An experimental investigation of endwall profiling in a turbine vane cascadeMeasurements of surface static pressures, flow total pressure loss, and exit air angle were obtained for two linear cascades to establish the effects of endwall profiling. Testing was conducted at an isentropic exit Mach number of 0.85. One cascade was fabricated with planar endwalls while the other had one planar and one profiled endwall. Both cascades utilized the same high pressure turbine inlet guide vane section. It was found that in terms of full passage loss the profiled endwall cascade has the superior performance. The secondary loss results obtained are reasonably well predicted by correlations developed from incompressible flow testing of similar configurations. Inviscid flow and boundary layer calculations are compared with the test data, and overall, the agreement is found to be good. Use of the results for design purposes is briefly discussed.
Document ID
19800054734
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kopper, F. C. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Milano, R. (United Technologies Corp. Pratt and Whitney Aircraft Group, East Hartford, Conn., United States)
Vanco, M. (NASA Lewis Research Center Cleveland, Ohio, United States)