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公开(公告)号：US11525406B2
公开(公告)日：2022-12-13
申请号：US17023860
申请日：2020-09-17
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a compressor section, and a turbine section including a fan drive turbine that drives the fan through a gear reduction. The gear reduction includes at least two double helical gears in meshed engagement, each of the at least two double helical gears having a first plurality of gear teeth separated from a second plurality of gear teeth such that a first end of the first plurality of gear teeth and a first end of the second plurality of gear teeth are spaced apart by an axial distance. Each of the first plurality of gear teeth is offset a first circumferential offset distance in relation to the next gear tooth of the second plurality of gear teeth when moving in a circumferential direction relative to respective axes.
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公开(公告)号：US11499624B2
公开(公告)日：2022-11-15
申请号：US17540400
申请日：2021-12-02
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Lawrence E. Portlock
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface and respective flanges extending along the radial interface radially outward from the teeth. The first and second portions define a trough axially between and separating the teeth of the first portion from the teeth of the second portion. The first and second portions include facing recesses that form an internal annular cavity along the radial interface.
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公开(公告)号：US11339726B2
公开(公告)日：2022-05-24
申请号：US16936791
申请日：2020-07-23
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune , William G. Sheridan
Abstract: A method of assembling an epicyclic gear train includes the steps of providing a carrier having a central axis that includes spaced apart side walls and circumferentially spaced connecting structure defining spaced apart apertures provided at an outer circumference of the carrier, gear pockets provided between the side walls and extending to the apertures, and a central opening in at least one of the side walls, inserting a plurality of intermediate gears through the central opening and moving the intermediate gears radially outwardly into the gear pockets to extend into the apertures, inserting a sun gear through the central opening after the step of inserting the plurality of intermediate gears through the central opening, moving the plurality of intermediate gears radially inwardly to engage the sun gear, and placing a ring gear on an outer periphery of the intermediate gears to engage the intermediate gears after the step of moving the plurality of intermediate gears radially inwardly.
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公开(公告)号：US20220018311A1
公开(公告)日：2022-01-20
申请号：US16931685
申请日：2020-07-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael E. McCune , Andrew J. Murphy
Abstract: A gas turbine engine includes a fan shaft rotatable about an axis, a fan connected to the fan shaft, and an outer housing surrounding the fan to define a bypass passage. A compressor section has both a low pressure compressor that is fixed to rotate with the fan shaft and a high pressure compressor. A turbine section has a low pressure turbine driving a low speed spool and a high pressure turbine driving the high pressure compressor. The low pressure turbine includes rotating blades and a static structure aft of the rotating blades. A fan drivetrain includes a geared architecture connecting the low speed spool to the fan shaft such that the fan and low pressure compressor rotate at a lower speed than the low pressure turbine. A thrust bearing is axially aft of the geared architecture and axially forward of the high pressure compressor. A tower shaft is rotatably driven by the low speed spool.
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公开(公告)号：US11208958B2
公开(公告)日：2021-12-28
申请号：US16939291
申请日：2020-07-27
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A method of assembling a fan drive gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier defining a central axis and that includes spaced apart walls and circumferentially spaced mounts defining spaced apart apertures at an outer circumference of the carrier, gear pockets defined between the walls and extending to the apertures, and a central opening in at least one of the walls. The method includes the steps of inserting a plurality of intermediate gears through the central opening, moving the intermediate gears radially outwardly relative to the central axis into the gear pockets, inserting a sun gear through the central opening, moving the plurality of intermediate gears radially inwardly relative to the central axis to engage the sun gear, and coupling a fan shaft to the carrier such that the fan shaft and intermediate gears are rotatable about the central axis. A fan drive gear system is also disclosed.
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Patent Agency Ranking
公开(公告)号：US20210363898A1
公开(公告)日：2021-11-25
申请号：US17394497
申请日：2021-08-05
Applicant: Raytheon Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
IPC: F01D25/16 , F02C7/32 , F02C7/36 , F01D15/12 , F01D25/28 , F01D5/06 , F01D9/02 , F02K3/06 , F04D25/04 , F04D29/053 , F04D29/32 , F04D19/02 , F04D29/056
Abstract: A gas turbine engine includes a fan section that has fan blades that drive air along a bypass flow path in a bypass duct. A fan shaft is drivingly connected to the fan. A turbine section includes a turbine drive shaft. A gear system is connected to the turbine draft shaft through an input and connected to the fan shaft through an output. At least one of the input and the output include a flexible coupling. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the turbine drive shaft during operation. The gear system flex mount arrangement includes a gear mesh that defines a gear mesh lateral stiffness and a ring gear that defines a ring gear lateral stiffness that is less than 12% of the gear mesh lateral stiffness.
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公开(公告)号：US20210239052A1
公开(公告)日：2021-08-05
申请号：US17236850
申请日：2021-04-21
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.
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公开(公告)号：US11047337B2
公开(公告)日：2021-06-29
申请号：US15485512
申请日：2017-04-12
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
IPC: F02K3/06 , F02C3/107 , F02C7/36 , F02C7/20 , F01D15/12 , F01D5/06 , F04D19/00 , F04D25/04 , F04D29/053 , F04D29/32 , F01D9/04
Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.
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公开(公告)号：US11021996B2
公开(公告)日：2021-06-01
申请号：US16298319
申请日：2019-03-11
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband
IPC: F01D25/16 , F02C7/32 , F02C7/36 , F01D15/12 , F01D25/28 , F01D5/06 , F01D9/02 , F02K3/06 , F04D25/04 , F04D29/053 , F04D29/32 , F04D19/02 , F04D29/056
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. The fan delivers airflow to a bypass duct. A fan shaft support supports the fan shaft and defines a support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input is connected to the gear system and defines a gear system input lateral stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness.
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公开(公告)号：US20210140373A1
公开(公告)日：2021-05-13
申请号：US16939291
申请日：2020-07-27
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
Abstract: A method of assembling a fan drive gear system for a gas turbine engine according to an example of the present disclosure includes the steps of providing a unitary carrier defining a central axis and that includes spaced apart walls and circumferentially spaced mounts defining spaced apart apertures at an outer circumference of the carrier, gear pockets defined between the walls and extending to the apertures, and a central opening in at least one of the walls. The method includes the steps of inserting a plurality of intermediate gears through the central opening, moving the intermediate gears radially outwardly relative to the central axis into the gear pockets, inserting a sun gear through the central opening, moving the plurality of intermediate gears radially inwardly relative to the central axis to engage the sun gear, and coupling a fan shaft to the carrier such that the fan shaft and intermediate gears are rotatable about the central axis. A fan drive gear system is also disclosed.
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