RU2686353C2 - Place of mounting of working blades and low and high pressure compressor of aviation engines of fifth generation, rotor of low pressure compressor and rotor of high pressure compressor of fifth generation aviation engine, with working blades, fixed with help of dovetail type locks in ring grooves of these devices, method of assembling place of mounting working blades of rotors and compressor - Google Patents

Abstract

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. Fastening points for rotor blades of low and high pressure compressor rotors for fifth generation aircraft engines, made in the form of an annular protrusion on the inner and outer surfaces, made in the form of a barrel of rotors of the low and high pressure compressor, in which an annular profiled groove is made from the side of the outer surface of the barrel, in which the dovetail type locks are fixed with working blades with platforms, in the annular groove in diametrically opposite places, grooves are made with such a width and length in the tangential direction, so that the blade lock with a rectangular transverse radial section with depth can be accommodated therein, equal to the depth of the annular groove, and in the grooves and notches in the platforms locks are fixed, limiting the displacement of the blades in the tangential direction, with the outer diameter of the impeller, measured by locks, equal to the outer diameter, measured by the platforms of the blades, characterized in that the annular shaped groove is made with a conical bottom, the axis of the conical bottom surface coincides with the longitudinal axis of the rotor of the compressor of low and high pressure, and the angle at the apex of this cone is chosen from the condition of creating the required value of preload between the padlocks and the elastic hysteresis element, providing support therefor, and the radial cross section of the annular profiled groove has the shape of a dovetail, connected at the base with a trapezium with vertical side walls, the height of the trapezium, along which it is connected to the dovetail figure, is equal in mmwhere b is the larger base of the dovetail figure, c is its smaller base,- the value by which the trapezoid stands for the magnitude of the larger base of the dovetail figure, equal in mmwhere δ - the tension in mm between the padlocks and the elastic hysteresis element, ϕ - the angle at the top of the cone bottom of the annular profiled groove, so that in one of the side walls of the protrusion of the attachment of working blades formed annular process groove with the greatest height, measured in a radial cross section equal in mm h=δ+H+0÷0.2, where H is the greatest height of the transverse radial section of the annular intermediate spacer, and the annular intermediate spacer is made of two diametrically opposed semirings with a transverse radial section in the form of a trapezoid - a truncated wedge, with the greatest height H, the width equal to or smaller than the width of the smaller base of the dovetail ring shaped grooves, and the angle of the wedge - half the angle of the wedge cone, equal toat the end with a smaller thickness of each semiring, two semicircular technological grooves or three such grooves are made at its ends, in this case one of the grooves is located in the middle part of the semiring, and the annular intermediate spacer is installed on the bottom of the annular profiled groove in such a way that its end with the notches is in contact with the side of the protrusion of the blade attachment point, in which there is no technological groove, between the annular intermediate spacer and the locks installed in the grooves and the locks of the rotor blades with radial tension δ there is a ring elastic hysteresis element with a width measured in the direction of the longitudinal axis of the rotor, equal to or less than the width of the smaller base of the dovetail of the annular profiled groove made up of one, two or more ring parts equidistant around the circumference, and between the ends of these parts there are gaps, the magnitude of which is either zero or equal to or less than half the permissible total value of the relative working displacements in the circumferential direction of the ends of this part of the ring and equal to 0.2÷0.5 mm, and between the outer surface of the barrel and the platform of each blade, as well as between the ends of the platforms of the adjacent blades and the counter ends of the platforms of the blades and locks, there are gaps, the value of which is limited by the values of the allowable displacement of the blade under the action of static and dynamic working loads, and under the platforms of the blades between the ends of the locks fixed in the recesses of the annular profiled groove, and the ends of the padlock locks, as well as between the ends of the padlock locks with tension along the annular elastic hysteresis element, the ends of the locks fixed in the recesses in the annular profiled groove, padlocks locks and platforms thereof are fitted with elastic hysteresis or elastic elements, and the values of these tensions are chosen in such a way that, when the blades oscillate, elastic mutual slippage occurs with dry friction of the contacting e

Description

The group of inventions relates to the field of vibration damping of the working blades of the compressor of the fifth generation aviation gas turbine engines.

Improving reliability by preventing fatigue damage of rotor blades is an important task of modern aircraft engine building. The occurrence of these damages in aircraft GTEs in operation is largely determined by the level of vibration stresses in the blades over the entire range of engine operating modes. One of the most important factors reducing the level of these stresses is the damping capacity of the blades, which is determined by the energy dissipated in the flowing gas stream (aero damping), in the material, and in aircraft engines in the old “classical” version due to structural damping in the lock joint, and in contact of retaining or anti-vibration shelves for steps with these shelves.

Aero-damping and structural damping in locks of blades and in the contact of retaining shelves, if any, in fans, compressors and turbines of “classical” generations of aircraft engines are far from optimal values.

Therefore, to prevent dangerous resonant oscillations of the blades, special damping devices are used. In the absolute majority of known cases, these are structural damping devices, in which energy is dissipated due to the work of dry friction forces between the contacting surfaces during their mutual elastic slippage during the oscillation process.

This type of damping is chosen because its use allows you to create special damping devices that provide the optimum level of damping of the blades of the turbomachines with the design parameters of the damping devices. The design parameters are understood here as parameters that are not substantially (permissible) degrading the overall, mass, technological, design characteristics of the impellers of the turbomachine and, at the same time, improve the performance characteristics of these wheels and the turbomachine as a whole. The choice in favor of this type of damping was made already in the earliest developments of these devices.

So known is the rotor of the turbomachine (see pp. 333277. The rotor of the turbomachine / NS Kondrashov, P.D. Vilner, I.D. Eskin. - Declared 11/12/1966. Publ. 23.03.1972, Bul. No. 11 .) containing a disk with blades having a damping device in the form of a package of metal plates, characterized in that in order to increase the effectiveness of the damping of the blades, they are made with split shanks, into the cut of which metal plates are inserted with a tightness created by elastic deformation (straightening ) pre-bent metal plates, and in the paddle lock under p zlichnymi angles press pins.

The originality of this proposal lies in the fact that the elastic-damping element is located inside the blade blade and a multi-layer steel plate pack compressed by a distributed load obtained due to large elastic deformations of the packet when it is installed in the leg is used as such an element. In the case when the stiffness on the bend of the leg side is of the same order as the flexural stiffness of one plate, with the number of plates n≥10 in the package, the maximum value of the packet dispersion can reach very high values Ψ _max ≈ 4 ÷ 5 (see Eskin II D. Study of the generalized elastic-friction characteristics of aircraft engine dampers and shock absorbers: dis ... Candidate of Technical Sciences / ID Eskin. - Kuibyshev: KuAI, 1973. - 150 p.), I.e. these devices, with proper selection of its parameters, are capable of providing a high dispersion coefficient for the system “blade-damping device” on the most dangerous low forms of its oscillations and, consequently, effective damping of these oscillations of the blades.

However, this proposal is unsuitable for use as a damping device for low-and high-pressure compressor blades of a fifth-generation aviation GTE fixed in the annular grooves of these devices, since these blades either have no legs or are made with low legs.

Known damping device (US patent No. 5205714, 04/27/1993), whose action is based on the scattering of the oscillation energy of the blade due to the work of dry friction forces arising from the contact of a sedentary element of the damping device located inside its leg and in the castle connections. To create contact pressure springs or other elastic elements are used.

It is also known damping device (US patent No. 6283707, 04.09.2001), using to create the contact pressure of the centrifugal force of inertia from the rotation of the impeller design elements placed inside the blade and lock the blade through the elastic elements.

This device is fundamentally similar to the device according to US Patent No. 5,205,514, since the slow-moving element of this device is pressed against the surfaces of the blade in contact with it also by centrifugal force.

Working blades of the compressor of low and high pressure of aviation GTEs do not perform hollow, and these proposals are not suitable for use for damping oscillations of these blades.

It is possible to analyze the designs of a number of well-known damping devices for turbomachine blades, but all of them, for the reasons described above, are unsuitable for damping oscillations of the low-and high-pressure aviation turbine blades of the fifth-generation GTE fixed in the annular grooves of the rims of the impellers, and cannot be used as a prototype of the present invention.

The three-stage rotor of the KND of the SaM 146 aircraft engine is known (see Kiselev Yu.V. SaM 146 engine. Main unit assembly / Yu.V. Kiselev, D.Yu. Kiselev. - Electronic training manual. SGAU, Samara, 2012, rice 13), made in the form of a barrel with three annular projections on the inner and outer surfaces of the barrel. In each annular protrusion, a profiled annular groove with a transverse radial section is made, which responds to the lock of the working blade of the “dovetail” type. Working blades with their locks are inserted into these grooves and made with platforms that the blades rest against each other, and which, together with the feathers of the blades, organize the flow channels of these blades. The rotor of the low pressure compressor is rigidly connected to the fan rotor. Four blades on each of the steps (a pair of these blades are diametrically opposed) have special cuts in the platform for two locks.

The six-speed rotor of the KVD aircraft engine SaM 146 is also known (see Kiselev, Yu.V., SaM 146 engine. Main units / Yu.V. Fig. 15), consisting of the following elements: HPC blades; blisches of the first and second stages of the ARC; KVD impeller; disc labyrinth seal.

The first and second stages of the ARC rotor are made using the "Blisk" technology.

