公开(公告)号：US20210300575A1

公开(公告)日：2021-09-30

申请号：US16832477

申请日：2020-03-27

Applicant: United Technologies Corporation

Inventor： Joseph B. Staubach ,  Amanda J. L. Boucher

IPC: B64D27/12 ,  B64D41/00 ,  B64D13/08

Abstract: Aircraft propulsion systems and aircraft having such propulsion systems are described. The aircraft propulsion systems include a fan, a motor operably connected to the fan by a drive shaft, and an aircraft power generation system operably coupled to the motor to drive rotation of the fan through the drive shaft, wherein the aircraft power generation system comprises a fuel cell configured to generate at least 1 MW of electrical power.

公开(公告)号：US11131314B2

公开(公告)日：2021-09-28

申请号：US15265294

申请日：2016-09-14

Applicant: United Technologies Corporation

Inventor： David A. Welch

IPC: F04D29/02 ,  F01D5/14 ,  F04D29/32 ,  F01D5/28

Abstract: An airfoil includes a leading edge, a trailing edge, a pressure side extending between the leading and the trailing edge, and a suction side that is disposed opposite the pressure side extending between the leading edge and the trailing edge. The airfoil further includes a spar and a structural member. The spar defines the leading edge. The structural member is bonded to the spar.

公开(公告)号：US11131199B2

公开(公告)日：2021-09-28

申请号：US16672781

申请日：2019-11-04

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov

IPC: F01D5/18 ,  F23R3/00 ,  F01D11/08 ,  F01D9/04 ,  F01D25/12

Abstract: Impingement assemblies and components of gas turbine engines are described. The impingement assemblies include an impingement plate having a plurality of impingement holes formed therein and an impingement surface arranged relative to the impingement plate with an impingement cavity defined between the impingement plate and the impingement surface. A raised wall is configured on the impingement surface and extends in a direction from the impingement surface toward the impingement plate and defines a plurality of impingement cells each having a geometric shape on the impingement surface.

公开(公告)号：US11130212B2

公开(公告)日：2021-09-28

申请号：US16269728

申请日：2019-02-07

Applicant: United Technologies Corporation

Inventor： Daniel A. Bales

IPC: B25B5/06 ,  B25B5/02

Abstract: A directional translating clamping device comprises a housing that includes a distal housing end and proximate housing end separated along a central axis, and a housing recess at the proximate housing end and extending along the central axis end. The device also includes a slide located in the housing recess, and the slide comprises a slide recess at a slide proximate end co-axial with the housing recess, and a detent in a radial sidewall of the slide prevents the slide from translating beyond a predetermined axial distance along the central axis. A spring is located in the housing recess and exerts an axial force on the distal end of the slide. A stub shaft extends from the distal end of the housing. A roller ball assembly includes a threaded sidewall that engages with the slide recess to removably and replaceably secure the roller ball assembly to the slide.

公开(公告)号：US11125187B2

公开(公告)日：2021-09-21

申请号：US16052022

申请日：2018-08-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Victor G. Filipenco

IPC: F02K3/075 ,  F02C3/13 ,  F02C9/18 ,  F02K3/06

Abstract: A gas turbine engine includes a case assembly, a splitter, an upstream blade row, and a transition duct. The case assembly defines an outer flow path wall and an inner flow path wall. The splitter is disposed between the outer flow path wall and the inner flow path wall. The splitter has a first surface and a second surface disposed opposite the first surface. The transition duct is defined by the outer flow path and the inner flow path and extends between the upstream blade row and the leading edge of the splitter.

公开(公告)号：US11125168B2

公开(公告)日：2021-09-21

申请号：US16168934

申请日：2018-10-24

Applicant: United Technologies Corporation

Inventor： Christopher J. Hanlon ,  James F. Krenzer ,  Becky E. Rose ,  Mark F. Zelesky

IPC: F02C9/18 ,  F02C6/08 ,  F02C7/052 ,  F02C9/44 ,  F02K3/075 ,  F04D27/02 ,  F01D25/00 ,  B64D45/00

Abstract: An aspect includes a dirt mitigation system for a gas turbine engine. The dirt mitigation system includes a plurality of bleeds of the gas turbine engine and a control system configured to determine a particulate ingestion estimate indicative of dirt ingested in the gas turbine engine. The control system is further configured to determine one or more operating parameters of the gas turbine engine and alter a bleed control schedule of the gas turbine engine to purge at least a portion of the dirt ingested in the gas turbine engine through one or more of the bleeds of the gas turbine engine based on the particulate ingestion estimate and the one or more operating parameters.

公开(公告)号：US11125167B2

公开(公告)日：2021-09-21

申请号：US16291392

申请日：2019-03-04

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F02C7/06 ,  F01D25/18 ,  F02K3/06 ,  F02C3/107

Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.

公开(公告)号：US11125099B2

公开(公告)日：2021-09-21

申请号：US16675881

申请日：2019-11-06

Applicant: United Technologies Corporation

Inventor： Carson A. Roy Thill ,  Andrew D. Keene ,  Danielle Mahoney ,  Jaime A. Arbona ,  Justin K. Bleil

IPC: F01D11/08 ,  F01D25/24

Abstract: A flow path component assembly includes a support structure. A flow path component has a plurality of segments that are arranged circumferentially about an axis and are mounted in the support structure by a carrier. At least one of the segments have a first wall axially spaced from a second wall. The first wall has first and second hooks spaced apart from one another in a circumferential direction. The second wall has third and fourth hooks spaced apart from one another in the circumferential direction. The first, second, third, and fourth hooks are in engagement with the carrier.

公开(公告)号：US11125098B2

公开(公告)日：2021-09-21

申请号：US16567561

申请日：2019-09-11

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark

IPC: F01D11/08 ,  F02C7/28

Abstract: A blade outer air seal includes a carrier, a ceramic seal segment, and a face seal. The ceramic seal segment is supported on the carrier and has first and second axial ends, first and second circumferential sides, an inner side, and an outer side. The face seal is carried on the ceramic seal segment at the first axial end. The face seal has a radial seal wall and a tongue that extends axially from the radial seal wall.

公开(公告)号：US11125095B2

公开(公告)日：2021-09-21

申请号：US16161739

申请日：2018-10-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Timothy M. Davis

IPC: F01D11/00 ,  F16J15/06 ,  F16J15/10 ,  F16J15/02 ,  F02C7/28 ,  F16J15/08

Abstract: A seal for sealing a space defined between first and second components, the seal having: an annular member having a substantially U-shaped cross section along at least a portion thereof, the portion configured to provide a seal interface at each of the first and second components.