Effects of interstage diffuser flow distortion on the performance of a 15. 41-centimeter tip diameter axial power turbine
The performance of a variable-area stator, axial flow power turbine was determined in a cold-air component research rig for two inlet duct configurations. The two ducts were an interstage diffuser duct and an accelerated-flow inlet duct which produced stator inlet boundary layer flow blockages of 11 percent and 3 percent, respectively. Turbine blade total efficiency at design point was measured to be 5.3 percent greater with the accelerated-flow inlet duct installed due to the reduction in inlet blockage. Blade component measurements show that of this performance improvement, 35 percent occurred in the stator and 65 percent occurred in the rotor. Analysis of inlet duct internal flow using an Axisymmetric Diffuser Duct Code (ADD Code) was in substantial agreement with the test data.
- Research Organization:
- National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center; AVRADCOM Research and Technology Labs., Cleveland, OH (USA)
- DOE Contract Number:
- AI01-77CS51040
- OSTI ID:
- 6317410
- Report Number(s):
- DOE/NASA/51040-46; NASA-TM-83359; CONF-830635-1; ON: DE83011470
- Resource Relation:
- Conference: 19. AIAA-SAE-ASME joint propulsion conference, Seattle, WA, USA, 27 Jun 1983
- Country of Publication:
- United States
- Language:
- English
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