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公开(公告)号：US11982238B2
公开(公告)日：2024-05-14
申请号：US17881399
申请日：2022-08-04
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Michael E. McCune
CPC classification number: F02C7/36 , F16H1/28 , F05D2220/36 , F05D2260/40311
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：US20230235715A1
公开(公告)日：2023-07-27
申请号：US18130539
申请日：2023-04-04
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
Abstract: A turbofan engine includes a propulsor section that has a propulsor shaft in driving engagement with a propulsor. An epicyclic gear system has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first turbine section rotates at a first speed, and a second turbine rotates at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area of the first turbine, a second performance quantity is defined as the product of the second speed squared and the second area of the second turbine, and a performance quantity ratio is between 0.5 and 1.5.
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公开(公告)号：US20230220781A1
公开(公告)日：2023-07-13
申请号：US18187796
申请日：2023-03-22
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael E. McCune , Keith B. Allyn
CPC classification number: F01D9/041 , F01D25/162 , F01D25/28 , F05D2220/32
Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction. An inner core engine has an inner core engine housing surrounding a compressor section, including a low pressure compressor. A rigid connection between a fan case and the inner core engine includes A-frames rigidly connected at a connection point to the fan case. Fan exit guide vanes rigidly connect to the fan case, and to the inner core engine. A fan intermediate case is positioned forward of a first rotor stage in the low pressure compressor. A rigid structure is connected to the inner core engine and to the fan exit guide vanes. The rigid structure defines a structure moment stiffness. The fan intermediate case defines an intermediate case moment stiffness. A ratio of the structure moment stiffness to the intermediate case moment stiffness is between 5 and 15.
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公开(公告)号：US20230193818A1
公开(公告)日：2023-06-22
申请号：US18108270
申请日：2023-02-10
Applicant: Raytheon Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
CPC classification number: F02C3/107 , F02C7/36 , F02K3/06 , F02C7/06 , F05D2260/4031 , F05D2260/403
Abstract: A gas turbine engine includes a propulsor and a drive gear system. The drive gear system includes at least one ring gear, a plurality of intermediate gears positioned between and enmeshing with a sun gear and the at least one ring gear, with the plurality of intermediate gears carried by a gear carrier. A first bearing is configured to rotate with the gear carrier. A second bearing is on an opposite side of the drive gear system from the first bearing.
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公开(公告)号：US11680492B2
公开(公告)日：2023-06-20
申请号：US17711177
申请日：2022-04-01
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
IPC: F16H57/04 , F01D15/12 , F01D25/18 , F01D25/16 , F01D1/02 , F01D5/02 , F02C7/32 , F16H57/08 , F02C7/36 , F02K3/06
CPC classification number: F01D15/12 , F01D1/02 , F01D5/02 , F01D5/027 , F01D25/16 , F01D25/18 , F02C7/32 , F16H57/04 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2220/36 , F05D2240/70 , F05D2260/34 , F05D2260/40311 , F16H57/0423 , F16H57/0479 , F16H57/0486 , F16H2057/085
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, a compressor section, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The 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. The first and second portions have grooves at the radial interface that form a hole that expels oil through the ring gear.
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Patent Agency Ranking
公开(公告)号：US20230167787A1
公开(公告)日：2023-06-01
申请号：US18161340
申请日：2023-01-30
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Michael E. McCune
CPC classification number: F02K3/06 , F02C7/36 , F01D25/168 , F04D29/522 , F05D2220/36 , F05D2260/40311
Abstract: An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.
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公开(公告)号：US11635043B2
公开(公告)日：2023-04-25
申请号：US17342100
申请日：2021-06-08
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 turbofan engine includes a fan section that drives air along a bypass flow path in a bypass duct. An epicyclic gear system in driving engagement with the fan shaft and has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first performance quantity is defined as the product of a first speed squared and a first area and a second performance quantity is defined as the product of a second speed squared and a second area. A performance quantity ratio of a first performance quantity to a second performance quantity is between 0.5 and 1.5.
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公开(公告)号：US20220372918A1
公开(公告)日：2022-11-24
申请号：US17881399
申请日：2022-08-04
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：US20210301765A1
公开(公告)日：2021-09-30
申请号：US17342100
申请日：2021-06-08
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
Abstract: A turbofan engine includes a fan section that drives air along a bypass flow path in a bypass duct. An epicyclic gear system in driving engagement with the fan shaft and has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first performance quantity is defined as the product of a first speed squared and a first area and a second performance quantity is defined as the product of a second speed squared and a second area. A performance quantity ratio of a first performance quantity to a second performance quantity is between 0.5 and 1.5.
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公开(公告)号：US11111818B2
公开(公告)日：2021-09-07
申请号：US16667154
申请日：2019-10-29
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 shaft that drives a fan that has fan blades. An outer housing surrounds the fan. A bypass flow path is within the outer housing. A fan shaft support that supports the fan shaft defines a fan shaft support transverse stiffness. A gear system is connected to the fan shaft. The gear system includes a gear mesh that defines a gear mesh transverse stiffness. A flexible support which supports the gear system relative to a static structure defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 11% of the fan shaft support transverse stiffness. The flexible support transverse stiffness is less than 8% of the gear mesh transverse stiffness.
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