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The place of fastening of the rotor blades of the booster rotors and the compressor of the fifth generation aircraft engines. The booster rotor and the high-pressure compressor rotor of a fifth-generation aircraft engine, with rotor blades secured with dovetail locks in the ring grooves of these devices. The method of assembly of the mounting point of the rotor blades of the booster and compressor rotors
The place of fastening of the rotor blades of the booster rotors and the compressor of the fifth generation aircraft engines. The booster rotor and the high-pressure compressor rotor of a fifth-generation aircraft engine, with rotor blades secured with dovetail locks in the ring grooves of these devices. The method of assembly of the mounting point of the rotor blades of the booster and compressor rotors
FIELD: machine building.SUBSTANCE: group of inventions refers to the area of vibration damping of the booster working blades and the compressor of fifth generation aviation gas turbine engines. Place of attachment of the rotor blades of the booster rotors and the compressor of the fifth-generation aircraft engines, made in the form of an annular protrusion on the outer and inner surfaces of the booster rotor or the compressor rotor, in which an annular profiled groove is made from the side of the outer surface of the barrel, in which the swallowtail type locks are fixed with working blades with platforms, in the annular groove, in two diametrically opposite locations, two notches are made with such a width and length in the tangential direction so that the blade lock can be accommodated in it, with a depth equal to the depth of the annular groove, and locks in the notches and cuts in the platforms are fixed, limiting the displacement of the blades in the tangential direction, the annular profiled groove is formed with a conical bottom and the axis of the conical bottom surface coincides with the longitudinal axis of the rotor of the booster or compressor, and the angle at the apex of this cone is chosen from the condition for creating the required value of the interference between the blade locks and the elastic-hysteresis element on which they rest, and the radial cross-section of the annular profiled groove is in the form of a "swallowtail" connected in the base with a horizontally arranged trapezoid with vertical sidewalls, the height of the trapezoid, along which it is connected to the figure "swallowtail", the smaller the base of this figure by an amount equal to in mm, where δ – the value of the interference in mm between the blade locks and the elastic-hysteresis element, ϕ – the angle at the vertex of the cone of the bottom of the annular profiled groove, in such a way that in one of the lateral walls of the projection of the attachment point of the working blades an annular technological groove is formed with the greatest height measured in a radial cross section equal to in mm h=δ+H+0÷0.2, where H – the maximum height of the transverse radial section of the annular intermediate spacer, and the annular intermediate spacer is made of two diametrically opposite semi-rings with an outer cylindrical surface, with a transverse radial section in the form of a trapezium – a truncated wedge, with the greatest height H, width equal to or less than the width of the larger base of the "swallowtail" of the annular profiled groove and the angle of inclination of the wedge is half the angle of the cone of the wedge equal to. Ring spacer is installed on the bottom of the annular