公开(公告)号：EP3091210B1

公开(公告)日：2018-07-04

申请号：EP16168495.6

申请日：2016-05-05

Applicant: United Technologies Corporation

Inventor： FEULNER, Matthew R. ,  MERRY, Brian D. ,  CHANDLER, Jesse M. ,  SUCIU, Gabriel L. ,  STAUBACH, Joseph B.

IPC: F02C6/08 ,  F02C9/18 ,  F04D27/02 ,  F04D29/52 ,  F02C7/052 ,  F01D25/32 ,  F04D29/70

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 (24) of a gas turbine engine (20) includes a bleed port (201) having a flow splitter (210) therein so as to define a downstream bleed channel (207) having a downstream inlet (205) and an upstream bleed channel (203) having an upstream inlet (271) that is positioned radially outward from the downstream inlet (205).

公开(公告)号：EP3109435B1

公开(公告)日：2018-03-07

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).

公开(公告)号：EP3276151A1

公开(公告)日：2018-01-31

申请号：EP17182545.8

申请日：2017-07-21

Applicant: United Technologies Corporation

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

IPC: F02K1/72

CPC classification number: F02K1/70 ,  F02K1/72 ,  F02K3/06 ,  F02K3/062 ,  F05D2220/323 ,  F05D2230/72

Abstract: A gas turbine engine (20) has a core engine (36) and a fan (42). A pivoting D-door structure includes a pivoting inner D-door portion (72) and a pivoting outer D-door portion (74), which is axially moveable relative to the inner D-door portion (72) between a stowed and thrust reverse position. A fan case (70) surrounds the fan (42). Cascades (76) are axially moveable along with the outer D-door portion (74) between a stowed and a thrust reverse position. Structure supporting the cascades (76) is mounted on the fan case (70).

Abstract translation: 燃气涡轮发动机（20）具有核心发动机（36）和风扇（42）。 一种枢转D型门结构包括枢转内D门部分（72）和枢转外D型门部分（74），所述外D型门部分相对于内D门部分（72）在收起和推力反向之间轴向移动 位置。 风扇箱（70）围绕风扇（42）。 叶栅（76）可与外D形门部分（74）一起在收起位置和推力反向位置之间轴向移动。 支撑级联结构（76）的结构安装在风扇壳体（70）上。

公开(公告)号：EP3260685A1

公开(公告)日：2017-12-27

申请号：EP17176946.6

申请日：2017-06-20

Applicant: United Technologies Corporation

Inventor： TAYLOR, Stephen H. ,  LENTS, Charles E. ,  SUCIU, Gabriel L. ,  MERRY, Brian D. ,  CHANDLER, Jesse M.

IPC: F02C6/08 ,  F02C9/18

Abstract: A gas turbine engine (20) includes a main engine compressor section (24). A booster compressor (72) changes a pressure of airflow received from the main engine compressor section (24) to a pressure desired for a pneumatic system (64). The booster compressor (72) is configured to operate at airflow conditions greater than a demand of the pneumatic system (64). An exhaust valve (82) controls airflow between an exhaust outlet (88) and an outlet passage (80) to the pneumatic system (64). The exhaust valve (82) is operable to exhaust airflow from the booster compressor (72) in excess of the demand of the pneumatic system (64). A bleed air system (62) for a gas turbine engine (20) and a method of controlling engine bleed airflow are also disclosed.

Abstract translation: 燃气涡轮发动机（20）包括主发动机压缩机部分（24）。 增压压缩机（72）将从主发动机压缩机部分（24）接收的气流压力改变为气动系统（64）所需的压力。 增压压缩机（72）构造成在大于气动系统（64）的需求的气流条件下操作。 排气阀（82）控制排气出口（88）和出气通道（80）之间的气流至气动系统（64）。 排气阀（82）可操作以排出超过气动系统（64）的需求的来自增压压缩机（72）的气流。 还公开了用于燃气涡轮发动机（20）的引气系统（62）和控制发动机引气流的方法。

公开(公告)号：EP3260684A1

公开(公告)日：2017-12-27

申请号：EP17176943.3

申请日：2017-06-20

Applicant: United Technologies Corporation

Inventor： TAYLOR, Stephen H. ,  LENTS, Charles E. ,  SUCIU, Gabriel L. ,  MERRY, Brian D. ,  CHANDLER, Jesse M.

IPC: F02C6/08 ,  F01D15/08 ,  F04D25/02 ,  F02C3/113 ,  F04D27/02

CPC classification number: F04D27/009 ,  F01D5/02 ,  F01D15/08 ,  F01D15/12 ,  F01D17/145 ,  F02C6/08 ,  F02C7/32 ,  F04D25/02 ,  F04D27/004 ,  F04D27/023 ,  F04D29/321 ,  F05D2220/32 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine (20) includes a main engine compressor section (24). A booster compressor (70) changing a pressure of airflow received from the main engine compressor section (24) to a pressure desired for a pneumatic system (64). The booster compressor (70) operates at airflow conditions greater than a demand by the pneumatic system (64). A speed change system (84) drives the booster compressor (70) at speeds corresponding to a demand of the pneumatic system (64). A bleed air system (62) for a gas turbine engine (20) and a method of controlling engine bleed airflow are also disclosed.

Abstract translation: 燃气涡轮发动机（20）包括主发动机压缩机部分（24）。 增压压缩机（70）将从主发动机压缩机部分（24）接收的气流压力改变为气动系统（64）所需的压力。 增压压缩机（70）在大于气动系统（64）的需求的气流条件下运行。 变速系统（84）以对应于气动系统（64）的需求的速度驱动增压压缩机（70）。 还公开了用于燃气涡轮发动机（20）的引气系统（62）和控制发动机引气流的方法。

公开(公告)号：EP3109438A1

公开(公告)日：2016-12-28

申请号：EP16175760.4

申请日：2016-06-22

Applicant: United Technologies Corporation

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

IPC: F02C6/08 ,  F02C7/141 ,  F02C7/18 ,  F02C9/18 ,  F02K3/115

Abstract: A gas turbine engine (12) comprises a main compressor section having a high pressure compressor (141) with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine (144). A first tap taps (126) air from at least one of the more upstream locations in the main compressor section, passing the tapped air through a first heat exchanger (122) and then to a cooling compressor (124). A second tap (140) 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 (144). The cooling compressor (124) is positioned downstream of the first heat exchanger (122), and upstream of a location where air from the first and second taps mix together.

Abstract translation: 燃气涡轮发动机（12）包括主压缩机部分，其具有具有下游最末端的高压压缩机（141）和更多的上游位置。 涡轮部分具有高压涡轮机（144）。 第一抽头从主压缩机部分中的上游位置中的至少一个抽头抽吸（126）空气，使抽头的空气通过第一热交换器（122），然后通到冷却压缩机（124）。 第二分接头（140）从比第一分接头的位置更靠近下游最端部的位置抽吸空气，并且第一和第二抽头混合在一起并被输送到高压涡轮机（144）中。 冷却压缩机124位于第一热交换器122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：EP3054127A1

公开(公告)日：2016-08-10

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

Abstract: A thermal management system (100) for a gas turbine engine includes a heat exchanger (102), an oil circuit (108), and a coolant circuit (110). The oil circuit (108) is in fluid communication with the heat exchanger (102). The coolant circuit (110) is in fluid communication with the heat exchanger (102) and in thermal communication with the oil circuit (108) through the heat exchanger (102) to return heat from the oil circuit (108) to a core flow path of a gas turbine engine (10) using a thermally neutral heat transfer fluid (TN HTF).

Abstract translation: 用于燃气涡轮发动机的热管理系统（100）包括热交换器（102），油回路（108）和冷却剂回路（110）。 油回路（108）与热交换器（102）流体连通。 冷却剂回路（110）与热交换器（102）流体连通并通过热交换器（102）与油回路（108）热连通，以将来自油回路（108）的热量返回至芯流道 使用热中性传热流体（TN HTF）的燃气涡轮发动机（10）。

公开(公告)号：EP2957746A1

公开(公告)日：2015-12-23

申请号：EP15171982.0

申请日：2015-06-12

Applicant: United Technologies Corporation

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

IPC: F02C9/18 ,  F01D9/06 ,  F01D25/12 ,  F02C7/141 ,  F02K9/40

CPC classification number: F02C9/18 ,  F01D9/065 ,  F02C7/185 ,  Y02T50/671 ,  Y02T50/675

Abstract: A gas turbine engine includes a compressor section having a plurality of compressor stages, a combustor, a turbine section having at least one stage, a compressor bleed structure disposed in one of the compressor stages to remove air therefrom, a heat exchanger having an input connected to the compressor bleed, and an output connected to an active cooling system of at least one turbine stage. The compressor stage in which the compressor bleed structure is disposed includes airflow at a pressure above a minimum pressure threshold and at a temperature above a maximum temperature threshold.

Abstract translation: 燃气涡轮发动机包括具有多个压缩机级的压缩机部分，燃烧器，具有至少一个级的涡轮部分，设置在其中一个压缩机级中的压缩机排放结构以从其中排出空气;具有输入连接的热交换器 压缩机排气，以及连接到至少一个涡轮机级的主动冷却系统的输出。 设置压缩机排气结构的压缩机级包括在高于最小压力阈值并且高于最大温度阈值的温度下的气流。

公开(公告)号：EP2952689A1

公开(公告)日：2015-12-09

申请号：EP15171030.8

申请日：2015-06-08

Applicant: United Technologies Corporation

Inventor： PACK, David R. ,  PARTYKA, Julian ,  HILL, James D. ,  SUCIU, Gabriel L. ,  DOLANSKY, Gregory M. ,  MERRY, Brian D.

IPC: F01D11/00

CPC classification number: F01D11/008 ,  F01D5/06 ,  F01D11/001 ,  F01D11/005 ,  F05D2220/32 ,  F05D2240/55 ,  Y02T50/671

Abstract: A seal segment (102) for a gas turbine engine (20) includes a first axial span (134) that extends between a first radial span (130) and a second radial span (132). A second axial span (136) extends between the first radial span (130) and the second radial span (132), the first radial span (130), the second radial span (132), the first axial span (134) and the second axial span (136) form a torque box. A plurality of seal segments (102) may be located between first and second rotor disks (68, 70).

Abstract translation: 用于燃气涡轮发动机（20）的密封段（102）包括在第一径向跨度（130）和第二径向跨度（132）之间延伸的第一轴向跨度（134）。 第二轴向跨度（136）在第一径向间距（130）和第二径向跨度（132）之间延伸，第一径向跨度（130），第二径向跨度（132），第一轴向跨度（134）和 第二轴向跨度（136）形成扭矩箱。 多个密封段（102）可以位于第一和第二转子盘（68,70）之间。

公开(公告)号：EP2952680A1

公开(公告)日：2015-12-09

申请号：EP15170704.9

申请日：2015-06-04

Applicant: United Technologies Corporation

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

IPC: F01D5/08 ,  F02C7/18 ,  F01D11/00 ,  F02C7/28

CPC classification number: F01D5/088 ,  F01D11/00 ,  F02C3/04 ,  F02C3/14 ,  F02C7/18 ,  F02C7/28 ,  F05D2220/32 ,  F05D2260/231 ,  Y02T50/676

Abstract: A gas turbine engine includes a turbine section (54) fluidly connected to a combustor (56) by a primary flow path (C). The turbine section (54) includes a first portion at a high pressure relative to a second portion. A thermally isolated cooling plenum (180) is positioned radially inward of the primary flow path (C). The cooling plenum (180) is defined by a forward wall (150), a shaft structure (170), an aft wall (160), and an inner diameter wall of the primary flow path (C). Air in the thermally isolated cooling plenum (180) is thermally isolated from air in the primary flow path (C). At least one cooling air system is operable to provide cooling air to the thermally isolated cooling plenum (180).

Abstract translation: 燃气涡轮发动机包括通过主流路（C）流体连接到燃烧器（56）的涡轮部分（54）。 涡轮部分（54）包括相对于第二部分处于高压的第一部分。 隔热冷却室（180）位于主流路（C）的径向内侧。 冷却室（180）由前壁（150），轴结构（170），后壁（160）和主流路（C）的内径壁限定。 热隔离冷却室（180）中的空气与主流路（C）中的空气热隔离。 至少一个冷却空气系统可操作以向热隔离的冷却通风室（180）提供冷却空气。