公开(公告)号：EP2820266A2

公开(公告)日：2015-01-07

申请号：EP13793559.9

申请日：2013-02-15

Applicant: United Technologies Corporation

Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L.

IPC: F02C3/067 ,  F02K3/072 ,  F01D25/24

CPC classification number: F01D15/12 ,  F01D1/24 ,  F01D25/162 ,  F01D25/30 ,  F02C3/107 ,  F02C7/32 ,  F02K3/072 ,  Y02T50/671

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.

公开(公告)号：EP3054127B1

公开(公告)日：2020-05-06

申请号：EP16154942.3

申请日：2016-02-09

Applicant: United Technologies Corporation

Inventor： SNAPE, Nathan D. ,  SUCIU, Gabriel L. ,  ACKERMAN, William K. ,  HILL, James D. ,  MERRY, Brian D.

IPC: F02C7/224 ,  F02C7/18

公开(公告)号：EP3473834B1

公开(公告)日：2020-04-22

申请号：EP18208937.5

申请日：2013-01-07

Applicant: United Technologies Corporation

Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L.

IPC: F02C7/06 ,  F02C7/36 ,  F02K3/02 ,  F01D25/16 ,  F02K3/04

公开(公告)号：EP3179034B1

公开(公告)日：2020-03-18

申请号：EP16203026.6

申请日：2016-12-08

Applicant: United Technologies Corporation

Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L. ,  ACKERMANN, William K.

IPC: F01D5/08 ,  F02K3/06 ,  F02C6/08 ,  F02C7/12 ,  F02C7/36

公开(公告)号：EP2820266B1

公开(公告)日：2018-12-26

申请号：EP13793559.9

申请日：2013-02-15

Applicant: United Technologies Corporation

Inventor： MERRY, Brian D. ,  SUCIU, Gabriel L.

IPC: F02C3/067 ,  F02K3/072 ,  F01D25/24 ,  F02C3/107 ,  F02C7/32 ,  F01D25/30 ,  F01D25/12 ,  F01D15/12 ,  F01D25/16 ,  F01D1/24

CPC classification number: F01D15/12 ,  F01D1/24 ,  F01D25/162 ,  F01D25/30 ,  F02C3/107 ,  F02C7/32 ,  F02K3/072 ,  Y02T50/671

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.

公开(公告)号：EP3217001A1

公开(公告)日：2017-09-13

申请号：EP17158992.2

申请日：2017-03-02

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  MERRY, Brian D.

IPC: F02C7/25 ,  F02C7/32

CPC classification number: F01D25/08 ,  F01D25/20 ,  F02C7/22 ,  F02C7/25 ,  F02C7/32 ,  F04D19/02 ,  F04D27/009 ,  F04D29/563 ,  F05D2220/32 ,  F05D2260/231 ,  Y02T50/675

Abstract: A gas turbine engine (20) comprises an engine having a compressor section (24), and a turbine section (28). A firewall (80) and accessory pumps (88, 90) are mounted on a downstream side of the firewall (80). The accessory pumps (88, 90) are driven by electric motors (92, 94, 98, 100) mounted on the firewall (80) on an upstream side of the firewall (80).

Abstract translation: 燃气涡轮发动机（20）包括具有压缩机部分（24）和涡轮部分（28）的发动机。 防火墙（80）和附属泵（88,90）安装在防火墙（80）的下游侧。 附件泵（88,90）由安装在防火墙（80）上游侧的防火墙（80）上的电动机（92,94,98,100）驱动。

公开(公告)号：EP3181869A1

公开(公告)日：2017-06-21

申请号：EP16203857.4

申请日：2016-12-13

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  CHANDLER, Jesse M. ,  ACKERMANN, William K. ,  FEULNER, Matthew R. ,  SHARMA, Om P.

IPC: F02C7/143 ,  F02C7/18 ,  F02C9/18 ,  F01D5/08 ,  F04D29/58

CPC classification number: F02C7/18 ,  F01D5/08 ,  F02C3/04 ,  F02C7/143 ,  F02C7/185 ,  F02C9/18 ,  F02K3/06 ,  F04D27/0215 ,  F04D29/582 ,  F05D2220/32 ,  F05D2220/3219 ,  F05D2240/24 ,  F05D2260/205 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/676

Abstract: A compressor section (100) for use in a gas turbine engine (20) comprises a compressor rotor having a hub (109; 123) and a plurality of blades extending radially outwardly from the hub (109; 123) and an outer housing surrounding an outer periphery of the blades. A tap (104; 116) taps air at a radially outer first location, passing the tapped air through a heat exchanger (106; 118), and returning the tapped air to an outlet (110; 122) at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub (109; 123).