Blis KVD is milled from a single blank detail that combines the impeller, a set of blades, labyrinth seals and shaft ARC. Blis of the first stage of the ARC rotor is connected together with the blisk of the second stage of the ARC rotor and the impeller from the third to the sixth stage of the ARC rotor using bolts. Splined grooves are made on the blisch shaft of the second stage of the ARC for connection with the rear part of the fan shaft. Bliski first and second stages of the rotor of the ARC is made of titanium alloy. The blades of the third stage of the ARC rotor are mounted on the impeller impeller using a dovetail slot. The blades of the third stage of the ARC rotor are axially tightened by an anvil ring attached to the front surface of the dovetail slot with bolts. The blades of the third stage of the KVD rotor are made of titanium alloy. The retaining ring is made of nickel alloy. The blades from the fourth to the sixth stages of the ARC rotor are mounted on the impeller wheel of the ARC rotor using a profiled annular groove. Platforms of blades from the fourth to the sixth stages of the ARC fit snugly to each other, ensuring reliable fixation of the blades in the tangential direction. Four blades at each of the steps (from 4 to 6 steps) KVD have special cuts in the platform for two locks. The blades from the fourth to the sixth stage of the ARC are made of nickel alloy. To the front flange of the KVD impeller are attached both bliska KVD. The rear flange of the KVD impeller is attached to the disk with a labyrinth seal with bolts. 70 dovetail slots for the third-stage rotor of the ARC rotor are made on the HPC impeller, as well as three profiled annular grooves for fastening the fourth, fifth and sixth-blade CVC blades. Also on the impeller wheel, there are four labyrinth seals, for sealing the articulation with the liners of the abradable seal and the honeycomb seal of the stator of the ARC. The KVD impeller is made of nickel alloy in the form of a barrel, which is made together with disks. The labyrinth seal disc has labyrinth seal teeth, which provide sealing of the articulation with the seal body support. The labyrinth seal disc is made of nickel alloy.

The advantages of these rotor structures, for example, compared to similar rotors of fourth-generation aircraft engines with “classic” impellers, bolted into drum-shaped disc structures, with working blades installed in the dovetail grooves of these wheels, significantly reduce the number of parts and weight these structures and, as a consequence, the improvement of engine performance: a decrease in specific fuel consumption, an increase in engine specific thrust.

Among the shortcomings of these structures in the case when the designer is faced with the need to design damping devices for damping oscillations of working blades, is the lack of developed designs of these damping devices suitable for damping oscillations of blaster blades and blades with dovetail locks installed in the annular grooves of the impeller.

Note that the conclusion about the absence of such devices by us was made on the basis that we did not find published materials where these devices would be described. It is possible that they simply did not have time to develop.

Therefore, the place of attachment of the working blades in the annular grooves of the stages of the rotors of the low and high pressure compressor of the aircraft engine SaM 146, as the closest in technical essence to the proposed, is taken as a prototype.

For the same reason, the rotors of the SaM 146 aircraft low-and high-pressure compressor are taken as prototypes.

The task is to develop the attachment points for the working blades in the annular grooves of the rotors of the low-and high-pressure compressor of the fifth generation aircraft engine, ensuring reliable mounting and highly effective damping of the blades on all dangerous low oscillation modes, with an allowable increase in the mass of the rotors and the number of their parts (with a slight increase in the mass of the rotors and an increase in the number of their parts, which practically does not reduce the described advantages of these structures, and does not change their overall dimensions).

Highly effective damping of the blades is achieved by using damping devices with the same type of loading, according to which this device is loaded assembled with a blade, the maximum dissipation factor ψ _max ≥2 and its rigidity must be of the same order as the blade stiffness.

The problem is solved by the fact that a mounting location for rotor blades of low and high pressure compressor rotors of fifth generation aircraft engines is proposed, made in the form of an annular protrusion on the inner and outer surfaces of barreled rotors of the low and high pressure compressor, in which an annular shaped groove is made on the side the outer surface of the barrel, in which the working blades with platforms are secured in dovetail locks, in an annular groove in diametrically opposite m Stach made notches with such a width and length in the tangential direction so that it can freely accommodate the blade lock, with a rectangular transverse radial section with a depth equal to the depth of the annular groove, and locks fixed in the notches and notches in the platforms, limiting the displacement of the blades in the tangential direction , moreover, the outer diameter of the impeller, measured by locks, is equal to the outer diameter, measured by the platforms of the blades, characterized in that the annular shaped groove is made with a conical the bottom, the axis of the conical bottom surface coincides with the longitudinal axis of the rotor of the low and high pressure compressors, and the angle at the apex of this cone is chosen from the condition of creating the required amount of tension between the padlocks and the elastic hysteresis element on which they rest, and the radial cross section of the annular shaped the grooves have the shape of a “dovetail”, connected at the base with a trapezium with vertical side walls, moreover, the height of the trapezium along which it is connected to the figure “dovetail”, equal in mm

where b is the larger base of the “dovetail” figure, c is its smaller base, and is the value by which the trapezium stands for the larger base of the figure “dovetail” equal in mm

