公开(公告)号：US20210172333A1

公开(公告)日：2021-06-10

申请号：US16706058

申请日：2019-12-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： GABRIEL L. SUCIU ,  Om P. Sharma ,  Joseph B. Staubach ,  Marc J. Muldoon ,  Jesse M. Chandler ,  David Lei Ma

IPC: F01D15/10 ,  F02K5/00 ,  F02C3/10

Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.

公开(公告)号：US10830152B2

公开(公告)日：2020-11-10

申请号：US15184253

申请日：2016-06-16

Applicant: United Technologies Corporation

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

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F02C3/04 ,  F02K3/02 ,  F02C3/06

Abstract: A gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to about 8 at cruise power. A gear arrangement is configured to drive the fan section. A compressor section includes both a first compressor section and a second compressor section. A turbine section is configured to drive the gear arrangement, and may have a low pressure turbine with four stages and a low pressure turbine pressure ratio greater than about 5:1, and a high pressure turbine with two stages. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than about 40, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the second compressor section is greater than about 7.

公开(公告)号：US20200224590A1

公开(公告)日：2020-07-16

申请号：US16248922

申请日：2019-01-16

Applicant: United Technologies Corporation

Inventor： Brendan T. McAuliffe ,  Joseph B. Staubach ,  Nagendra Somanath

IPC: F02C6/18 ,  F02C3/073 ,  F02C6/08 ,  F02C7/18 ,  F02C6/04 ,  F01K23/02 ,  F01K25/10 ,  F02C7/32

Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) coolant circuit and a second outlet connected to the sCO2 work recovery cycle. The sCO2 work recovery cycle is a recuperated Brayton cycle

公开(公告)号：US20200224557A1

公开(公告)日：2020-07-16

申请号：US16248942

申请日：2019-01-16

Applicant: United Technologies Corporation

Inventor： Brendan T. McAuliffe ,  Joseph B. Staubach ,  Nagendra Somanath

IPC: F01K23/02 ,  F02C3/073 ,  F02C6/06 ,  F02C6/18 ,  F01K25/10

Abstract: A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) work recovery cycle and a second outlet connected to the sCO2 work recovery cycle. The sCO2 work recovery cycle is an overexpanded, recuperated work recovery cycle.

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：US09909497B2

公开(公告)日：2018-03-06

申请号：US14706748

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Matthew R. Feulner ,  Brian D. Merry ,  Jesse M. Chandler ,  Gabriel L. Suciu ,  Joseph B. Staubach

IPC: F02C6/08 ,  F04D27/02 ,  F02C7/052 ,  F04D29/52 ,  F04D29/70 ,  F02C3/10 ,  F02K3/06

CPC classification number: F02C6/08 ,  F02C3/10 ,  F02C7/052 ,  F02K3/06 ,  F04D27/0215 ,  F04D29/526 ,  F04D29/701 ,  F05D2210/12 ,  F05D2220/36 ,  F05D2260/607 ,  F05D2260/608 ,  F05D2270/101 ,  Y02T50/675

Abstract: A compressor section of a gas turbine engine includes a bleed port having a flow splitter therein so as to define a downstream bleed channel having a downstream inlet and an upstream bleed channel having an upstream inlet that is positioned radially outward from the downstream inlet.

公开(公告)号：US20180003072A1

公开(公告)日：2018-01-04

申请号：US15200149

申请日：2016-07-01

Applicant: United Technologies Corporation

Inventor： Charles E. Lents ,  Larry W. Hardin ,  Jonathan Rheaume ,  Joseph B. Staubach

IPC: F01D15/10 ,  B64D27/16 ,  B64D27/24 ,  F02C6/14 ,  F02C7/36 ,  F02C9/50 ,  F02C3/04 ,  B64D31/06 ,  B64D27/02

CPC classification number: F01D15/10 ,  B64D27/10 ,  B64D27/24 ,  B64D31/06 ,  B64D2027/026 ,  F02C6/14 ,  F02C7/36 ,  F02C9/50 ,  F05D2220/76 ,  Y10S903/905 ,  Y10S903/906

Abstract: A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.

公开(公告)号：US20160326957A1

公开(公告)日：2016-11-10

申请号：US14706748

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Matthew R. Feulner ,  Brian D. Merry ,  Jesse M. Chandler ,  Gabriel L. Suciu ,  Joseph B. Staubach

IPC: F02C6/08 ,  F02K3/06 ,  F02C3/10

CPC classification number: F02C6/08 ,  F02C3/10 ,  F02C7/052 ,  F02K3/06 ,  F04D27/0215 ,  F04D29/526 ,  F04D29/701 ,  F05D2210/12 ,  F05D2220/36 ,  F05D2260/607 ,  F05D2260/608 ,  F05D2270/101 ,  Y02T50/675

Abstract: A compressor section of a gas turbine engine includes a bleed port having a flow splitter therein so as to define a downstream bleed channel having a downstream inlet and an upstream bleed channel having an upstream inlet that is positioned radially outward from the downstream inlet.

Abstract translation: 燃气涡轮发动机的压缩机部分包括具有分流器的排出口，以便限定具有下游入口的下游排放通道和具有从下游入口径向向外定位的上游入口的上游排出通道。

公开(公告)号：US20150345404A1

公开(公告)日：2015-12-03

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

IPC: F02C9/18 ,  F02C7/36 ,  F01D25/24 ,  F01D1/02 ,  F01D5/02 ,  F01D9/04 ,  F02C3/04 ,  F02C7/20

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：US20140165534A1

公开(公告)日：2014-06-19

申请号：US14179714

申请日：2014-02-13

Applicant: United Technologies Corporation

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

IPC: F02K3/06

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

Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. A bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than or equal to about 8.

Abstract translation: 一种燃气涡轮发动机具有风扇部分，包括风扇，构造成驱动风扇部分的齿轮装置和包括第一压缩机和第二压缩机的压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供，总压力比大于或等于约35.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 的空气进入旁路管道。 旁路比被定义为与通过压缩机部分的空气体积相比通过旁通管道的空气体积大于或等于约8。