公开(公告)号：EP3260686A1

公开(公告)日：2017-12-27

申请号：EP17176981.3

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 ,  F02C7/18 ,  F02C7/32 ,  F01D25/12 ,  F02C9/18

CPC classification number: F02C9/24 ,  F01D25/12 ,  F02C3/13 ,  F02C6/08 ,  F02C7/185 ,  F02C7/32 ,  F02C9/18 ,  F02K3/06 ,  F05D2270/301 ,  Y02T50/675

Abstract: A gas turbine engine (20) includes a main compressor section (24). A booster compressor (72) includes an inlet (74) and an outlet (76). The inlet (74) receives airflow from the main compressor section (24) and the outlet (76) provides airflow to a pneumatic system (64). A recirculation passage (78) is between the inlet (74) and the outlet (76). A flow splitter valve (80) controls airflow between the outlet (76) and the inlet (74) through the recirculation passage (78) for controlling airflow to the pneumatic system (64) based on airflow output from the booster compressor (72). A bleed air system (100) 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）包括主压缩机部分（24）。 增压压缩机（72）包括入口（74）和出口（76）。 入口（74）接收来自主压缩机部分（24）的气流并且出口（76）将气流提供给气动系统（64）。 再循环通道（78）位于入口（74）和出口（76）之间。 分流阀（80）通过再循环通道（78）控制出口（76）和入口（74）之间的气流，用于基于从增压压缩机（72）输出的气流来控制流向气动系统（64）的气流。 还公开了用于燃气涡轮发动机（20）的引气系统（100）和控制发动机引气流的方法。

公开(公告)号：EP3112591B1

公开(公告)日：2017-12-27

申请号：EP16177557.2

申请日：2016-07-01

Applicant: United Technologies Corporation

Inventor： EPSTEIN, Alan H. ,  SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

IPC: F01D5/14 ,  F01D5/22 ,  F04D29/16 ,  F04D29/32 ,  F01D11/02 ,  F02K3/065 ,  F01D5/30 ,  F02K3/02

CPC classification number: F01D5/141 ,  F01D5/14 ,  F01D5/225 ,  F01D5/303 ,  F01D11/02 ,  F02K3/025 ,  F02K3/065 ,  F04D29/164 ,  F04D29/321 ,  Y02T50/671 ,  Y02T50/673

Abstract: A gas turbine engine compressor stage includes a rotor (70). Compressor blades (71) are supported by the rotor (70). The blades (71) include an inner flow path surface each supporting an airfoil that has a chord (80) that extends radially along a span (78) to a tip. A shroud (82) is supported at the tip and provides an outer flow path surface. The shroud (82) provides a noncontiguous ring about the compressor stage.

公开(公告)号：EP3241997A1

公开(公告)日：2017-11-08

申请号：EP17162883.7

申请日：2017-03-24

Applicant: United Technologies Corporation

Inventor： BIFULCO, Anthony R. ,  SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

IPC: F01D9/04 ,  F01D17/12 ,  F01D25/34

CPC classification number: F01D17/162 ,  F01D9/04 ,  F01D17/12 ,  F01D25/34 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/40 ,  F16H19/04 ,  F16H49/001 ,  Y02T50/671

Abstract: An actuator system (118) including a harmonic drive (122) operable to drive a variable vane system (100) of a gas turbine engine (20).

Abstract translation: 一种致动器系统（118），包括可操作以驱动燃气涡轮发动机（20）的可变叶片系统（100）的谐波驱动器（122）。

公开(公告)号：EP3228822A1

公开(公告)日：2017-10-11

申请号：EP17162813.4

申请日：2017-03-24

Applicant: United Technologies Corporation

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

IPC: F01D9/04 ,  F01D17/12 ,  F01D17/14 ,  F01D17/16 ,  F01D25/34

CPC classification number: F01D17/162 ,  F01D9/04 ,  F01D9/042 ,  F01D17/12 ,  F01D17/14 ,  F01D25/34 ,  F05D2220/32 ,  F05D2240/128 ,  F16H49/001 ,  Y02T50/671 ,  Y02T50/673

Abstract: A variable vane system includes an actuator, a harmonic drive, a unison ring (306) and a multiple of variable vanes. The harmonic drive is driven by the actuator. The unison ring (306) is driven by the harmonic drive and includes a multiple of pins (304). The multiple of variable vanes is driven by the unison ring (306) and each of the vanes is connected to the unison ring (306) through a drive arm (300) including a slot which receives one of the pins (304) to accommodate axial motion of the unison ring (306).

Abstract translation: 可变叶片系统包括致动器，谐波驱动器，协调环（306）和多个可变叶片。 谐波传动由执行机构驱动。 协调环（306）由谐波驱动器驱动并且包括多个销（304）。 多个可变叶片由协调环（306）驱动并且每个叶片通过驱动臂（300）连接到协调环（306），驱动臂包括容纳销（304）中的一个以容纳轴向 协调环（306）的运动。

公开(公告)号：EP3222823A2

公开(公告)日：2017-09-27

申请号：EP17162778.9

申请日：2017-03-24

Applicant: United Technologies Corporation

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

IPC: F01D9/04 ,  F01D17/12 ,  F01D17/14 ,  F01D25/34

Abstract: An actuator system (118E) including a harmonic drive (122) operable to drive a variable vane system (100) of a gas turbine engine (20). A multi-planar drive gear set (200) is driven by the harmonic drive (122) and drives first and second actuator gears (210,214) of first and second variable vane stages (212,216).

