公开(公告)号：WO2013101805A1

公开(公告)日：2013-07-04

申请号：PCT/US2012/071614

申请日：2012-12-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： HASEL, Karl L. ,  STAUBACH, Joseph B. ,  MERRY, Brian D. ,  SUCIU, Gabriel L. ,  DYE, Christohper M.

IPC: F01D1/04

CPC classification number: F02C3/107 ,  F02K3/06

Abstract: 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.

Abstract translation: 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约 而高压压缩机部分的压力比为约7至约15。