发明名称 |
GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT |
摘要 |
A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15. |
申请公布号 |
WO2013101805(A1) |
申请公布日期 |
2013.07.04 |
申请号 |
WO2012US71614 |
申请日期 |
2012.12.26 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
HASEL, KARL L.;STAUBACH, JOSEPH B.;MERRY, BRIAN D.;SUCIU, GABRIEL L.;DYE, CHRISTOHPER M. |
分类号 |
F01D1/04 |
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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