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

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

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE