公开(公告)号：US20160061052A1

公开(公告)日：2016-03-03

申请号：US14935539

申请日：2015-11-09

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Frederick M. Schwarz ,  William K. Ackermann ,  Daniel Bernard Kupratis

IPC: F01D15/12 ,  F01D25/24 ,  F01D25/16 ,  F01D5/06

CPC classification number: F01D15/12 ,  F02C3/06 ,  F02K3/072 ,  F05D2220/3215 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan having one or more fan blades. A compressor section is in fluid communication with the fan. The compressor section includes a first compressor section and a second compressor section. A turbine section is in fluid communication with the compressor section. The turbine section includes a first turbine section and a second turbine section. The first turbine section has a first exit area at a first exit point and rotates at a first speed. The second turbine section has a second exit area at a second exit point and rotates at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括具有一个或多个风扇叶片的风扇。 压缩机部分与风扇流体连通。 压缩机部分包括第一压缩机部分和第二压缩机部分。 涡轮部分与压缩机部分流体连通。 涡轮部分包括第一涡轮部分和第二涡轮部分。 第一涡轮部分在第一出口处具有第一出口区域并以第一速度旋转。 第二涡轮部分在第二出口处具有第二出口区域并以第二速度旋转。 第一性能数量被定义为第一速度平方和第一区域的乘积。 第二性能量被定义为第二速度平方和第二区域的乘积。

公开(公告)号：US09097138B2

公开(公告)日：2015-08-04

申请号：US14044282

申请日：2013-10-02

Applicant: United Technologies Corporation

Inventor： Jorn A. Glahn ,  Clifton J. Crawley, Jr. ,  Philip S. Stripinis ,  William K. Ackermann

IPC: F02C6/08 ,  F01D25/00 ,  F02C7/18 ,  F01D11/04 ,  F01D25/16 ,  F02C7/06 ,  F02C7/12 ,  F02C7/28 ,  F02C9/18

CPC classification number: F02C9/18 ,  F01D11/04 ,  F01D25/00 ,  F01D25/16 ,  F02C6/08 ,  F02C7/06 ,  F02C7/12 ,  F02C7/18 ,  F02C7/28 ,  F05D2260/601 ,  Y02T50/675 ,  Y10T29/49229

Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a buffer system. The buffer system can include a first circuit that supplies a first buffer supply air and a second circuit that supplies a second buffer supply air. The first circuit can include a first bleed air supply a second bleed air supply and at least one of an ejector and a valve. The second circuit can include a third bleed air supply, a fourth bleed air supply and at least one of an ejector and a valve.

Abstract translation: 燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器流体连通的涡轮机部分和缓冲系统。 缓冲系统可以包括提供第一缓冲器供应空气的第一电路和供应第二缓冲器供应空气的第二电路。 第一回路可以包括第一排放空气源和第二排放空气源，以及喷射器和阀中的至少一个。 第二回路可以包括第三排气供应源，第四排放空气源以及喷射器和阀门中的至少一个。

公开(公告)号：US20140196470A1

公开(公告)日：2014-07-17

申请号：US14219070

申请日：2014-03-19

Applicant: United Technologies Corporation

Inventor： Jorn A. Glahn ,  Clifton J. Crawley, JR. ,  Philip S. Stripinis ,  William K. Ackermann

IPC: F02C9/18

CPC classification number: F02C9/18 ,  F01D11/04 ,  F01D25/00 ,  F01D25/16 ,  F02C6/08 ,  F02C7/06 ,  F02C7/12 ,  F02C7/18 ,  F02C7/28 ,  F05D2260/601 ,  Y02T50/675 ,  Y10T29/49229

Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure.

Abstract translation: 燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器流体连通的涡轮机部分，经由齿轮架构被涡轮部分驱动的风扇部分和缓冲系统， 将缓冲空气传送到燃气涡轮发动机的一部分。 缓冲系统包括第一回路，其被配置为选择性地混合具有第一压力的第一排气供应源和第二排气源，其具有大于第一压力的第二压力，以提供具有中压的第一缓冲器供应空气， 第一压力和第二压力。

公开(公告)号：US08756908B2

公开(公告)日：2014-06-24

申请号：US14034720

申请日：2013-09-24

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann ,  Jason Husband

IPC: F02C7/06

CPC classification number: F02C7/06 ,  F01D25/18 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  Y02T50/671

Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system.

Abstract translation: 用于燃气涡轮发动机的风扇驱动齿轮系统包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统和齿轮系统的柔性支撑部分的安装件。 支持风扇驱动齿轮系统的润滑系统为齿轮系统提供润滑剂，并去除由齿轮系产生的热能。 润滑系统包括能量消除等于输入到齿轮系统中的能量的小于约2％的能量。