公开(公告)号：US11572928B2

公开(公告)日：2023-02-07

申请号：US16279358

申请日：2019-02-19

Applicant: United Technologies Corporation

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F16F7/09 ,  F28F9/02 ,  F02K3/115 ,  F02C7/141 ,  F04D29/58 ,  F28F9/24 ,  F28D7/06 ,  F16F7/08 ,  F28D1/047 ,  F28D21/00

Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbine engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.

公开(公告)号：US10830086B2

公开(公告)日：2020-11-10

申请号：US16038344

申请日：2018-07-18

Applicant: United Technologies Corporation

Inventor： William S. Pratt ,  Paul W. Duesler

IPC: F01D17/16 ,  F01D25/28

Abstract: A cam isolation system for a gas turbine engine compressor actuator includes a torque tube. The system also includes a cam bracket operatively coupled to an engine case structure, the cam bracket defining a slot. The system further includes an actuator bracket operatively coupled to the torque tube at a first end of the actuator bracket, the actuator bracket having a pin disposed within the slot of the cam bracket.

公开(公告)号：US20200240280A1

公开(公告)日：2020-07-30

申请号：US16260650

申请日：2019-01-29

Applicant: United Technologies Corporation

Inventor： Curtis C. Cowan ,  Paul W. Duesler ,  Michael R. Thomas ,  Michael Joseph Murphy

IPC: F01D11/00 ,  F02C7/28

Abstract: A slider seal assembly for a gas turbine engine, comprising a housing comprising an outer surface and an inner surface, and a recessed opening between the inner surface and the outer surface, wherein the inner surface of the housing includes a flat portion configured to match a receiver on an inner wall of a casing of the gas turbine engine; a seal plate received within the recessed opening and moveable relative to the housing; and a retaining ring configured to retain the seal plate adjacent the housing, the retaining ring includes a plurality of tabs configured to retain the seal plate adjacent the housing.

公开(公告)号：US20200173297A1

公开(公告)日：2020-06-04

申请号：US16207669

申请日：2018-12-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian Merry ,  Paul W. Duesler

IPC: F01D11/08

Abstract: A gas turbine engine may include a rotor overspeed protection (ROP) assembly. The ROP assembly may include an annular blade outer air seal (BOAS) assembly including a ROP segment. The ROP assembly may include a stator vane coupled with the BOAS assembly/. The stator vane may include a stator flange disposed about a forward edge portion of the stator vane. The ROP segment may include a ROP flange extending in an axially aft direction from a main body of the ROP segment toward the stator vane, wherein the ROP flange is disposed radially inward of the stator flange.

公开(公告)号：US10563582B2

公开(公告)日：2020-02-18

申请号：US15000618

申请日：2016-01-19

Applicant: United Technologies Corporation

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F28D1/053 ,  F28F13/06 ,  F28D1/04 ,  F02C7/14 ,  F28D21/00 ,  F28D1/02 ,  F02C3/04 ,  F02C7/36 ,  F02C9/18

Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.

公开(公告)号：US20200025023A1

公开(公告)日：2020-01-23

申请号：US16038344

申请日：2018-07-18

Applicant: United Technologies Corporation

Inventor： William S. Pratt ,  Paul W. Duesler

IPC: F01D17/16 ,  F01D25/28

Abstract: A cam isolation system for a gas turbine engine compressor actuator includes a torque tube. The system also includes a cam bracket operatively coupled to an engine case structure, the cam bracket defining a slot. The system further includes an actuator bracket operatively coupled to the torque tube at a first end of the actuator bracket, the actuator bracket having a pin disposed within the slot of the cam bracket.

公开(公告)号：US10151247B2

公开(公告)日：2018-12-11

申请号：US15074829

申请日：2016-03-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/32 ,  F28D7/06 ,  F02K3/115 ,  F02C6/08 ,  F02C7/141 ,  F02C7/18 ,  F04D29/58 ,  F28F9/00 ,  F28F9/02 ,  F28D21/00

Abstract: A heat exchanger (HEX) arrangement for cooling air in a gas turbine engine is provided. The HEX arrangement may include a heat exchanger coupled to a plurality of ducts comprising a hot-side inlet duct and a hot-side outlet duct. The hot-side outlet duct may be in fluid communication with a compressor section of the gas turbine engine and in mechanical communication with a diffuser case. The HEX arrangement may further include a plurality of supporting links coupled between the heat exchanger and the gas turbine engine for securing the heat exchanger relative to the gas turbine engine. The supporting links may comprise a statically determined system. A spring rate ratio of between 1% and 30% may exist between the plurality of ducts and the plurality of supporting links.

公开(公告)号：US10018120B2

公开(公告)日：2018-07-10

申请号：US14598252

申请日：2015-01-16

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Paul W. Duesler

IPC: F02C9/16 ,  F01D5/08 ,  F01D25/10 ,  F02C9/18 ,  F02C3/04

CPC classification number: F02C9/16 ,  F01D5/08 ,  F01D25/10 ,  F02C3/04 ,  F02C9/18 ,  F05D2260/232 ,  F05D2260/941 ,  F05D2270/303 ,  Y02T50/676

Abstract: A gas turbine engine comprises a compressor rotor including blades and a disk, with a bore defined radially inwardly of the disk, and a combustor. A tap directs the products of combustion first to a valve and then into the bore of the disk. At least two temperature sensors sense a temperature of the products of combustion downstream of the valve. A control compares sensed temperatures from the at least two temperature sensors to ensure the at least two temperature sensors are functioning properly. The sensed temperatures are utilized to control the valve. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US20180051630A1

公开(公告)日：2018-02-22

申请号：US15242973

申请日：2016-08-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F01D25/12

CPC classification number: F02C7/18 ,  F01D25/12 ,  F02C6/12 ,  F02C7/20 ,  F05D2260/213 ,  F05D2260/30 ,  F05D2260/96 ,  Y02T50/676

Abstract: A gas turbine engine has a core engine with a compressor section and a turbine section. The compressor section includes a low pressure compressor and a high pressure compressor. A cooling air system taps compressed air and passes the compressed air through a heat exchanger. Cooling air passes over the heat exchanger to cool the compressed air, which is returned to the core engine to provide a cooling function. The heat exchanger is mounted through a flexible mount allowing movement between a static structure and the heat exchanger.

公开(公告)号：US20170009657A1

公开(公告)日：2017-01-12

申请号：US14793119

申请日：2015-07-07

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Paul W. Duesler

IPC: F02C7/18 ,  F02K3/02 ,  F02C7/04

Abstract: An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core. The cooled cooling air system including an air-air heat exchanger.

Abstract translation: 示例性的燃气涡轮发动机包括限定在发动机芯的风扇机舱和核心罩之间的风扇旁路管道。 发动机内核包括冷却的冷却空气系统，该冷却空气系统构造成从发动机核心内的扩散器处的主要流路泄漏接收冷却空气，并且被配置为向发动机芯内的至少一个部件提供冷却的冷却空气。 冷却的冷却空气系统包括空气 - 空气热交换器。