| 摘要 |
PROBLEM TO BE SOLVED: To provide a combustor assembly for a turbine engine. SOLUTION: The combustor assembly for the turbine engine includes a combustor liner and a flow sleeve surrounding the combustor liner. Pressurized air flows through an annular space formed between the outer surface of the combustor liner and the inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve so that the pressurized air can flow from the outside of the flow sleeve into the annular space through the cooling holes. The height of the annular space is changeable in the longitudinal direction of the combustor assembly. Therefore, the flow sleeve has a diameter-reduced portion. By the diameter-reduced portion, the height of the annular space can be reduced more at some position than at the other positions in the longitudinal direction of the combustor assembly. COPYRIGHT: (C)2011,JPO&INPIT
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