Abstract 1,071,865. Boundary layer control. GENERAL MOTORS CORPORATION. Jan. 27, 1966 [Feb. 24, 1965], No. 3663/66. Heading F2R. An axial flow compressor, wherein the last three stages of compressor blading are shown at 17, 18, 19, discharges into an annular diffuser bounded by walls 2 and 25, the wall 25 diverging sharply from an inner shroud 33. The blading stages are bolted to the flange 21 of shaft 13 and a ring 29, also bolted to flange 21, forms an annular passage 38 within which are housed a ring of stator blades 39 attached to shroud 33 and a ring of rotor blades 41 attached to ring 29. Shroud 33 is spaced at 37 and 43 from blade row 19 and curved transition 30 of wall 25, respectively whereby, in operation, auxiliary compressor 41 draws air through passage 38 to deliver it over transition 30 and cause the boundary layer to adhere to wall 25. The apparatus may be used to cause the boundary layer to adhere to wall 2.
IN COMBINATION, AN AXIAL-FLOW COMPRESSOR HAVING AN OUTLET AND A DIFFUSING PASSAGE EXTENDING DOWNSTREAM FROM THE OUTLET DEFINED BY OUTER AND INNER ANNULAR WALLS, ONE OF SAID WALLS DIVERGING SHARPLY FROM THE AXIAL DIRECTION ADJACENT THE OUTLET; THE COMPRESSOR INCLUDING OUTLET GUIDE VANES HAVING AN ANNULAR SHROUD ADJACENT SAID ONE WALL SEPARATING AN ANNULAR AUXILIARY AIR PASSAGE FROM THE COMPRESSOR OUTLET THE UPSTREAM END OF THE AUXILIARY AIR PASSAGE HAVING AN INLET CONNECTING WITH AND SUPPLIED FROM THE COMPRESSOR ADJACENT THE OUTLET OF THE COMPRESSOR; AND AN ADDITIONAL COMPRESSOR STAGE, INCLUDING A ROTATING BLADE STAGE, DISPOSED IN SAID AUXILIARY AIR PASDISCHARGE PASSAGE DISPOSED TO BLOW A SHEET OF AIR ENERGIZED BY SAID ROTATING BLADE STAGE OVER SAID ONE WALL TO ENERGIZE THE BOUNDARY LAYER THERON.
Claim 2
Dependent Claim
125 words
IN COMBINATION, AN AXIAL-FLOW COMPRESSOR HAVING AN OUTLET AND A DIFFUSING PASSAGE EXTENDING DOWNSTREAM FROM THE OUTLET DEFINED BY OUTER AND INNER ANNULAR WALLS, ONE OF SAID WALLS DIVERGING SHARPLY FROM THE AXIAL DIRECTION ADJACENT THE OUTLET; THE COMPRESSOR INCLUDING OUTLET GUIDE VANES HAVING AN ANNULAR SHROUD ADJACENT SAID ONE WALL SEPARATING AN ANNULAR AUXILIARY AIR PASSAGE FROM THE COMPRESSOR OUTLET THE UPSTREAM END OF THE AUXILIARY AIR PASSAGE HAVING AN INLET CONNECTING WITH AND SUPPLIED FROM THE COMPRESSOR ADJACENT THE OUTLET OF THE COMPRESSOR; AND AN ADDITIONAL COMPRESSOR STAGE, INCLUDING A ROTATING BLADE STAGE, DISPOSED IN SAID AUXILIARY AIR PASDISCHARGE PASSAGE DISPOSED TO BLOW A SHEET OF AIR ENERGIZED BY SAID ROTATING BLADE STAGE OVER SAID ONE WALL TO ENERGIZE THE BOUNDARY LAYER THERON.