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1. 发明申请

WO2015102779A1 FAN DRIVE GEAR SYSTEM INCLUDING A TWO-PIECE FAN SHAFT WITH LUBRICANT TRANSFER LEAKAGE RECAPTURE 审中-公开
标题翻译：风扇驱动齿轮系统，包括带有润滑剂传输泄漏记录的双风扇风扇轴
公开(公告)号：WO2015102779A1
公开(公告)日：2015-07-09
申请号：PCT/US2014/067303
申请日：2014-11-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G. , BLUME, Karl D.
IPC分类号： F02C7/06 , F01D25/18 , F01D25/16
CPC分类号： F04D29/063 , F01D25/18 , F01D25/183 , F01M11/02 , F02C7/36 , F04D25/028 , F04D29/054 , F04D29/056 , F04D29/644 , F05B2220/302 , F05B2260/40311 , F05D2260/40311 , F05D2260/98
摘要： A disclosed fan drive gear system for a gas turbine engine includes a first fan shaft coupled to a second fan shaft, a first shaft support bearing assembly disposed about the first fan shaft and a second shaft support bearing assembly disposed about the second fan shaft. A planetary gear system is coupled to the second fan shaft. A transfer bearing is configured to receive lubricant from a lubricant input and is positioned between the first and second fan shaft support bearings. A second bearing is configured to rotate with the second fan shaft and receive lubricant from the transfer bearing and communicate lubricant to at least one lubricant passage and a conduit fluidly connecting the at least one lubricant passage to the planetary gear system.
摘要翻译：所公开的用于燃气涡轮发动机的风扇驱动齿轮系统包括联接到第二风扇轴的第一风扇轴，围绕第一风扇轴设置的第一轴支撑轴承组件和围绕第二风扇轴设置的第二轴支撑轴承组件。行星齿轮系统联接到第二风扇轴。传送轴承构造成从润滑剂输入端接收润滑剂并且位于第一和第二风扇轴支撑轴承之间。第二轴承构造成与第二风扇轴一起旋转并从传送轴承接收润滑剂，并将润滑剂与至少一个润滑剂通道和将至少一个润滑剂通道流体连接到行星齿轮系统的导管连通。

2. 发明申请

WO2015094607A1 GEARED TURBOFAN WITH IMPROVED GEAR SYSTEM MAINTAINABILITY 审中-公开
标题翻译：具有改进的齿轮系统维护的齿轮涡轮机
公开(公告)号：WO2015094607A1
公开(公告)日：2015-06-25
申请号：PCT/US2014/067270
申请日：2014-11-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G.
IPC分类号： F02C7/06 , F01D25/16 , F02K3/06 , F16H1/28
CPC分类号： F02C3/113 , F01D25/16 , F02C3/107 , F02C7/06 , F02C7/36 , F02K3/06 , F05D2220/323 , F05D2230/70 , F05D2230/72 , F05D2240/35 , F05D2260/4031
摘要： A disclosed gas turbine engine includes a fan section including a hub supporting a plurality of fan blades rotatable about an axis, and a bearing assembly supporting rotation of the hub about the axis. A compressor section is in fluid communication with a combustor and a turbine is in fluid communication with the compressor section. A speed reduction device driven by the turbine section for rotating the fan about the axis is mounted forward of the bearing assembly supporting rotation of the hub.
摘要翻译：所公开的燃气涡轮发动机包括风扇部分，该风扇部分包括支撑可围绕轴线旋转的多个风扇叶片的轮毂和支撑轮毂绕轴线旋转的轴承组件。压缩机部分与燃烧器流体连通，涡轮与压缩机部分流体连通。由涡轮部分驱动的用于围绕轴线旋转风扇的减速装置安装在支撑轮毂旋转的轴承组件的前方。

3. 发明申请

WO2014134256A1 LOW SPOOL STARTER SYSTEM FOR GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的低气压起动器系统
公开(公告)号：WO2014134256A1
公开(公告)日：2014-09-04
申请号：PCT/US2014/018877
申请日：2014-02-27
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G. , SUCIU, Gabriel L. , MERRY, Brian D.
IPC分类号： F02C7/26 , F02C7/32
CPC分类号： F02C7/275 , F01D19/00 , F02C3/107 , F02C7/36 , F05D2260/40 , F05D2260/403 , F05D2260/85
摘要： A gas turbine engine 10 comprises a first compressor 14, a second compressor 18, a starter generator 12 and a clutch 16. The starter generator 12 is coupled to the first compressor 14. The clutch 16 selectively couples the second compressor 18 and the first compressor 14. The clutch 16 is disposed between a first shaft 78B and a second shaft 22 to engage the first shaft 78B with the second shaft 22 at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft 78B relative to the second shaft 22 when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine 10 comprises engaging a low pressure compressor 14 with a high pressure compressor 18 utilizing a clutch 16, rotating the low pressure compressor 14 and the high pressure compressor 18 utilizing a starter generator 12 coupled to the low pressure compressor 14, igniting the gas turbine engine 10, and disengaging the clutch 16 at an operational speed of the gas turbine engine 10.
摘要翻译：燃气涡轮发动机10包括第一压缩机14，第二压缩机18，起动发电机12和离合器16.起动发电机12联接到第一压缩机14.离合器16选择性地将第二压缩机18和第一压缩机离合器16设置在第一轴78B和第二轴22之间，以使第一轴78B与静止的第二轴22接合。飞行重量系统与离合器机构接合，以允许当超过阈值速度的旋转运动时第一轴78B相对于第二轴22的续流。用于启动燃气涡轮发动机10的方法包括利用离合器16将低压压缩机14与高压压缩机18接合，利用联接到低压压缩机的起动器发电机12来旋转低压压缩机14和高压压缩机18 如图14所示，点燃燃气涡轮发动机10，并以燃气轮机发动机10的运转速度离合离合器16。

