发明名称 |
Method and apparatus for cooling combustor liner and transition piece of a gas turbine |
摘要 |
A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.
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申请公布号 |
US7493767(B2) |
申请公布日期 |
2009.02.24 |
申请号 |
US20050907866 |
申请日期 |
2005.04.19 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
BUNKER RONALD SCOTT;BAILEY JEREMY CLYDE;WIDENER STANLEY KEVIN;JOHNSON THOMAS EDWARD;INTILE JOHN C |
分类号 |
F02C1/00;F23R3/06;F02C7/12;F02C7/18;F02G3/00;F23R3/00;F23R3/30;F23R3/42 |
主分类号 |
F02C1/00 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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