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The results attest to the effectiveness of this way to control separation in blade cascades by the boundary layer suction and the feasibility of this proposed design concept.
The opportunity of considerable delaying of laminar turbulent transition due to special wing profile geometry and using boundary layer suction and surface cooling has been verified at sub- and supersonic speeds through various wind tunnel testing at TsAGI and during flying laboratory experiments at the Flight Research Institute (LII).
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Experimental results indicate that boundary layer suction can improve the compressor characteristics and the best suction methodology varies along the operating line.
Based on this concept, a single-stage, low-reaction and low-speed axial compressor is constructed in association with analysis and computation of boundary layer suction on vanes with the aid of a three-dimensional numerical approach.
The accuracy of Menter and Langtry's transition model applied for simulating the flow with boundary layer suction is validated.
The characteristic features of the concept are made clear through its comparison with the MIT boundary layer suction compressor.
OGVs are hollow blades with two slots designed on the suction side which can better control the flow on the suction surface through boundary layer suction.
There is introduced a new low-reaction, highly-loaded axial compressor design concept which is coupled with boundary layer suction method.
Around the peak efficiency point, boundary layer suction from the slots of OGVs is the best choice in improving the efficiency, but it causes a 0.1% loss in the total pressure ratio.
A laser tuft method was used to differentiate between boundary layer transition and separation on the suction surface of the blade.
Cross flow from endwall to midspan, mixing of corner boundary layer and the main stream, and reversal flow on the suction surface are caused by corner separation vortex structures.
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