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公开(公告)号：US5236302A
公开(公告)日：1993-08-17
申请号：US785404
申请日：1991-10-30
申请人： Robert H. Weisgerber , Richard W. Albrecht , Christopher C. Glynn , John T. Kutney, Jr. , Robert J. Meade
发明人： Robert H. Weisgerber , Richard W. Albrecht , Christopher C. Glynn , John T. Kutney, Jr. , Robert J. Meade
CPC分类号： F01D5/06 , F01D11/001 , F01D5/066
摘要： A turbine engine of the type having a compressor section, combustor section and high-pressure turbine section in which compressor air is conveyed internally of the compressor and turbine sections to cool the turbine interstage volume, a first stage turbine disk includes a shaft supporting a second stage turbine disk, a turbine interstage seal is secured by boltless engagement to the disks and is prestressed to resist flexure, and the first stage disk carries a forward seal attached by boltless connections. The interstage seal includes a bore having a rearwardly-extending arm engaging the aft shaft in a bayonet connection to prevent deflection of the bore and includes passages to allow air flow around the bore. The forward seal includes radially-extending vanes to convey cooling air along the disk, and is secured by inward and outward bayonet connections, the inward connection including locking pins which are arranged to perform a balancing function.
摘要翻译： 一种具有压缩机部分，燃烧器部分和高压涡轮机部分的涡轮发动机，其中压缩机空气在压缩机和涡轮机部分内部被输送以冷却涡轮机级间容积，第一级涡轮盘包括支撑第二 涡轮机级间密封件通过与盘的无螺纹接合来固定，并且预应力以抵抗挠曲，并且第一级盘承载通过无螺栓连接附接的前密封。 级间密封件包括具有向后延伸的臂的孔，该臂在卡口连接处与后轴接合以防止孔的偏转，并且包括允许空气围绕孔流动的通道。 前密封件包括径向延伸的叶片，以沿着盘传送冷却空气，并且通过向内和向外的卡口连接来固定，所述向内连接包括被布置成执行平衡功能的锁定销。
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公开(公告)号：US5292138A
公开(公告)日：1994-03-08
申请号：US947698
申请日：1992-09-21
CPC分类号： F16J15/164
摘要： A split ring seal having an outer split ring and an inner split ring with the inner and outer split rings having overlapping portions. The split ring seal is located between a seating seal and a carrier and separates a high pressure cavity from a low pressure cavity. Movement of the split ring seal is restricted by sidewalls of the carrier. A diagonal edge on the outer ring reacts against centrifugal loading from the inner ring so that said outer ring is urged axially against a sidewall of the carrier to form a positive seal for blocking any leakage path between the high and low pressure cavities.
摘要翻译： 具有外部开口环和内部开口环的开口环密封件，内部和外部开口环具有重叠部分。 分离环密封件位于座密封件和载体之间，并将高压腔与低压腔分离。 开口环密封件的移动受到载体侧壁的限制。 外环上的对角边缘与来自内圈的离心负载反应，使得所述外环被轴向地推靠在载体的侧壁上，以形成用于阻挡高压腔和低压腔之间的任何泄漏路径的正密封。
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公开(公告)号：US5333993A
公开(公告)日：1994-08-02
申请号：US024581
申请日：1993-03-01
申请人： Henry B. Stueber , Eric E. Baehre , Richard W. Albrecht , Christopher C. Glynn , Robert J. Hemmelgarn
发明人： Henry B. Stueber , Eric E. Baehre , Richard W. Albrecht , Christopher C. Glynn , Robert J. Hemmelgarn
CPC分类号： F01D11/025 , F01D11/001 , F01D11/04
摘要： A stator seal assembly for a gas turbine engine of a type having a high pressure compressor section and a high pressure turbine section, the stator seal having a seal segment extending between a stator vane support structure and disk seal teeth, the stator seal segment having an arm for forming a cavity, a retaining segment attached to the seal segment and the arm for sealing the cavity to form a dead air space, a control ring located in the cavity having a coefficient of thermal expansion lower than a coefficient of thermal expansion for the seal segment, and a honeycomb pad located between the arm and the seal teeth, whereby thermal expansion clearance between the stator vane and the rotor disk is minimized.
摘要翻译： 一种用于具有高压压缩机部分和高压涡轮部分类型的燃气涡轮发动机的定子密封组件，所述定子密封件具有在定子叶片支撑结构和盘密封齿之间延伸的密封段，所述定子密封段具有 用于形成空腔的臂，附接到密封段的保持段和用于密封空腔以形成死空间的臂，位于空腔中的控制环，其热膨胀系数低于热膨胀系数 密封段和位于臂和密封齿之间的蜂窝垫，由此定子叶片和转子盘之间的热膨胀间隙最小化。
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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：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：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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公开(公告)号：US06240719B1
公开(公告)日：2001-06-05
申请号：US09207818
申请日：1998-12-09
IPC分类号： F02K304
CPC分类号： F01D21/045 , F01D21/04 , F01D25/16 , F01D25/162 , F05B2260/3011
摘要： A support structure for a gas turbine engine includes a support arm (214, 216) extending between a low pressure shaft (202) and a rotor. The support arm includes a fuse (220) having a low failure point. A high pressure stub shaft (270) axially and radially supports the low pressure shaft (202) after fuse failure. An axial gap (A) between a portion of the low pressure shaft and the stub shaft permits movement of the low pressure shaft after fuse failure. A radial gap (B) between the stub shaft (270) and the low pressure shaft (202) allows radial deflection of the low pressure rotor system after fuse failure.
摘要翻译： 用于燃气涡轮发动机的支撑结构包括在低压轴（202）和转子之间延伸的支撑臂（214,216）。 支撑臂包括具有低故障点的保险丝（220）。 保险丝故障后，高压短轴（270）轴向和径向地支撑低压轴（202）。 在低压轴的一部分和短轴之间的轴向间隙（A）允许熔丝故障后低压轴的移动。 短轴（270）和低压轴（202）之间的径向间隙（B）允许在保险丝故障之后低压转子系统的径向偏转。
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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：US5281098A
公开(公告)日：1994-01-25
申请号：US967890
申请日：1992-10-28
CPC分类号： F01D5/3015 , Y02T50/671
摘要： The present invention provides an axial blade to disk retaining assembly having a plurality of circumferentially disposed lugs arranged in a ring around an axial facing surface of the blade and disk assembly and a plurality of circumferentially disposed hooks arranged in a ring around the axial facing surface and in circumferential alternating positions with the hooks and radially spaced apart from and open towards the lugs. A split retaining ring is provided that is operable to be placed between said hooks and lugs to axially secure the blades on the disk. In the preferred embodiment each hook is disposed on a disk post between the blades and each lug is disposed on a blade root.
摘要翻译： 本发明提供了一种轴向刀片到盘片保持组件，其具有围绕刀片和盘组件的面向轴向的表面布置成环的多个周向设置的凸耳和围绕轴向面向表面布置成环的多个周向设置的钩， 与钩的周向交替位置并且朝向凸耳径向间隔开并且朝向凸耳敞开。 提供了分离保持环，其可操作地放置在所述钩和凸耳之间以将叶片轴向地固定在盘上。 在优选实施例中，每个钩设置在叶片之间的盘柱上，并且每个凸耳设置在叶片根部上。
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