Gas turbine engine bleed scoops
AssigneeGeneral Electric Company
InventorsRobert Proctor, Julius John Montgomery, Michael Jay Epstein, Roger Owen Barbe, Hai Buu Sam, James Bernar Ogzewalla, Andrew David Kemp, Bryan Keith Doloresco
Life of this patent
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Abstract
A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.
Claims13
A compressor for a gas turbine engine, said compressor comprising:
- a casing;
- and
- a stator assembly comprising a plurality of stator vanes, adjacent stator vanes defining a static high pressure region between said vanes, said stator assembly defining at least one bleed scoop extending at least partially through the static high-pressure region adjacent said stator vanes and in flow communication with the gas flowpath and a bleed plenum, each said stator vane comprises a pressure sidewall and a suction sidewall, said bleed scoop comprises an adjacent side, an aft side, and a contoured side, said adjacent side adjacent at least one said stator vane pressure sidewall.
A gas turbine engine comprising a compressor comprising a casing and a stator assembly, said casing extending around said stator assembly, said stator assembly comprising a plurality of stator vanes, and a plurality of bleed scoops, adjacent stator vanes defining a static high-pressure region, said bleed scoops formed at least partially within the high pressure region, each said compressor bleed scoop cross-sectional area is greater than about 0.08 square inches.
Dependencies are inferred from the claim text.