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US 2017/0321602 A1Published application
Gas turbine engine with an offtake
AssigneeGeneral Electric Company
InventorsAntonio GUIJARRO VALENCIA, Vittorio MICHELASSI
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Abstract
An apparatus and method are disclosed for a gas turbine engine including an offtake located within the air flow of the engine. The offtake has an inlet and a louver covering the inlet. The louver has multiple airfoils arranged to direct the air flow into the inlet of the offtake.
Claims20
A gas turbine engine comprising:
- an annular fan exhaust section;
- an engine core at least partially located within the fan exhaust section;
- a cooling air offtake located in the engine core and having an inlet;
- and
- a louver located at the inlet and having at least two different size airfoils in spaced axial arrangement.
2 more elements
A louver assembly for an off take of a gas turbine engine comprising at least four airfoils in axial arrangement, wherein none of the airfoils are of the same size.
Dependencies are inferred from the claim text.