发明名称 |
GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE |
摘要 |
A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000° F. and about 1500° F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis. |
申请公布号 |
EP2904254(A1) |
申请公布日期 |
2015.08.12 |
申请号 |
EP20130843958 |
申请日期 |
2013.03.12 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
SCHWARZ, FREDERICK M.;HASEL, KARL L. |
分类号 |
F02K3/06;F01D9/02;F02K3/00 |
主分类号 |
F02K3/06 |
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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