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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,CHRISTOHPER M.
申请号：EP12861657申请日：20121226公开号：EP2776677A4公开日：20141008
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
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