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US 2010/0247306 A1Published application
Gas turbine engine with 2.5 bleed duct core case section
AssigneeUnited Technologies Corporation
InventorsBrian D. Merry, Gabriel L. Suciu
Life of this patent
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Abstract
A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a structural wall.
Claims13
A core case section for a gas turbine engine comprising:
- a structural wall which at least partially supports a multiple of Fan Exit Guide Vanes;
- and
- a multitude of discreet radial extending 2.5 bleed ducts defined at least in part by said structural wall.
A gas turbine engine comprising:
- a fan case section defined about an engine axis of rotation;
- a core case section defined about said axis of rotation;
- a multiple of fan exit guide vanes mounted to said fan case section and said core case section;
- a structural wall of said core case section which at least partially supports said multiple of Fan Exit Guide Vanes;
- and
- a multitude of discreet radial extending 2.5 bleed ducts defined at least in part by said structural wall.
3 more elements
Dependencies are inferred from the claim text.