Investigation of a High-Through Flow, Single-Stage Axial-Flow Compressor with Tip Clearance Increased o.010 Inch and Casing Vortex Generator Configuration 'C' (Configuration 2C).
Interim rept. 1 Mar 76-1 Jul 77
AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH
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Complete experimental results are presented from tests of an axial compressor with casing vortex generators. The design objectives were for a flow per unit frontal area of 39.7 lbsecsq ft, a total pressure ratio of 1.912 and a tip speed of 1500 ftsec. These experimental results were achieved with one of a series of minor parametric modifications to the baseline compressor stage. No conclusions concerning the effects of these modifications will be drawn until the complete series of tests has been reported. Author
- Jet and Gas Turbine Engines