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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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Patent Agency Ranking
公开(公告)号：US11739845B2
公开(公告)日：2023-08-29
申请号：US17541593
申请日：2021-12-03
Applicant: Raytheon Technologies Corporation
Inventor： Brian P. Cigal , Christopher T. Anglin
IPC: F16J15/34
CPC classification number: F16J15/3452 , F16J15/3496
Abstract: An apparatus has: a first member; a shaft rotatable relative to the first member about an axis; and a seal system. The seal system has: a seal carried by the first member and having a seal face; a seal carrier; a seat carried by the shaft and having a seat face in sliding sealing engagement with the seal face; and one or more springs biasing the seal carrier relative to the first member so as to bias the seal face against the seat face. The seal carrier has: an axially-extending wall having an inner diameter (ID) surface; and a radially-extending wall having a first surface. The seal carrier axially-extending wall ID surface has a radially inwardly open groove having a first sidewall and a second sidewall and a base. A wave-form split ring contacts the first sidewall and biases the seal into engagement with the radial wall first surface.
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公开(公告)号：US11365648B2
公开(公告)日：2022-06-21
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：US11713713B2
公开(公告)日：2023-08-01
申请号：US16836001
申请日：2020-03-31
Applicant: Raytheon Technologies Corporation
Inventor： Todd A. Davis , Brian P. Cigal
CPC classification number: F02C7/06 , F01D15/12 , F01D25/162 , F01D25/285 , F02C7/20 , F02C7/36 , F02K3/06 , F05D2230/60 , F05D2230/70 , F05D2230/72 , F05D2230/80 , Y02T50/60 , Y10T29/49245
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 a spline for engaging the bearing package.
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公开(公告)号：US20230175589A1
公开(公告)日：2023-06-08
申请号：US17541593
申请日：2021-12-03
Applicant: Raytheon Technologies Corporation
Inventor： Brian P. Cigal , Christopher T. Anglin
IPC: F16J15/34
CPC classification number: F16J15/3452 , F16J15/3496
Abstract: An apparatus has: a first member; a shaft rotatable relative to the first member about an axis; and a seal system. The seal system has: a seal carried by the first member and having a seal face; a seal carrier; a seat carried by the shaft and having a seat face in sliding sealing engagement with the seal face; and one or more springs biasing the seal carrier relative to the first member so as to bias the seal face against the seat face. The seal carrier has: an axially-extending wall having an inner diameter (ID) surface; and a radially-extending wall having a first surface. The seal carrier axially-extending wall ID surface has a radially inwardly open groove having a first sidewall and a second sidewall and a base. A wave-form split ring contacts the first sidewall and biases the seal into engagement with the radial wall first surface.
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公开(公告)号：US20210348565A1
公开(公告)日：2021-11-11
申请号：US16871163
申请日：2020-05-11
Applicant: Raytheon Technologies Corporation
Inventor： Todd A. Davis , Brian P. Cigal
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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