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公开(公告)号：US10392953B2
公开(公告)日：2019-08-27
申请号：US15623835
申请日：2017-06-15
Applicant: United Technologies Corporation
Inventor： Jonathan Logan Miller , Colin D. Craig
Abstract: A ring seal assembly includes a first ring seal that is symmetrical with respect to a radially extending plane. A second ring seal is separated axially from the first ring seal by a spring. The second ring seal includes a first inner circumferential surface. An interference feature extends radially inward from the first inner circumferential surface to a second inner circumferential surface.
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2.发明申请公开(公告)号：US20190178381A1
公开(公告)日：2019-06-13
申请号：US15840632
申请日：2017-12-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan Logan Miller , Colin D. Craig
Abstract: A force balanced face seal may comprise a seal housing comprising an annular extrusion, a seal support, wherein the annular extrusion is disposed within the seal support, and a primary seal coupled to the seal housing, wherein the primary seal comprises a sealing face and a base opposite the sealing face and proximate the seal housing.
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公开(公告)号：US10145255B2
公开(公告)日：2018-12-04
申请号：US15405376
申请日：2017-01-13
Applicant: United Technologies Corporation
Inventor： Jonathan Logan Miller , Colin D. Craig
Abstract: A carbon ring for a seal assembly in a gas turbine engine includes an outer face extending circumferentially around a center axis of the carbon ring. The carbon ring also includes an inner face extending around the center axis and disposed radially inward from the outer face. A forward face of the carbon ring extends radially between the inner face and the outer face. A rear face of the carbon ring extends radially between the inner face and the outer face and is disposed axially opposite the forward face. At least one tab extends axially from at least one of the forward face and the rear face.
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公开(公告)号：US20180202304A1
公开(公告)日：2018-07-19
申请号：US15405376
申请日：2017-01-13
Applicant: United Technologies Corporation
Inventor： Jonathan Logan Miller , Colin D. Craig
CPC classification number: F01D11/003 , F05D2220/32 , F05D2240/60 , F05D2250/182 , F05D2260/52 , F16J15/16 , F16J15/30 , F16J15/441
Abstract: A carbon ring for a seal assembly in a gas turbine engine includes an outer face extending circumferentially around a center axis of the carbon ring. The carbon ring also includes an inner face extending around the center axis and disposed radially inward from the outer face. A forward face of the carbon ring extends radially between the inner face and the outer face. A rear face of the carbon ring extends radially between the inner face and the outer face and is disposed axially opposite the forward face. At least one tab extends axially from at least one of the forward face and the rear face.
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公开(公告)号：US09765644B2
公开(公告)日：2017-09-19
申请号：US14600910
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Colin D. Craig , Matthew J. Orsini
CPC classification number: F01D25/18 , B01D45/14 , B01D46/0023 , B04B5/12 , B04B2005/125 , F01M13/04 , F01M2013/0422 , F01M2013/0433 , F05D2260/607 , F05D2260/609 , Y02T50/671 , Y02T50/675
Abstract: Aspects of the disclosure are directed to a system associated with an engine of an aircraft, comprising: a deoiler configured to receive a mixture of air and oil at an input of the deoiler and separate the air from the oil, and a baffle coupled to the input of the deoiler and configured to prevent debris that is larger than a threshold from entering the deoiler.
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Patent Agency Ranking
公开(公告)号：US10788131B2
公开(公告)日：2020-09-29
申请号：US15666136
申请日：2017-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan L. Miller , Colin D. Craig
IPC: F01D11/00 , F16J15/34 , F16J15/16 , F16J15/3248 , F01D25/18
Abstract: A carbon seal assembly may comprise a seal support, a seal housing coupled to the seal support, and a carbon seal adjacent an aft portion of the seal housing. The carbon seal may comprise a nose defined by an axial surface of the carbon seal, a first radial surface of the carbon seal, and a second radial surface of the carbon seal radially inward of the first radial surface. The first radial surface and the second radial surface may extend forward from the axial surface. A first axial length of the first radial surface may be greater than a second axial length of the second radial surface.
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公开(公告)号：US20190040957A1
公开(公告)日：2019-02-07
申请号：US15666136
申请日：2017-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan L. Miller , Colin D. Craig
Abstract: A carbon seal assembly may comprise a seal support, a seal housing coupled to the seal support, and a carbon seal adjacent an aft portion of the seal housing. The carbon seal may comprise a nose defined by an axial surface of the carbon seal, a first radial surface of the carbon seal, and a second radial surface of the carbon seal radially inward of the first radial surface. The first radial surface and the second radial surface may extend forward from the axial surface. A first axial length of the first radial surface may be greater than a second axial length of the second radial surface.
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公开(公告)号：US20190017605A1
公开(公告)日：2019-01-17
申请号：US15650171
申请日：2017-07-14
Applicant: United Technologies Corporation
Inventor： Jonathan Logan Miller , Joseph G. Colucci , Colin D. Craig , Aneil S. Hegde , Michael M. Davis
IPC: F16J15/3296 , F16J15/3268
Abstract: A ring seal in a gas turbine engine includes a ring seal body, an axial sealing dam, a radial sealing dam, and at least one bleed slot. The ring seal body is annular in shape and has a first axial side, a second axial side, a radially outer side, and a radially inner side. The axial sealing dam is on the first axial side and is configured to provide a first sealing surface with a first component. The radial sealing dam is on the radially outer side and is configured to provide a second sealing surface with a second component radially outward from the radially outer side. The at least one bleed slot is on the second axial side and configured to allow fluid to pass through when the ring seal is incorrectly oriented such that the at least one bleed slot is adjacent to the first component.
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公开(公告)号：US09835086B2
公开(公告)日：2017-12-05
申请号：US14494081
申请日：2014-09-23
Applicant: United Technologies Corporation
Inventor： Colin D. Craig
IPC: F02C7/06
CPC classification number: F02C7/06 , F05D2260/602
Abstract: An oil accumulator assembly may comprise a scavenge tube including an aperture defined by a break in the scavenge tube and/or an annular cylindrical structure concentrically situated about the scavenge tube. The aperture may be configured to receive oil flowing through the scavenge tube, and the annular cylindrical structure may be configured to accumulate oil flowing through the aperture. The oil accumulator assembly may further comprise a drainage outlet disposed in the annular cylindrical structure. Oil accumulated within the annular cylindrical structure may drain through the drainage outlet in response to an engine being shut down. The oil accumulated within the annular cylindrical structure may fill a portion of the scavenge tube situated within an engine fan case to prevent coking within the scavenge tube.
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公开(公告)号：US11230946B2
公开(公告)日：2022-01-25
申请号：US16269637
申请日：2019-02-07
Applicant: United Technologies Corporation
Inventor： Michael M. Davis , Colin D. Craig
Abstract: A gas turbine engine includes an engine static structure. A rotating structure is configured to rotate relative to the engine static structure. The rotating structure has a target area with first and second directions. The first direction is greater than the second direction. A lubrication system includes a nozzle having a non-circular exit aimed at the target area. The exit provides a width and a height. The width is greater than the height. The width is oriented in the first direction.
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