APPLICATION OF BLUNT TRAILING EDGE BLADINGS TO SUPERSONIC COMPRESSOR STAGES.
Final scientific rept., 30 Apr 66-1 May 67,
VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM)
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A review is given of cascade, rotor and stage tests made on blunt trailing edge blades in the high subsonic, the transonic and the supersonic regimes. For what concerns cascade tests, satisfactory high subsonic operation was obtained with turning of the order of 55 degrees. The positive effect of back pressure on the losses was ascertained, as well as the possibility of reducing secondary flow effects by using slots. Reduction of 50 of the losses at mid-span. The rotor tests on a second generation design showed significant improvement on the first model. A peak total pressure ratio of 2.8 with an adiabatic efficiency close to 85 was reached. The stage tests were made to investigate rotor-stator interference, stagger effect and effect of slotting. An optimum rotor-stator distance and stagger are found. The positive effect of slotting the stator blades is confirmed. Author
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