Abstract translation: 一种致动器系统（118E），包括可操作以驱动燃气涡轮发动机（20）的可变叶片系统（100）的谐波驱动器（122）。 多谐振动驱动齿轮组（200）由谐波驱动器（122）驱动并驱动第一和第二可变叶片级（212,216）的第一和第二致动器齿轮（210,214）。

公开(公告)号：EP3165451A1

公开(公告)日：2017-05-10

申请号：EP16196921.7

申请日：2016-11-02

Applicant: United Technologies Corporation

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

IPC: B64C11/14 ,  F02K3/06

CPC classification number: F02C7/14 ,  B64C11/14 ,  F01D5/12 ,  F01D9/041 ,  F01D25/12 ,  F02C3/04 ,  F02C7/04 ,  F02C7/18 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213

Abstract: A gas turbine engine (10) has a nose cone (80), a fan for delivering air into a bypass duct as bypass flow, and into a core engine to be delivered to a compressor. The nose cone (80) includes a vent (84) to receive air and deliver the air across a heat exchanger (86), which receives a fluid to be cooled. The air from the vent (84) is delivered to an outlet (104) downstream of the heat exchanger (86), such that a majority of the air being delivered to the outlet (104) becomes part of the bypass flow.

Abstract translation: 燃气涡轮发动机（10）具有前锥体（80），用于将空气作为旁路流输送到旁路管道中的风扇以及输送到压缩机的核心发动机中。 鼻锥（80）包括通风口（84），以接收空气并通过热交换器（86）输送空气，该热交换器接收待冷却的流体。 来自通风口（84）的空气被输送到热交换器（86）下游的出口（104），使得输送到出口（104）的大部分空气成为旁路流的一部分。

公开(公告)号：EP3121411A1

公开(公告)日：2017-01-25

申请号：EP16180657.5

申请日：2016-07-21

Applicant: United Technologies Corporation

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

IPC: F02C6/08 ,  F02C9/18 ,  F02C7/18

CPC classification number: F02C6/08 ,  F02C7/185 ,  F02C9/18 ,  F05D2220/3219 ,  F05D2260/211 ,  F05D2260/213 ,  Y02T50/671 ,  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. A tap taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger also receives air to be delivered to an aircraft cabin. 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。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后通过冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 热交换器还接收要传送到飞机机舱的空气。 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：EP3108129A1

公开(公告)日：2016-12-28

申请号：EP14882642.3

申请日：2014-09-18

Applicant: United Technologies Corporation

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

IPC: F02C7/057 ,  F01D17/00 ,  F01D25/24 ,  F02C7/24

Abstract: A compressor intermediate case for a gas turbine engine includes a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure. Each strut of the plurality of intermediate case struts includes a leading edge. A turning scoop is disposed at the leading edge of each strut of the plurality of intermediate case struts. A plurality of diffusers extends radially outwardly from the compressor intermediate case so that each diffuser of the plurality of diffusers engages with a corresponding turning scoop. A substantially annular structural fire wall extends radially outwardly from the compressor intermediate case. An environmental control system manifold is disposed on the compressor intermediate case. The environmental control system manifold includes an exit port.

Abstract translation: 用于燃气涡轮发动机的压缩机中间壳体包括将压缩机中间壳体连接到内部发动机结构的多个中间壳体支柱。 多个中间壳支柱的每个支柱包括前缘。 在多个中间壳支柱的每个支柱的前缘设置有转向勺。 多个扩散器从压缩机中间壳体径向向外延伸，使得多个扩散器的每个扩散器与相应的转向勺接合。 大致环形的结构防火墙从压缩机中间壳径向向外延伸。 环境控制系统歧管设置在压缩机中间壳体上。 环境控制系统歧管包括出口。

公开(公告)号：EP3091210A1

公开(公告)日：2016-11-09

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).

Abstract translation: 燃气涡轮发动机（20）的压缩机部分（24）包括具有分流器（210），一个排出口（201）。其中，以限定具有下游入口（205）的下游泄放通道（207），并在上游 流血信道（203）具有上游入口（271）确实是从下游入口（205）径向向外地定位。

公开(公告)号：EP3088685A1

公开(公告)日：2016-11-02

申请号：EP16165168.2

申请日：2016-04-13

Applicant: United Technologies Corporation

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

IPC: F01D25/12

Abstract: A thermal management system (100) and method (200) of circulating air in a gas turbine engine (20) are disclosed. The thermal management system includes a nose cone (102) having an aperture (104) communicating air to an interior space (106) of the nose cone and a fan blade (112) coupled to the nose cone and having a blade passage (114), wherein the nose cone rotates with the fan blade to circulate air from the aperture to the blade passage.

Abstract translation: 在燃气涡轮发动机（20）中循环的空气的热管理系统（100）和方法（200）是圆盘游离缺失。 所述热管理系统包括具有孔（104）连通的空气耦合到所述鼻锥鼻锥和风扇叶片（112）的内部空间（106）和具有叶片通道中的鼻锥（102）（114） ，worin鼻锥体与所述风扇叶片旋转，以从孔到叶片通道使空气循环。