- Patent Title: Gas turbine engine wall assembly with support shell contour regions
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Application No.: US14910964Application Date: 2014-08-29
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Publication No.: US10655855B2Publication Date: 2020-05-19
- Inventor: James P. Bangerter , Kevin J. Low , Russell B. Hanson , Nurhak Erbas-Sen , Frank J. Cunha
- Applicant: United Technologies Corporation
- Applicant Address: US CT Farmington
- Assignee: Raytheon Technologies Corporation
- Current Assignee: Raytheon Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: Getz Balich LLC
- International Application: PCT/US2014/053514 WO 20140829
- International Announcement: WO2015/031816 WO 20150305
- Main IPC: F23R3/00
- IPC: F23R3/00 ; F23R3/60 ; F02C3/14 ; F02C7/12 ; F23R3/06
Abstract:
A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.
Public/Granted literature
- US20160201909A1 GAS TURBINE ENGINE WALL ASSEMBLY WITH SUPPORT SHELL CONTOUR REGIONS Public/Granted day:2016-07-14
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