where δ is the amount of tension in mm between the padlocks and the elastic hysteresis element, ϕ is the angle at the top of the cone of the bottom of the annular shaped groove, so that an annular groove with the greatest height measured in the radial cross section equal in mm

h = δ + H + 0 ÷ 0.2,

на торце с меньшей толщиной каждого полукольца у его концов выполнены две полукруглых технологических выемки или три таких выемки, в этом случае одна из выемок находится в средней части полукольца, и кольцевая промежуточная проставка установлена на дно кольцевой профилированной канавки таким образом, что ее торец с выемками контактирует с боковой стороной выступа места крепления лопаток, в которой нет технологической канавки, между кольцевой промежуточной проставкой и замками, установленными в выемках, и замками рабочих лопаток с радиальным натягом δ установлен кольцевой упругогистерезисный элемент с шириной, измеренной в направлении продольной оси ротора, равной или меньшей ширины меньшего основания «ласточкиного хвоста» кольцевой профилированной канавки, составленный из одной, двух и более частей кольца, равнорасположенных по окружности, и между концами этих частей имеются зазоры, величина которых либо равна нулю, либо равна или меньше половины допустимой суммарной величины относительных рабочих смещений в окружном направлении концов этой части кольца и равна 0,2÷0,5 мм, и между наружной поверхностью бочки и платформой каждой лопатки, а также между торцами платформ соседних лопаток и ответными торцами платформ лопаток и замков имеются зазоры, величина которых ограничена величинами допустимых смещений лопатки под действием статических и динамических рабочих нагрузок, и под платформами лопаток между торцами замков, закрепленных в выемках кольцевой профилированной канаки, и торцами замков лопаток, а также между торцами замков лопаток с натягом по кольцевому упругогистерезисному элементу, торцам замков, закрепленных в выемках в кольцевой профилированной канавке, замкам лопаток и их платформам установлены упругогистерезисные или упругие элементы, причем величины этих натягов подобраны таким образом, что при колебаниях лопаток происходят упругие взаимные проскальзывания с сухим трением контактирующих элементов, причем в выемках в кольцевой канавке закреплены четыре, шесть или более равнорасположенных по окружности замков, и боковые стороны замков, закрепленных в выемках в кольцевой профилированной канавке, на части своей длины, у дна кольцевой канавки, срезаны и образуют заборный клин, и в боковой стенке с технологической канавкой выступа места крепления рабочих лопаток выполнено четыре или шесть отверстий, из которых два расположены в районах расположения концов полуколец промежуточной проставки, а при выполнении шести отверстий еще по одному в районе средней части каждого полукольца, и в эти отверстия до упора в кольцевую промежуточную проставку запрессованы заглушки, а само место крепления рабочих лопаток собрано по способу п. 11 формулы изобретения, и все трущиеся поверхности деталей предлагаемого места крепления покрыты износостойким покрытием.where H is the greatest height of the transverse radial section of the annular intermediate spacer, and the annular intermediate spacer is made of two diametrically opposed half-rings with a transverse radial section in the form of a trapezium, a truncated wedge, with the greatest height H, width equal or smaller than the width of the smaller base “dovetail tail” "Annular profiled groove, and the angle of the wedge is half the wedge cone angle equal to

at the end with a smaller thickness of each half-ring, two half-round technological grooves or three such grooves are made at its ends, in this case one of the grooves is located in the middle part of the semi-ring, and the annular intermediate spacer is installed on the bottom of the annular grooved in such a way that its end with grooves in contact with the side of the protrusion of the place of attachment of the blades, in which there is no technological grooves, between the annular intermediate spacer and the locks installed in the grooves, and locks working blades with for An annular elastic-hysteresis element with a width measured in the direction of the longitudinal axis of the rotor equal to or smaller than the width of the smaller base of the “dovetail” circular shaped groove made of one, two or more ring parts, equally spaced around the circumference, and between the ends of these parts there are gaps, the magnitude of which is either zero or equal to or less than half the permissible total value of the relative working displacements in the circumferential direction of the ends of this part of the ring and is 0, 2 ÷ 0.5 mm, and between the outer surface of the barrel and the platform of each blade, as well as between the ends of the platforms of the adjacent blades and the response ends of the blades and lock platforms, there are gaps, the magnitude of which is limited by the values of the allowable displacements of the blades under the action of static and dynamic working loads, and under the platforms of the blades between the ends of the locks fixed in the grooves of the annular profiled Kanaka, and the ends of the locks of the blades, and between the ends of the locks of the blades with tension on the annular elastic hysteresis element, the ends Ams fixed in grooves in an annular shaped groove, padlocks locks and their platforms are fitted with elastic hysteresis or elastic elements, and the values of these tensions are chosen in such a way that when oscillations of the blades elastic mutual slippage occurs with dry friction of the contacting elements, and in the grooves in the ring groove fixed four, six or more locks equally spaced around the circumference, and the sides of the locks secured in recesses in the annular shaped groove on part of their lengths , at the bottom of the annular groove, cut off and form an intake wedge, and in the side wall with the technological groove of the protrusion of the place of attachment of the working blades four or six holes are made, of which two are located in the regions of the ends of the semi-rings of the intermediate spacer, in the middle part of each half-ring, and into these holes all the way into the annular intermediate spacer, the plugs are pressed in, and the point of attachment of the working blades is assembled according to method 11 of the claims, and all ruschiesya surface of the proposed site of attachment of parts coated with a wear resistant coating.

