Accession Number:

ADP003090

Title:

Experimental Verification of an Endwall Boundary Layer Prediction Method,

Descriptive Note:

Corporate Author:

AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1983-09-01

Pagination or Media Count:

21.0

Abstract:

An endwall boundary layer code was verified in a low speed compressor facility and used to compute casing blockage and efficiency penalty in a full-scale engine. Detailed endwall boundary layer measurements and overall compressor performance measurements were obtained for various conditions of surface roughness, porosity and tip clearance in the low speed compressor facility. Stage pressure ratio and stall margin were determined for the single-stage compressor at three corrected speeds. Shroud roughness did not markedly reduce overall compressor performance at design conditions, but did result in some loss of stall margin. The shroud endwall boundary layer code exhibited overall satisfactory agreement with solid smoothrough endwall experimental results, but was not as effective for the T56-A-100 experimental results. The code was effective in predicting tip clearance effects. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE