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公开(公告)号：US11073106B2
公开(公告)日：2021-07-27
申请号：US15881240
申请日：2018-01-26
Applicant: UNITED 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 some 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 relatively high.
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公开(公告)号：US20200291816A1
公开(公告)日：2020-09-17
申请号：US16406371
申请日：2019-05-08
Applicant: United 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 configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness.
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公开(公告)号：US20200025031A1
公开(公告)日：2020-01-23
申请号：US16125179
申请日：2018-09-07
Applicant: United 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. 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 and includes a gear mesh that defines a gear mesh transverse stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 11% of the fan shaft support transverse stiffness and less than 8% of the gear mesh transverse stiffness.
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公开(公告)号：US10539222B2
公开(公告)日：2020-01-21
申请号：US15185292
申请日：2016-06-17
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
IPC: F02C7/36 , F16H57/028 , F01D25/16 , F02K3/06 , F04D25/02 , F04D29/053 , F04D29/056 , F16H1/28
Abstract: A geared architecture for a gas turbine engine includes a fan shaft and a frame which supports said fan shaft. The frame defines a frame stiffness. A plurality of gears drives the fan shaft and includes a gear mesh that defines a gear mesh stiffness. A stiffness of a ring gear of the plurality of gears is less than about 20% of the gear mesh stiffness. A flexible support supports the geared architecture and defines a flexible support stiffness. An input coupling to the plurality of gears defines an input coupling stiffness. The flexible support stiffness and the input coupling stiffness are each less than about 11% of the frame stiffness.
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公开(公告)号：US20190153945A1
公开(公告)日：2019-05-23
申请号：US15819011
申请日：2017-11-21
Applicant: United Technologies Corporation
Inventor： Kaliya Balamurugan , Jason Husband
CPC classification number: F02C7/06 , F01D1/26 , F01D5/02 , F01D21/045 , F02C3/067 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2230/90 , F05D2240/24 , F05D2240/60 , F05D2300/17 , F05D2300/509
Abstract: A multi-shaft assembly includes an inner shaft and an outer shaft coaxially aligned with the inner shaft to establish a shared axis of rotation. The multi-shaft assembly also includes an ablatable shaft feature with a lubricant surface coating on an interior surface of the outer shaft and an ablatable metallic alloy layer overlaying a portion of the lubricant surface coating with a radial air gap formed between the ablatable metallic alloy layer and an exterior surface of the inner shaft.
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Patent Agency Ranking
公开(公告)号：US10227893B2
公开(公告)日：2019-03-12
申请号：US15606494
申请日：2017-05-26
Applicant: United 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. 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：US10077671B2
公开(公告)日：2018-09-18
申请号：US14768775
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Husband , Drew W. Lancaster
CPC classification number: F01D11/122 , B05D5/083 , F01D5/02 , F01D11/127 , F01D21/045 , F01D25/24 , F02C7/24 , F04D29/526 , F05D2220/32 , F05D2220/36 , F05D2230/23 , F05D2230/60
Abstract: A fan case for a gas turbine engine includes a fan case surrounding a fan with fan blades. A liner is disposed between the fan case and the fan and is spaced a radial distance from the fan case. A torque stop is arranged between the fan case and the liner. A method for reducing fan case liner loads is also disclosed.
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88.发明授权公开(公告)号：US10041498B2
公开(公告)日：2018-08-07
申请号：US14912105
申请日：2014-08-21
Applicant: United Technologies Corporation
Inventor： John R. Otto , James B. Coffin , Jason Husband
IPC: F02K3/06 , F04D25/04 , F02C3/107 , F01D5/02 , F01D15/12 , F04D25/02 , F04D27/00 , F04D29/32 , F02C7/36
Abstract: A turbofan engine is disclosed that includes a fan rotatable about an axis, a compressor section including a high pressure compressor, a medium pressure compressor and a low pressure compressor and a turbine section including a high pressure turbine, an intermediate turbine and a fan drive turbine. A fan drive gear system is driven by the fan drive turbine for driving the fan. A compressor drive gear system is driven by the intermediate turbine for driving the low pressure compressor. A gear controller controls rotation of at least one of the fan drive gear system and the compressor drive gear system relative to a static structure to vary an effective speed reduction ratio of one of the fan drive gear system and the compressor drive gear system.
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公开(公告)号：US20180135454A1
公开(公告)日：2018-05-17
申请号：US15856396
申请日：2017-12-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear lateral stiffness and a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral stiffness and the ring gear transverse stiffness is less than 12% of a respective one of the gear mesh lateral stiffness the ring gear transverse stiffness.
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公开(公告)号：US20180119564A1
公开(公告)日：2018-05-03
申请号：US15856441
申请日：2017-12-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. A gear system input connected to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness At least one of the gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.
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