公开(公告)号：US20160312711A1

公开(公告)日：2016-10-27

申请号：US14745567

申请日：2015-06-22

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry

IPC: F02C9/18 ,  F01D25/12 ,  F02K3/06 ,  F02C7/18 ,  F02C7/143 ,  F02C3/04

CPC classification number: F02C9/18 ,  F01D25/12 ,  F02C3/13 ,  F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02K3/06 ,  F04D29/5826 ,  F04D29/5833 ,  F05D2220/3212 ,  F05D2220/3219 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2270/3062 ,  Y02T50/675

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passing the tapped air through a first heat exchanger and then to a cooling compressor. A second tap taps air from a location closer to the downstream most end than the location of the first tap, and the first and second taps mix together and are delivered into the high pressure turbine. The cooling compressor is positioned downstream of the first heat exchanger, and upstream of a location where air from the first and second taps mix together.

Abstract translation: 燃气涡轮发动机包括具有下游最末端的高压压缩机和更上游位置的主压缩机部分。 涡轮机部分具有高压涡轮机。 第一分接头从主压缩机部分中的更上游位置中的至少一个抽头抽吸空气，使抽头的空气通过第一热交换器，然后到冷却压缩机。 第二分接头从比第一抽头的位置更靠近下游最端部的位置敲击空气，并且第一和第二抽头混合在一起并被输送到高压涡轮机中。 冷却压缩机位于第一热交换器的下游，并且位于将来自第一和第二抽头的空气混合在一起的位置的上游。

公开(公告)号：US10914242B2

公开(公告)日：2021-02-09

申请号：US15823639

申请日：2017-11-28

Applicant: United Technologies Corporation

Inventor： Joseph Brent Staubach ,  Nathan Snape ,  Frederick M. Schwarz ,  Charles E. Lents ,  Michael K. Ikeda

IPC: F02C9/18 ,  F02C7/18 ,  B64D33/02 ,  B64D13/00 ,  F02C7/14 ,  F02C7/32 ,  F02C7/224 ,  F02C3/04 ,  F02C7/22 ,  B64D13/06

Abstract: A lower pressure tap is connected to a first heat exchanger to be cooled by cooling air, and then to a selection valve. The selection valve selectively delivers the lower pressure tap air to a boost compressor. The lower pressure tap air downstream of the boost compressor is connected to cool the at least one turbine. The selection valve also selectively delivers a portion of the lower pressure tap air across a first cooling turbine, and to a line associated with an air delivery system for a cabin on an associated aircraft. A portion of the air downstream of the first cooling turbine is connected to a second cooling turbine, and air downstream of the second cooling turbine is connected for use in a cold loop A method of operating an air supply system is also disclosed.

公开(公告)号：US10823462B2

公开(公告)日：2020-11-03

申请号：US15269217

申请日：2016-09-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nathan Snape ,  Joseph Brent Staubach

IPC: F25B9/00 ,  F02C3/04 ,  F02C7/18 ,  F02C7/22 ,  F02C7/224 ,  F25B9/06 ,  F25B40/02

Abstract: A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.

公开(公告)号：US10371061B2

公开(公告)日：2019-08-06

申请号：US15292405

申请日：2016-10-13

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/107 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F01D11/12

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

公开(公告)号：US20190154059A1

公开(公告)日：2019-05-23

申请号：US16251133

申请日：2019-01-18

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry

IPC: F04D29/58 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C3/13 ,  F02C7/18 ,  F02C9/18

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US20180128178A1

公开(公告)日：2018-05-10

申请号：US15806992

申请日：2017-11-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nathan Snape ,  Joseph Brent Staubach ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F02C9/18 ,  B64D13/08

CPC classification number: F02C7/18 ,  B64D13/08 ,  B64D2013/0644 ,  F02C6/08 ,  F02C9/18 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/676

Abstract: A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increases a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A valve is downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.

公开(公告)号：US20170044990A1

公开(公告)日：2017-02-16

申请号：US15292405

申请日：2016-10-13

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F01D5/06 ,  F01D25/24 ,  F04D19/02 ,  F02C7/20 ,  F02C3/04 ,  F02K3/06

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D11/122 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/20 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F04D19/02 ,  F05B2250/283 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

Abstract translation: 涡轮风扇发动机具有发动机壳体和通过发动机壳体的气路。 风扇具有圆周阵列的风扇叶片。 发动机还具有压缩机，燃烧器，气体发生涡轮机和低压涡轮部分。 减速机构将低压涡轮部分连接到风扇。 旁路面积比大于约6.0。 低压涡轮机翼型计数到旁路面积比低于约170。

公开(公告)号：US20170044978A1

公开(公告)日：2017-02-16

申请号：US15292249

申请日：2016-10-13

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C3/107 ,  F02C9/18 ,  F02C7/36

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D11/122 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/20 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F04D19/02 ,  F05B2250/283 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

公开(公告)号：US20160312797A1

公开(公告)日：2016-10-27

申请号：US14695534

申请日：2015-04-24

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry

IPC: F04D29/58 ,  F01D25/12 ,  F02C7/143

CPC classification number: F04D29/5826 ,  F01D25/12 ,  F02C3/13 ,  F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02C9/18 ,  F04D29/5833 ,  F05D2220/3212 ,  F05D2220/3217 ,  F05D2220/3219 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2270/3062 ,  Y02T50/675

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

Abstract translation: 燃气涡轮发动机包括具有下游最末端的高压压缩机和更上游位置的主压缩机部分。 涡轮机部分具有高压涡轮机。 第一分接头从主压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气。 第二分接头从距离第一抽头的位置更靠近下游最端的位置敲击空气。 第一和第二抽头混合在一起并被输送到高压涡轮。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

公开(公告)号：US20160237905A1

公开(公告)日：2016-08-18

申请号：US14695578

申请日：2015-04-24

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry

IPC: F02C7/18 ,  F02C3/04

CPC classification number: F41A9/63 ,  F02C3/04 ,  F02C7/18 ,  F02C7/185 ,  F02C7/32 ,  F02K3/06 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/4031 ,  F41A9/65 ,  Y02T50/676

Abstract: Aa gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

Abstract translation: Aa燃气涡轮发动机包括具有具有下游排出口的高压压缩机和更多上游位置的主压缩机部分。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 还公开了一种用于燃气涡轮发动机的中间冷却系统。