公开(公告)号：US10724541B2

公开(公告)日：2020-07-28

申请号：US15378371

申请日：2016-12-14

Applicant: United Technologies Corporation

Inventor： Yuan J. Qiu ,  Robert E. Malecki ,  Wesley K. Lord

IPC: F04D29/54 ,  F02C7/04 ,  F02K3/06 ,  B64D33/02 ,  F04D29/32

Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades. Each fan blade extends radially outwardly from a fan hub to a blade tip. The plurality of blade tips define a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade of the plurality of fan blades. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath. The nacelle flowpath has a convex throat portion and a concave diffusion portion between the throat portion and the leading edge of the fan blade at a bottommost portion of the nacelle.

公开(公告)号：US10723470B2

公开(公告)日：2020-07-28

申请号：US15619893

申请日：2017-06-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Wesley K. Lord

IPC: B64D27/14 ,  F02K3/062 ,  F02K3/072 ,  F02C7/18 ,  B64D35/06 ,  B64D41/00

Abstract: A boundary layer ingestion engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan mechanically linked to the turbine via at least one shaft. The linkage is configured such that rotation of the turbine is translated to the fan. The boundary layer ingestion engine further includes an exhaust duct fluidly connected to an outlet of the turbine. The exhaust duct is positioned radially inward of the fan.

公开(公告)号：US10662880B2

公开(公告)日：2020-05-26

申请号：US14692090

申请日：2015-04-21

Applicant: United Technologies Corporation

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

IPC: F02C9/18 ,  F02C3/04 ,  F02C7/20 ,  F01D1/02 ,  F01D5/02 ,  F01D9/04 ,  F01D25/24 ,  F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F02C3/113 ,  F02K3/02 ,  F02K3/075 ,  F02K7/06

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：US10301971B2

公开(公告)日：2019-05-28

申请号：US15887136

申请日：2018-02-02

Applicant: United Technologies Corporation

Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

IPC: F01D1/02 ,  F01D25/24 ,  F02K3/06 ,  F01D5/14 ,  F02C7/04 ,  F01D5/02 ,  F01D15/12 ,  F01D17/10

Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.

公开(公告)号：US10267263B2

公开(公告)日：2019-04-23

申请号：US15230590

申请日：2016-08-08

Applicant: United Technologies Corporation

Inventor： Wesley K. Lord ,  Jesse M. Chandler ,  Gabriel L. Suciu

IPC: B64D27/14 ,  F02K3/00 ,  B64D33/02 ,  B64D33/04 ,  F02K1/52 ,  B64D35/04 ,  F02K3/062

Abstract: A gas turbine engine includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A propulsor section aft of the core engine is driven by the turbine section. An exhaust duct routing exhaust gases around the propulsor section. The exhaust duct includes an inlet forward of the propulsor section, an outlet aft of the turbine section and a passageway between the inlet and the outlet. An aircraft and exhaust duct are also disclosed.

公开(公告)号：US10060357B2

公开(公告)日：2018-08-28

申请号：US15292472

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

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：US20180066587A1

公开(公告)日：2018-03-08

申请号：US15807911

申请日：2017-11-09

Applicant: United Technologies Corporation

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

IPC: F02C7/18 ,  F02C3/13 ,  F02C7/143 ,  F01D25/12

Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, 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 ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US20180038315A1

公开(公告)日：2018-02-08

申请号：US15230590

申请日：2016-08-08

Applicant: United Technologies Corporation

Inventor： Wesley K. Lord ,  Jesse M. Chandler ,  Gabriel L. Suciu

IPC: F02K3/00 ,  B64D33/04 ,  B64D33/02 ,  F02K1/52 ,  B64D27/14

CPC classification number: F02K3/00 ,  B64D27/14 ,  B64D33/02 ,  B64D33/04 ,  B64D35/04 ,  F02K1/52 ,  F02K3/062 ,  F05D2250/312

Abstract: A gas turbine engine includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A propulsor section aft of the core engine is driven by the turbine section. An exhaust duct routing exhaust gases around the propulsor section. The exhaust duct includes an inlet forward of the propulsor section, an outlet aft of the turbine section and a passageway between the inlet and the outlet. An aircraft and exhaust duct are also disclosed.

公开(公告)号：US20170298832A1

公开(公告)日：2017-10-19

申请号：US15292438

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

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：US20160369706A1

公开(公告)日：2016-12-22

申请号：US14745606

申请日：2015-06-22

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler

IPC: F02C9/18 ,  F02C7/14

CPC classification number: F02C9/18 ,  F02C6/08 ,  F02C7/06 ,  F02C7/14 ,  F02K3/115 ,  F05D2230/31 ,  F05D2260/213 ,  Y02T50/675

Abstract: A gas turbine engine comprises a main fan that delivers air into a bypass duct and into a core engine. A heat exchanger is positioned within the bypass duct and receives a fluid to be cooled from a component associated with the gas turbine engine. A heat exchanger fan is positioned to draw air across the heat exchanger and a control for the heat exchanger fan. The control is programmed to stop operation of the fan during certain conditions, and to drive the heat exchanger fan under other conditions. A method of forming a heat exchanger is also disclosed.

Abstract translation: 燃气涡轮发动机包括将空气输送到旁通管道并进入核心发动机的主风扇。 热交换器定位在旁路管道内，并从与燃气涡轮发动机相关联的部件接收待冷却的流体。 定位热交换器风扇以抽吸空气穿过热交换器和用于热交换器风扇的控制。 控制器被编程为在某些条件下停止风扇的运行，并在其他条件下驱动热交换器风扇。 还公开了形成热交换器的方法。