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公开(公告)号：US10968767B2
公开(公告)日：2021-04-06
申请号：US15968058
申请日：2018-05-01
IPC分类号： F01D17/16
摘要： A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.
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公开(公告)号：US09551294B2
公开(公告)日：2017-01-24
申请号：US14155802
申请日：2014-01-15
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.
摘要翻译： 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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公开(公告)号：US20200232336A1
公开(公告)日：2020-07-23
申请号：US16251674
申请日：2019-01-18
摘要： A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
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公开(公告)号：US20190338665A1
公开(公告)日：2019-11-07
申请号：US15968058
申请日：2018-05-01
IPC分类号： F01D17/16
摘要： A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.
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公开(公告)号：US20190264574A1
公开(公告)日：2019-08-29
申请号：US15908268
申请日：2018-02-28
摘要： A vane arm assembly for a gas turbine engine. The vane arm assembly includes a vane arm defining an aperture at an end thereof with an aperture wall. The vane arm assembly also includes a vane stem extending through the aperture of the vane arm. The vane arm assembly further includes a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem. The vane arm assembly yet further includes an impedance ring disposed within the aperture of the vane arm and within an impedance ring groove defined by the vane stem to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
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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
发明人： Joseph J. Czapski, JR. , David C. Pimenta , Chung-Han Liou , Paul R. Senofonte , Steven D. Roberts
IPC分类号： F02K1/06
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.
摘要翻译： 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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公开(公告)号：US11008879B2
公开(公告)日：2021-05-18
申请号：US16251674
申请日：2019-01-18
摘要： A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
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公开(公告)号：US20200291802A1
公开(公告)日：2020-09-17
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：US20200032669A1
公开(公告)日：2020-01-30
申请号：US16043413
申请日：2018-07-24
发明人： Steven D. Roberts
摘要： A rotor system for a gas turbine engine may comprise a shrouded blade assembly. The shrouded blade assembly may include a blade configured to rotate about a central longitudinal axis of the gas turbine engine, an inner diameter shroud located at a proximal end of the blade, and a blade tip shroud located at a distal end of the blade. A radial seal assembly may be located radially outward of a distal surface of the blade tip shroud.
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10.发明申请INTEGRAL INSTRUMENTATION IN ADDITIVELY MANUFACTURED COMPONENTS OF GAS TURBINE ENGINES 审中-公开气体涡轮发动机的大量制造成分的综合仪表公开(公告)号：US20140182292A1
公开(公告)日：2014-07-03
申请号：US13730905
申请日：2012-12-29
IPC分类号： F02C7/00
CPC分类号： F01D21/003 , F01D17/02 , F01D17/08 , F05D2230/22 , F05D2230/30 , F05D2260/83 , Y10T29/49
摘要： An article includes a body portion made of a metal and configured for use in a gas turbine engine, a sensing feature monolithically formed with the body portion, and an interior passage connected to the sensing feature and passing through the body portion. An article with integrated sensing features may be made additive manufacturing, resulting in a structure having internal passageways connecting an aperture at one surface of the monolithic article to a second aperture at another surface of the monolithic article at the opposite end of the internal passageway.
摘要翻译： 一种物品包括由金属制成并构造成用于燃气涡轮发动机的主体部分，与主体部分整体形成的感测特征，以及连接到感测特征并穿过主体部分的内部通道。 具有集成感测特征的物品可以被制成添加剂制造，从而形成一个结构，其内部通道将整体制品的一个表面处的孔连接到在内部通道的相对端处的整体制品的另一个表面处的第二孔。
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