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公开(公告)号：US20220235823A1
公开(公告)日：2022-07-28
申请号：US17555567
申请日：2021-12-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Todd A. Davis , Dale C. Humphries
IPC: F16C33/76
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a bearing compartment, a seal runner, a seal configured to cooperate with the seal runner to seal the bearing compartment, and a catcher in contact with the seal runner to minimize deflection of the seal runner. A method is also disclosed.
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公开(公告)号：US11268442B2
公开(公告)日：2022-03-08
申请号：US16918225
申请日：2020-07-01
Applicant: Raytheon Technologies Corporation
Inventor： Todd A. Davis , Paul R. Hanrahan
Abstract: A shaft and sleeve assembly of a gas turbine engine includes an outer shaft extending about an engine central longitudinal axis and having a radially inner shaft surface. The radially inner shaft surface has a shaft groove define therein. A sleeve is located radially inboard of the radially inner shaft surface. The sleeve includes a sleeve groove defined in a radially outer sleeve surface. The sleeve groove is formed at an axial location between a first axial end and a second axial end of the sleeve. A retaining element is installed in the shaft groove and the sleeve groove to retain the sleeve relative to the outer shaft. The sleeve includes one or more sleeve openings formed therein, and the sleeve groove is aligned with the one or more sleeve openings.
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公开(公告)号：US20220003164A1
公开(公告)日：2022-01-06
申请号：US16918225
申请日：2020-07-01
Applicant: Raytheon Technologies Corporation
Inventor： Todd A. Davis , Paul R. Hanrahan
Abstract: A shaft and sleeve assembly of a gas turbine engine includes an outer shaft extending about an engine central longitudinal axis and having a radially inner shaft surface. The radially inner shaft surface has a shaft groove define therein. A sleeve is located radially inboard of the radially inner shaft surface. The sleeve includes a sleeve groove defined in a radially outer sleeve surface. The sleeve groove is formed at an axial location between a first axial end and a second axial end of the sleeve. A retaining element is installed in the shaft groove and the sleeve groove to retain the sleeve relative to the outer shaft. The sleeve includes one or more sleeve openings formed therein, and the sleeve groove is aligned with the one or more sleeve openings.
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公开(公告)号：US11753964B2
公开(公告)日：2023-09-12
申请号：US17320593
申请日：2021-05-14
Applicant: Raytheon Technologies Corporation
Inventor： Nigel David Sawyers-Abbott , Armando Amador , Todd A. Davis
CPC classification number: F01D25/183 , F01D11/00 , F01D25/12 , F16J15/162 , F05D2220/32 , F05D2240/55 , F05D2260/232
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 on a first piece of the second member, the seat having a seat face in sliding sealing engagement with the seal face; and a radially outwardly closed collection channel for collecting centrifuged oil; a second piece encircling and attached to the first piece and having a circumferential array of apertures; and cooperating with the first piece to define a plenum; and a flowpath from the collection channel passing radially outward axially spaced from the seat face to cool the seat face and passing axially away from the seat face in the plenum.
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公开(公告)号：US11725694B2
公开(公告)日：2023-08-15
申请号：US17555567
申请日：2021-12-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Todd A. Davis , Dale C. Humphries
IPC: F16C33/76
CPC classification number: F16C33/76 , F16C2360/23
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a bearing compartment, a seal runner, a seal configured to cooperate with the seal runner to seal the bearing compartment, and a catcher in contact with the seal runner to minimize deflection of the seal runner. A method is also disclosed.
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Patent Agency Ranking
公开(公告)号：US20230272745A1
公开(公告)日：2023-08-31
申请号：US18142131
申请日：2023-05-02
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Todd A. Davis , Brian P. Cigal
CPC classification number: F02C7/06 , F01D25/285 , F01D25/162 , F01D15/12 , F02K3/06 , F02C7/20 , F02C7/36 , Y10T29/49245 , F05D2230/80 , F05D2230/70 , F05D2230/72 , F05D2230/60 , Y02T50/60
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.
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公开(公告)号：US11629649B2
公开(公告)日：2023-04-18
申请号：US16871163
申请日：2020-05-11
Applicant: Raytheon Technologies Corporation
Inventor： Todd A. Davis , Brian P. Cigal
IPC: F02C7/06 , F01D17/06 , F01D25/16 , F02C7/36 , F02K3/06 , F16C41/00 , G01P3/44 , F01D21/00 , F01D15/12
Abstract: A gas turbine engine includes, among other things, a fan, a fan drive gear system that is coupled with the fan and a fan drive input shaft, a compressor section that includes a first compressor and a second compressor, and a turbine section. The turbine section includes a first turbine coupled with a first shaft and a second turbine coupled through a second shaft to the second compressor. A bearing supports the fan drive input shaft. The bearing is located proximal to, and radially spaced from, a forward end of the first shaft. The bearing includes a speed sensor target that is rotatable with the forward end and that defines a rotation path. A speed sensor probe is situated proximal to the rotation path and is operable to read the speed sensor target.
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公开(公告)号：US20210164363A1
公开(公告)日：2021-06-03
申请号：US17175828
申请日：2021-02-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Brian P. Cigal , Todd A. Davis
Abstract: A fan drive gear system for a turbofan engine is disclosed and includes a gear assembly and a front center body. The front center body is an annular case that supports the gear assembly. The front center body includes a passage portion that defines a portion of a core flow path, a forward flange configured for attachment to a first case structure forward of the front center body, and a gutter portion disposed on a radially inner side of the front center body for collecting lubricant exhausted from the geared assembly.
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公开(公告)号：US12203412B2
公开(公告)日：2025-01-21
申请号：US17837935
申请日：2022-06-10
Applicant: Raytheon Technologies Corporation
Inventor： Russell B. Witlicki , Todd A. Davis , Ryan William Lureau , Shadd Andrew Bradshaw , Christopher M. Valva
IPC: F02C7/06
Abstract: A gas turbine engine has a shaft having an inner diameter surface. A plug is mounted in the shaft. An oil nozzle is positioned to direct a flow of oil to an interior of the shaft. The plug has: a first section; a second section having an outer diameter periphery; and an axial gap between the first section and the second section.
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公开(公告)号：US20230399978A1
公开(公告)日：2023-12-14
申请号：US17837935
申请日：2022-06-10
Applicant: Raytheon Technologies Corporation
Inventor： Russell B. Witlicki , Todd A. Davis , Ryan William Lureau , Shadd Andrew Bradshaw , Christopher M. Valva
IPC: F02C7/06
CPC classification number: F02C7/06 , F05D2240/61 , F05D2220/32 , F05D2240/55
Abstract: A gas turbine engine has a shaft having an inner diameter surface. A plug is mounted in the shaft. An oil nozzle is positioned to direct a flow of oil to an interior of the shaft. The plug has: a first section; a second section having an outer diameter periphery; and an axial gap between the first section and the second section.
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