Accession Number:
AD0756870
Title:
Test of a Supersonic Compressor Cascade. Volume I.
Descriptive Note:
Interim rept. Jul 71-Aug 72,
Corporate Author:
GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
Personal Author(s):
Report Date:
1972-12-01
Pagination or Media Count:
411.0
Abstract:
The report describes in detail the experimental investigation of a stationary, linear, supersonic compressor blade cascade. The cascade incorporated contoured sidewalls to control the change in stream-tube area in the quasi-axial direction. The blades had a constant spanwise geometry. The selected blade element was from a recent compressor configuration resulting from the Aerospace Research Laboratories supersonic axial compressor research program. The investigation covered a range of inlet relative Mach numbers of 1.40 - 1.50 and a range of static pressure ratios of approximately 1.5 - 2.1. Volume I describes the cascade design, instrumentation, data reduction techniques, test results, and correlation of results with design characteristics. Author
Descriptors:
Subject Categories:
- Jet and Gas Turbine Engines