发明名称 |
Gas turbine engine compressor arrangement |
摘要 |
A gas turbine engine includes a low pressure compressor section and a high pressure compressor section. A low pressure turbine drives the low pressure compressor section. A gear arrangement is driven by the low pressure turbine to in turn drive a fan section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case 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 than the front compressor case portion. A support member extends between the fan section and the front compressor case portion. |
申请公布号 |
US8337147(B2) |
申请公布日期 |
2012.12.25 |
申请号 |
US201113337354 |
申请日期 |
2011.12.27 |
申请人 |
STAUBACH JOSEPH B.;MERRY BRIAN D.;SUCIU GABRIEL L.;DYE CHRISTOPHER M.;UNITED TECHNOLOGIES CORPORATION |
发明人 |
STAUBACH JOSEPH B.;MERRY BRIAN D.;SUCIU GABRIEL L.;DYE CHRISTOPHER M. |
分类号 |
F01D5/06 |
主分类号 |
F01D5/06 |
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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