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.
Claims19
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 which bleeds bypass air from a bypass duct, wherein the cooling air offtake is located in the engine core and having an inlet extending between a leading edge and a trailing edge;
- and
- a louver located at the inlet and having at least two different size airfoils including an initial airfoil. and a primary airfoil in spaced axial arrangement with the initial airfoil located nearer to the leading edge of the inlet than the primary airfoil and the initial airfoil is axially spaced from the leading edge of the inlet;
- wherein the primary airfoil has a primary chord length greater than an initial chord length of the initial airfoil.
A louver assembly in a gas turbine engine located in an offtake which bleeds bypass air from a bypass duct, wherein the louver assembly has an inlet extending between a leading edge and a trailing edge, comprising at least four airfoils in axial arrangement, a first airfoil axially spaced from the leading edge of the inlet, and a primary airfoil axially spaced from the first airfoil, wherein the first airfoil is located nearer to the leading edge of the inlet than the primary airfoil, and the primary airfoil having a. primary chord length greater than a chord length of any of the other airfoils of the at least four airfoils, wherein none of the at least four airfoils are of the same size.
Dependencies are inferred from the claim text.