scholarly journals Textron Lycoming AGT1500 Engine: Transitioning for Future Applications

1992 ◽  
Author(s):  
Richard Horan
Keyword(s):  
Gas Turbine ◽  
Modular Design ◽  
Low Cost ◽  
Turbine Engine ◽  
Power Generators ◽  
Automotive Engine ◽  
Marine Propulsion ◽  
Design Characteristics ◽  
Propulsion Unit ◽  
Electrical Generation

The AGT1500 engine was specifically designed as a propulsion unit for U.S. Army main battle tanks. This application required a gas turbine unique in configuration with features, capabilities and attributes different from conventional aircraft gas turbine engines. The engine is a very compact, rugged, modular design with overhead access for maintenance and good part power fuel consumption achieved through a unique compact recuperator. These features, along with a cycle and control system optimized for sea level operation, low smoke and low thermal and noise signature, also provide a low cost gas turbine engine which readily meets requirements for other ground based commercial and military applications. The commercial marine industrial derivative of the AGT1500 is designated the TF15. TF15 applications currently under active consideration and development by Textron Lycoming and potential users include (1) railroad locomotives, (2) stationary continuous duty cogenerative power units, (3) standby emergency and peaking power generators, and (4) natural gas and liquid pumping and (5) marine propulsion and shipboard electrical generation systems. This paper considers the operational and design characteristics for these applications and shows how the AGT1500/TF15 engine will accommodate these requirements with little or no modifications to the basic automotive engine.

Design, Development and Application of Vehicle Gas Turbine Engines

1966 ◽  
Vol 181 (1) ◽  
pp. 149-172
Author(s):  
P. A. Phillips ◽  
Peter Spear
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Low Cost ◽  
Engine Performance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Development ◽  
Turbine Engine ◽  
Wide Range ◽  
Cycle Temperature

After briefly summarizing worldwide automotive gas turbine activity, the paper analyses the power plant requirements of a wide range of vehicle applications in order to formulate the design criteria for acceptable vehicle gas turbines. Ample data are available on the thermodynamic merits of various gas turbine cycles; however, the low cost of its piston engine competitor tends to eliminate all but the simplest cycles from vehicle gas turbine considerations. In order to improve the part load fuel economy, some complexity is inevitable, but this is limited to the addition of a glass ceramic regenerator in the 150 b.h.p. engine which is described in some detail. The alternative further complications necessary to achieve satisfactory vehicle response at various power/weight ratios are examined. Further improvement in engine performance will come by increasing the maximum cycle temperature. This can be achieved at lower cost by the extension of the use of ceramics. The paper is intended to stimulate the design application of the gas turbine engine.

Low Emission Variable Area Combustor for Vehicular Gas Turbines

1973 ◽  
Vol 95 (3) ◽  
pp. 191-198 ◽  
Author(s):  
D. J. White ◽  
P. B. Roberts ◽  
W. A. Compton
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Environmental Protection Agency ◽  
Gas Turbines ◽  
Gas Turbine Engine ◽  
Protection Agency ◽  
Engine Emissions ◽  
Turbine Engine ◽  
Automotive Engine ◽  
Low Emission

In recent years automotive engine emissions have become subject to stringent Federal legislation. The most severe of these regulations pertains to the 1976 Emission Standards as defined by the Advanced Automotive Power Systems (AAPS) Division of the Environmental Protection Agency (EPA). A unique combustor concept has been developed by Solar which has demonstrated the feasibility of meeting these emission requirements. The integrated emissions of a typical regenerative gas turbine engine employing this combustor type were each below one half of the levels specified by the Federal 1976 Standards, when tested over a simulated federal driving cycle. The success of the feasibility tests for this combustor concept has lead to more fundamental studies and the planned development of a prototype combustor for demonstration on the EPA-AAPS baseline gas turbine engine. The prototype combustor for the baseline engine is described together with its variable area port mechanisms, which has been demonstrated as necessary for emission control.

