发明名称 WALL STRUCTURE FOR A GAS TURBINE ENGINE
摘要 A combustion wall or liner construction which utilizes a unique geometry, primarily a plurality of flow channels with predetermined length-to-diameter ratio which are positioned between the walls of the liner, to maintain the liner wall at an acceptable operating temperature. Cooling air flows through the flow channels and control of the frictional pressure losses of this stream provide the control of the wall temperature.
申请公布号 US3706203(A) 申请公布日期 1972.12.19
申请号 USD3706203 申请日期 1970.10.30
申请人 UNITED AIRCRAFT CORP. 发明人 PERRY GOLDBERG;IRWIN SEGALMAN
分类号 F23R3/08;(IPC1-7):F02C7/18 主分类号 F23R3/08
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