发明名称 |
COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE WITH ENHANCED COOLING |
摘要 |
A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.
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申请公布号 |
US2011107766(A1) |
申请公布日期 |
2011.05.12 |
申请号 |
US20090616304 |
申请日期 |
2009.11.11 |
申请人 |
DAVIS JR LEWIS BERKLEY;CHILA RONALD JAMES |
发明人 |
DAVIS, JR. LEWIS BERKLEY;CHILA RONALD JAMES |
分类号 |
F02C7/12 |
主分类号 |
F02C7/12 |
代理机构 |
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代理人 |
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