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1.发明授权Turbomachine stator having a double skin casing including means for preventing gas flow longitudinally therethrough 失效涡轮机定子，其具有双皮肤外壳，包括用于防止气体纵向流过其中的装置
公开(公告)号：US5320484A
公开(公告)日：1994-06-14
申请号：US055068
申请日：1993-04-29
申请人： Jean-Louis Charbonnel , Pierre Debeneix , Christopher C. Glynn , Daniel J. Marey , Jean-Pierre A. J. Mourlan , Jacky S. Naudet , Gerard Receveur , Yann J. M. Rigaud , Roger C. Walker
发明人： Jean-Louis Charbonnel , Pierre Debeneix , Christopher C. Glynn , Daniel J. Marey , Jean-Pierre A. J. Mourlan , Jacky S. Naudet , Gerard Receveur , Yann J. M. Rigaud , Roger C. Walker
CPC分类号： F01D25/26 , F01D11/005
摘要： A turboshaft engine in which the stator comprises an outer casing surrounding a ring formed by a number of ring elements each having an apertured rib which spaces the element from the casing, the ribs dividing the space between the casing and the ring into separate compartments, and each rib having a sealing element disposed alongside it to cover the apertures and seal one compartment from the next. The casing and the ring are fixed together by virtue of bolts which have their axes inclined to the radial direction so that tightening the bolts causes the casing to press radially on the sealing elements at the same time as pressing them axially against the respective ribs.
摘要翻译： 一种涡轮轴发动机，其中定子包括围绕由多个环形元件形成的环的外壳，每个环形元件具有将元件与壳体隔开的多孔肋，将外壳和环之间的空间分隔成独立的隔间， 每个肋具有密封元件，沿着密封元件设置以覆盖孔并将一个隔室与下一个隔室密封。 壳体和环通过螺栓固定在一起，该螺栓的轴线相对于径向方向倾斜，使得紧固螺栓使得壳体在密封元件上径向挤压，同时将其按压在相应的肋上。
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公开(公告)号：US5713721A
公开(公告)日：1998-02-03
申请号：US644019
申请日：1996-05-09
申请人： Christopher C. Glynn , Poul D. Pedersen , Frederick M. Miller , Roger C. Walker , Sang Yeng Park , Clifford C. May
发明人： Christopher C. Glynn , Poul D. Pedersen , Frederick M. Miller , Roger C. Walker , Sang Yeng Park , Clifford C. May
CPC分类号： F01D5/323 , F01D5/326 , F04D29/322
摘要： One form of a retention system includes a pair of aft segments of 180.degree. in length disposed in annular grooves about a compressor spool, the segments having radial projections against which the aft end faces of the base portions of rotor blades abut. The blade base portions are shaped and are received in complementary-shaped slots of the spool. The forward retention system includes a plurality of arcuate segments approximately 30.degree. in length disposed in grooves adjacent the forward end faces of the blades. With the exception of the final pair of blades, the blade base portions thereof are located in the axial complementary slots in pairs, with each forward arcuate segment, except the final segment, being disposed in the groove at a circumferentially spaced location and displaced circumferentially to abut the forward end faces. The final arcuate segment is radially reduced and disposed in the remaining portion of the groove to lie flush with the spool. The base portions of the final blades are axially inserted over the final segments and the latter is displaced radially outwardly and pinned to abut the forward end faces of the final blade base portions. In another form, tabs project forwardly or rearwardly from the base portions of the blades. The tabs have holes in registry with corresponding holes in the blade slot for receiving pins thereby preventing axial movement of the blades relative to the spool.
摘要翻译： 保持系统的一种形式包括长度为180度的一对后部，其围绕压缩机线轴设置在环形槽中，所述段具有径向突出部，转子叶片的基部的后端面邻接。 叶片基部成形并被容纳在卷轴的互补形状的槽中。 前保持系统包括多个大约30度的弧形段，其设置在与刀片的前端面相邻的凹槽中。 除了最后一对叶片之外，其叶片基座部分成对地位于轴向互补的槽中，除了最后的部分之外，每个前部的弧形段在周向间隔开的位置设置在槽中， 靠近前端面。 最终弧形段径向减小并设置在凹槽的剩余部分中以与卷轴齐平。 最终叶片的基部轴向插入到最终的段上，并且后端径向向外移动并固定以邻接最终叶片基部的前端面。 在另一种形式中，翼片从叶片的基部向前或向后突出。 突片具有与刀片槽中的相应孔对准的孔，用于接收销，从而防止刀片相对于线轴的轴向移动。
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公开(公告)号：US5211407A
公开(公告)日：1993-05-18
申请号：US876602
申请日：1992-04-30
IPC分类号： F01D11/00
CPC分类号： F01D11/006
摘要： A seal assembly for use in a compressor stage of a turbine engine having a rotor disk which is attached to a plurality of rotor blades. Each rotor blade has an axially oriented dovetail attachment which connects to the rotor disk. Each rotor blade has an aftward side which is in contact with a high pressure region and a forward side which is in contact with a low pressure region. A plurality of seal segments form an annular ring located radially inward from the plurality of rotor blades. Each seal segment has an offset center of gravity which causes each seal segment to be securely attached to the rotor disk as centrifugal forces act upon each seal segment during rotation.
摘要翻译： 一种用于涡轮发动机的压缩机级的密封组件，其具有附接到多个转子叶片的转子盘。 每个转子叶片具有连接到转子盘的轴向定向的燕尾座附件。 每个转子叶片具有与高压区域接触的向前侧和与低压区域接触的前侧。 多个密封段形成从多个转子叶片径向向内定位的环形圈。 每个密封段具有偏移重心，这使得每个密封段在转动过程中随着离心力作用在每个密封段上而牢固地附接到转子盘上。
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公开(公告)号：US5320486A
公开(公告)日：1994-06-14
申请号：US6445
申请日：1993-01-21
CPC分类号： F01D25/246 , F05D2230/64 , F05D2230/642 , Y02T50/671
摘要： In a gas turbine engine, a system for maintaining uniform circumferential spacing between adjacent segments of a compressor liner, the liner segments being retained within an outer casing by a flanged connection. The system includes a T-shaped pin retained within the flanged connection radially and circumferentially by engagement with a slot formed in the outer casing, and axially by engagement with a notch formed in the adjacent liner segment, such that the liner segment overlaps the positioning pin. In a preferred embodiment, each liner segment is notched and held in place by a pin which, in turn, is retained within a slot in the compressor casing.
摘要翻译： 在燃气涡轮发动机中，用于在压缩机衬套的相邻节段之间保持均匀的周向间隔的系统，衬套段通过法兰连接保持在外壳内。 该系统包括T形销，其通过与形成在外壳中的槽接合而径向和周向地保持在凸缘连接件内，并且通过与形成在相邻衬套段中的凹口接合而轴向地使得衬套段与定位销重叠 。 在一个优选实施例中，每个衬套段被一个销子切口并保持在适当的位置，该销又被保持在压缩机壳体中的狭槽内。
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公开(公告)号：US06398500B2
公开(公告)日：2002-06-04
申请号：US09863899
申请日：2001-05-24
IPC分类号： F01D532
CPC分类号： F01D5/326 , Y10T29/49321
摘要： A retention system and method for the blades of a rotary machine for preventing forward or aft axial movement of the rotor blades includes a circumferential hub slot formed about a circumference of the machine hub. The rotor blades have machined therein a blade retention slot which is aligned with the circumferential hub slot when the blades are received in correspondingly shaped openings in the hub. At least one ring segment is secured in the blade retention slots and the circumferential hub slot to retain the blades from axial movement. A key assembly is used to secure the ring segments in the aligned slots via a hook portion receiving the ring segments and a threaded portion that is driven radially outwardly by a nut. A cap may be provided to provide a redundant back-up load path for the centrifugal loads on the key. Alternatively, the key assembly may be formed in the blade dovetail.
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公开(公告)号：US5211533A
公开(公告)日：1993-05-18
申请号：US785377
申请日：1991-10-30
CPC分类号： F01D11/001 , F04D29/083 , Y10S415/914
摘要： A method and system for diverting leakage air back into the flow path of a turbine engine. A stator vane assembly is connected to a shroud assembly at the radially inner end of the stator vane assembly, the shroud assembly is provided with a scoop which is placed in the path of leakage air traversing in a forward direction from the high pressure static side of the stator vane to the low static pressure side of the stator vane. The leakage path is located between the stator vane assembly and a rotating member. The scoop intercepts the leakage air and re-directs the leakage air into an airflow path of the turbine engine with an aftward component of velocity.
