公开(公告)号：US20140252160A1

公开(公告)日：2014-09-11

申请号：US14190150

申请日：2014-02-26

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry

IPC: B64D27/12

CPC classification number: B64D27/12 ,  F02C3/10 ,  F02C3/107 ,  F02K3/077 ,  F05D2210/40 ,  F05D2230/50 ,  F05D2230/72 ,  F05D2250/30 ,  F05D2250/314 ,  Y10T29/49721

Abstract: An engine mounting arrangement includes a propulsor mounted to an aircraft wing, and an engine core aerodynamically connected to the propulsor and positioned rearward of the propulsor.

Abstract translation: 发动机安装装置包括安装在飞行器机翼上的推进器以及空气动力学连接到推进器并位于推进器后方的发动机核心。

公开(公告)号：US20140205439A1

公开(公告)日：2014-07-24

申请号：US14219112

申请日：2014-03-19

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Karl L. Hasel

IPC: F02C3/107 ,  F02C7/36 ,  F02C7/06 ,  F02K3/00

CPC classification number: F02C7/06 ,  F01D25/162 ,  F02C3/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/00 ,  F02K3/04 ,  Y02T50/671 ,  Y10T29/4932

Abstract: A gas turbine engine includes a housing including 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. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.

Abstract translation: 燃气涡轮发动机包括壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 入口箱内设有齿轮架构。 齿轮架构包括行星齿轮系。 风扇由齿轮架构旋转驱动。 轴提供旋转轴。 轮毂由轴可操作地支撑。 第一和第二轴承分别相对于中间壳体和进气口支撑轴。

公开(公告)号：US20140157756A1

公开(公告)日：2014-06-12

申请号：US14179771

申请日：2014-02-13

Applicant: United Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02K3/06

CPC classification number: F02K3/06 ,  F02C3/107 ,  F05D2260/4031

Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, the geared arrangement defining a gear reduction ratio greater than or equal to about 2.6. A compressor section includes both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor.

Abstract translation: 燃气涡轮发动机具有风扇部分，其包括风扇，构造成驱动风扇部分的齿轮装置，齿轮装置限定大于或等于约2.6的齿轮减速比。 压缩机部分包括第一压缩机和第二压缩机。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供。

公开(公告)号：US20140157754A1

公开(公告)日：2014-06-12

申请号：US14179640

申请日：2014-02-13

Applicant: United Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02K3/06

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D5/12 ,  F01D9/02 ,  F01D21/003 ,  F01D25/24 ,  F01D25/28 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/40 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. A pressure ratio across the fan section is less than or equal to about 1.50. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.

Abstract translation: 一种燃气涡轮发动机具有风扇部分，包括风扇，构造成驱动风扇部分的齿轮装置和包括第一压缩机和第二压缩机的压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供，总压力比大于或等于约35.风扇部分的压力比小于或等于约1.50。 风扇被配置为将一部分空气输送到压缩机部分中，并且一部分空气进入旁通管道。

公开(公告)号：US20140157753A1

公开(公告)日：2014-06-12

申请号：US14179864

申请日：2014-02-13

Applicant: United Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02K3/06

CPC classification number: F02K3/06 ,  F02C3/107 ,  F05D2260/4031

Abstract: A method of designing a gas turbine engine includes providing a fan section including a fan; driving the fan section via a gear arrangement; providing a compressor section, including both a first compressor and a second compressor; and driving the compressor section and the gear arrangement via a turbine section. An overall pressure ratio, being provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor, is greater than or equal to about 35. The pressure ratio across the first compressor is greater than or equal to about 7.

Abstract translation: 一种设计燃气涡轮发动机的方法包括：提供包括风扇的风扇部分; 通过齿轮装置驱动风扇部分; 提供包括第一压缩机和第二压缩机的压缩机部分; 并且经由涡轮机部分驱动压缩机部分和齿轮装置。 通过跨第一压缩机的压力比和跨第二压缩机的压力比的组合提供的总压力比大于或等于约35.跨第一压缩机的压力比大于或等于约 7。

公开(公告)号：US11808210B2

公开(公告)日：2023-11-07

申请号：US15978517

申请日：2018-05-14

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry ,  Nathan Snape

IPC: F02C7/18 ,  F02C3/04 ,  F02C7/32 ,  F02C9/18

CPC classification number: F02C7/185 ,  F02C3/04 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/323 ,  F05D2240/90 ,  F05D2260/213 ,  F05D2260/4031

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A tap connects to the compressor section. A heat exchanger connects downstream of the tap. A cooling compressor connects downstream of the heat exchanger, and the cooling compressor connects to deliver air to at least one of the rotating components. A core housing has an outer peripheral surface and a fan housing defines an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is disposed within the at least one bifurcation duct.

公开(公告)号：US11002195B2

公开(公告)日：2021-05-11

申请号：US16374995

申请日：2019-04-04

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Michael G. McCaffrey

IPC: F02C9/18 ,  F02C7/143 ,  F02C7/32 ,  F02C7/18 ,  F01D17/10 ,  F01D25/12 ,  F02C7/36 ,  F04D29/28

Abstract: A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions.

公开(公告)号：US20200095929A1

公开(公告)日：2020-03-26

申请号：US16676788

申请日：2019-11-07

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Karl L. Hasel ,  Brian D. Merry

IPC: F02C3/06 ,  F02C3/107 ,  F02K3/06 ,  F01D5/14 ,  F02C7/36

Abstract: A ratio of an outer diameter of a fan hub at a leading edge of the blades to an outer tip diameter of the blades at the leading edge is greater than or equal to about 0.24 and less than or equal to about 0.38. The fan tip diameter is greater than or equal to about 84 inches (213.36 centimeters) and a fan tip speed is less than or equal to about 1050 ft/second (320.04 meters/second). The fan drive turbine has between three and six stages.

公开(公告)号：US10443508B2

公开(公告)日：2019-10-15

申请号：US14967446

申请日：2015-12-14

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Michael G. McCaffrey

IPC: F02C7/18 ,  F02C7/32 ,  F02C7/36 ,  F02C9/18 ,  F01D17/10 ,  F01D25/12 ,  F02C7/143 ,  F04D29/28

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor, and at least one more upstream compressor. A turbine section has a high pressure turbine. A tap line taps air from at least one of the more upstream compressors in the compressor section, passes 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. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions. An intercooling system is also disclosed.

公开(公告)号：US10400629B2

公开(公告)日：2019-09-03

申请号：US14012576

申请日：2013-08-28

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Todd A. Davis ,  Gregory E. Reinhardt ,  Enzo DiBenedetto

IPC: F02C7/06 ,  F01D25/16 ,  F02C7/36 ,  F02K3/04

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 first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.