Relative working displacements in the circumferential direction based on the annular groove bottom, here refers to the amount of displacement of the elastic hysteresis element in any radial section relative to the annular intermediate spacer under the action of working static gas and centrifugal loads, dynamic loads materials of these parts.

As you know (see Skubachevsky, GS Aviation gas turbine engines. Design and calculation of details. From the 2nd, supplement .. A textbook for aviation universities / GS Skubachevsky. - M .: Mashinostroenie. 1965. - 451 p., Fig. 7.31), the damping in the dovetail lock joint of third-stage blades at low rotor speeds (2000 ÷ 5000 rpm) is small, and at high speeds (7000 or more) is almost zero due to jamming the action of large centrifugal forces of the blade lock in the slot of the disk and the regulation of the damping characteristics of this compound in possible only in a narrow range and not productive.

In the proposed design, although the attachment of blades of the “dovetail” type is applied, but the locking of the locks of the blades under the action of centrifugal forces in the annular profiled groove in all engine operating modes is excluded. This is explained by the fact that in this design the action of constant gas forces in all modes is balanced by the action of dry friction forces acting on the blade lock and the reactive forces of elastic or elastic hysteresis elements, or the total effect of these forces exceeds the action of constant gas forces, but always surmountable by dynamic forces acting on the blade.

Consequently, in all modes of operation of the engine in the proposed design, when the blade is oscillating, cyclic loading will occur both of the annular elastic hysteresis element and the elastic or elastic hysteresis elements located under the blades platforms, the blade is elastically suspended. This statement is also true because when the blade is swung in the circumferential direction under the action of the moments of forces acting on it when the component of the gas load on the blade acting in the direction of the rotor axis does not overcome the friction forces acting on the bottom of the blade lock, even an insignificant small turn, at which a large part of the length of the padlock lock is reset to zero the tension on the sides of the paddle lock and, consequently, on this part of the paddle sides of the paddle lock, the friction forces become zero, and at negligibly small rotation and radial displacement of the rotor center of frictional forces on the sides of the blade lock become zero. Here, a negligibly small rotation and a radial displacement of the blade means a rotation in which the smaller radial displacement of the blade to the center of the rotor, defined on a large part of the blade lock, is equal to the greatest deformation of the blade lock in the radial direction under the action of centrifugal force and reactive force of the elastic-hardened element acting on the lock blades at the time of overcoming the friction forces on the sides of the lock, and a negligibly small radial displacement of the blade means the radial displacement of the blade, which is equal to th greatest strain. The qualitative character of the hysteresis loop obtained by cyclic loading of the working blade in the field of centrifugal forces of the proposed attachment point in this case is described below.

In the case when the component of the gas load on the blade, acting in the direction of the rotor axis, overcomes the friction forces acting on the bottom of the blade lock, the blade with one side of the lock is pressed against the counter side of the ring groove and slips relative to it.

Note that the described phenomenon is inherent in the proposed design of the place of attachment and is absent from the prototype, is new and has not been described anywhere else. It is this that is the physical basis of our proposal and allowed us to offer a place for fastening the working blades of a low and high pressure compressor with a highly effective damping device.

The elastic-damping characteristics (UDH) of the “attachment-working blades” system can be varied over a wide range by changing the parameters of these elements. Moreover, the width of the range of variation of the UDH below the proposed mounting points for the working blades is such that in most practical cases the initial optimal setting of this system and its final setting, providing the required service life of the system, lie in this range.

