviolet radiation sensor detects the presence of flame. Both sensors have electronic outputs and are readily adaptable to present electronic control systems. The principle of operation, accuracy and response data, along with application and installation information is presented for both sensors.
The Two-Shaft Industrial Gas Turbine Goes to Sea — Again
Authors: Loft Arne
Published: April 2015

This paper gives a brief summary of the experience of the first industrial gas turbine ship, the John Sergeant, then enumerates the basic characteristics of the heavy duty gas turbine and the philosophy employed in the design. The unique features of the second-stage variable area turbine nozzle, its effects on performance, and particularly the flexible control it affords in conjunction with the controllable and reversible pitch propeller, are discussed. The philosophy of design of the solid state control, protection and sequential systems are outlined, as are the experiences to date with a number of industrial gas turbines of the two-shaft, off-shore and heavy fuel varieties. It concludes by discussing some of the considerations for burning residual fuel and boil-off from liquefied natural gas.
Low Cost Short Life Gas Turbine Design
Authors: Murray D. L. , Kidd W. E.
Published: April 2015

Results of low cost gas turbine engine design studies are presented. System requirements are discussed and their effects on engine design and cost are analyzed. Parametric performance data are presented and the use of these data in engine build cost trades is discussed. The evolution of specific component fabrication techniques on selected components is discussed, and the overall effect on the engine cost is analyzed and described. The technique of achieving low manufacturing costs by the use of innovative design, keyed to operational requirements rather than new processes, is described. The accessory problem is discussed and a potentially low cost fuel control concept described. A cross section drawing of a simple production turbojet is shown and the use of a technique for low cost design is outlined.
An Experimental Study of Coolant Combustion Effects in Transpiration Cooling
Authors: Jenczmionka J. P. C. , Gorton R. L.
Published: April 2015

Hydrogen, ammonia, and nitrogen coolants were used in a study of combustion effects on transpiration cooling. It was found that hydrogen combustion at low coolant blowing rates resulted in increased porous surface temperatures. However, at higher blowing rates (F > 0.002), hydrogen was more effective in surface temperature reduction than the other coolants. It is demonstrated that assumption of temperature equality of coolant and wall leads to erroneous results in heat transfer determination.
A Dynamic Model of Gas Turbine Engine Main Combustor Instability
Authors: Ehrich F. F.
Published: April 2015

The subject of main engine combustor stability is viewed from the perspective of two interacting dynamic chambers — on the one hand, the premixing or vaporizing chamber which supplies fuel ladened air to a second chamber where combustion takes place. The system is modeled with each of the two chambers as a Helmholz resonator each with an orifice to a constant reference pressure, and with a third orifice interconnecting the two subsystems. Futhermore, it is hypothesized that a dynamic heat release is possible which is proportional to the velocity of the fuel ladened air exiting from the premixing chamber into the combustion chamber. On the basis of this model, a stability criterion is derived which gives the critical combustor temperature ratio as a function of geometry of the combustor — the two-chamber volumes and the effective perimeters and areas of the orifices. Additionally, the frequency of oscillation of the unstable system is derived as a function of these same parameters. The analytic result suggests that the most potent configuration detail that can be manipulated to eliminate or avoid instability is ratio of the natural frequency of the premixing chamber of the natural frequency of the combustion chamber (as computed with the passage between the premixing chamber and the combustion chamber blocked). If this ratio can be maintained above unity, stability is assured.
Holographic Characterization of Aerospace Components
Authors: Erf R. K. , Waters J. P.
Published: April 2015

Holography, by virtue of its three-dimensional recording characteristic, offers a process for performing interferometry on nonplanar, diffusely reflecting objects. As such, it has found application in many areas. Furthermore, the use of pulsed laser techniques provides a method for studying dynamic, nonrecurring three-dimensional events, with or without the interferometric feature. More importantly, the pulsed holographic capability eliminates environmental vibration problems, often encountered in holography, thereby permitting its use in hostile, field situations whether the subject be static or dynamic. A holographic study program to examine possible applications of both the CW and pulsed laser methods has been in progress at United Aircraft Research Laboratories for several years. More recent investigations in this area are summarized with the intent of describing the several tools which have been developed and are now available for studying the various problems confronting the aerospace industry. Several examples will be described. Investigations at UARL in this particular area have included examination of various PT-6, JT-9D, and JT-8D components, as well as more general studies of fuel nozzle spray characteristics, aerospace materials bond inspection, and rotor flow visualization studies.
Lift Jet Engine, JR100
Authors: Matsuki Masakatsu , Torisaki Tadao , Imai Kaneichiro , Miyazawa Kiyoto
Published: April 2015

As part of the program for developing VTOL craft, the National Aerospace Laboratory (NAL) of the Japanese Government installed two JR100 lift jet engines on their Flying Test Bed, following upon the successful outcome of tests on the Height Control Tower with other JR100 engines. These JR100 engines were developed in a joint effort between NAL and IHI. Five engines in three successively modified version have been produced, and the aggregate number of runs has already reached 1700, recording accumulated operating time of more than 200 hrs. The engine which has a 6-stage compressor, an annular combuster and a single-stage turbine, produces 3350 lb thrust and weighs 340 lb.
Gas Turbine and Steam Turbine Combined Generating Plants in Japan
Authors: Ujita Sooji , Hirai Harumi
Published: April 2015

In these days, there has been a progressive increase in the application of gas turbines to the industrial field in Japan. Based on favorable reliability, the increasing demands of electric power have created the high capacity of gas and steam turbine combined plants.
Reverse Reduction Marine Drives for High Powered Gas Turbines
Authors: Phinney J. M.
Published: April 2015

Recent requirements for marine propulsion gearing have dictated the analysis of and designs for reversing reduction drives with very high power levels, utilizing aricraft type gas turbines as prime movers. Service in either high-speed cargo vessels or ships operating in icebound waters is contemplated. Individual design features of the drive assemblies as well as methods of control and response to transient conditions is explored.
Meeting Europe’s Low Noise Requirements for Compressor Stations
Authors: Grettum R. S.
Published: April 2015

Conditions peculiar to Europe have resulted in stringent noise level requirements being placed on industrial facilities where these facilities are located outside of industrial areas. Compressor stations, for example, are being constructed to conform to very severe noise limitations. Commonwealth Associates has participated in the design and installation of compressor stations in The Netherlands, and England. This paper describes the noise limitations imposed in these countries and the methods used to achieve these limitations.