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公开(公告)号：US20150192092A1
公开(公告)日：2015-07-09
申请号：US14155802
申请日：2014-01-15
Applicant: United Technologies Corporation
Inventor： Joseph J. Czapski, JR. , David C. Pimenta , Chung-Han Liou , Paul R. Senofonte , Steven D. Roberts
IPC: F02K1/06
CPC classification number: F02K1/06 , F02K1/09 , F05D2220/36 , F05D2260/50
Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.
Abstract translation: 紧固在飞机发动机喷嘴的静态结构上的轨道（35），引导滑块（32），其固定在固定到喷嘴的挡板（23）上的支柱（27,28）中。 每个滑块和附加的轴颈轴或螺栓（33）由钴形成，并且每个轨道滑块表面（61）和轴颈衬套（43,44）由镍合金形成以减少摩擦磨损。 轨道滑块（40,41）通过在其螺纹尖端具有工具凹口（70）的盲螺栓（68）安装到喷嘴的静态结构，以防止螺母（68）在螺母固定时转动。 每个滑块由于其上的销（102）而具有有限的旋转，其接合衬套（43）的突片（100）中的狭槽，以帮助将滑块（32）插入轨道（35,36）的倾斜端部， ，当安装或更换翼片时。
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Patent Agency Ranking
2.发明申请公开(公告)号：US20190048796A1
公开(公告)日：2019-02-14
申请号：US16048738
申请日：2018-07-30
Applicant: United Technologies Corporation
Inventor： Walter A. Ledwith, Jr. , Scott A. Carr , Christopher J. Hanlon , Peter A. White , Theodore W. Hall , John R. Farris , Andrew S. Miller , Christopher W. Robak , David C. Pimenta , David Richard Griffin
Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.
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3.发明申请公开(公告)号：US20170328231A1
公开(公告)日：2017-11-16
申请号：US14640060
申请日：2015-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Walter A. Ledwith, JR. , Scott A. Carr , Christopher J. Hanlon , Peter A. White , Theodore W. Hall , John R. Farris , Andrew S. Miller , Christopher W. Robak , David C. Pimenta , David Richard Griffin
CPC classification number: F02C3/055 , F01D11/24 , F02C7/185 , F05D2260/213 , F05D2270/20 , F05D2270/44 , Y02T50/676
Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.
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4.发明申请公开(公告)号：US20160341075A1
公开(公告)日：2016-11-24
申请号：US15106615
申请日：2014-08-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shu Liu , Robert Russell Mayer , Paul W. Palmer , Peter Balawajder , Igor S. Garcia , David C. Pimenta , Stephanie Ernst , Fernando K. Grant , Eric Baker , Andrew S. Miller
CPC classification number: F01D25/26 , F01D21/045 , F01D25/24 , F02C3/04 , F02K3/06 , F04D29/522 , F04D29/526 , F05D2220/32 , F05D2250/283 , F05D2250/29 , F05D2300/506 , F23R3/002
Abstract: A gas turbine engine includes a core assembly with a core case having a containment section for containing liberated compressor and turbine blades and blade fragments. The containment section includes first and second containment layers and the containment section is configured to have a non-linear rate of energy dissipation across the first and second containment layers, thereby to improve containment of blades and blade fragments.
Abstract translation: 燃气涡轮发动机包括具有芯壳的芯组件，所述芯壳具有用于容纳释放的压缩机和涡轮叶片和叶片碎片的容纳部分。 容纳部分包括第一和第二容纳层，并且容纳部分被配置为具有穿过第一和第二容纳层的非线性能量消耗速率，从而改善叶片和叶片碎片的收容。
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公开(公告)号：US10302041B2
公开(公告)日：2019-05-28
申请号：US15373948
申请日：2016-12-09
Applicant: United Technologies Corporation
Inventor： Joseph J. Czapski, Jr. , David C. Pimenta , Chung-Han Liou , Paul R. Senofonte , Steven D. Roberts
Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.
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公开(公告)号：US20170298867A1
公开(公告)日：2017-10-19
申请号：US15373948
申请日：2016-12-09
Applicant: United Technologies Corporation
Inventor： Joseph J. Czapski, Jr. , David C. Pimenta , Chung-Han Liou , Paul R. Senofonte , Steven D. Roberts
CPC classification number: F02K1/06 , F02K1/09 , F05D2220/36 , F05D2260/50
Abstract: Tracks (35), fastened to static structure of an aircraft engine nozzle, guide sliders (32) journaled in struts (27, 28) fastened to a flap (23) of the nozzle. Each slider and attached journal axle or bolt (33) is formed of cobalt, and each track slider surface (61) and journal bushings (43, 44) are formed of a nickel alloy to reduce wear from rubbing. Track slides (40, 41) are mounted to the static structure of the nozzle by blind bolts (68) having a tool recess (70) at its threaded tip to prevent the bolt (68) from turning as a nut is secured. Each slider has limited rotation due to a pin (102), thereon engaging a slot in a tab (100) of the bushing (43) to assist in inserting the slider (32) into the beveled ends of the tracks (35, 36), when mounting or replacing a flap.
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