发明名称 |
GAS TURBINE ENGINE THERMAL MANAGEMENT SYSTEM FOR HEAT EXCHANGER USING BYPASS FLOW |
摘要 |
A gas turbine engine has a fan nacelle and a core nacelle arranged to provide a bypass flow path. A compressor section is provided within the core nacelle. A heat exchanger is arranged within a duct. The heat exchanger is configured to receive bypass flow from the bypass flow path. The duct is in fluid communication with the compressor section and is configured to pass bleed air through the heat exchanger. |
申请公布号 |
EP2900965(A1) |
申请公布日期 |
2015.08.05 |
申请号 |
EP20130842467 |
申请日期 |
2013.03.12 |
申请人 |
UNITED TECHNOLOGIES CORPORATION;SUCIU, GABRIEL L. |
发明人 |
SUCIU, GABRIEL L. |
分类号 |
F02C7/12;F01D17/10;F01D25/12;F02C7/14;F02C9/00;F02K3/00;F02K3/04;F02K3/075 |
主分类号 |
F02C7/12 |
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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