Accession Number : AD0774454

Title :   Test of Supersonic Compressor Cascade with Splitter Vanes and Vortex Generators on Blades.

Descriptive Note : Final rept. Jul 72-Apr 73,

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

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

Report Date : NOV 1973

Pagination or Media Count : 431

Abstract : The report describes experimental research conducted with a linear, stationary, supersonic compressor cascade with blades of constant spanwise geometry and contoured sidewalls. The cascade incorporated splitter vanes midway between blades in the latter half of each blade passage. The influence of splitter vane orientation was investigated. The investigation covered a range of Mach numbers from 1.40 to 1.50 and a range of static pressure ratios. This report describes work accomplished with vortex generators mounted on the suction surfaces of the blades. (Modified author abstract)

Descriptors :   *Axial flow compressors, *Supersonic airfoils, *Cascade structures, *Vortex generators, Axial flow compressor blades, Guide vanes, Gas turbines, Supersonic flow, Data acquisition, Data processing

Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE