Invention Grant
US08789374B2 Gas turbine combustor with liner air admission holes associated with interpersed main and pilot swirler assemblies
有权
燃气轮机燃烧器具有与间接的主和先导式旋流器组件相关联的衬管进气孔
- Patent Title: Gas turbine combustor with liner air admission holes associated with interpersed main and pilot swirler assemblies
- Patent Title (中): 燃气轮机燃烧器具有与间接的主和先导式旋流器组件相关联的衬管进气孔
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Application No.: US13761454Application Date: 2013-02-07
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Publication No.: US08789374B2Publication Date: 2014-07-29
- Inventor: James B. Hoke
- Applicant: United Technologies Corporation
- Applicant Address: US CT Hartford
- Assignee: United Technologies Corporation
- Current Assignee: United Technologies Corporation
- Current Assignee Address: US CT Hartford
- Agency: Miller, Matthias & Hull LLP
- Main IPC: F02C1/00
- IPC: F02C1/00 ; F02G3/00
Abstract:
A combustor for a gas turbine engine having an annular combustion chamber includes a plurality of main fuel injection and air swirler assemblies and a plurality of pilot fuel injection and air swirler assemblies disposed in a circumferential ring extending about the circumferential expanse of a forward bulkhead. The plurality of pilot fuel injection and air swirler assemblies are interspersed amongst and disposed in the circumferential ring of main fuel injection and air swirler assemblies. Fuel being supplied to the combustor is selectively distributed between the plurality of main fuel injection and air swirler assemblies and the plurality of pilot fuel injection and air swirler assemblies in response to the level of power demand on the gas turbine engine.
Public/Granted literature
- US20130186099A1 Gas Turbine Combustor Public/Granted day:2013-07-25
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