Invention Grant
- Patent Title: Co-swirl orientation of combustor effusion passages for gas turbine engine combustor
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Application No.: US15037484Application Date: 2014-12-03
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Publication No.: US10317080B2Publication Date: 2019-06-11
- Inventor: John S. Tu, Jr. , Timothy S. Snyder , James B. Hoke , James P. Bangerter , Dennis J. Duhamel , David A. Burns
- Applicant: United Technologies Corporation
- Applicant Address: US CT Farmington
- Assignee: United Technologies Corporation
- Current Assignee: United Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: O'Shea Getz P.C.
- International Application: PCT/US2014/068377 WO 20141203
- International Announcement: WO2015/126501 WO 20150827
- Main IPC: F23R3/00
- IPC: F23R3/00 ; F23R3/06

Abstract:
A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.
Public/Granted literature
- US20160281988A1 CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR Public/Granted day:2016-09-29
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