Invention Grant
US08096133B2 Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface
失效
用于冷却和稀释调整燃气轮机燃烧器衬套和过渡件接口的方法和装置
- Patent Title: Method and apparatus for cooling and dilution tuning a gas turbine combustor liner and transition piece interface
- Patent Title (中): 用于冷却和稀释调整燃气轮机燃烧器衬套和过渡件接口的方法和装置
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Application No.: US12153020Application Date: 2008-05-13
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Publication No.: US08096133B2Publication Date: 2012-01-17
- Inventor: William K. Hessler , Predrag Popovic , Charles Nyberg
- Applicant: William K. Hessler , Predrag Popovic , Charles Nyberg
- Applicant Address: US NY Schenectady
- Assignee: General Electric Company
- Current Assignee: General Electric Company
- Current Assignee Address: US NY Schenectady
- Agency: Nixon & Vanderhye, P.C.
- Main IPC: F02C1/00
- IPC: F02C1/00 ; F02G3/00
Abstract:
A combustor liner includes a forward end and an aft end, the aft end having a reduced diameter portion and a cooling and dilution sleeve overlying the reduced diameter portion thereby establishing a cooling plenum therebetween. A plurality of cooling and dilution air entry holes are formed in the cooling and dilution sleeve and a plurality of cooling and dilution air exit holes formed adjacent an aft edge of the liner such that, in use, cooling and dilution air flows through the cooling and dilution air entry holes, and through the plenum, exiting the cooling and dilution air exit holes, thereby cooling and dilution tuning the aft end of the combustor liner without having to remove the transition piece.
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