In the impellers of aviation GTE usually set n = 60, 70 and more blades. Blades located between the two locks in the circumferential direction are connected in series with the help of elastic elements. Therefore, when determining the number of locks fixed in the grooves, the number of consecutive blades need to ensure that a number of conditions are met. So to ensure reliable and effective damping of the oscillations of the blades in the circumferential direction, the tension δ _okr in the assembled attachment point between the end of the lock of each blade and the elastic element should preferably be equal to or greater than 0.1 ÷ 0.2 mm. When the blades oscillate in all engine operating modes, there should not be a gap between the elastic elements and the locks fixed in the grooves, the elastic elements and the locks of the blades, and the stiffness of the elastic elements should be chosen so that the dangerous operating mode of the engine, with a dangerous form of oscillation, is provided optimal adjustment of the attachment point, determined by the minimum or close to it value of the dimensionless maximum stress in the dangerous section of the blade, and at the same time the strength of the control is ensured GIH elements. Moreover, it should be noted that in the circumferential direction the elastic elements located between each two locks secured in the grooves are unevenly loaded, since the loads acting on the blades in the circumferential direction (perceived by the elastic elements) are summed in the opposite direction of the rotor rotation. The proposed device creates tension members δ _env locks in their installation and fastening recesses shaped annular groove. To facilitate the installation of these locks on them made intake wedge. To avoid unacceptable collapse in the radial directions of elastic elements in contact with locks installed in the grooves, the angle of the intake wedge of these locks should not exceed 60 °. Therefore, with the commonly used heights of the dovetail locks of the blades of the leg K, the angle of inclination of the side of the intake wedge, measured in the circumferential direction, should not exceed 3–3.5 mm. The required number of N locks, installed in the grooves, providing the required amount of tension between the elastic elements and these locks and padlocks, is determined from a simple relationship:

and is rounded to the nearest even whole number. An even number of locks was chosen because they can be diametrically opposed and exclude the possibility of introducing a noticeable imbalance into the rotor design. It is easy to verify that the number of locks N in the application of the proposed device in modern aviation GTE will be 4 or 6. In the case when the rigidity of the elastic elements are not the same number of locks fixed in the grooves is calculated from (1) by substituting in (1) instead of tightness δ _okr its average value.

It is also proposed to attach the rotor blades of the rotors of the low-pressure and high-pressure engines of the fifth generation, characterized in that the elastic elements are made in the form of round, or oval, or round and oval split steel, hardened and ground rings arranged so that the cut point is made forming ring, located at the gap between the ends of the platforms of adjacent blades in the radial plane of the rotor and at the end on the inner surface of the platform of one of the blades in contact with this prugim element, a projection with a clearance in a part-sectional view of the elastic member.

The protrusion of the blade platform eliminates the rotation of the elastic element in the circumferential direction within the gap between the elastic element and the protrusion.

A mounting point for rotor blades for compressor rotors of low and high pressure engines of the fifth generation is also proposed, characterized in that the resistive element is made of two, four, six or more parts, each of which is made of one, two or more polished, bonded or hardened, corrugated tapes made of heat-resistant or heat-resistant stainless steel, and in each part with two or more tapes in it they are assembled “corrugations into corrugations”, and two diametrically located locks installed in the grooves of the annular profiled groove are made with protrusions with which they rest on the bottom of the annular profiled groove, and between the protrusions and the response ends of the parts of the annular elastic-hardened element there are gaps which either equal to zero or equal to or less than half of the allowable total value of the relative working displacements the circumferential direction of the ends of this part of the annular elastic-hysteresis element and preferably equal to 0.2 ÷ 0.5 mm, and between these protrusions and the response ends of each of the semi-arcs The intermediate spacer space has gaps, the total value of which is equal to or greater than the maximum relative temperature elongation of the intermediate spacer half-ring, and each hole made in the wall of the annular profiled groove without a process groove, located at the middle of each part of the elastic-hysteresis element, in the radial section, where the top of the corrugation is parts rests on the bottom of the annular profiled groove, made with a diameter equal to the sum of the thickness of the intermediate spacer and tape or le t elastic hysteresis element, and these holes are pressed into the plugs, which with their spherical ends without a gap or with a gap equal to the value of mutual slippage of this vertex relative to the bottom of the annular profiled groove, enter into the reciprocal grooves made in the semi-rings of the intermediate spacer and in the lateral side of each part of the elastic spacer. an item.

The barrel of the low pressure compressor is made of titanium alloy, and the intermediate spacer is made of hardened stainless steel, and the coefficient of thermal linear elongation of titanium is less than that of stainless steel. The relative temperature lengthening of half of the intermediate spacer in the circumferential direction is understood here to mean the difference in temperature lengthening of the half of the intermediate spacer and the half of the annular shaped groove.

The elastic hysteresis element, made in the form of a multilayer multi-span corrugated package, working for cyclical compression in the mode of one-sided elastic hysteresis stop, has high damping properties (the maximum value of the dispersion coefficient of such a package is Ψ _max = 3.5 ÷ 3.7, see. Eskin I.D. Investigation of the generalized elastic-friction characteristics of aircraft engine dampers and shock absorbers: dis ... candidate of technical sciences / I. Eskin. - Kuibyshev: KuAI, 1973. - 150 p.).