Off-Design Characteristics of Low-Fuel Consumption Gas Turbine Engine for Long-Range UAV

2013 ◽  
Author(s):  
Roberto Andriani ◽  
Umberto Ghezzi ◽  
Antonella Ingenito ◽  
Fausto Gamma ◽  
Antonio Agresta
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Long Range ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Design Characteristics

Blade Erosion in Automotive Gas Turbine Engine

1995 ◽  
Vol 117 (1) ◽  
pp. 213-219 ◽  
Author(s):  
M. Metwally ◽  
W. Tabakoff ◽  
A. Hamed
Keyword(s):  
Gas Turbine ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Particulate Flow ◽  
Particle Impact ◽  
Surface Erosion ◽  
Blade Surface ◽  
Erosion Model ◽  
Turbine Engine ◽  
Automotive Engine

In this work, a study has been conducted to predict blade erosion and surface deterioration of the free power turbine of an automotive gas turbine engine. The blade material erosion model is based on three-dimensional particle trajectory simulations in the three-dimensional turbine flow field. The particle rebound characteristics after surface impacts were determined from experimental measurements of restitution ratios for blade material samples in a particulate flow tunnel. The trajectories provide the spatial distribution of the particle impact parameters over the blade surfaces. A semi-empirical erosion model, derived from erosion tests of material samples at different particulate flow conditions, is used in the prediction of blade surface erosion based on the trajectory impact data. The results are presented for the three-dimensional particle trajectories through the turbine blade passages, the particle impact locations, blade surface erosion pattern, and the associated erosion parameters. These parameters include impact velocity, impact angle, and impact frequency. The data can be used for life prediction and performance deterioration of the automotive engine under investigation.

scholarly journals John Deere Score™ Engines in Marine Applications

1986 ◽  
Author(s):  
William B. Silvestri ◽  
Edward S. Wright
Keyword(s):  
Modular Design ◽  
Combustion Engine ◽  
Combustion Process ◽  
Production Costs ◽  
Turbine Engine ◽  
Stratified Charge ◽  
Rotary Engine ◽  
Service Training ◽  
Marine Applications ◽  
Electrical Generation

The paper gives a basic description of the stratified charge combustion process in the Stratified Charge Omnivorous Rotary Engine - SCORE. The inherent advantages of the Wankel geometry combined with spark ignition of a stratified mixture for a unique combustion cycle are explained with diagrams. The discussion points out why the engine is neither octane or cetane sensitive, making it a truly multifuel (omnivorous) intermittent combustion engine. A brief description of the parts and their function help to explain the inherent compactness of the engine and confirm its simplicity and efficiency. The engine specific size, weight, air flow and fuel flow are compared to an equivalent output turbine engine to place the performance in a familiar context. A most impressive feature of the engine, attractive cost of production, is demonstrated by the modular nature of its design. This feature is amplified by an in-depth description of the “Family of Engines” concept, highlighting the large number of common parts in a family of one to six rotor models. The ability to cover a complete market segment with one geometry is attractive for production costs, service, training and logistics. Modular design also enhances application flexibility. Development programs are underway for a diversity of applications for families of SCORE engines. Each application utilizes the unique characteristics available with this engine and is further justified by the economies realized in volume production. Thus low volume, high power applications (1000kW and up) can realize savings by utilizing the same major parts tooled for higher volume use in smaller engines. Some potential applications are discussed with particular emphasis on marine installations. Specific comparisons with other powerplants for shipboard electrical generation are presented.

scholarly journals Justifications for an All-Radial 1600-HP Gas Turbine Engine

1970 ◽  
Author(s):  
R. J. Mowill
Keyword(s):  
Gas Turbine ◽  
Low Cost ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Engine Development

The philosophy and justifications behind a large all-radial single-shaft gas turbine engine development are discussed. In addition, some of the factors affecting the marketing of a simple and low cost engine are dealt with.

