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公开(公告)号：US4732536A
公开(公告)日：1988-03-22
申请号：US875684
申请日：1986-06-18
CPC分类号： F01D17/162
摘要： A turbo-machine compressor which includes variable incidence stator vanes the angular adjustment of which is controlled by a control ring coupled to individual vanes by individual links. Each link has at least one contact surface on each of its longitudinal edges, such surfaces being either plane or convex. In the event of failure of any link, the change in orientation is controlled within narrow limits by contact with the contact surfaces of adjacent links which have not failed.
摘要翻译： 涡轮机压缩机，其包括可变入口定子叶片，其角度调节由通过单独链节联接到各个叶片的控制环控制。 每个链节在其每个纵向边缘上具有至少一个接触表面，这些表面是平面或凸面的。 在任何链路故障的情况下，通过与没有失败的相邻链路的接触表面的接触将方向的改变控制在狭窄的范围内。
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2.发明授权Method of manufacturing a root pivot assembly of a variable incidence turbo-machine blade 失效制造可变入口涡轮机叶片的根部枢轴组件的方法
公开(公告)号：US4706354A
公开(公告)日：1987-11-17
申请号：US868040
申请日：1986-05-29
CPC分类号： F01D17/162 , Y10S29/026 , Y10T29/49323 , Y10T29/49826 , Y10T29/49861 , Y10T29/49945
摘要： A method of manufacturing a variable incidence stator blade assembly comprising forming a blade with a root which forms an extension of the aerodynamic profile of the blade, forming a bush with a recess accommodating the root by ultrasonic, electro-chemical or electro-erosion machining and assembling the blade and bush in a turbo-machine outer casing and in an inner ring of channel section.A variable incidence stator blade assembled in a compressor of a gas turbine is also described, the blade assembly being as manufactured by the method. The channel section inner ring carried an abradable layer which co-operates to form a seal with annular lips carried by the compressor rotor drum.
摘要翻译： 一种制造可变定位定子叶片组件的方法，包括形成具有根部的叶片，叶片形成叶片的空气动力学轮廓的延伸部，通过超声波，电化学或电蚀加工形成具有容纳根部的凹部的衬套，以及 将叶片和衬套组装在涡轮机外壳和通道部分的内环中。 还描述了组装在燃气轮机的压缩机中的可变定位定子叶片，叶片组件由该方法制造。 通道部分内圈承载着可磨损层，该层与压缩机转子鼓承载的环形唇形成一个密封。
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3.发明授权Turbine plant compressor disc with centripetal accelerator for the induction of turbine cooling air 失效涡轮机厂用压缩机圆盘，用于感应涡轮冷却空气的向心加速器
公开(公告)号：US4787820A
公开(公告)日：1988-11-29
申请号：US140992
申请日：1988-01-05
CPC分类号： F02C7/18 , F01D5/08 , F01D5/087 , F04D29/321
摘要： A turbine plant compressor disc is formed from two halves which are welded together near the rim and define an internal cavity in which a centripetal accelerator is mounted for inducing cooling air to flow from the compressor through inclined passages in the rim on the downstream side of the blades carried by the rim, through the cavity of the disc, and towards the turbine to be cooled in the vicinity of the turbine shaft. The centripetal accelerator is composed of sectors which are removably mounted in the cavity of the disc, the sectors forming a perforated ring disposed in the central bore of the disc and each sector having a flat web extending radially outwards in the inner cavity of the disc to form radial centripetal channels communicating with the air passages in the rim.
摘要翻译： 涡轮机压缩机盘由两个半部形成，两个半部在边缘附近焊接在一起，并且限定内部空腔，其中安装有向心加速器，其中冷却空气通过来自压缩机的倾斜通道在边缘的下游侧 由轮辋承载的叶片通过盘的空腔并且朝向涡轮机在涡轮机轴附近被冷却。 向心加速器由可移除地安装在盘的空腔中的扇区组成，扇形部形成设置在盘的中心孔中的穿孔环，并且每个扇形体具有在盘的内腔中径向向外延伸的扁平腹板， 形成与边缘中的空气通道连通的径向向心通道。
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公开(公告)号：US4723889A
公开(公告)日：1988-02-09
申请号：US882401
申请日：1986-07-07
CPC分类号： F01D11/006 , F01D21/04 , F01D21/045 , F01D5/22
摘要： A turbomachine rotor disc assembly includes a rotor disc having a plurality of blade-root grooves in its periphery, each two adjacent grooves defining a lobe lug between them. Rotor blades each include an aerofoil portion, a root portion, a platform defining the radially inner boundary of the aerofoil portion, and a stilt portion interconnecting the radially inner face of the platform and the root portion, a free space being defined between each adjacent pair of blades. The angular clearance of each blade in its groove is limited by wedges operative between adjacent blades on the stilts thereof and connecting members carrying the wedges secured to the rotor disc and capable of transmitting shock loads and distributing resultant forces over an adjacent sector of the rotor. The wedges are so dimensioned in relation to the dimensions of the stilts of adjacent blades that the angular clearance is limited to the permissible angular clearance of each blade during auto-rotation of the rotor.
