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公开(公告)号：US11111804B2
公开(公告)日：2021-09-07
申请号：US16298027
申请日：2019-03-11
摘要： Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.
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公开(公告)号：US10808539B2
公开(公告)日：2020-10-20
申请号：US15218376
申请日：2016-07-25
发明人： Taryn Narrow , Matthew E. Bintz , Lucas D. Sorensen , Daniel J. Monahan , Steven D. Roberts , Jordan T. Wall , Yuan Dong , Lisa I. Brilliant , Andrew J. Murphy
摘要： A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.
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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
发明人： Joseph J. Czapski, Jr. , David C. Pimenta , Chung-Han Liou , Paul R. Senofonte , Steven D. Roberts
摘要： 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：US20180023396A1
公开(公告)日：2018-01-25
申请号：US15218376
申请日：2016-07-25
发明人： Taryn Narrow , Matthew E. Bintz , Lucas D. Sorensen , Daniel J. Monahan , Steven D. Roberts , Jordan T. Wall , Yuan Dong , Lisa I. Brilliant , Andrew J. Murphy
摘要： A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.
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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
发明人： Joseph J. Czapski, Jr. , David C. Pimenta , Chung-Han Liou , Paul R. Senofonte , Steven D. Roberts
CPC分类号： F02K1/06 , F02K1/09 , F05D2220/36 , F05D2260/50
摘要： 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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