摘要翻译： 一种用于将泄漏空气转回到涡轮发动机的流动路径中的方法和系统。 定子叶片组件在定子叶片组件的径向内端处连接到护罩组件，护罩组件设置有勺子，该勺子放置在从高压静电侧的向前方向上横向移动的泄漏空气的路径中 定子叶片到定子叶片的低静压侧。 泄漏路径位于定子叶片组件和旋转构件之间。 铲斗拦截泄漏空气，并将泄漏空气重新引导到涡轮发动机的气流路径中，并且具有向后的速度分量。
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7.发明授权Spring clip made of a directionally solidified material for use in a gas turbine engine 失效由用于燃气涡轮发动机的定向凝固材料制成的弹簧夹
公开(公告)号：US5320487A
公开(公告)日：1994-06-14
申请号：US6231
申请日：1993-01-19
CPC分类号： F01D25/246 , C30B11/00 , C30B29/52 , F01D11/08 , F05D2260/30 , Y02T50/671
摘要： The present invention discloses a spring clip made of a directionally solidified nickel-base superalloy for use in a high pressure compressor stator sub-assembly of a gas turbine engine. The spring clip includes a body section and a pair of arms integrally connected to opposing sides of the body section and the spring clip is used as a means for attaching circumferentially segmented flowpath liners to an annular casing. Each arm of the spring clips exerts a spring force against a flowpath liner mount lug causing the mount lug to be seated radially against an inner surface of the casing and axially against an annular seal, wherein the pair of arms of each spring clip engage mount lugs located on circumferentially adjacent ones of the flowpath liners. The spring clip material has a relatively low modulus of elasticity in a direction which is generally parallel to a longitudinal axis of the spring clip, and to the base surface of the spring clip arms, and a relatively high modulus of elasticity in a direction which is parallel to the centerlines of the holes used to fixedly connect the body sections of the spring clips to the casing. Accordingly, the spring clip of the present invention has a smaller size and reduced weight, as compared to a clip made of a conventional equiax nickel-base superalloy, with no loss in preload capability of the fasteners used to attach the body sections of the clips to the casing.
摘要翻译： 本发明公开了一种由定向凝固的镍基超级合金制成的弹簧夹，用于燃气轮机的高压压缩机定子子组件中。 弹簧夹包括主体部分和一体地连接到主体部分的相对侧上的一对臂，并且弹簧夹被用作将周向分段的流路衬套附接到环形壳体的装置。 弹簧夹的每个臂对流路衬套安装凸耳施加弹簧力，使得安装凸耳径向抵靠壳体的内表面并且轴向地抵靠环形密封件，其中每个弹簧夹的一对臂与安装凸耳接合 位于周向相邻的流路衬套上。 弹簧夹材料在通常平行于弹簧夹的纵向轴线的方向和弹簧夹臂的基部表面上具有相对低的弹性模量，并且在一个方向上具有相对高的弹性模量 平行于用于将弹簧夹的主体部分固定地连接到壳体的孔的中心线。 因此，与由常规的等轴镍基超级合金制成的夹子相比，本发明的弹簧夹具有更小的尺寸和更小的重量，而不会损坏用于固定夹子的主体部分的紧固件的预紧能力 到套管
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公开(公告)号：US5257909A
公开(公告)日：1993-11-02
申请号：US931079
申请日：1992-08-17
CPC分类号： F01D5/3015 , F01D11/006 , F01D5/326
摘要： A sealing device for compressor axial dovetail rotor blades for a gas turbine engine comprising a sealing member having a finger portion extending from a main body portion which engages a disk hook located on each disk post and forms a first point of contact about which the sealing member rotates. The sealing member further comprises an extended skirt portion which engages the blade platform of the rotor blades forming a second point of contact. The main body has a center of gravity positioned such that during operation of the engine the main body pivots due to centrifugal force about the disk hook such that the skirt portion engages the blade platform. A split ring is located between the disk posts and a tail portion extending from the lower portion of the sealing member and engages the disk post and tail portion during operation of the engine thereby forming a third point of contact. The combination of the skirt element contacting the blade platform and the split ring contacting the tail portion and the disk posts effectively prevents any leakage axially through the rotor blade dovetail.
摘要翻译： 一种用于燃气涡轮发动机的压缩机轴向燕尾转子叶片的密封装置，包括密封构件，该密封构件具有从主体部延伸的指状部分，该主体部分接合位于每个盘柱上的盘钩，并形成第一接触点，密封构件 旋转 密封构件还包括延伸的裙部，其接合形成第二接触点的转子叶片的叶片平台。 主体具有重心定位，使得在发动机操作期间，主体由于围绕盘钩的离心力枢转，使得裙部接合刀片平台。 开口环位于盘柱和从密封构件的下部延伸的尾部之间并且在发动机操作期间与盘柱和尾部接合，从而形成第三接触点。 接触叶片平台的裙部元件和接触尾部和圆盘柱的开口环的组合有效地防止轴向穿过转子叶片燕尾榫的任何泄漏。
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公开(公告)号：US06357237B1
公开(公告)日：2002-03-19
申请号：US09398558
申请日：1999-09-17
IPC分类号： F02C100
CPC分类号： F23R3/28 , F23D11/36 , F23D11/402 , F23D2206/10 , F23D2209/30
摘要： A fuel injection assembly for a gas turbine engine combustor, including at least one fuel stem, a plurality of concentrically disposed tubes positioned within each fuel stem, wherein a cooling supply flow passage, a cooling return flow passage, and a tip fuel flow passage are defined thereby, and at least one fuel tip assembly connected to each fuel stem so as to be in flow communication with the flow passages, wherein an active cooling circuit for each fuel stem and fuel tip assembly is maintained by providing all active fuel through the cooling supply flow passage and the cooling return flow passage during each stage of combustor operation. The fuel flowing through the active cooling circuit is then collected so that a predetermined portion thereof is provided to the tip fuel flow passage for injection by the fuel tip assembly.
摘要翻译： 一种用于燃气涡轮发动机燃烧器的燃料喷射组件，其包括至少一个燃料杆，位于每个燃料杆内的多个同心设置的管，其中，冷却供给流路，冷却回流通道和末端燃料流动通道 以及与每个燃料杆连接以便与流动通道流动连通的至少一个燃料末端组件，其中通过提供所有活性燃料通过冷却来维持每个燃料杆和燃料末端组件的主动冷却回路 在燃烧器运行的每个阶段，供应流通道和冷却回流通道。 然后，流过主动冷却回路的燃料被收集，使得其预定部分被提供给燃料末端组件用于喷射的末端燃料流动通道。
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公开(公告)号：US06676369B2
公开(公告)日：2004-01-13
申请号：US10106401
申请日：2002-03-26
IPC分类号： F01D1102
CPC分类号： F16J15/442 , F01D11/025
摘要： A gas turbine engine aspirating face seal includes a rotatable engine member and a non-rotatable engine member and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces circumscribed about a centerline are operably associated the rotatable and non-rotatable engine members respectively. Radially inner and outer tooth rings axially extend away from a first one of the rotatable and non-rotatable gas bearing face surfaces across the leakage path and towards a second one of the gas bearing face surfaces. A pull off biasing means is used for urging the inner and outer tooth rings axially away from the second one of the gas bearing face surfaces. The rotatable engine member may be a side plate mounted on a rotor disk and the non-rotatable engine member is mounted on a translatable piston axially movably supported on a stationary face seal support structure.
摘要翻译： 燃气涡轮发动机抽吸面密封件包括可旋转的发动机构件和不可旋转的发动机构件以及它们之间的泄漏路径。 围绕中心线环绕的环形大致平面的可旋转和不可旋转的气体支承面表面分别可操作地与可旋转和不可旋转的发动机构件相关联。 径向内齿和外齿环沿穿过泄漏路径并朝着气体支承面表面中的第二个轴向延伸远离可旋转和不可旋转的气体支承面表面中的第一个。 使用拉脱偏压装置来推动内齿轮和外齿环轴向远离第二气体支承面表面。 可旋转的发动机构件可以是安装在转子盘上的侧板，并且不可旋转的发动机构件安装在可移动地支撑在固定面密封支撑结构上的可平移活塞上。
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