Accession Number : AD0774549

Title :   Test of a Supersonic Compressor Cascade with Splitter Vanes.

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 : DEC 1973

Pagination or Media Count : 471

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. A prior investigation with this cascade was conducted without splitter vanes and was reported previously. The principal objective of that program was to obtain cascade-type data for a selected blade element from a compressor configuration resulting from the Aerospace Research Laboratories in-house program of research on supersonic axial compressors. Splitter vanes, designed in a manner similar to those used in the rotor, were incorporated in the supersonic compressor cascade. Additional work was conducted and the primary objective was to obtain cascade-type data for the particular compressor blade-splitter vane combination. (Modified author abstract)

Descriptors :   *Axial flow compressors, *Supersonic airfoils, *Cascade structures, 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