发明名称 |
Gas turbine engine compressor arrangement |
摘要 |
<p>A gas turbine engine (90) includes a low pressure compressor section (18) and a high pressure compressor section (22). A low pressure turbine (34) drives the low pressure compressor section (18). A gear arrangement (62) is driven by the low pressure turbine (34) to in turn drive a fan section (14). A pressure ratio across the low pressure compressor section (18) is between about 4-8 and a pressure ratio across the high pressure compressor section (22) is between about 8-15. A compressor case (66) includes a front compressor case portion and a rear compressor case portion, with the rear compressor case portion being axially further from an inlet case (64) than the front compressor case portion. A support member (78) extends between the fan section (14) and the front compressor case portion.
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申请公布号 |
EP2592235(A3) |
申请公布日期 |
2014.10.15 |
申请号 |
EP20120191265 |
申请日期 |
2012.11.05 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
STAUBACH, JOSEPH B.;MERRY, BRIAN D.;SUCIU, GABRIEL L.;DYE, CHRISTOPHER M. |
分类号 |
F01D1/04;F01D13/00;F02C3/107;F02K3/06 |
主分类号 |
F01D1/04 |
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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