公开(公告)号：US09909497B2

公开(公告)日：2018-03-06

申请号：US14706748

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Matthew R. Feulner ,  Brian D. Merry ,  Jesse M. Chandler ,  Gabriel L. Suciu ,  Joseph B. Staubach

IPC: F02C6/08 ,  F04D27/02 ,  F02C7/052 ,  F04D29/52 ,  F04D29/70 ,  F02C3/10 ,  F02K3/06

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 of a gas turbine engine includes a bleed port having a flow splitter therein so as to define a downstream bleed channel having a downstream inlet and an upstream bleed channel having an upstream inlet that is positioned radially outward from the downstream inlet.

公开(公告)号：US20180038315A1

公开(公告)日：2018-02-08

申请号：US15230590

申请日：2016-08-08

Applicant: United Technologies Corporation

Inventor： Wesley K. Lord ,  Jesse M. Chandler ,  Gabriel L. Suciu

IPC: F02K3/00 ,  B64D33/04 ,  B64D33/02 ,  F02K1/52 ,  B64D27/14

CPC classification number: F02K3/00 ,  B64D27/14 ,  B64D33/02 ,  B64D33/04 ,  B64D35/04 ,  F02K1/52 ,  F02K3/062 ,  F05D2250/312

Abstract: A gas turbine engine includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A propulsor section aft of the core engine is driven by the turbine section. An exhaust duct routing exhaust gases around the propulsor section. The exhaust duct includes an inlet forward of the propulsor section, an outlet aft of the turbine section and a passageway between the inlet and the outlet. An aircraft and exhaust duct are also disclosed.

公开(公告)号：US20170363099A1

公开(公告)日：2017-12-21

申请号：US15186739

申请日：2016-06-20

Applicant: United Technologies Corporation

Inventor： Stephen H. Taylor ,  Charles E. Lents ,  Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler

IPC: F04D27/02 ,  F01D15/08 ,  F01D17/14 ,  F04D29/32 ,  F01D5/02 ,  F04D25/06 ,  F04D27/00 ,  F01D15/12

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

公开(公告)号：US20170363014A1

公开(公告)日：2017-12-21

申请号：US15186722

申请日：2016-06-20

Applicant: United Technologies Corporation

Inventor： Stephen H. Taylor ,  Charles E. Lents ,  Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler

IPC: F02C9/24 ,  F02C9/18 ,  F02C6/08 ,  F02K3/06 ,  F02C3/13

Abstract: A gas turbine engine includes a main compressor section. A booster compressor includes an inlet and an outlet. The inlet receives airflow from the main compressor section and the outlet provides airflow to a pneumatic system. A recirculation passage is between the inlet and the outlet. A flow splitter valve controls airflow between the outlet and the inlet through the recirculation passage for controlling airflow to the pneumatic system based on airflow output from the booster compressor. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.

公开(公告)号：US09670876B2

公开(公告)日：2017-06-06

申请号：US14184335

申请日：2014-02-19

Applicant: United Technologies Corporation

Inventor： Jesse M. Chandler ,  Gabriel L. Suciu

IPC: F02K1/72 ,  F02K1/60 ,  F02K1/62 ,  F02K1/64 ,  B64D29/00 ,  B23P19/04 ,  F02K1/76

CPC classification number: F02K1/763 ,  B23P19/04 ,  B64D29/00 ,  B64D33/04 ,  F02K1/60 ,  F02K1/605 ,  F02K1/62 ,  F02K1/64 ,  F02K1/72 ,  F05D2260/50 ,  Y10T29/49229

Abstract: A pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a first sliding rail. A second tandem pivot door subassembly is included comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a second sliding rail.

公开(公告)号：US09573695B2

公开(公告)日：2017-02-21

申请号：US14187032

申请日：2014-02-21

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F01D25/28 ,  B64D29/06 ,  F01D9/02 ,  F01D25/24

CPC classification number: B64D29/06 ,  F01D9/02 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/128 ,  F05D2240/1281 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2240/91 ,  F05D2250/192 ,  F05D2250/292 ,  F05D2250/294 ,  F05D2250/34 ,  F05D2250/75 ,  F05D2260/96 ,  Y10T29/49721

Abstract: A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon portion and extends in the aft direction from the stationary portion. A second annular portion is positioned aft of the first portion and coupled to the rail, the second portion being movable along an engine core centerline between a closed position and an open position, wherein the second annular portion is configured to engage with the first annular portion in the closed position to provide access to an engine core. The second annular portion includes a nozzle plug.

