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