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

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

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 sp...

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Bibliographic Details
Corporate Author: GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
Other Authors: Holtman, Robert L, McClure, Robert B, Sinnet, George T
Format: Book
Language:English
Published: Ft. Belvoir Defense Technical Information Center NOV 1973
Subjects:
Axial flow compressors
Cascade structures
Fluid Mechanics
Supersonic airfoils
Vortex generators
Axial flow compressor blades
Data acquisition
Data processing
Gas turbines
Guide vanes
Jet and Gas Turbine Engines
Supersonic flow
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Summary: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)
Item Description:See also AD-774 549
This WorldCat-derived record is shareable under Open Data Commons ODC-BY, with attribution to OCLC
Physical Description:431 p
Access:APPROVED FOR PUBLIC RELEASE

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