公开(公告)号：US11209086B2

公开(公告)日：2021-12-28

申请号：US16173465

申请日：2018-10-29

Applicant: United Technologies Corporation

Inventor： Todd A. Davis ,  William G. Sheridan

IPC: F16J15/34 ,  F01D25/18

Abstract: A seal system has: a first member; a seal carried by the first member and having a seal face; and a second member rotatable relative to the first member about an axis. The second member has: a seat, the seat having a seat face in sliding sealing engagement with the seal face; and a circumferential array of passageway legs open to the seat face; and an oil pump for delivering oil via one or more first outlets to the passageway legs in at least a first mode of operation. The oil pump is coupled to one or more second outlets to deliver oil to a backside of the seat in at least a second mode of operation.

公开(公告)号：US11118629B2

公开(公告)日：2021-09-14

申请号：US16710667

申请日：2019-12-11

Applicant: United Technologies Corporation

Inventor： Russell B. Witlicki ,  Todd A. Davis ,  Christopher M. Valva ,  David C. Kiely ,  Andrew Newton

IPC: F16C35/06 ,  F01D25/16 ,  F16C35/063 ,  F16C19/10

Abstract: A gas turbine engine component includes a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race, and a bearing housing spaced radially outwardly of the outer race. A curved beam centering spring is positioned between the outer race and the bearing housing. A cylindrical wall is radially outward of the bearing housing and engages the outer race and the bearing housing.

公开(公告)号：US20210180651A1

公开(公告)日：2021-06-17

申请号：US16710667

申请日：2019-12-11

Applicant: United Technologies Corporation

Inventor： Russell B. Witlicki ,  Todd A. Davis ,  Christopher M. Valva ,  David C. Kiely ,  Andrew Newton

IPC: F16C35/063 ,  F16C19/10 ,  F01D25/16

Abstract: A gas turbine engine component includes a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race, and a bearing housing spaced radially outwardly of the outer race. A curved beam centering spring is positioned between the outer race and the bearing housing. A cylindrical wall is radially outward of the bearing housing and engages the outer race and the bearing housing.

公开(公告)号：US20200284197A1

公开(公告)日：2020-09-10

申请号：US16836001

申请日：2020-03-31

Applicant: United Technologies Corporation

Inventor： Todd A. Davis ,  Brian P. Cigal

IPC: F02C7/06 ,  F01D25/28 ,  F01D25/16 ,  F01D15/12 ,  F02K3/06 ,  F02C7/20 ,  F02C7/36

Abstract: A gas turbine engine includes a fan that has fan blades wherein the fan delivers airflow to a bypass duct. A gearbox is defined along an engine axis. A low spool is arranged aft of the gearbox and coupled to drive the gearbox. A front center body assembly is defined around the engine axis. A flexible support supports the gearbox relative to the front center body assembly. A bearing package is mounted to the front center body assembly and the low spool. A front wall is mounted to the front center body assembly. The front wall is removable from the front center body assembly to access at least one of the gearbox or the bearing package. The low spool includes a low pressure compressor hub that provides an engagement feature for engaging the bearing package.

公开(公告)号：US10767510B2

公开(公告)日：2020-09-08

申请号：US16269071

申请日：2019-02-06

Applicant: United Technologies Corporation

Inventor： Armando Amador ,  Todd A. Davis ,  Jorn Axel Glahn

IPC: F16J15/34 ,  F01D25/12 ,  F01D11/00 ,  F01D25/18

Abstract: A seal seat includes an annular body and an extension. The annular body is disposed about a centerline axis. The extension is connected to and extends radially outward from the annular body. The extension includes first, second, and third portions. The first portion is connected to the annular body and is defined by axially opposed upstream and downstream wall faces. The first portion includes a fin connected to the upstream wall face. The second portion is connected to the first portion and extends substantially parallel to the annular body. The third portion is connected to the second portion and extends substantially parallel to the second portion.