Abstract translation: 一种用于燃气涡轮发动机（20）的压缩机部分（100）包括压缩机转子，所述压缩机转子具有毂（109; 123）和从所述毂（109; 123）径向向外延伸的多个叶片，所述外壳围绕 叶片的外围。 龙头（104; 116）在径向外部的第一位置处抽吸空气，使抽取的空气通过热交换器（106; 118），并且将抽取的空气在径向的第二位置处返回到出口（110; 122） 在第一位置的内部，以提供邻近轮毂（109; 123）的冷却空气。

公开(公告)号：EP3109435A1

公开(公告)日：2016-12-28

申请号：EP16175531.9

申请日：2016-06-21

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  MERRY, Brian D. ,  SNAPE, Nathan

IPC: F02C6/08 ,  F02C7/143

CPC classification number: F02C6/08 ,  F02C7/185 ,  F02C7/20 ,  F02C7/32 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/676

Abstract: A 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 (117). A tap (110) taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger (112) and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger (112), and delivers air into the high pressure turbine. A core housing (150) has an outer peripheral surface and a fan housing (154) defining an inner peripheral surface. At least one bifurcation duct (158, 160) extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger (112) is received within the at least one bifurcation duct (158, 160).

Abstract translation: 燃气涡轮发动机包括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。 涡轮部分具有高压涡轮机（117）。 抽头（110）从压缩机部分中的至少一个上游位置抽吸空气，使抽头的空气通过热交换器（112），然后传递到冷却压缩机。 冷却压缩机压缩热交换器（112）下游的空气，并将空气输送到高压涡轮机中。 芯壳体（150）具有外周表面和限定内周表面的风扇壳体（154）。 至少一个分叉管道（158,160）在外周表面和内周表面之间延伸。 热交换器（112）被容纳在至少一个分叉管道（158,160）内。

公开(公告)号：EP3056716A1

公开(公告)日：2016-08-17

申请号：EP16154635.3

申请日：2016-02-08

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  STAUBACH, Joseph Brent ,  MERRY, Brian D.

IPC: F02C7/18 ,  F02C7/32 ,  F02K3/06

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: A gas turbine engine (20) comprises a main compressor section having a high pressure compressor (108) with a downstream discharge (82), and more upstream locations. A turbine section has a high pressure turbine (117). A tap (110) taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger (112) and then to a cooling compressor (114). The cooling compressor (114) compresses air downstream of the heat exchanger (112), and delivers air into the high pressure turbine (117).

Abstract translation: 燃气涡轮发动机（20）包括具有具有下游排出口（82）的高压压缩机（108）和更多上游位置的主压缩机部分。 涡轮部分具有高压涡轮机（117）。 抽头（110）从压缩机部分中的上游位置中的至少一个抽吸空气，将抽头的空气通过热交换器（112），然后传递到冷却压缩机（114）。 冷却压缩机（114）压缩热交换器（112）下游的空气，并将空气输送到高压涡轮机（117）中。

公开(公告)号：EP3000966A1

公开(公告)日：2016-03-30

申请号：EP15186522.7

申请日：2015-09-23

Applicant: United Technologies Corporation

Inventor： SUCUI, Gabriel L. ,  MERRY, Brian D. ,  HILL, James D. ,  ZELESKY, Mark F.

IPC: F01D5/06 ,  F01D5/18 ,  F01D11/00

CPC classification number: F01D5/18 ,  F01D5/06 ,  F01D5/185 ,  F01D5/186 ,  F01D5/187 ,  F01D11/001 ,  F01D11/003 ,  F01D11/005 ,  F02C3/08 ,  F05D2220/32 ,  F05D2260/20 ,  Y02T50/676

Abstract: A turbine section (28) includes a rotor assembly (62) which includes an internal cooling passage (160,162). A segmented seal (102) is adjacent the rotor assembly (62) and includes a fluid passage that is in fluid communication with the internal cooling passage (160,162).

Abstract translation: 涡轮部分（28）包括转子组件（62）包含：在内部冷却通道（160,162）。 分段式密封件（102）邻近于所述转子组件（62），并且包括一个流体通道流体连通的内部冷却通道（160,162）那样。