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US 2014/0212270 A1Published application
Gas turbine engine component having suction side cutback opening
AssigneeUnited Technologies Corporation
InventorBrandon W. Spangler
Life of this patent
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Abstract
An airfoil for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a pressure side wall and a suction side wall spaced apart from the pressure side wall and each extending between a leading edge portion and a trailing edge portion. A plurality of cutback openings are spaced along a radial axis of the suction side wall.
Claims20
An airfoil for a gas turbine engine, comprising:
- a pressure side wall and a suction side wall spaced apart from said pressure side wall and each extending between a leading edge portion and a trailing edge portion;
- and
- a plurality of cutback openings that are spaced along a radial axis of said suction side wall.
A component for a gas turbine engine, comprising:
- a body portion that includes a pressure side wall and a suction side wall spaced apart from said pressure side wall;
- and
- a plurality of cutback openings that are spaced along a radial axis of said suction side wall.
A gas turbine engine, comprising:
- a compressor section;
- a combustor section in fluid communication with said compressor section;
- a turbine section in fluid communication said combustor section;
- a first component disposed in at least one of said compressor section and said turbine section, wherein said first component includes a body portion having a pressure side wall and a suction side wall spaced apart from said pressure side wall and that each extend between a leading edge portion and a trailing edge portion;
- and
- a plurality of cutback openings that are spaced along a radial axis of said suction side wall.
3 more elements
Dependencies are inferred from the claim text.