摘要翻译： 涡轮机转子盘组件包括其圆周上具有多个叶片根槽的转子盘，每个两个相邻的槽在它们之间限定一个凸耳。 转子叶片各自包括机翼部分，根部部分，限定机翼部分的径向内边界的平台以及将平台的径向内表面和根部部分互连的突出部分，每个相邻对之间限定自由空间 的刀片。 每个叶片在其槽中的角度间隙受到在其高架上的相邻叶片之间操作的楔形物以及承载固定到转子盘上并且能够传递冲击载荷并且将合力分布在转子的相邻部分上的楔形物的连接构件的限制。 相对于相邻叶片的高跷的尺寸，楔的尺寸被确定为在转子的自转过程中角间隙被限制为每个叶片允许的角度间隙。
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5.发明授权
公开(公告)号：US5044886A
公开(公告)日：1991-09-03
申请号：US491209
申请日：1990-03-09
IPC分类号： F01D5/30
CPC分类号： F01D5/3038
摘要： Rotor blades having roots of the hammer-head type which are received in a circumferential groove in the rim of a rotor disc to secure the blades on the disc are provided with a raised portion on the underside of the blade platform which extends over the entire circumferential length of the platform and has a width equal to that of the mouth of the groove in the rim of the disc. The root of each blade is mounted on this raised portion, and when the root is received in the groove of the disc the raised portion is received closely in the mouth of the groove to ensure the correct alignment of the blade.
摘要翻译： 具有锤头型的根部的转子叶片被容纳在转子盘的边缘中的圆周槽中以将叶片固定在盘上，在叶片平台的下侧上设置有在整个圆周上延伸的凸起部分 平台的长度并且具有与盘的边缘中的凹槽的口的宽度相等的宽度。 每个叶片的根部安装在该凸起部分上，并且当根部被容纳在盘的凹槽中时，凸起部分被紧密地容纳在凹槽的口中，以确保叶片的正确对准。
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公开(公告)号：US5584658A
公开(公告)日：1996-12-17
申请号：US505386
申请日：1995-07-21
IPC分类号： F01D5/30
CPC分类号： F01D5/3038 , F05D2250/141 , Y02T50/671 , Y02T50/673
摘要： A turbocompressor disk having on its periphery a circular groove able to receive blade roots having a substantially hammer shape, said circular groove comprising an upstream lip and a downstream lip against which bear the blade roots. The upstream lip has a curvature of gradient inclined by an angle .alpha. with respect to the plane perpendicular to the rotation axis and the downstream lip has a curvature of gradient inclined by an angle .beta. with respect to the plane perpendicular to the rotation axis, .alpha. being strictly different from .beta..
摘要翻译： 涡轮压缩机盘在其周边上具有能够接收具有大致锤形状的叶片根部的圆形槽，所述圆形凹槽包括上游唇缘和下游唇缘，所述下游唇缘承载叶片根部。 上游唇缘具有相对于垂直于旋转轴线的平面倾斜角度α的渐变曲率，并且下游唇缘具有相对于垂直于旋转轴线的平面倾斜角度β的曲率曲率，α为 与beta严格不同。
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公开(公告)号：US5395213A
公开(公告)日：1995-03-07
申请号：US135568
申请日：1993-10-14
CPC分类号： F01D5/3007 , Y02T50/671
摘要： A turbojet engine rotor, wherein the circumference of the disk is occupiedy teeth and slots in an alternating form. The teeth have a variable rigidity in the axial direction, which leads to different shapes of their cross-section. The teeth have a twisted outer surface and oblique recesses are provided on the circumference of the rotor for receiving vane roots which alternate with the teeth for separating and retaining the vanes.
摘要翻译： 涡轮喷气发动机转子，其中盘的圆周以交替形式的齿和槽占据。 齿的轴向具有可变的刚度，这导致其横截面形状不同。 齿具有扭曲的外表面，并且在转子的圆周上设置倾斜的凹槽，用于接收与牙齿交替的叶片根以分离和保持叶片。
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