profiled groove. Intermediate spacer is fitted with a rigid, corrugated ribbon-limiter made of two half rings, made of roasted or cold-worked, polished band of heat-resistant or heat-resistant stainless steel, the tape parameters, its thickness, are selected so that the rigidity of each ribbon corrugation in the circumferential direction is such that, so that under the effect of the maximum possible load acting on the blade in the circumferential direction, the deformation of the corrugation in this direction does not exceed 0.1÷0.15 mm, and the bow of the corrugation was equal to or greater than ƒ=0.8÷1.0 mm. Between the belt-stopper and locks of working blades with radial interference δ an annular elastic-hysteresis element made of one corrugated or two or more corrugated ribbons, assembled "corrugation to corrugation", made of either roasted or cold-worked, polished tape of heat-resistant or heat-resistant stainless steel, so that the tops of its corrugations are supported by the valleys of the stop band, the parameters of the bands of the elastic-hysteresis element are chosen as follows: width measured in the direction of the longitudinal axis of the rotor is equal to or smaller than the width of the larger "swallowtail" base of the annular profiled groove, step of the corrugation is equal to the step of the corrugation of the tape-limiter and such that one, two or more vertices of the corrugations are supported on the blade lock and the boom of the corrugation is folded up to the assembly is ƒ=ƒ+δ+0.1÷0.25 mm, and the geometry of the corrugations is chosen such that in the assembled place the maximum value of the gap between the slopes of the corrugations of the elastic-hysteresis element and the restraining tape does not exceed 0.2 mm, and the preferred value of the interference δ on the tops of the corrugations on which the blade lock rests was such as to provide a reliable elastic fixation of the blade in the circumferential direction, and is preferably equal to δ=0.8÷1 mm and more. Ends of the locks of the blades are chamfered in such a way that the scapula is tilted by the sloping parts of the lock on the slopes of the corrugations and the interference along the tops of these two corrugations δ=0. Between the outer surface of t
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机译：领域：发明组是指第五代航空燃气涡轮发动机的增压器工作叶片和压缩机的减振领域。第五代飞机发动机的升压转子的转子叶片和压缩机的连接位置，以环形突起形式形成在升压转子或压缩机转子的内外表面上，其中环形轮廓凹槽是从枪管外表面的侧面制成的，其中燕尾型锁通过带有工作平台的工作刀片固定，在环形凹槽中的两个直径相对的位置上，制成了两个这样的宽度和长度的槽口切线方向，以便可以将刀片锁容纳在其中，深度等于环形凹槽的深度，并且固定在平台的凹口和切口中，从而限制了刀片在切线方向上的位移，环形轮廓槽形成有圆锥形底部，圆锥形底部表面的轴线与增压器或压缩机的转子的纵向轴线重合，并且在该锥的顶点是从以下条件中选择的，即用于在叶片锁和它们所倚靠的弹性滞后元件之间产生所需的干涉值的条件，并且环形异型槽的径向横截面为“燕尾”在底部与水平排列的梯形和垂直侧壁相连，梯形的高度沿其连接到“燕尾”图形，该图形的底部较小，其单位为mm，等于δ，其中δ –叶片锁和弹性滞后元件之间的干涉值，单位为mm，ϕ –环形异形槽底部锥角处的角度，以这样的方式在一个或多个侧壁中工作刀片的连接点的投影形成一个环形工艺槽，该工艺槽的最大径向高度等于mm h =δ+ H + 0÷0.2，其中H –横向径向最大高度秒环形中间垫片，由两个径向相对的半环制成，它们具有一个圆柱形的外表面，梯形的径向横截面是截顶楔形，最大高度为H，宽度为等于或小于环形异型槽的“燕尾形”的较大底部的宽度，并且楔形的倾斜角等于楔形的锥角的一半。环形垫片安装在环形异形槽的底部。中间垫片装有由两个半环制成的刚性波纹状带状限制器，该限制器由烤制或冷加工的耐高温或耐高温不锈钢抛光带制成，带子参数，其厚度选择为每个带状波纹在圆周方向上的刚度使得在圆周方向上作用在叶片上的最大可能载荷的作用下，波纹在该方向上的变形不超过0.1÷0.15 mm，并且波纹的弓度等于或大于ƒ= 0.8÷1.0 mm。在皮带夹和工作刀片的锁之间，带有径向干扰δ，由一个或两个或多个波纹带制成的环形弹性滞后元件，组装成“波纹至波纹”，由烘烤或冷加工的抛光带制成。耐热或耐热不锈钢，以便其波纹的顶部由止动带的谷部支撑，弹性磁滞元件的带的参数选择如下：沿宽度方向测量的宽度转子的纵轴等于或小于环形异型槽的较大“燕尾”形底部的宽度，波纹的阶数等于带限制器的波纹的阶数，使得一个，两个或两个瓦楞的更多顶点支撑在刀片锁上，瓦楞的吊臂折叠到组件=ƒ=ƒ+δ+ 0.1÷0.25 mm，并且选择瓦楞的几何形状，以便在已组装的pla中因为弹性滞后元件的波纹的斜率与约束带之间的间隙的最大值不超过0.2mm，并且在其上具有刀片锁的波纹的顶部的干涉δ的优选值为：为了使叶片在周向上可靠地弹性固定，优选等于δ＝ 0.8÷1mm以上。叶片的锁的端部被倒角，使得肩cap骨被锁的倾斜部分在波纹的斜面上倾斜，并且沿着这两个波纹的顶部的干涉δ＝ 0。 t外表面之间
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