公开(公告)号：US10577979B2

公开(公告)日：2020-03-03

申请号：US15958527

申请日：2018-04-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Todd A. Davis ,  Mark Ronski ,  David Allen Stachowiak

IPC: F16M11/00 ,  F01D25/28 ,  F02C7/06 ,  F02C7/32 ,  F01D25/18 ,  F16M13/02

Abstract: An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the oil tank in one degree of freedom, a second mount may fix the oil tank in two degrees of freedom, and a third mount may fix the oil tank in three degrees of freedom. This allows limited rotational and expansion movement while coupling the oil tank to the engine. The mount attachments may be embodied in rubber, with pins, or with spherical joints in a variety of configurations. Frangible pins may be used to absorb energy but still retain the oil tank in the event of a high energy event.

公开(公告)号：US10513938B2

公开(公告)日：2019-12-24

申请号：US15496399

申请日：2017-04-25

Applicant: United Technologies Corporation

Inventor： Russell B. Witlicki ,  Todd A. Davis ,  Francis Parnin

IPC: F01D5/18 ,  F01D11/00 ,  F01D25/16 ,  F04D27/00 ,  F04D29/054 ,  F01D5/02 ,  F01D25/18

Abstract: Aspects of the disclosure are directed to a system associated with an engine having a central longitudinal axis, including a first shaft axially extending along the central longitudinal axis, a second shaft coaxial with the first shaft, a first air seal that seals between the first shaft and the second shaft at a first axial location, a second air seal that seals between the first shaft and the second shaft at a second axial location, a first oil seal that provides intershaft sealing between the first shaft and the second shaft at a third axial location, a second oil seal that provides intershaft sealing between the first shaft and the second shaft at a fourth axial location axially adjacent to the third axial location, and a high pressure compressor that provides pressurized air to a first radially exterior side of the first air seal and to a second radially exterior side the second air seal.

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.

公开(公告)号：US20180328225A1

公开(公告)日：2018-11-15

申请号：US15592790

申请日：2017-05-11

Applicant: United Technologies Corporation

Inventor： Todd A. Davis ,  Denman H. James ,  Daniel L. Gysling ,  Joseph D. Walker

IPC: F01D25/16 ,  F16K15/00 ,  F16C27/04 ,  F01D25/20 ,  F02C7/06

CPC classification number: F01D25/164 ,  F01D25/20 ,  F02C7/06 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2240/53 ,  F05D2260/96 ,  F05D2260/98 ,  F16C27/045 ,  F16C2360/23 ,  F16F15/0237 ,  F16K15/00

Abstract: A fluid damping structure is provided that includes a damper ring. The damper ring includes an annular body a plurality of fluid check valves, and at least one fluid stop. The annular body extends circumferentially around an axial centerline, and is defined by a first end surface, a second end surface, an outer radial surface, and an inner radial surface. The outer radial surface and the inner radial surface extend axially from the first end surface toward the second end surface. The body includes one or more check valve passages. Each check valve passage extends axially from an open end disposed at the first end surface inwardly toward the second end surface, and is disposed between the inner radial surface and the outer radial surface. An inlet aperture extends between each check valve passage and the outer radial surface, and an outlet aperture extends between each check valve passage and the inner radial surface. Each fluid check valve is disposed in a check valve passage. The at least one fluid stop is configured to prevent fluid exit from the open end of each check valve passage.

公开(公告)号：US20180156113A1

公开(公告)日：2018-06-07

申请号：US15872051

申请日：2018-01-16

Applicant: United Technologies Corporation

Inventor： Brian P. Cigal ,  Todd A. Davis

IPC: F02C7/00 ,  F01D17/06 ,  F02C3/107 ,  F02K3/06 ,  G01P3/44 ,  F02D9/02

CPC classification number: F02C7/00 ,  F01D17/06 ,  F02C3/107 ,  F02D2009/023 ,  F02K3/06 ,  G01P3/44 ,  Y02T50/671 ,  Y10T29/49229

Abstract: A method for a gas turbine engine includes affixing a speed sensor probe in the gas turbine engine. The sensor probe is operable to determine a rotational speed in the gas turbine engine. The gas turbine engine includes a first spool that is coupled at a first axial position to a compressor hub that is coupled to drive a first compressor. The first spool is coupled at a second, different axial position to a fan drive input shaft that is coupled to drive a fan drive gear system. The second turbine is coupled through a second spool to drive a second compressor. The speed sensor probe is affixed at a third axial position that is axially forward of the first axial position and axially aft of the second axial position.