In the work (see Eskin ID. Cyclic compression of a multilayer multi-span corrugated package / I.D. Eskin, R.I. Alkeev, V.I. Ivaschenko // SGAU Bulletin. - №1 (39), 2013. - С 178-191) it is shown that the load processes under cyclic compression of a multi-layer, multi-span, corrugated package are identical (when solving a problem using the Galerkin method) to the corresponding one-layer multi-span corrugation processes with the same number of corrugations, but with rigidity

C ₀ = 2nπ ⁴ EI / t ³ ,

where n is the number of corrugated tapes in a multilayer package, EI is the flexural rigidity of one corrugation layer, t is the corrugation step.

Physically, this result is primarily due to the fact that the energy dissipated by the package during its cyclic compression is dissipated mainly due to the work of the dry friction forces on the slippage of the corrugations of the external strips of the package along rigid plates, and the energy dissipated inside the package is small compared to this energy, as well as using an approximate analytical method for solving a problem (the Galerkin method).

This result allows for the classification of structural damping systems developed in the work (see Eskin ID. Investigation of the generalized elastic-friction characteristics of dampers and shock absorbers of aircraft engines: dis ... candidate of technical sciences / ID Eskin. - Kuibyshev: KuAI, 1973 - 150 pp.), Add another class of these systems, namely the class of structural damping systems, in which the energy dissipated inside the elastic-hysteresis element is small compared to the energy dissipated at its borders. Structural damping systems belonging to this class will have the property described above.

The use of this property in the case of elastic hysteresis elements (damper) of the proposed attachment point allows determining the number of ribbons in the package from the condition for obtaining the lowest possible mass of the package while ensuring its strength and required UDH and allowed us to determine the claimed number of ribbons of these elastic hysteresis elements.

A multi-layer corrugated package, like all systems of structural damping, is a system with heredity, i.e. its elastic and strength properties depend on the sequence of its loading. Consequently, these properties of the package will significantly depend on the method of assembling the place of attachment.

With the proposed method of assembling the place of attachment of the blades (see below), due to the effect of "accumulation of dry friction forces" (see below the description of the method of assembling the proposed attachment point) applied to the tops of the corrugations of the package after assembling the attachment point (after compression to one and the same amount of deformation) stiffness of the spans of the package will be different - the stiffness of the spans will increase from the extreme spans to the central span of the package. Moreover, the greatest degree of increase of this rigidity will be in the case of simultaneous compression of all corrugations of the package.

Therefore, if, when the elastic hysteresis element is made in the form of a corrugated ribbon or a package of several such ribbons rolled into a ring, even if the blade is supported by one corrugation with the required setting (parameters) of the elastic hysteresis element, the number of its corrugations is too large, i.e. due to the effect of "accumulation of dry friction forces", the central tops of the corrugations during assembly or workload do not slip relative to the bottom of the annular grooves and padlocks and in these corrugations there are unacceptably large stresses, it is expedient to use an elastic hysteresis element made of an even number in these corrugations parts - two, four or six. Caps with spherical ends are fixed from displacement in the circumferential direction, as a solid, half-rings of the intermediate spacer and part of the elastic hysteresis element, but do not prevent the elastic slippage of the corrugation tops when loading parts of the elastic hysteresis element.

In order to increase the damping properties and to ensure an acceptable degree of isotropy of UDH in the circumferential direction of the damping devices, a mounting point for rotor blades of the low and high pressure compressor engines of the fifth generation is proposed, characterized in that the elastic-hysteresis element of the mounting point is made of one part and assembled corrugated tapes, in which the junction of the ends of one tape is diametrically opposite to the junction of the ends of the other tape, and the junction of the ends of the tape each blowing pair in contact with the tape of the previous pair is also offset from the junction of the ends of this tape by angle π and the tape joints are located at the tops of the corrugations resting on the half-rings of the intermediate spacer, and fillets are made at the end of each lock facing the bottom of the annular profiled groove with which the lock δ relies on the tops of the corrugations of the elastic hysteresis element, and the ends of the half rings of the intermediate spacer with the same tension are placed under two diametrically located of these locks and the gap between the ends of these halves Finger equal to or less than the maximum relative temperature elongation of the intermediate spacer

The elastic hysteresis element of the damping device of this place of attachment of the blades with the same number of belts in the package n, the same number of corrugations m, with the same geometrical dimensions of the belts and corrugations and with the same value of the elastic deformation of the corrugations when installing the package in the annular groove of the impeller will be the most rigid and in the assembled package, the greatest friction forces acting on the tops of the corrugations will be created, since the energy dissipated in the package during its assembly, with the same deformation, will be greater than by increasing mutual slippings on the contact surfaces of each pair of ribbons, and by increasing the friction forces themselves.

Note that with a certain number of ribbons in the packet, for example, with n≥10, this elastic-hysteresis element can no longer be attributed to the class of structural damping systems, in which the energy dissipated inside the elastic-hysteresis element is small compared to the energy dissipated at its borders. Note also that the friction characteristic of this package, characterized by the maximum dispersion coefficient, will be higher than that of the above described packages, precisely due to a significant increase in the energy dissipated inside the package when the blades oscillate.

