- Patent Title: Turbine blades with tip portions having converging cooling holes
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Application No.: US14030647Application Date: 2013-09-18
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Publication No.: US09856739B2Publication Date: 2018-01-02
- Inventor: Loris Bedrosyan , Ardeshir Riahi , Daniel C. Crites
- Applicant: HONEYWELL INTERNATIONAL INC.
- Applicant Address: US NJ Morris Plains
- Assignee: HONEYWELL INTERNATIONAL INC.
- Current Assignee: HONEYWELL INTERNATIONAL INC.
- Current Assignee Address: US NJ Morris Plains
- Agency: Lorenz & Kopf, LLP
- Main IPC: F01D5/20
- IPC: F01D5/20 ; F01D5/18 ; F01D11/10

Abstract:
A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap extending between the suction side wall and the pressure side wall, a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.
Public/Granted literature
- US20150078916A1 TURBINE BLADES WITH TIP PORTIONS HAVING CONVERGING COOLING HOLES Public/Granted day:2015-03-19
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