Abstract translation: 燃气涡轮发动机包括静止的第一环形部分，并适于部分地围绕发动机芯。 第一环形部分包括前挂架连接部分。 轨道连接到前挂架部分并且在后方向上从固定部分延伸。 第二环形部分位于第一部分的后部并且联接到轨道，第二部分可沿着发动机芯心中心线在关闭位置和打开位置之间移动，其中第二环形部分构造成与第一环形部分 在关闭位置以提供对发动机芯的通路。 第二环形部分包括喷嘴塞。

公开(公告)号：US20160369706A1

公开(公告)日：2016-12-22

申请号：US14745606

申请日：2015-06-22

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler

IPC: F02C9/18 ,  F02C7/14

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 that delivers air into a bypass duct and into a core engine. A heat exchanger 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 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。 热交换器定位在旁路管道内，并从与燃气涡轮发动机相关联的部件接收待冷却的流体。 定位热交换器风扇以抽吸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：US20160326957A1

公开(公告)日：2016-11-10

申请号：US14706748

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Matthew R. Feulner ,  Brian D. Merry ,  Jesse M. Chandler ,  Gabriel L. Suciu ,  Joseph B. Staubach

IPC: F02C6/08 ,  F02K3/06 ,  F02C3/10

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 of a gas turbine engine includes a bleed port having a flow splitter therein so as to define a downstream bleed channel having a downstream inlet and an upstream bleed channel having an upstream inlet that is positioned radially outward from the downstream inlet.

Abstract translation: 燃气涡轮发动机的压缩机部分包括具有分流器的排出口，以便限定具有下游入口的下游排放通道和具有从下游入口径向向外定位的上游入口的上游排出通道。

公开(公告)号：US20160312711A1

公开(公告)日：2016-10-27

申请号：US14745567

申请日：2015-06-22

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry

IPC: F02C9/18 ,  F01D25/12 ,  F02K3/06 ,  F02C7/18 ,  F02C7/143 ,  F02C3/04

CPC classification number: F02C9/18 ,  F01D25/12 ,  F02C3/13 ,  F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02K3/06 ,  F04D29/5826 ,  F04D29/5833 ,  F05D2220/3212 ,  F05D2220/3219 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/606 ,  F05D2270/3062 ,  Y02T50/675

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

Abstract translation: 燃气涡轮发动机包括具有下游最末端的高压压缩机和更上游位置的主压缩机部分。 涡轮机部分具有高压涡轮机。 第一分接头从主压缩机部分中的更上游位置中的至少一个抽头抽吸空气，使抽头的空气通过第一热交换器，然后到冷却压缩机。 第二分接头从比第一抽头的位置更靠近下游最端部的位置敲击空气，并且第一和第二抽头混合在一起并被输送到高压涡轮机中。 冷却压缩机位于第一热交换器的下游，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：US20160238032A1

公开(公告)日：2016-08-18

申请号：US15023289

申请日：2014-08-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James D. Hill ,  Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F04D29/64 ,  F04D29/52 ,  F01D25/24 ,  F04D29/32

CPC classification number: F04D29/644 ,  B64D27/26 ,  B64D2027/264 ,  B64D2027/266 ,  F01D25/243 ,  F02C7/20 ,  F04D29/324 ,  F04D29/522 ,  F05D2220/32 ,  Y02T50/44 ,  Y02T50/671

Abstract: A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades. The inlet frame connects to an inlet end of the compressor case. The outlet frame connects to an outlet end of the compressor case portion at an end opposite the compressor case inlet end. An axially fore mounting structure of the mounting structure connects to the inlet frame. An axially aft mounting structure of the mounting structure connects to the outlet frame. A bridging structure of the mounting structure is offset from the compressor case and connects the fore and aft mounting structures, thereby bridging engine loads across the inlet and outlet frames to reduce load induced distortion of the compressor case portion.

Abstract translation: 用于燃气涡轮发动机的安装系统包括压缩机壳体部分，入口框架，出口框架和安装结构。 压缩机壳体部分容纳可旋转的压缩机叶片。 入口框架连接到压缩机壳体的入口端。 出口框架在与压缩机壳体入口端相对的端部处连接到压缩机壳体部分的出口端。 安装结构的轴向前部安装结构连接到入口框架。 安装结构的轴向后部安装结构连接到出口框架。 安装结构的桥接结构偏离压缩机壳体并且连接前后安装结构，从而跨过入口和出口框架桥接发动机负载，以减少压缩机壳体部分的负载引起的变形。