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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：US5226784A
公开(公告)日：1993-07-13
申请号：US951929
申请日：1992-09-25
申请人： Peter W. Mueller , Joseph T. Stevenson , Josef Panovsky , Christopher C. Glynn , Sang Y. Park , Daniel E. Wines
发明人： Peter W. Mueller , Joseph T. Stevenson , Josef Panovsky , Christopher C. Glynn , Sang Y. Park , Daniel E. Wines
CPC分类号： F01D5/22 , F01D11/006 , Y10S416/50
摘要： The present invention provides a phase independent damper and damper assembly capable of damping rotor blade vibrations in the axial, circumferential, and radial directions. One embodiment, particularly useful in an aircraft gas turbine engine compressor rotor, provides a damper and damper assembly including a generally axially extending blade damper operable to fictionally engage a generally axially extending circumferentially facing surface of a disk and axially extending angled surface under the platform of the blade. The invention provides an additional advantage of allowing simple and easy modification of existing engines to incorporate the damper of the present invention.
摘要翻译： 本发明提供了一种相位独立的阻尼器和阻尼器组件，其能够在轴向，周向和径向上阻尼转子叶片的振动。 在飞行器燃气涡轮发动机压缩机转子中特别有用的一个实施例提供了一种阻尼器和阻尼器组件，其包括大致轴向延伸的叶片阻尼器，其可操作地虚拟地接合盘的大致轴向延伸的面向周向的表面并且在 刀片。 本发明提供了允许对现有发动机的简单和容易的修改以结合本发明的阻尼器的另外的优点。
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公开(公告)号：US5205713A
公开(公告)日：1993-04-27
申请号：US693165
申请日：1991-04-29
IPC分类号： F01D5/26
CPC分类号： F01D5/26 , Y02T50/673 , Y10S416/50
摘要： A fan blade damper system includes a fan disk integrally connected to a disk post. A retainer is fastened to the disk post and is molded to retain a damper block. The top portion of the damper block is shaped to make frictional contact with the underside of the platform of a fan blade, the underside of the platform being the region of the fan blade which experiences the highest platform vibratory amplitude when the fan blade is rotated. The damper block is thus mounted in a statically determinant fashion. The rotation of the fan blade produces centrifugal forces which produce reactionary forces in the damper block and retainer such that a maximum damping force amplitude is reacted to the fan disk.
摘要翻译： 风扇叶片阻尼器系统包括与盘柱一体地连接的风扇盘。 保持器被固定到盘柱上并被模制以保持阻尼块。 阻尼器块的顶部成形为与风扇叶片的平台的下侧摩擦接触，平台的下侧是当风扇叶片旋转时经历最高平台振动振幅的风扇叶片的区域。 因此，阻尼器块以静态方式安装。 风扇叶片的旋转产生离心力，其在阻尼器块和保持器中产生反作用力，使得最大阻尼力振幅与风扇盘反应。
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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：US5292227A
公开(公告)日：1994-03-08
申请号：US988637
申请日：1992-12-10
CPC分类号： F01D9/065 , F01D25/162
摘要： A turbine frame includes first and second coaxially disposed rings having a plurality of circumferentially spaced apart struts extending therebetween. A plurality of clevises join respective first ends of the struts to the first ring for removably joining the struts thereto. Each of the clevises includes a base removably fixedly joined to the first ring, and a pair of legs extending away from the base and spaced apart to define a U-shaped clevis slot receiving the strut first end. The first strut end is removably fixedly joined to the clevis legs by a pair of expansion bolts. The clevis base includes a central aperture aligned with a first port in the first ring for providing access therethrough. And, the strut first end abuts the first ring for carrying compressive loads therebetween and providing a seal therewith.
摘要翻译： 涡轮机框架包括第一和第二同轴设置的环，其具有在其间延伸的多个周向间隔开的支柱。 多个U形夹将支柱的相应的第一端连接到第一环，用于将支柱可拆卸地连接到其上。 每个夹头包括可移除地固定地连接到第一环的基座和一对从基部延伸并间隔开的一对腿，以限定接纳支柱第一端的U形U形夹。 第一支柱端通过一对膨胀螺栓可拆卸地固定在U形夹腿上。 U形夹底座包括与第一环中的第一端口对准的中心孔，用于提供通过其中的通路。 并且，支柱第一端邻接第一环以在其间承载压缩载荷并且提供与其的密封。
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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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公开(公告)号：US5167734A
公开(公告)日：1992-12-01
申请号：US804495
申请日：1991-12-09
CPC分类号： B22D31/002 , B21J5/00 , C21D10/00 , C22F1/10
摘要： A process for identificaiton, evaluation and removal of microshrinkage of investment cast superalloy parts and parts produced by the process. Parts free of deleterious microshrinkage capable of longer life at existing stress levels or use at higher alternating stresses are produced by first subjecting the parts to hot isostatic pressing to eliminate nonsurface connected subsurface microshrinkage. Next, in order to expose near-surface microshrinkage microscopically connected to the surface, the parts are immersed in an acid solution for a time sufficient to uniformly remove at least about 0.005 inches of the original as cast surface. The exposed microshrinkage is evaluated for acceptability or removal by standard nondestructive techniques, such as liquid penetration evaluation.
