Compressor configuration and design optimization for the high reliability gas turbine. Final report
The purpose of this program has been to develop a preliminary design of a low aspect ratio/high through-flow compressor configuration to be compatible with the Electric Power Research Institute/Department of Energy/Reliable Advanced Liquid Fueled Engine (EPRI-DOE/RALFE) program and to evaluate the design for use in the Reliable Engine. Our objective was to define the benefits of low aspect ratio and high through-flow (HTF) in a large industrial gas turbine in which high reliability and cost-of-electricity (COE) are major design considerations. These benefits have been identified, in aircraft gas turbines, as reduced number of stages, with reduced number of parts, and increased aerodynamic loading capability. The compressor and diffuser preliminary designs have been completed to define size and performance characteristics. The compressor has 9 stages and a predicted adiabatic efficiency of 88.35%. The diffuser selected is a conventional straightwall configuration with an equivalent conical angle of 8-degrees. An alternate diffuser configuration has also been recommended because of its excellent performance potential in high Mach number applications. The HTF compressor configuration appears to offer equivalent COE and reliability as compared to the Baseline Reliable Engine configuration, but at more conservative aerodynamic loading levels.
- Research Organization:
- United Technologies Corp., South Windsor, CT (USA). Power Systems Div.; Pratt and Whitney Aircraft, West Palm Beach, FL (US). Government Products Div.
- Sponsoring Organization:
- USDOE Office of Fossil Energy (FE)
- DOE Contract Number:
- AC03-79ET15425
- OSTI ID:
- 5138501
- Report Number(s):
- DOE/ET/15425--T1; GTR--2136
- Country of Publication:
- United States
- Language:
- English
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