Influence of Blade Tip Clearance on Aerodynamically Induced Vibration.
Final rept. 31 Aug 81-30 Sep 82,
GENERAL MOTORS CORP INDIANAPOLIS IN DETROIT DIESEL ALLISON DIV
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An experimental investigation, whose objective was to demonstrate the influence of rotor blade tip clearance effects on the dynamic pressure induced on a downstream vane, was conducted in a large, low speed, single-stage research compressor. The blade tip clearance was 0.48 span. The rig was heavily instrumented with dynamic pressure gages on the vane hub, mean, and tip section suction and pressure surfaces. Author
- Fluid Mechanics
- Jet and Gas Turbine Engines