摘要翻译： 用于鉴定，评估和清除由该方法生产的投资超级合金部件和零件的微收缩的过程。 通过首先使部件经受热等静压，以消除非表面连接的地下微收缩，产生无有害微量收缩的能够在现有应力水平下使用更长寿命或在较高交变应力下使用的部件。 接下来，为了暴露显微镜连接到表面的近表面微收缩，将部件浸入酸溶液中足够长的时间以均匀地去除原始铸件的至少约0.005英寸作为铸造表面。 通过标准非破坏性技术（如液体渗透性评估）评估暴露的微收缩率是否可接受性或去除。
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公开(公告)号：US5143383A
公开(公告)日：1992-09-01
申请号：US483594
申请日：1990-02-21
IPC分类号： F01D11/02 , F16J15/447
CPC分类号： F01D11/02 , F16J15/4472
摘要： A rotating labyrinth seal especially useful for effecting sealing between two plenums in aircraft gas turbine engines comprising a base and a plurality of radially-directed seal teeth rings extending circumferentially around the outer peripheral surface of the base. Each of the seal teeth rings has a body portion and a tip portion, with the body portion being substantially thicker than the tip portion. Seal teeth rings of the invention exhibit improved resistance to fatigue crack propagation compared to conventional seal teeth rings.
摘要翻译： 旋转式迷宫式密封件特别适用于在飞机燃气涡轮发动机中的两个增压室之间进行密封，其包括基部和围绕基座的外周表面周向延伸的多个径向定向的密封齿环。 每个密封齿环具有主体部分和尖端部分，其主体部分基本上比顶部部分更厚。 与传统的密封齿环相比，本发明的密封齿环表现出改善的耐疲劳裂纹扩展性。
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19.发明授权公开(公告)号：US06206638B1
公开(公告)日：2001-03-27
申请号：US09249204
申请日：1999-02-12
IPC分类号： F01D518
CPC分类号： F01D5/186 , F01D5/187 , F05D2230/21 , F05D2260/201 , F05D2260/202 , Y02T50/67 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine airfoil includes an airfoil outer wall having widthwise spaced apart pressure and suction sidewall sections extending chordally between leading and trailing edges of the airfoil and extending longitudinally from a base to a tip. Inside the airfoil is at least one internal cooling circuit having a plurality of longitudinally extending circuit channels between longitudinally extending internal ribs extending widthwise between the pressure and suction sidewall sections and a longitudinally extending first sidewall film cooling chamber positioned between one of the sidewall sections and a first inner wall bounding the cooling circuit. Sidewall film cooling holes extend through the pressure sidewall section from the first sidewall film cooling chamber. The internal ribs have corresponding rib angles with respect to a centerline, the first inner wall has a corresponding first wall angle with respect to the centerline, and each of the rib angles and the first wall angle are constant in a longitudinal direction from the base to the tip. In the preferred embodiment, all the inner walls are substantially parallel to each other and all the transverse ribs are substantially parallel to each other or are substantially parallel to the first and second inner walls.
摘要翻译： 燃气涡轮发动机翼型件包括具有宽度方向间隔开的压力的翼型件外壁和在翼型件的前缘和后缘之间弦状延伸并且从基部纵向延伸到尖端的抽吸侧壁部分。 在翼型件内部是至少一个内部冷却回路，该内部冷却回路在纵向延伸的内部肋条之间具有多个纵向延伸的电路通道，纵向延伸的内部肋条在压力和吸入侧壁部分之间横向延伸，以及纵向延伸的第一侧壁膜冷却室，其位于一个侧壁部分和 第一内壁围绕冷却回路。 侧壁膜冷却孔从第一侧壁膜冷却室延伸穿过加压侧壁部分。 内肋相对于中心线具有对应的肋角，第一内壁相对于中心线具有相应的第一壁角，并且每个肋角和第一壁角在从基部到纵向方向上是恒定的 小费。 在优选实施例中，所有内壁基本上彼此平行，并且所有横向肋基本上彼此平行或基本上平行于第一和第二内壁。
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公开(公告)号：US5971706A
公开(公告)日：1999-10-26
申请号：US984627
申请日：1997-12-03
IPC分类号： F01D5/06 , F01D11/00 , F01D25/16 , F16C15/00 , F16C33/62 , F16C35/067 , F01D25/00 , F03B11/00 , F03B11/06
CPC分类号： F16C35/067 , F01D25/16 , F16C15/00 , Y02T50/672 , Y10S384/911 , Y10S384/912
摘要： An inter-rotor bearing assembly includes a first annular member having a circumferential inner surface and a second annular member having a circumferential outer surface. The outer surface is concentric to and disposed radially inward of the inner surface and a bearing is disposed between the surfaces. The bearing has an outer race fixedly attached to the first annular member along the inner surface, an inner race fixedly attached to the second annular member along the outer surface, and rolling elements disposed between the races. A low density high circumferential strength support ring is fixedly attached to the first annular member disposed concentrically outside of the inner race and is preferably made of a titanium matrix composite. The rolling elements may be cylindrical rollers having cylindrical rolling surfaces. The support ring may be fixedly attached around or integral with the first annular member.
摘要翻译： 转子间轴承组件包括具有周向内表面的第一环形构件和具有周向外表面的第二环形构件。 外表面与内表面同心于并且设置在径向内侧，并且轴承设置在表面之间。 轴承具有沿着内表面固定地连接到第一环形构件的外圈，沿着外表面固定地附接到第二环形构件的内座圈和设置在座圈之间的滚动元件。 低密度高周向强度支撑环固定地附接到同心地设置在内圈外部的第一环形构件，并且优选地由钛基复合材料制成。 滚动元件可以是具有圆柱形滚动表面的圆柱滚子。 支撑环可以固定地附接在第一环形构件周围或与第一环形构件成一体。
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