发明名称 |
STRUCTURES AND METHODS FOR INTERCOOLING AIRCRAFT GAS TURBINE ENGINES |
摘要 |
<p>A turbine engine has a fan comprising a duct and supporting struts, a first compressor configured to pressurize inlet air, and a second compressor configured to further pressurize the inlet air. A cooling circuit is located to cool the inlet air after the inlet air is pressurized by the first compressor and before the inlet air is further pressurized by the second compressor, and includes at least intercooler configured to transfer heat from inlet air to a secondary fluid heat sink.</p> |
申请公布号 |
WO2013176727(A3) |
申请公布日期 |
2014.02.20 |
申请号 |
WO2013US29003 |
申请日期 |
2013.03.05 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
DASGUPTA, ARINDAM;SHARMA, OM P. |
分类号 |
F02C7/143;F02C7/12 |
主分类号 |
F02C7/143 |
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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