Accession Number : ADA014395

Title :   Experimental Investigation of a Supersonic Compressor Cascade.

Descriptive Note : Final rept. Jul 71-Apr 73,

Corporate Author : GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV

Personal Author(s) : Fleeter,Sanford ; Holtman,Robert L. ; McClure,Robert B. ; Sinnet,George T.

Report Date : JUN 1975

Pagination or Media Count : 336

Abstract : This report describes in detail the experimental investigation of a stationary, linear, supersonic compressor cascade with blades of constant spanwise geometry and constant thickness linear sidewalls. The selected blade element was representative of streamline 19 of an advanced compressor configuration resulting from the Aerospace Research Laboratories axial compressor research program. The investigation covered the range of inlet relative Mach numbers of 1.535 - 1.683 and a range of static pressure ratios of approximately 1.1 - 2.3 and included laser velocimeter measurements of the flow within and around the cascade at the design Mach number.

Descriptors :   *Gas turbines, *Axial flow compressors, *Cascade structures, Supersonic flow, Flow fields, Laser velocimeters, Data reduction, Computer applications

Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE