公开(公告)号：EP3179034A1

公开(公告)日：2017-06-14

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

Abstract: A gas turbine engine (80) comprises a compressor section (82) and a turbine section (93), with the turbine section having a first stage blade row (91) and a downstream blade row (110). A higher pressure tap (86) is tapped from a higher pressure first location in the compressor (82). A lower pressure tap (88) is tapped from a lower pressure location in the compressor (82) which is at a lower pressure than the first location. The higher pressure tap (86) passes through a heat exchanger (84), and then is delivered to cool the first stage blade row (91) in the turbine section (93). The lower pressure tap (84) is delivered to at least partially cool the downstream blade row (110).

Abstract translation: 燃气涡轮发动机（80）包括压缩机部分（82）和涡轮部分（93），涡轮部分具有第一级叶片排（91）和下游叶片排（110）。 高压分接头（86）从压缩机（82）中的较高压力第一位置分接。 低压分接头（88）从压缩机（82）中处于比第一位置低的压力下的较低压力位置分接。 高压水龙头86穿过热交换器84，然后被输送以冷却涡轮机部分93中的第一级叶片排91。 输送低压分接头（84）以至少部分冷却下游叶片排（110）。

公开(公告)号：EP3163062A1

公开(公告)日：2017-05-03

申请号：EP16196567.8

申请日：2016-10-31

Applicant: United Technologies Corporation

Inventor： SCHWARZ, Frederick M. ,  KUPRATIS, Daniel Bernard ,  MERRY, Brian D. ,  SUCIU, Gabriel L. ,  ACKERMANN, William K.

IPC: F02K3/06

CPC classification number: F02K3/06 ,  F05D2260/40311

Abstract: A turbine section (28) of a gas turbine engine (20) includes a fan drive turbine section (46), and a second turbine section (54). The fan drive turbine section (46) has a first exit area (401) at a first exit point and is configured to rotate at a first speed. The second turbine section (54) has a second exit area at a second exit point (400) and is configured to rotate at a second speed, which is faster than the first speed.

Abstract translation: 燃气涡轮发动机（20）的涡轮部段（28）包括风扇驱动涡轮部段（46）和第二涡轮部段（54）。 风扇驱动涡轮部段（46）在第一出口点处具有第一出口区域（401）并且构造成以第一速度旋转。 第二涡轮部段（54）在第二出口点（400）处具有第二出口区域并且构造成以比第一速度更快的第二速度旋转。

公开(公告)号：EP3109437A1

公开(公告)日：2016-12-28

申请号：EP16175552.5

申请日：2016-06-21

Applicant: United Technologies Corporation

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

IPC: F02C6/08 ,  F02C7/12 ,  F02C9/18

CPC classification number: F02C6/08 ,  F02C7/12 ,  F02C9/18 ,  Y02T50/675

Abstract: A gas turbine engine comprises a main compressor section (24) having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section (28) has a high pressure turbine (117). A tap (110) taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger (112) and then to a cooling compressor (114), which compresses air downstream of the heat exchanger (112), and delivers air into the high pressure turbine (117). The cooling compressor (114) rotates at a speed proportional to a speed of at least one rotor in the turbine section (28). The cooling compressor (114) is allowed to rotate at a speed that is not proportional to a speed of the at least one rotor under certain conditions. An intercooling system for a gas turbine engine is also disclosed.

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（24）。 涡轮机部分（28）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，使抽头的空气通过热交换器（112），然后到达冷却压缩机（114），该冷却压缩机压缩热交换器 （112），并且将空气输送到高压涡轮机（117）中。 冷却压缩机（114）以与涡轮部（28）中的至少一个转子的速度成比例的速度旋转。 允许冷却压缩机（114）在一定条件下以与至少一个转子的速度成比例的速度旋转。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

公开(公告)号：EP3109436A1

公开(公告)日：2016-12-28

申请号：EP16175533.5

申请日：2016-06-21

Applicant: United Technologies Corporation

Inventor： ZELESKY, Mark F. ,  SUCIU, Gabriel L. ,  MERRY, Brian D.

IPC: F02C6/08 ,  F02C7/18

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 (117). The cooling compressor includes a downstream connection that delivers discharge pressure air to an upstream location in the high pressure turbine and a second tap (160) from an intermediate pressure location within the cooling compressor. The second tap (160) is connected to a downstream location within the high pressure turbine (117). An intercooling system for a gas turbine engine is also disclosed.

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（117）中。 冷却压缩机包括将排出压力空气输送到高压涡轮机中的上游位置并且从冷却压缩机内的中间压力位置输送第二分接头（160）的下游连接。 第二分接头（160）连接到高压涡轮机（117）内的下游位置。 还公开了一种用于燃气涡轮发动机的中间冷却系统。

公开(公告)号：EP3054091A1

公开(公告)日：2016-08-10

申请号：EP16154312.9

申请日：2016-02-04

Applicant: United Technologies Corporation

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

IPC: F01D5/08 ,  F02C3/107

CPC classification number: F02C7/18 ,  F01D5/08 ,  F01D5/081 ,  F01D5/082 ,  F01D5/088 ,  F02C3/10 ,  F02C3/107 ,  F05D2220/3217 ,  F05D2220/3219 ,  F05D2250/411

Abstract: A gas turbine engine (20) according to an exemplary aspect of the present disclosure includes, among other things, a first compressor (44) having a first overall pressure ratio, and a second compressor (52) having a second overall pressure ratio. A ratio of the first overall pressure ratio to the second overall pressure ratio is greater than or equal to about 2.0. Further, a section of the gas turbine engine includes a thermally isolated area (78).

Abstract translation: 根据本公开示例性方面的燃气涡轮发动机（20）包括具有第一总压力比的第一压缩机（44）和具有第二总压力比的第二压缩机（52）。 第一总压力比与第二总压力比的比率大于或等于约2.0。 此外，燃气涡轮发动机的一部分包括热隔离区域（78）。

公开(公告)号：EP3045681A1

公开(公告)日：2016-07-20

申请号：EP16151310.6

申请日：2016-01-14

Applicant: United Technologies Corporation

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

IPC: F01D25/12 ,  F02C7/18 ,  F02C9/18 ,  F01D5/08

CPC classification number: F02C9/18 ,  F01D5/082 ,  F01D5/084 ,  F01D5/088 ,  F01D25/12 ,  F02C3/10 ,  F02C7/18 ,  F05D2250/322 ,  F05D2260/20 ,  Y02T50/676

Abstract: A gas turbine engine (20) includes a turbine section (54) that includes a turbine rotor (132) arranged in a plenum (180). A compressor section (54) includes a compressor rotor assembly (60) that has spaced apart inner and outer portions (71, 73) that provide an axially extending cooling channel (84). Compressor blades (78) extend radially outward from the outer portion (73) which provides an inner core flow path (C). A rotor spoke is configured to receive a first cooling flow (76) and fluidly connect the outer portion (73) to the cooling channel (84). The compressor rotor assembly (60) has a coolant exit (90) that is in fluid communication with the cooling channel (84). The compressor rotor assembly (60) is configured to communicate the first cooling flow (76) to the turbine rotor (132). A bleed source (91) is configured to provide a second cooling flow (190). A combustor section (56) includes an injector (120) in fluid communication with the bleed source (91). The tangential onboard injector (120) is configured to communicate the second cooling flow (190) to the turbine rotor (132).

Abstract translation: 燃气涡轮发动机（20）包括涡轮部分（54），其包括布置在增压室（180）中的涡轮机转子（132）。 压缩机部分（54）包括压缩机转子组件（60），其具有间隔开的内部和外部部分（71,73），其提供轴向延伸的冷却通道（84）。 压缩机叶片（78）从提供内芯流路（C）的外部部分（73）径向向外延伸。 转子轮辐构造成接收第一冷却流（76）并且将外部部分（73）流体连接到冷却通道（84）。 压缩机转子组件（60）具有与冷却通道（84）流体连通的冷却剂出口（90）。 压缩机转子组件（60）构造成将第一冷却流（76）连通到涡轮转子（132）。 排放源（91）构造成提供第二冷却流（190）。 燃烧器部分（56）包括与排出源（91）流体连通的喷射器（120）。 切向车载喷射器（120）构造成将第二冷却流（190）传递到涡轮转子（132）。

公开(公告)号：EP3027864A1

公开(公告)日：2016-06-08

申请号：EP14849357.0

申请日：2014-06-19

Applicant: United Technologies Corporation

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

IPC: F02C1/06 ,  F02K3/02

CPC classification number: F02C7/36 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F05D2260/40311

Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.

