Gas turbine engine bleed scoops

This invention relates generally to gas turbine engines, and more specifically to bleed scoops used in gas turbine engine high-pressure compressors. A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly...

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Bibliographic Details
Main Authors Proctor, Robert, Montgomery, Julius John, Epstein, Michael Jay, Barbe, Roger Owen, Sam, Hai Buu, Ogzewalla, James Bernar, Kemp, Andrew David, Doloresco, Bryan Keith
Format Patent
LanguageEnglish
Published 22.04.2003
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Summary:This invention relates generally to gas turbine engines, and more specifically to bleed scoops used in gas turbine engine high-pressure compressors. 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.