公开(公告)号：US10309306B2

公开(公告)日：2019-06-04

申请号：US14510644

申请日：2014-10-09

Applicant: United Technologies Corporation

Inventor： Marc J. Muldoon

IPC: F02C7/36 ,  F02C7/06 ,  F02C3/04 ,  F16H57/04

Abstract: A turbofan engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan drive gear system including a carrier for supporting a plurality of gears, and a scupper capturing lubricant during gear operation and directing lubricant into the carrier. A fan drive gear system is also disclosed.

公开(公告)号：US20190022804A1

公开(公告)日：2019-01-24

申请号：US15652712

申请日：2017-07-18

Applicant: United Technologies Corporation

Inventor： Marc J. Muldoon

IPC: B23P11/02 ,  F01D25/16 ,  F01D25/12 ,  F16C43/00

CPC classification number: B23P11/025 ,  F01D25/125 ,  F01D25/16 ,  F01D25/162 ,  F01D25/28 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2240/52 ,  F05D2240/54 ,  F16C35/06 ,  F16C35/063 ,  F16C43/00 ,  F16C2226/14 ,  F16C2360/23

Abstract: Aspects of the disclosure are directed to components of an engine and one or more methods for assembling the components. A first component is positioned adjacent to a second component such that a first surface of the first component abuts the second component. A cooling plate is coupled to the first component such that a first surface of the cooling plate abuts a second surface of the first component. A loading ram is coupled to the cooling plate such that a second surface of the cooling plate abuts the loading ram.

公开(公告)号：US20180283531A1

公开(公告)日：2018-10-04

申请号：US15962819

申请日：2018-04-25

Applicant: United Technologies Corporation

Inventor： Marc J. Muldoon

IPC: F16H57/08 ,  F16H57/04 ,  F16C17/02 ,  F16H1/28 ,  F02C7/36

CPC classification number: F16H57/08 ,  F02C7/36 ,  F05D2260/40311 ,  F16C17/02 ,  F16H1/28 ,  F16H57/043 ,  F16H57/0479 ,  F16H57/0482 ,  F16H2057/085 ,  H05K999/99 ,  Y02T50/671

Abstract: A journal pin may comprise an internal bore formed along an axis of rotation of the journal pin, a recessed wall of the internal bore having a diameter greater than the diameter of the internal bore, the internal bore extending completely through the journal pin, and a collar coupled to the journal pin, wherein the collar comprises a second recessed wall; and a carrier press fit onto the collar. The journal pin may comprise an undercut radially outward from the internal bore and radially inward from an outer diameter of the journal pin.

公开(公告)号：US09982771B2

公开(公告)日：2018-05-29

申请号：US14853208

申请日：2015-09-14

Applicant: United Technologies Corporation

Inventor： Marc J. Muldoon

IPC: F16H57/08 ,  F16C17/02 ,  F16H1/28 ,  F16H57/04 ,  F02C7/36

CPC classification number: F16H57/08 ,  F02C7/36 ,  F05D2260/40311 ,  F16C17/02 ,  F16H1/28 ,  F16H57/043 ,  F16H57/0479 ,  F16H57/0482 ,  F16H2057/085 ,  Y02T50/671

Abstract: An epicyclic gear system is provided. The gear system may comprise an annular gear centered about an axis, a star gear radially inward from the annular gear, a journal pin inside the star gear and comprising an internal bore with a recessed wall, and a sun gear radially inward from the star gear. A journal pin is also provided. The journal pin may include an internal bore formed along an axis of rotation of the journal pin, and a recessed wall of the internal bore with a diameter greater than the diameter of the internal bore.

公开(公告)号：US09599019B2

公开(公告)日：2017-03-21

申请号：US14609095

申请日：2015-01-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Marc J. Muldoon ,  Gary L. Grogg ,  Grace E. Szymanski

IPC: F02C1/00 ,  F02C7/06 ,  F01D25/18

CPC classification number: F02C7/06 ,  F01D25/18 ,  F01M11/02 ,  F05D2240/53 ,  F05D2250/311 ,  F16N2210/02

Abstract: The present disclosure relates generally to a dual oil supply tube for a gas turbine engine. The dual oil supply tube locates a scheduled damper supply tube inside a compartment oil supply tube which remains full while the engine is operating.

公开(公告)号：US20150219011A1

公开(公告)日：2015-08-06

申请号：US14609095

申请日：2015-01-29

Applicant: United Technologies Corporation

Inventor： Marc J. Muldoon ,  Gary L. Grogg ,  Grace E. Szymanski

IPC: F02C7/06 ,  F02C3/045 ,  F01D25/18

CPC classification number: F02C7/06 ,  F01D25/18 ,  F01M11/02 ,  F05D2240/53 ,  F05D2250/311 ,  F16N2210/02

Abstract: The present disclosure relates generally to a dual oil supply tube for a gas turbine engine. The dual oil supply tube locates a scheduled damper supply tube inside a compartment oil supply tube which remains full while the engine is operating.

Abstract translation: 本公开总体上涉及一种用于燃气涡轮发动机的双重供油管。 双重供油管将预定的阻尼器供应管定位在发动机运行期间保持充满的隔室供油管内。

公开(公告)号：US11519289B2

公开(公告)日：2022-12-06

申请号：US16706058

申请日：2019-12-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Om P. Sharma ,  Joseph B. Staubach ,  Marc J. Muldoon ,  Jesse M. Chandler ,  David Lei Ma

IPC: B64D27/00 ,  F01D15/10 ,  F02C3/10 ,  F02K5/00 ,  B64D27/02

Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.

公开(公告)号：US11255263B2

公开(公告)日：2022-02-22

申请号：US16733504

申请日：2020-01-03

Applicant: United Technologies Corporation

Inventor： Marc J. Muldoon ,  Joseph B. Staubach ,  Jesse M. Chandler ,  Neil Terwilliger ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C6/20

Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

公开(公告)号：US20210239046A1

公开(公告)日：2021-08-05

申请号：US16782650

申请日：2020-02-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Marc J. Muldoon

IPC: F02C7/18 ,  F04D25/06 ,  B64C21/06

Abstract: A cooling system for a plurality of conductive cables in a gas turbine engine includes a cooling source and an electric motor disposed in a tail cone. The cooling source may comprise an electric fan or an oil pump. The cooling source may be configured for active cooling of the plurality of conductive cables. The electric fan may be in fluid communication with ambient air during operation of the gas turbine engine.

公开(公告)号：US20210172333A1

公开(公告)日：2021-06-10

申请号：US16706058

申请日：2019-12-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： GABRIEL L. SUCIU ,  Om P. Sharma ,  Joseph B. Staubach ,  Marc J. Muldoon ,  Jesse M. Chandler ,  David Lei Ma

IPC: F01D15/10 ,  F02K5/00 ,  F02C3/10

Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.