GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT

专利名称：GAS TURBINE ENGINE COMPRESSOR

ARRANGEMENT

发明人：HASEL, Karl L.,STAUBACH, Joseph B.,MERRY,

Brian D.,SUCIU, Gabriel L.,DYE, ChristohperM.

申请号：EP12861657.0申请日：20121226公开号：EP2776677A1公开日：20140917

摘要：A gas turbine engine includes a fan section, a gear arrangement configured todrive the fan section, a compressor section and a turbine section. The compressor sectionincludes a low pressure compressor section and a high pressure compressor section. Theturbine section is configured to drive compressor section and the gear arrangement. Anoverall pressure ratio, which is provided by a combination of a pressure ratio across saidlow pressure compressor section and a pressure ratio across said high pressure

compressor section, is greater than about 35. The pressure ratio across the low pressurecompressor section is between about 3 and about 8 whereas the pressure ratio acrossthe high pressure compressor section is between about 7 and about 15.

申请人：United Technologies Corporation

地址：One Financial Plaza Hartford, CT 06101 US

国籍：US

代理机构：Hull, James Edward

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