Closed Gas Turbine Engines for Future Marine Propulsion

1976 ◽  
Vol 13 (03) ◽  
pp. 309-314
Author(s):  
F. Critelli ◽  
A. Pietsch ◽  
N. Spicer
Keyword(s):  
Gas Turbine ◽  
New Technology ◽  
Operating Cost ◽  
Advanced Technology ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Closed Cycle ◽  
Turbine Engine ◽  
Excellent Opportunity ◽  
Marine Propulsion

The Maritime Administration, in its pursuit of improved economics and advanced technology, initiated a study which would evaluate new marine powerplants. It became quite apparent for several sound technical reasons that the closed-cycle gas turbine engine afforded an excellent opportunity for achievement of Mar-Ad's goal. This paper addresses the new-technology engine as applied to maritime ships, illustrating the advantages to shipowners and operators. Efficiency, multifuel capability, installation flexibility, reduction in ship's manning, as well as the overall reduced operating cost are highlighted in this paper.

scholarly journals Low Cost Short Life Gas Turbine Design

1971 ◽  
Author(s):  
D. L. Murray ◽  
W. E. Kidd
Keyword(s):  
Gas Turbine ◽  
Low Cost ◽  
Innovative Design ◽  
Design Studies ◽  
Turbine Engine ◽  
Engine Design ◽  
Control Concept ◽  
System Requirements ◽  
Turbine Design ◽  
Accessory Problem

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.

Experimental Inlet Air Cooling of a 75 kW Gas Turbine

2004 ◽  
Author(s):  
Andrew Banta
Keyword(s):  
Gas Turbine ◽  
Low Cost ◽  
Ambient Air ◽  
Air Cooling ◽  
Turbine Engine ◽  
Small Water ◽  
Discharge Temperature ◽  
Absorption Cooling ◽  
Water Sprays ◽  
Compressor Inlet

An experimental study of gas turbine inlet air cooling was conducted in the Cogeneration Laboratory at California State University, Sacramento (CSUS). The cooling was done using both water sprays and air cooled by an absorption chiller. The primary objectives were to determine the effectiveness of inlet air cooling on a very small gas turbine and compare using water sprays with absorption cooled air. Secondary objectives were to investigate the use of low cost water spray equipment which is typically used in green houses, and the cost effectiveness of absorption cooling with a small turbine. The very small quantities of water, less than 0.006 L/s (0.1 gpm), required to saturate the turbine air flow was difficult to meter. With the low cost spray equipment employed, the only way to accomplish full saturation was to over saturate the air. The gas turbine engine did not respond well to this situation. The lower density of the inlet air caused unstable operation of the compressor resulting in reduced compressor efficiency. With about 2/3 of the turbine work going to the compressor, this loss in efficiency caused the electricity generated to be limited to about half the rated 75 kW. Concerns about damage to the engine caused early termination of these tests. The experiments using air cooled by absorption chilling were more successful but encountered some of the same difficulties. Again, the high humidity and lower density of the inlet air appeared to cause some instability in the compressor. Control of the air temperature proved to be difficult; thus the compressor inlet air was at the chiller discharge temperature, approximately 13 C (55 F). With this arrangement it was possible to operate the engine at full rated capacity which is substantially higher than the 60% fo full load possible with ambient air at approximately 32 C (90 F). In the case of this particular engine, it was concluded that the use of water sprays was not practical and in fact may cause damage. The difficulties of metering very small water quantities would be encountered with any similar size engine. The use of absorption cooling did improve performance but this is a costly solution. The economics of inlet cooling of micro-turbines is very questionable.

scholarly journals A New Small Power Output Gas Turbine Concept

1974 ◽  
Author(s):  
Max Berchtold ◽  
T. W. Lutz
Keyword(s):  
Steady Flow ◽  
Gas Turbine ◽  
Thermodynamic Parameters ◽  
Power Output ◽  
Low Cost ◽  
High Quality ◽  
Small Power ◽  
Turbine Engine ◽  
The One ◽  
Engine Components

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.

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