4. 发明申请

WO2014133713A1 TURBOMACHINE FAN CLUTCH 审中-公开
标题翻译：涡轮风扇离合器
公开(公告)号：WO2014133713A1
公开(公告)日：2014-09-04
申请号：PCT/US2014/014120
申请日：2014-01-31
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G. , MCCUNE, Michael E.
IPC分类号： F02C7/36 , F02C7/00 , F01D25/00
CPC分类号： F02C3/107 , F02C7/36 , F05D2260/4023 , F16D41/088 , F16D43/06
摘要： A gas turbine engine assembly includes, among other things, a clutch configured to move from a first position to a second position in response to rotation of a gas turbine engine fan at a speed greater than a threshold speed. Whether the clutch is in the first position or the second position, the clutch permits rotation of the gas turbine engine fan in a first direction. When the clutch is in the first position, the clutch limits rotation of the gas turbine engine fan only in an opposite, second direction. The clutch is disposed within a compartment that is accessible and removable via removal of an aft engine cover structure. The clutch is removable on-wing.
摘要翻译：燃气涡轮发动机组件尤其包括一个离合器，该离合器配置成响应于燃气涡轮发动机风扇以大于阈值速度的速度旋转而从第一位置移动到第二位置。离合器是否处于第一位置或第二位置，离合器允许燃气涡轮发动机风扇沿第一方向旋转。当离合器处于第一位置时，离合器仅在相反的第二方向限制燃气涡轮发动机风扇的旋转。离合器设置在通过拆卸后部发动机盖结构可接近和可拆卸的隔室内。离合器是可拆卸的机翼。

5. 发明申请

WO2014035581A1 FACE SEAL RETAINING ASSEMBLY FOR GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的面密封保持装置
公开(公告)号：WO2014035581A1
公开(公告)日：2014-03-06
申请号：PCT/US2013/052650
申请日：2013-07-30
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： DAVIS, Todd A. , SHERIDAN, William G.
IPC分类号： F02C7/00 , F02C7/28
CPC分类号： F16J15/3436 , F01D11/003 , F05D2260/38 , Y10T29/49718
摘要： A face seal assembly for a gas turbine engine includes an engine static structure. A guide assembly supports a face seal for movement relative to the engine static structure in an axial direction. The guide assembly includes a guide pin having a first end that supports a washer that is retained by a circlip secured to the first end. The circlip is configured to limit movement of the face seal in the axial direction.
摘要翻译：用于燃气涡轮发动机的面部密封组件包括发动机静止结构。引导组件支撑用于沿轴向相对于发动机静态结构运动的面密封件。引导组件包括导向销，该引导销具有第一端，该第一端支撑由固定到第一端的卡环保持的垫圈。簧环被配置为限制面密封件沿轴向的移动。

6. 发明申请

WO2015147949A2 AUXILIARY OIL SYSTEM FOR GEARED GAS TURBINE ENGINE 审中-公开
标题翻译：用于齿轮式涡轮发动机的辅助油系统
公开(公告)号：WO2015147949A2
公开(公告)日：2015-10-01
申请号：PCT/US2015/010020
申请日：2015-01-02
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G.
IPC分类号： F02C7/06 , F16H57/04 , F16H57/08 , F16H1/28
CPC分类号： F02C7/36 , F01D25/20 , F02C7/06 , F02K3/06 , F05D2260/40311 , F05D2260/608 , F05D2260/98 , F16H57/04 , F16H57/0427 , F16H57/0479 , F16H57/0486 , F16H57/08 , Y02T50/671
摘要： A gas turbine engine comprises a fan drive turbine, a fan rotor, and a gear reduction driven by the fan drive turbine to, in turn, drive the gear architecture. A main oil supply system supplies oil to components within the gear reduction, and an auxiliary oil supply system. The auxiliary oil system operates to ensure that the gear reduction will be adequately supplied with lubricant for at least 30 seconds at power should the main oil supply system fail.
摘要翻译：燃气涡轮发动机包括风扇驱动涡轮机，风扇转子和由风扇驱动涡轮机驱动的齿轮减速器，从而驱动齿轮结构。主要的供油系统为齿轮减速器内的部件和辅助供油系统供油。辅助油系统运行，以确保在主供油系统出现故障时，齿轮减速将能够充分供应润滑油至少30秒的动力。

