Accession Number : AD0689384

Title :   EFFECT OF PRESSURE RATIO ON THE PERFORMANCE OF SUPERSONIC TURBINE-NOZZLES.

Descriptive Note : Summary rept.,

Corporate Author : SUNDSTRAND AVIATION-DENVER COLO

Personal Author(s) : Barber,Robert E.

Report Date : 1967

Pagination or Media Count : 44

Abstract : The object of the study was to obtain information to improve the off-design performance of supersonic turbine nozzles. Results show that contoured nozzles provide the best performance for turbines which operate at near design pressure ratios or at greater-than-design pressure ratios. For operation at pressure ratios below design, the conical or plug types are superior. The free expansion nozzles generally produce inferior performance as compared to the other types. Axial spacing between nozzle and rotor had little effect on off-design performance. This analysis together with limited test data indicates that the gas ratio of specific heats has a strong effect on off-design nozzle performance. The indication is that performance may be greatly reduced when operating with gases with low ratios of specific heat. The design point performance, however, does not appear to be affected. (Author)

Descriptors :   (*GAS TURBINE NOZZLES, PERFORMANCE(ENGINEERING)), (*SUPERSONIC NOZZLES, PERFORMANCE(ENGINEERING)), PRESSURE, DESIGN, SUPERSONIC CHARACTERISTICS, GEOMETRIC FORMS, SPECIFIC HEAT

Subject Categories : Aerodynamics
      Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE