Invention Application
- Patent Title: IMPINGEMENT COOLING ARRANGEMENT FOR AIRFOILS
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Application No.: US16734464Application Date: 2020-01-06
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Publication No.: US20200149409A1Publication Date: 2020-05-14
- Inventor: Jason Shenny , Jeffrey T. Morton , Alberto A. Mateo , San Quach , Gregory Anselmi
- Applicant: United Technologies Corporation
- Main IPC: F01D5/18
- IPC: F01D5/18 ; F04D29/58 ; F04D29/32

Abstract:
An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.
Public/Granted literature
- US11255197B2 Impingement cooling arrangement for airfoils Public/Granted day:2022-02-22
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