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公开(公告)号：US20220074351A1
公开(公告)日：2022-03-10
申请号：US17527549
申请日：2021-11-16
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
Abstract: A gas turbine engine comprises a fan drive turbine driving a shaft. The shaft engages a gear reduction. The gear reduction drives a fan rotor at a speed that is less than the speed of the fan drive turbine. The gear reduction is a non-epicyclic gear reduction.
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公开(公告)号：US20220034263A1
公开(公告)日：2022-02-03
申请号：US17218369
申请日：2021-03-31
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
Abstract: A gas turbine engine includes a nacelle, and a bypass flow path in a bypass duct within the nacelle of the turbofan engine. A fan section includes a fan with fan blades. The fan section drives air along the bypass flow path. A fan shaft drives a fan that has fan blades and the fan rotates about a central longitudinal axis of the turbofan engine. A speed reduction device includes an epicyclic gear system. A turbine section is connected to the fan section through the speed reduction device and the turbine section rotates about the central longitudinal axis. A first fan bearing for supporting rotation of the fan hub is located axially forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is located axially aft of the speed reduction device. A first outer race of the first fan bearing is fixed relative to the fan hub.
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公开(公告)号：US11162430B2
公开(公告)日：2021-11-02
申请号：US16889942
申请日：2020-06-02
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
Abstract: A speed change device includes a sun gear. A plurality of intermediate gears surround the sun gear. Each of the plurality of intermediate gears includes a forward set of teeth and an aft set of teeth. A ring gear surrounds the plurality of intermediate gears. The ring gear includes a forward portion with a forward set of teeth in meshing engagement with the forward set of teeth on each of the plurality of intermediate gears and an aft portion with an aft set of teeth in meshing engagement with the aft set of teeth on each of the plurality of intermediate gears. A carrier includes a carrier forward portion and a carrier aft portion. Each of the plurality of intermediate gears are located axially between the carrier forward portion and the carrier aft portion.
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公开(公告)号：US20210285380A1
公开(公告)日：2021-09-16
申请号：US17195848
申请日：2021-03-09
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Hung Duong , Jonathan F. Zimmitti , William G. Sheridan , Michael E. McCune , Brian Merry
IPC: F02C7/32 , F02C3/06 , F02C7/18 , F02C7/36 , F02C7/268 , F01D15/10 , F01D25/12 , F16H1/22 , H02K7/116 , H02K7/18 , F01D15/12 , F02C7/275
Abstract: An exemplary gas turbine engine assembly includes a fan section including a fan, a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox includes a set of gears. A compressor is driven by the first towershaft. A transmission couples a starter generator assembly to the set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft in response to rotation of the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft in response to rotation of the second towershaft.
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公开(公告)号：US20210231059A1
公开(公告)日：2021-07-29
申请号：US17085616
申请日：2020-10-30
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
Abstract: A gas turbine engine comprises a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction. The lubrication system includes a lubricant pump supplying a mixed air and oil to a deaerator inlet. The deaerator includes a separator that for separating oil, and delivering separated air to an air outlet, and for delivering separated oil back into an oil tank. The separator includes a member having lubricant flow paths on both of two opposed sides. A method of designing a gas turbine engine is also disclosed.
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Patent Agency Ranking
公开(公告)号：US11067005B2
公开(公告)日：2021-07-20
申请号：US14612514
申请日：2015-02-03
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan
Abstract: A gas turbine engine includes a fan section and a star gear system for driving the fan section. A first fan section support bearing is mounted forward of the star gear system and a second fan section bearing is mounted aft of the star gear system.
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公开(公告)号：US20210215101A1
公开(公告)日：2021-07-15
申请号：US17217754
申请日：2021-03-30
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan , Karl L. Hasel
IPC: F02C7/32 , F02C7/00 , F02C7/36 , F02C3/04 , F02C3/06 , F02C3/113 , F16H1/36 , F02C3/107 , F16H1/28
Abstract: In one exemplary embodiment, a gas turbine engine includes an engine centerline longitudinal axis. A fan section includes a fan with a plurality of fan blades. The fan has a low corrected fan tip speed less than 1400 ft/sec. A bypass ratio is greater than 13 and less than 20. A fan pressure ratio less than 1.38 at cruise conditions of 0.8 Mach and about 35,000 feet. A speed reduction device comprises a gear system with a gear ratio of at least 2.6 and less than or equal to 4.1. A low pressure turbine is in communication with a first shaft. A high pressure turbine is in communication a second shaft. The first shaft is in communication with the fan through the speed reduction device. The low pressure turbine includes at least three stages and no more than four stages. The high pressure turbine includes two stages.
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公开(公告)号：US20210215060A1
公开(公告)日：2021-07-15
申请号：US17213444
申请日：2021-03-26
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
Abstract: An epicyclic gear assembly includes a carrier that includes a first plate axially spaced from a second plate. At least one epicyclic gear set is located between the first plate and the second plate. The first plate is configured to rotate with an output of the epicyclic gear assembly. A first bearing race is attached to the first plate for supporting a first bearing. A second bearing race is attached to the second plate for supporting a second bearing.
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公开(公告)号：US11008947B2
公开(公告)日：2021-05-18
申请号：US16203088
申请日：2018-11-28
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan
Abstract: A gas turbine engine includes a nacelle, and a bypass flow path in a bypass duct within the nacelle of the turbofan engine. A fan section includes a fan with fan blades. The fan section drives air along the bypass flow path. A fan shaft drives a fan that has fan blades and the fan rotates about a central longitudinal axis of the turbofan engine. A speed reduction device includes an epicyclic gear system. A turbine section is connected to the fan section through the speed reduction device and the turbine section rotates about the central longitudinal axis. A first fan bearing for supporting rotation of the fan hub is located axially forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is located axially aft of the speed reduction device. A first outer race of the first fan bearing is fixed relative to the fan hub.
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公开(公告)号：US20210087944A1
公开(公告)日：2021-03-25
申请号：US16940538
申请日：2020-07-28
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan
Abstract: A turbine engine has a fan and a low pressure compressor that rotate at a common speed and in a common direction. A fan drive turbine drives a gear reduction to, in turn, drive the low pressure compressor and the fan at a speed which is slower than a speed of the fan drive turbine. A combustor intermediate the low pressure compressor and the fan drive turbine and a thrust bearing mount the fan drive turbine, the thrust bearing being aft of a location of the combustor. A shear section in a drive connection connecting the fan drive turbine to the gear reduction is weaker than other portions of the drive connection. The shear section is aft of the thrust bearing.
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