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公开(公告)号：US10815818B2
公开(公告)日：2020-10-27
申请号：US15653064
申请日：2017-07-18
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Raymond Surace , Robert L. Hazzard , Mark Borja
IPC: F01D17/16
Abstract: A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.
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公开(公告)号：US10378363B2
公开(公告)日：2019-08-13
申请号：US15483003
申请日：2017-04-10
Applicant: United Technologies Corporation
Inventor： Christopher Whitfield , Carey Clum , Mark Borja
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction. A serpentine cooling passage is provided between the pressure and suction side walls. A passageway adjoins a passage wall and is fluidly interconnected to an upstream turn that has radially spaced apart innermost and outermost contours. The innermost contour is provided at the wall. A resupply hole is configured to exit downstream from the innermost contour.
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公开(公告)号：US09677407B2
公开(公告)日：2017-06-13
申请号：US13737093
申请日：2013-01-09
Applicant: United Technologies Corporation
Inventor： Mark Borja , Ehren B. Holt
IPC: F01D5/30
CPC classification number: F01D5/3069 , F01D5/3015
Abstract: A cover plate for a rotor disk in a gas turbine machine includes a cylindrical body having multiple outward facing snaps and multiple inward facing snaps.
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公开(公告)号：US20200308976A1
公开(公告)日：2020-10-01
申请号：US16800257
申请日：2020-02-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark Borja
Abstract: A control ring for use in a gas turbine engine includes a control ring segment defining a centerline axis. The control ring segment includes an inner diameter surface and an outer diameter surface. A thermally isolating contact is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring.
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公开(公告)号：US10544679B2
公开(公告)日：2020-01-28
申请号：US15111364
申请日：2015-01-09
Applicant: United Technologies Corporation
Inventor： Jesus S. Lopez , Mark Borja
Abstract: An example method of balancing a shaft includes inserting a balancing insert into one of a plurality of cavities. The plurality of cavities are radially inside an outermost surface of the shaft.
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Patent Agency Ranking
公开(公告)号：US09976435B2
公开(公告)日：2018-05-22
申请号：US14884015
申请日：2015-10-15
Applicant: United Technologies Corporation
Inventor： Mark Borja , Paul W. Palmer
CPC classification number: F01D11/18 , F01D5/02 , F01D25/24 , F05D2220/32 , F05D2230/21 , F05D2230/22 , F05D2230/30 , F05D2240/24 , F05D2240/307
Abstract: A rotating blade tip clearance system includes a control ring carrier defining a centerline axis. The control ring carrier has a connecting portion, a retaining portion radially inward of the connecting portion, and a flange connecting radially between the connecting portion and the retaining portion. The flange isolates the retaining portion of the control ring carrier from the thermal deflection of a case and assists in keeping the control ring carrier aligned about centerline axis A during thermal deflection. The retaining portion includes radially inner and outer diameter sides defining a retaining cavity therebetween. The system includes a control ring within the retaining cavity. The control ring has a different thermal response rate from the control ring carrier so that the control ring thermally deflects slower than the control ring carrier, thereby controlling the rate and/or extent of thermal deflection of the control ring carrier.
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公开(公告)号：US10280782B2
公开(公告)日：2019-05-07
申请号：US14759317
申请日：2013-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Igor S. Garcia , John R. Farris , Brian R. Pelletier , Thomas Almy , Brandon T. Rouse , Mark Borja
Abstract: A clearance control ring having at least two segments is disclosed. Each of the segments interlock with adjacent segments to form a full hoop clearance control ring. Separate carriers and seals or one-piece carriers and seals may be mounted on the clearance control ring. The segmented structure of the clearance control ring allows for simpler assembly with segmented cases for gas turbine engines than prior art one-piece clearance control rings. The segmented structure also may be used with one-piece pre-assembled and multi-stage rotors.
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公开(公告)号：US20190024530A1
公开(公告)日：2019-01-24
申请号：US15653064
申请日：2017-07-18
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Raymond Surace , Robert L. Hazzard , Mark Borja
IPC: F01D17/16
CPC classification number: F01D17/162 , F05D2230/60 , F05D2240/128 , F05D2260/30 , F05D2260/50
Abstract: A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.
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公开(公告)号：US20160326900A1
公开(公告)日：2016-11-10
申请号：US14705273
申请日：2015-05-06
Applicant: United Technologies Corporation
Inventor： Mark Borja
CPC classification number: F01D11/18 , F05D2240/11 , F05D2300/5023 , F05D2300/5024
Abstract: A control ring for use in a gas turbine engine includes a control ring segment defining a centerline axis. The control ring segment includes an inner diameter surface and an outer diameter surface. A thermally isolating contact is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring.
Abstract translation: 用于燃气涡轮发动机的控制环包括限定中心线轴线的控制环段。 控制环段包括内径表面和外径表面。 热隔离接触件可操作地连接到内径表面和外径表面中的至少一个。 隔热接触件的热导率低于控制环。
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10.发明申请RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE WITH AXIAL REACTION MEMBER 审中-公开具有轴向反应构件的壳体支撑结构的径向位置控制公开(公告)号：US20160053624A1
公开(公告)日：2016-02-25
申请号：US14781263
申请日：2014-04-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Brandon T. Rouse , Mark Borja , Igor S. Garcia , John R. Farris , Thomas Almy , Brian R. Pelletier
CPC classification number: F01D11/08 , F01D9/04 , F01D11/12 , F01D11/14 , F01D11/20 , F01D11/22 , F01D11/24 , F01D25/24 , Y02T50/672
Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.
Abstract translation: 用于燃气涡轮发动机级的径向位置控制组件包括壳体结构。 支撑结构由壳体结构可操作地支撑。 支撑环可操作地支撑所支撑的结构。 支撑结构和支撑环具有不同的热膨胀系数。 密封结构与支撑结构相邻。 基于相邻的支撑结构之间的周向间隙，并且基于支撑环和支撑结构之间的径向间隙，支撑环在热瞬变期间的间隙处相对于密封结构保持支撑结构。 销支撑相对于壳体结构的支撑结构，并且被配置为将支撑环与支撑结构上的负载隔离开。
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