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公开(公告)号：US20200025032A1
公开(公告)日：2020-01-23
申请号：US16298319
申请日：2019-03-11
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：US10352194B2
公开(公告)日：2019-07-16
申请号：US15690554
申请日：2017-08-30
Applicant: United Technologies Corporation
Inventor： Philip Andrew Varney , Jason Husband
IPC: F16C19/06 , F16C33/10 , F16C27/00 , F16C33/66 , F01D25/16 , F01D25/18 , F01D11/00 , F16F15/023 , F16C27/04
Abstract: A bearing assembly includes a case, a bearing spring positioned inside the case, a first seal positioned between the case and the bearing spring, and a second seal. The a second seal is positioned between the case and the bearing spring and is spaced apart from the first seal, wherein the second seal is an adjustable seal that is movable between a closed position and an opened position to inhibit or allow, respectively, a fluid to flow from a cavity that is defined by the case, the bearing spring, the first seal and the second seal.
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公开(公告)号：US20190145423A1
公开(公告)日：2019-05-16
申请号：US15812331
申请日：2017-11-14
Applicant: United Technologies Corporation
Inventor： Jason Husband , James Glaspey
Abstract: A fan of a gas turbine engine is provided. The fan having: a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end and a tip portion that is secured to a shroud that circumscribes the plurality of fan blades.
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公开(公告)号：US20190063452A1
公开(公告)日：2019-02-28
申请号：US15689946
申请日：2017-08-29
Applicant: United Technologies Corporation
Inventor： Jason Husband , James Glaspey
Abstract: A conical hub for a fan of a gas turbine engine is provided. The conical hub having: a plurality of attachment features located on an outer circumferential surface of the conical hub, wherein at least some of the plurality attachment features are axially aligned with each other and at least some of the plurality of attachment features are off set from each other, and wherein each of the plurality of attachment features have an opening configured to receive a portion of a pin; and the outer circumferential surface of the conical hub increases in diameter with respect to an axis of the conical hub in a forward to aft direction of the conical hub.
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公开(公告)号：US20190063261A1
公开(公告)日：2019-02-28
申请号：US15690554
申请日：2017-08-30
Applicant: United Technologies Corporation
Inventor： Philip Andrew Varney , Jason Husband
CPC classification number: F01D25/164 , F01D11/003 , F01D25/183 , F05D2220/32 , F05D2240/50 , F05D2260/98 , F16C19/06 , F16C27/00 , F16C27/045 , F16C33/104 , F16C33/6659 , F16C2360/23 , F16F15/0237
Abstract: A bearing assembly includes a case, a bearing spring positioned inside the case, a first seal positioned between the case and the bearing spring, and a second seal. The a second seal is positioned between the case and the bearing spring and is spaced apart from the first seal, wherein the second seal is an adjustable seal that is movable between a closed position and an opened position to inhibit or allow, respectively, a fluid to flow from a cavity that is defined by the case, the bearing spring, the first seal and the second seal.
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Patent Agency Ranking
公开(公告)号：US20180094532A1
公开(公告)日：2018-04-05
申请号：US15816512
申请日：2017-11-17
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 includes a fan shaft that has fan blades. A fan shaft is drivingly connected to the fan. A fan shaft support supports the fan shaft and defines a fan shaft support lateral stiffness. A gear system is connected to the fan shaft and driven through an input. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the input during operation and includes a flexible support that defines a flexible support lateral stiffness that is less than 11% of the shaft support lateral stiffness.
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公开(公告)号：US20170260875A1
公开(公告)日：2017-09-14
申请号：US15606556
申请日：2017-05-26
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
CPC classification number: F01D25/164 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/16 , F01D25/28 , F02C7/32 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/045 , F04D29/053 , F04D29/056 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/60 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y10T29/49321
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 that supports the fan shaft and defines a fan shaft support transverse stiffness. A gear system 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 flexible support supports said gear system and defines a flexible support transverse stiffness. 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：US09752511B2
公开(公告)日：2017-09-05
申请号：US15484441
申请日：2017-04-11
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 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：US20170175581A1
公开(公告)日：2017-06-22
申请号：US15451929
申请日：2017-03-07
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
IPC: F01D25/16 , F04D29/053 , F04D25/04 , F01D5/06 , F04D29/056 , F01D9/02 , F02K3/06 , F02C7/36 , F04D19/02 , F04D29/32 , F01D15/12
CPC classification number: F01D25/164 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/16 , F01D25/28 , F02C7/32 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/045 , F04D29/053 , F04D29/056 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/60 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y10T29/49321
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 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 transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. The ring gear transverse stiffness is less than 20% of the gear mesh transverse stiffness.
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50.发明申请公开(公告)号：US20160195096A1
公开(公告)日：2016-07-07
申请号：US14912105
申请日：2014-08-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John R. Otto , James B. Coffin , Jason Husband
CPC classification number: F04D25/045 , F01D5/02 , F01D15/12 , F02C3/107 , F02C7/36 , F02K3/06 , F04D25/028 , F04D27/004 , F04D29/321 , F05D2220/32 , F05D2260/40311 , F05D2270/02
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.
Abstract translation: 公开了一种涡轮风扇发动机，其包括可围绕轴线旋转的风扇，包括高压压缩机，中压压缩机和低压压缩机的压缩机部分和包括高压涡轮机，中间涡轮机和风扇驱动涡轮机 。 风扇驱动齿轮系由风扇驱动涡轮驱动，用于驱动风扇。 压缩机驱动齿轮系由驱动低压压缩机的中间涡轮驱动。 齿轮控制器相对于静态结构控制风扇驱动齿轮系统和压缩机驱动齿轮系统中的至少一个的旋转，以改变风扇驱动齿轮系统和压缩机驱动齿轮系统之一的有效减速比。
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