Methods and systems for gas turbine engine bleed scoops
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...
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Main Authors | , , , , , , , |
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Format | Patent |
Language | English |
Published |
20.02.2003
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Edition | 7 |
Subjects | |
Online Access | Get full text |
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Summary: | 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. |
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Bibliography: | Application Number: US20010932585 |