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 ƒe=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 the barrel projections and the platform of each blade, as well as between the ends of the platforms of adjacent blades and the counter faces of the platforms of blades and locks, there are gaps, the value of which is limited by the values of permissible displacements of the blade under the action of static and dynamic workloads. Both castles with their bottom, having the shape of the bottom of the annular groove, rest against its bottom. Between the locks and the ends of the semi-rings of the intermediate spacer and the stopper strip, the gaps are either zero or less than half the relative maximum temperature elongation of these parts. In the sidewall with the technological groove of the projection of the attachment point of the working blades, four or six holes are provided that extend into the groove, and in them, until the stop in the annular intermediate spacer, the plugs are pressed, all the friction parts of the proposed attachment point are covered with a wear-resistant coating. Optimum and limiting settings of the "fragment of the blade attachment point – blade – damping device" system and the dimensional parameters of the elastic-hysteresis element are determined from the virtual experiment.
EFFECT: method for assembling the attachment point for the rotor blades of the booster and compressor is proposed.
15 cl, 15 dwg
