发明名称 Aircraft combination engines thermal management system
摘要 An engine combination for generating forces with a gas turbine engine generating force that utilizes an engine lubricant for lubricating moving components in the turbofan engine, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force that utilizes a coolant for transporting heat generated in the intermittent combustion engine away therefrom and having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto. A coupling heat exchanger is coupled to both the gas turbine engine and the intermittent combustion engine to have the engine lubricant and the coolant pass therethrough to thereby permit the coolant to transport heat in the engine lubricant away therefrom. A further cooling heat exchanger is coupled to both the coupling heat exchanger and the intermittent combustion engine to have a remote fluid from a source thereof and the coolant pass therethrough to permit the remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the coupling heat exchanger and the intermittent combustion engine.
申请公布号 US2008314573(A1) 申请公布日期 2008.12.25
申请号 US20070820722 申请日期 2007.06.20
申请人 UNITED TECHNOLOGIES CORPORATION 发明人 SCHWARZ FREDERICK M.;GLAHN JORN A.;FENTRESS BRIAN M.
分类号 F28F3/02 主分类号 F28F3/02
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