Abstract translation: 燃气涡轮发动机包括：芯壳体，其包括分别设置入口壳体流路和中间壳体流路的入口壳体和中间壳体。 入口箱内设有齿轮架构。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分轴向布置在入口壳体流动路径和中间壳体流动路径之间。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。

公开(公告)号：EP3009596A1

公开(公告)日：2016-04-20

申请号：EP15185751.3

申请日：2015-09-17

Applicant: United Technologies Corporation

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

IPC: F01D5/06 ,  F01D5/08

CPC classification number: F01D5/18 ,  F01D5/066 ,  F01D5/084 ,  F01D5/085 ,  F04D29/321 ,  F04D29/584 ,  F05D2260/205 ,  F05D2260/221 ,  Y02T50/671 ,  Y02T50/676

Abstract: A rotor assembly of a gas turbine engine 20 may be spoked and includes a rotor 58 and a shell 110. The rotor 58 has a rotor disk 64 and a plurality of blades 62 each having a platform 74 attached to the rotor disk 64 and with a first channel 80 defined radially between the platforms 74 and the rotor disk 64. The shell 110 projects aft of the rotor 58 and includes inner and outer walls 112,114 with a passage 116 defined therebetween. The passage 116 is in fluid communication with the first channel 80 and, together, form part of a secondary flowpath S for cooling of adjacent components. The rotor assembly may further include a structure 118 located radially inward of the rotor disk 64 and shell 110. The structure 118 defines a supply conduit 126 for flowing air from the passage 80 and into a rotor bore 122 defined at least in part by adjacent rotor disks 58. The entering air, being pre-heated when flowing through the channel 80 and passage 116, warms the bore 122 and reduces thermal gradients, thus thermal fatigue, across the rotor disk 58.

Abstract translation: 燃气涡轮发动机20的转子组件可以被喷射并且包括转子58和壳体110.转子58具有转子盘64和多个叶片62，每个叶片62具有附接到转子盘64的平台74，并且具有 第一通道80在平台74和转子盘64之间径向地限定。壳体110突出转子58的后方，并且包括内壁112和外壁112，其间限定有通道116。 通道116与第一通道80流体连通，并且一起形成用于冷却相邻部件的次级流路S的一部分。 转子组件还可以包括位于转子盘64和壳体110的径向内侧的结构118.结构118限定用于将空气从通道80流入至转子孔122中的供应管道126，转子孔122至少部分地由相邻转子 在流过通道80和通道116时被预热的进入空气加热孔122并降低横跨转子盘58的热梯度，从而降低热疲劳。

公开(公告)号：EP2969758A1

公开(公告)日：2016-01-20

申请号：EP14779843.3

申请日：2014-03-11

Applicant: United Technologies Corporation

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

IPC: B64D27/10 ,  F02C7/20 ,  F01D15/02

CPC classification number: F01D25/162 ,  B64D27/18 ,  B64D2027/264 ,  F01D25/28 ,  F02C7/20 ,  Y02T50/44 ,  Y02T50/671

Abstract: A mounting system for a gas turbine engine includes a low pressure turbine section, a first bearing, a mid-turbine frame, and a rear mount. The first bearing supports at least a portion of the low pressure turbine section. The mid-turbine frame supports the first bearing. The rear mount is connected to the mid-turbine frame and is configured to react loads from the gas turbine engine.

Abstract translation: 用于燃气涡轮发动机的安装系统包括低压涡轮段，第一轴承，中间涡轮机框架和后部安装件。 第一轴承支撑低压涡轮部分的至少一部分。 中间涡轮机框架支撑第一轴承。 后部安装件连接到中间涡轮机框架并且构造成对来自燃气涡轮发动机的负载作出反应。

公开(公告)号：EP2937509A1

公开(公告)日：2015-10-28

申请号：EP15166722.7

申请日：2012-12-26

Applicant: United Technologies Corporation

Inventor： HASEL, Karl L. ,  STAUBACH, Joseph B. ,  MERRY, Brian D. ,  SUCIU, Gabriel L. ,  DYE, Christopher M.

IPC: F01D1/04 ,  F02C3/107 ,  F02K3/06 ,  F01D13/00

CPC classification number: F02C3/107 ,  F02K3/06

Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.

Abstract translation: 燃气涡轮发动机包括风扇部分，构造成驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 由所述低压压缩机部分上的压力比和跨过所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分两端的压力比在大约 3和大约8之间，而高压压缩机部分的压力比在大约7和大约15之间。