GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT

专利名称：GAS TURBINE ENGINE COMPRESSOR

ARRANGEMENT

发明人：Hasel Karl,Joseph B. Staubach,Brian D.

Merry,Gabriel L. Suciu,Christopher M. Dye

申请号：US13869057申请日：20130424

公开号：US20130239587A1公开日：20130919

专利附图：

摘要：A gas turbine engine has a fan section, a gear arrangement configured to drivethe fan section, a compressor section, including both a low pressure compressor section

and a high pressure compressor section. A turbine section is configured to drive thecompressor section and the gear arrangement. An overall pressure ratio provided by thecombination of a pressure ratio across the low pressure compressor section and apressure ratio across the high pressure compressor section is greater than about 35. Thepressure ratio across a first of the low and high pressure compressor sections is betweenabout 3 and about 8. The pressure ratio across a second of the low and high pressurecompressor sections is between about 7 and about 15. The fan is configured to deliver aportion of air into the compressor section, and a portion of air into a bypass duct.

申请人：UNITED TECHNOLOGIES CORPORATION

地址：Hartford CT US

国籍：US

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