公开(公告)号：US20190120140A1

公开(公告)日：2019-04-25

申请号：US15791483

申请日：2017-10-24

Applicant: United Technologies Corporation

Inventor： Jorn A. Glahn ,  Matthew J. Howlett ,  Myles R. Kelly ,  Victor M. Pinedo ,  Gregory E. Reinhardt ,  Bradley C. Schafer ,  Ethan K. Stearns

IPC: F02C7/06

Abstract: A gas turbine engine includes a bearing compartment that has at least one seal, a bearing disposed in the bearing compartment, a deoiler fluidly connected with the bearing compartment, and a vacuum generator fluidly connected with the deoiler.

公开(公告)号：US10196936B2

公开(公告)日：2019-02-05

申请号：US14774412

申请日：2014-03-14

Applicant: United Technologies Corporation

Inventor： Ethan K. Stearns ,  Jorn A. Glahn ,  Daniel J. McKaveney

IPC: F01D25/18 ,  F01D25/20 ,  F02C7/224 ,  F02C7/18 ,  F01M1/12 ,  F02C7/06 ,  F02C7/14 ,  F02C9/18 ,  F01D25/12

Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.

公开(公告)号：US10107198B2

公开(公告)日：2018-10-23

申请号：US14761427

申请日：2014-03-14

Applicant: United Technologies Corporation

Inventor： Ethan K. Stearns ,  Jorn A. Glahn ,  Daniel J. McKaveney

IPC: F02C7/06 ,  F02C7/14 ,  F02C7/224 ,  F02C7/36 ,  F02C3/32 ,  F02C9/18

Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.

公开(公告)号：US10087782B2

公开(公告)日：2018-10-02

申请号：US14773876

申请日：2014-03-12

Applicant: United Technologies Corporation

Inventor： Cheng-Zhang Wang ,  Jorn A. Glahn ,  David F. Cloud ,  Peter M. Munsell ,  Clifton J. Crawley, Jr. ,  Robert Newman ,  Michelle Diana Stearns

IPC: F01D25/24 ,  F01D25/00 ,  F01D9/06 ,  F01D25/16 ,  F01D9/04 ,  F02C7/18

Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.

公开(公告)号：US20170335770A1

公开(公告)日：2017-11-23

申请号：US15160365

申请日：2016-05-20

Applicant: United Technologies Corporation

Inventor： Jorn A. Glahn ,  Denman H. James ,  Amy R. Grace

IPC: F02C7/24 ,  F02C7/06 ,  F02C3/04 ,  F02C7/32

CPC classification number: F02C7/24 ,  F01D21/12 ,  F01D21/14 ,  F01D25/18 ,  F02C3/04 ,  F02C7/06 ,  F02C7/14 ,  F02C7/224 ,  F02C7/32 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/81 ,  F05D2260/821 ,  F05D2260/98 ,  F05D2270/112 ,  F05D2270/303 ,  F05D2270/304 ,  Y02T50/676

Abstract: According to an aspect, a method includes predicting, by a processor, a projected oil-wetted metal temperature in a lubrication system of a gas turbine engine at shutdown based on one or more thermal models prior to shutdown of the gas turbine engine. The processor determines a coking index based on the projected oil-wetted metal temperature and a coking limit threshold associated with one or more engine components. An oil coking mitigation action is triggered as a shutdown management event of the gas turbine engine based on the coking index.

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。