7. 发明申请

WO2015069361A2 LOAD BALANCED JOURNAL BEARING PIN 审中-公开
标题翻译：负载平衡轴承销
公开(公告)号：WO2015069361A2
公开(公告)日：2015-05-14
申请号：PCT/US2014/051830
申请日：2014-08-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G.
IPC分类号： F16H1/28
CPC分类号： F02C7/36 , F02C3/04 , F05D2220/32 , F05D2230/50 , F05D2240/50 , F05D2260/40311 , F16H1/2836 , F16H1/48 , F16H57/0479 , Y10T29/49464
摘要： A disclosed fan drive gear system includes a sun gear rotatable about an axis of rotation, a plurality of intermediate gears rotatable about an intermediate gear rotation axis in meshing engagement with the sun gear and a ring gear circumscribing the intermediate gears. A bearing assembly supports at least one of the plurality of intermediate gears and includes a first beam extending in a first direction and a second beam extending from an end of the first beam in a second direction. The bearing surface supported on the second beam such that first and second beams are configured to maintain the bearing surface substantially parallel to the intermediate gear rotation axis during operation.
摘要翻译：所公开的风扇驱动齿轮系统包括可围绕旋转轴线旋转的太阳齿轮，可围绕与太阳齿轮啮合的中间齿轮旋转轴线旋转的多个中间齿轮以及环绕中间齿轮。轴承组件支承多个中间齿轮中的至少一个，并且包括在第一方向上延伸的第一梁和在第二方向上从第一梁的端部延伸的第二梁。支承面支承在第二梁上，使得第一和第二梁构造成在操作期间保持支承面基本上平行于中间齿轮旋转轴线。

8. 发明申请

WO2015060912A3 DUAL DIRECTION WINDMILL PUMP FOR GEARED TURBOFAN ENGINE 审中-公开
公开(公告)号：WO2015060912A3
公开(公告)日：2015-04-30
申请号：PCT/US2014/047795
申请日：2014-07-23
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G. , JAMES, Reade W. , MASTRO, Jacob Peter
IPC分类号： F02C7/06 , F01D25/20 , F16H57/04
摘要： A lubrication system includes a shaft rotatable about an axis, a lubrication pump configured to supply a lubricant flow to a gear system, and a gear train coupled to the shaft and configured to drive the lubrication pump in a first direction responsive to rotation of the shaft in both the first direction and a second direction. A gas turbine engine and method are also disclosed.

9. 发明申请

WO2014151785A1 TURBOFAN ENGINE BEARING AND GEARBOX ARRANGEMENT 审中-公开
标题翻译：涡轮发动机轴承和齿轮架布置
公开(公告)号：WO2014151785A1
公开(公告)日：2014-09-25
申请号：PCT/US2014/026446
申请日：2014-03-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G. , MCCUNE, Michael E.
IPC分类号： F02C7/06 , F16H1/34
CPC分类号： F02C3/107 , F02C7/06 , F02C7/36 , F02K3/06 , F05D2260/403 , F05D2260/4031
摘要： A turbofan engine (20) has a fan shaft (120) coupling a fan drive gear system (60) to the fan (28). A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. A core spool comprises a high pressure turbine (46), a compressor (44), and a core shaft (52) coupling the high pressure turbine to the core spool compressor. A first bearing (150) engages the fan shaft, the first bearing being a thrust bearing. A second bearing (160) engages the fan shaft on an opposite side of the fan drive gear system from the first bearing, the second bearing being a roller bearing. A third bearing (180) engages the low spool shaft and the fan shaft.
摘要翻译：涡扇发动机（20）具有将风扇驱动齿轮系统（60）联接到风扇（28）的风扇轴（120）。低阀芯包括将低压涡轮机联接到风扇驱动齿轮系统的低压涡轮机（50）和低轴（56）。芯轴卷轴包括高压涡轮机（46），压缩机（44）和将高压涡轮机联接到芯轴卷轴压缩机的芯轴（52）。第一轴承（150）接合风扇轴，第一轴承是推力轴承。第二轴承（160）与风扇驱动齿轮系的与第一轴承相反的一侧接合风扇轴，第二轴承是滚子轴承。第三轴承（180）接合低卷筒轴和风扇轴。

10. 发明申请

WO2014028085A3 FUNDAMENTAL GEAR SYSTEM ARCHITECTURE 审中-公开
公开(公告)号：WO2014028085A3
公开(公告)日：2014-02-20
申请号：PCT/US2013/041761
申请日：2013-05-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G.
IPC分类号： F02C3/04 , F02C7/06
摘要： A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.

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