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：EP3109434A1

公开(公告)日：2016-12-28

申请号：EP16175506.1

申请日：2016-06-21

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  LORD, Wesley K. ,  CHANDLER, Jesse M.

IPC: F02C6/08 ,  F02C7/14 ,  F02C9/18 ,  F02K3/115

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 (99) that delivers air into a bypass duct and into a core engine. A heat exchanger (104) 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 (116) 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（99）。 热交换器（104）定位在旁通管道内并且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（116）以吸引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。

公开(公告)号：EP3105438A1

公开(公告)日：2016-12-21

申请号：EP15749596.1

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  PAPA, Federico

IPC: F02C7/18 ,  F02C7/32

CPC classification number: F01D17/145 ,  F01D25/26 ,  F02C3/04 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/608 ,  Y02T50/675

Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

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：EP3054126A1

公开(公告)日：2016-08-10

申请号：EP16154939.9

申请日：2016-02-09

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  HILL, James D. ,  ACKERMAN, William K. ,  CHANDLER, Jesse M.

IPC: F02C7/14 ,  F28D1/047 ,  F02K3/06 ,  F02C6/08 ,  F01D25/12 ,  F02C7/16

CPC classification number: F02C7/14 ,  F01D25/12 ,  F02C6/08 ,  F02C7/16 ,  F02K3/06 ,  F05D2250/185 ,  F05D2260/213 ,  F28D1/03 ,  F28D7/082 ,  Y02T50/676

Abstract: A cooling system (100) for a gas turbine engine (10) includes a main fluid duct (106) with an inlet (112) and an outlet (110), a first heat exchanger (102), and a second heat exchanger (104). The first and second heat exchanger (102,104) are both in fluid communication with the main fluid duct (106) between the inlet (112) and the outlet (110) of the main fluid duct (106), and the second heat exchanger (104) is downstream of the first heat exchanger (102) for controlling heat transfer between compressor high-pressure bleed air traversing the first heat exchanger (102) and low-pressure ambient air traversing the second heat exchanger (104).

Abstract translation: 用于燃气涡轮发动机（10）的冷却系统（100）包括具有入口（112）和出口（110）的主流体管道（106），第一热交换器（102）和第二热交换器（104） ）。 第一和第二热交换器（102,104）都与主流体管道（106）的入口（112）和出口（110）之间的主流体管道（106）流体连通，并且第二热交换器（104） ）在第一热交换器（102）的下游，用于控制穿过第一热交换器（102）的压缩机高压排放空气与穿过第二热交换器（104）的低压环境空气之间的热传递。

公开(公告)号：EP2943670A1

公开(公告)日：2015-11-18

申请号：EP13870617.1

申请日：2013-06-04

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

IPC: F02C7/36 ,  F02C7/32

CPC classification number: F02C7/36 ,  B64D27/10 ,  B64D2027/005 ,  F02C7/06 ,  F02C7/20 ,  F02C7/32 ,  F02K3/072 ,  F05D2240/90 ,  Y02T50/66

Abstract: A gas turbine engine has a first shaft including a first turbine rotor, and a second shaft including a second turbine rotor disposed downstream of the first turbine rotor. A third shaft includes a propulsor turbine positioned downstream of the second turbine rotor for driving a propeller. A mount ring is secured between the second turbine rotor and the propeller.

公开(公告)号：EP2902608A1

公开(公告)日：2015-08-05

申请号：EP15152453.5

申请日：2015-01-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

IPC: F02K3/062 ,  F02K3/072 ,  F02C7/36

CPC classification number: F02K1/66 ,  F02C7/36 ,  F02K3/062 ,  F02K3/072 ,  F05D2260/4031

Abstract: A gas turbine engine (20) comprises an outer shroud (22). An inner core housing (24) is positioned radially inwardly of the outer shroud (22), and has a core engine including at least one compressor rotor (28) and at least one turbine rotor (32). A combustor section (40) is intermediate the at least one compressor rotor (28) and the at least one turbine rotor. A fan turbine is positioned downstream of the at least one turbine rotor (32). The fan turbine (44) drives a gear reduction (42) to, in turn, drive at least one fan blade (46,48) positioned radially inwardly of the outer shroud (22).

Abstract translation: 燃气涡轮发动机（20）包括外罩（22）。 内芯壳体（24）定位在外护罩（22）的径向内侧，并且具有包括至少一个压缩机转子（28）和至少一个涡轮转子（32）的核心发动机。 燃烧器部分（40）位于所述至少一个压缩机转子（28）和所述至少一个涡轮机转子之间。 风扇涡轮机位于至少一个涡轮机转子（32）的下游。 风扇涡轮（44）驱动齿轮减速器（42），从而驱动位于外罩（22）的径向内侧的至少一个风扇叶片（46,48）。

公开(公告)号：EP3044442B1

公开(公告)日：2020-03-04

申请号：EP14860946.4

申请日：2014-08-19

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

IPC: F02C7/20 ,  F01D9/04 ,  F01D25/24 ,  F01D25/28 ,  F02K1/82

公开(公告)号：EP3366589B1

公开(公告)日：2020-01-22

申请号：EP18158420.2

申请日：2018-02-23

Applicant: United Technologies Corporation

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

IPC: B64D27/14 ,  B64D27/20 ,  B64D27/26