公开(公告)号：US20130239587A1

公开(公告)日：2013-09-19

申请号：US13869057

申请日：2013-04-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Hasel Karl ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02C7/00

CPC classification number: F02K3/025 ,  F02C3/107 ,  F02C7/00 ,  F02K3/06 ,  F05D2260/4031

Abstract: A gas turbine engine has a fan section, a gear arrangement configured to drive the 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 the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.

Abstract translation: 燃气涡轮发动机具有风扇部，构造成驱动风扇部的齿轮装置，包括低压压缩部和高压压缩部两者的压缩部。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过低压压缩机部分的压力比和高压压缩机部分的压力比的组合提供的总压力比大于约35。第一低压压缩机部分和高压压缩机部分之间的压力比在 约3和约8之间。跨过第二个低压和高压压缩机段的压力比在约7至约15之间。风扇构造成将一部分空气输送到压缩机部分中，并且一部分空气进入 旁路管道。

公开(公告)号：US09121367B2

公开(公告)日：2015-09-01

申请号：US13869057

申请日：2013-04-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Hasel Karl ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F01D1/00 ,  F02K3/02 ,  F02C3/107 ,  F02C7/00 ,  F02K3/06

CPC classification number: F02K3/025 ,  F02C3/107 ,  F02C7/00 ,  F02K3/06 ,  F05D2260/4031

Abstract: A gas turbine engine has a fan section, a gear arrangement configured to drive the 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 the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.

Abstract translation: 燃气涡轮发动机具有风扇部，构造成驱动风扇部的齿轮装置，包括低压压缩部和高压压缩部两者的压缩部。 涡轮部分构造成驱动压缩机部分和齿轮装置。 通过低压压缩机部分的压力比和高压压缩机部分的压力比的组合提供的总压力比大于约35。第一低压压缩机部分和高压压缩机部分之间的压力比在 约3和约8之间。跨过第二个低压和高压压缩机段的压力比在约7至约15之间。风扇构造成将一部分空气输送到压缩机部分中，并且一部分空气进入 旁路管道。

公开(公告)号：US20130202415A1

公开(公告)日：2013-08-08

申请号：US13836799

申请日：2013-03-15

Applicant: United Technologies Corporation

Inventor： Hasel Karl ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02K3/02

CPC classification number: F02K3/025 ,  F02C3/107 ,  F02C7/00 ,  F02K3/06 ,  F05D2260/4031

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. The engine includes a combination of quantities providing beneficial operation.

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。 发动机包括提供有益操作的量的组合。