Analytical design of an advanced radial turbine
The analytical design of an advanced radial turbine, which is part of an optimum ceramic radial inflow, single-stage turbine system for an advanced automotive gas turbine engine is reported. The turbine study program is based on an advanced gas turbine cycle, 100.67-kW (135-shp) engine for use in a 1588-kg (3500-lb) automobile, with a specific fuel consumption of 0.227 kg/kW-hr (0.373 lb/hp-hr). Utilization of high turbine cycle temperatures of 1370/sup 0/C and ceramic materials are prime features of this study. The program objective was to investigate the effects of tip speed, non-radial rotor blading, inducer-to-exducer work split, and deswirl vanes on the system efficiency and mechanical reliability of a single-stage, ceramic, radial turbine designed to meet the performance requirements of an advanced automotive gas turbine cycle. Analysis results indicate that, based on projected 1983 aerodynamic performance and ceramic material properties, radial blade rotor configurations with a tip speed of 701 m/sec (2300 fps) are feasible and satisfy the goals of 87.0% system efficiency and 0.9999 cumulative probability of success mechanically. As compared with the blade stress complications of nonradial rotor configurations, from aerodynamic, mechanical, and off-design considerations, the radial-blade rotor appears to offer the lowest overall risk and is the optimum configuration considered in this study.
- Research Organization:
- Garrett Turbine Engine Co., Phoenix, AZ (USA)
- DOE Contract Number:
- AI01-77CS51040
- OSTI ID:
- 6540300
- Report Number(s):
- DOE/NASA/0106-1; NASA-CR-165170; GARRETT-31-3653
- Country of Publication:
- United States
- Language:
- English
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AUTOMOBILES
GAS TURBINE ENGINES
DESIGN
PERFORMANCE
TURBINE BLADES
STRESS ANALYSIS
AERODYNAMICS
CERAMICS
THEORETICAL DATA
VERY HIGH TEMPERATURE
DATA
ENGINES
FLUID MECHANICS
HEAT ENGINES
INFORMATION
INTERNAL COMBUSTION ENGINES
MECHANICS
NUMERICAL DATA
VEHICLES
330103* - Internal Combustion Engines- Turbine