In addition, in this package can be applied thinner tape, for example, with a thickness of h = 0.3 ÷ 0.4 mm.

In each pair of contacting corrugated ribbons, the corrugations of each strip change with a period T = 2π, but the pattern of distribution of the stiffnesses of the corrugations of one tape is shifted by π relative to this picture of the other tape pair. As a result, the stiffness of the corrugations of the package changes in the circumferential direction with a period T = π, but the difference between the maximum and minimum values of the corrugations of the corrugations will be significantly less than that of the corrugated package with the same parameters, whose ends of the belts are located at the same vertex of the corrugation.

In order to improve the reliability of the elastic fixation of the blades in the circumferential direction and reduce the number of N locks used, fixed in the grooves, there is suggested a mounting point for the blades of the low and high pressure compressor rotors of fifth-generation aircraft engines, characterized by the fact that at the ends of the padlock locks chamfers at such an angle that the blade with these chamfers additionally abuts against the slopes of the corrugations, and the elastic elements located in the depressions of these corrugations rest under pressure either in the bottom of the depression or in the other th slope of these corrugations.

Parts of the corrugated package with the help of plugs are fixed against twisting. Therefore, the corrugations, on the slopes of which the locks of the blades rest with chamfers, serve as additional supports, which elastically fix the blades from their displacement, as a solid, in the circumferential direction. Due to this, the reliability of this fixation increases, and in some cases it becomes possible to reduce the number of N locks fixed in the recesses.

In order to ensure constant running stiffness of the elastic hysteresis element after the assembly, the attachment points for the blades are proposed:

attachment of rotor blades for low and high pressure compressor rotors of fifth generation aircraft engines, characterized in that the elastic hysteresis element is designed as a single-sided cable section without a central wire - from six or eighteen wires wound to the coil closely adjacent to the intermediate spacer that the width of the winding, measured in the direction of the rotor axis, is equal to the width of the blade lock base, with one end of the cable secured under one lock without a protrusion installed in the recess y in the annular profiled groove, and the second in another such lock, or both ends of the cable are fixed with water from such locks so that in any radial section of the place of attachment of the blades there is the same number of turns.

At this place of attachment of the working blades, the elastic hysteresis element (cable) works for cyclic compression in radial directions. UDH cable with this type of loading little studied, although it can be argued that in the absence of a central wire in the cable and proper selection of its parameters using an intermediate spacer you can create in the cable the required amount of elastic tension δ and provide the required linear stiffness of the cable for radial compression.

The choice of cables is based on the following considerations: cables with standard parameters are selected, a cable of six wires from all standard cables with proper selection of wire diameter has the highest rigidity for compression in the radial direction with the smallest cable diameter; standard cable of eighteen wires due to the asymptotic nature of the dependence change Ψ _max (n), where n is the number of wires in the cable (see Eskin ID. Study of generalized elastic-friction characteristics of dampers and shock absorbers of aircraft engines: Ph.D. D. Eskin. - Kuybyshev: KuAI, 1973. - 150 s.), With its cyclic compression in the radial direction, has a value Ψ _max not significantly different from the maximum possible for standard cables with this type of loading, and with the same wire diameter will have the smallest diameter of all standard cable with approximately the same value of the maximum dissipation factor.

The elastic hysteresis element, made of a cable, has a constant linear stiffness and its UDH practically does not depend on the choice of the variant of the proposed method of assembling the attachment point.

The same property has the proposed mounting location of the rotor blades of the rotors of the compressor of low and high pressure aircraft engines of the fifth generation, characterized in that the elastic hysteresis element located under the padlocks, and the elastic hysteresis elements located under the platforms between the ends of the blade locks, are made in the form of separate elastic hysteresis elements, having the form of a corner, each of which is located so under the lock of its shoulder blade that the smaller shelf of the corner is located between the ends of the locks adjacent their blades, and the locks of the four blades located at the locks installed in the grooves of the annular profiled groove, are fitted with elastic hysteresis elements having the shape of a channel and one channel shelf is located between the ends of the locks of adjacent blades, and the other between the ends of the lock installed in the groove and the end of the blade lock, and part of the elastic hysteresis elements installed with tension on the parts in contact with them, located under the padlocks locks, have a cross-sectional radial cross-section with a w measured in the direction of the axis of the rotor, equal to the base of the dovetail of the blade lock, and their parts located between the locks have a cross section in the form of a rectangle connected to the dovetail, exactly coinciding with the dovetail of the padlock, and The elastic hysteresis elements themselves were made by cold pressing of high-density wire material MP = λ = 2.5–4 g / cm ³ or more, of stainless steel stainless steel wire with preferred wire diameter d = 0.15 ÷ 0.3 mm, with a D / d ratio = 8 ÷ 10, where D - diameter of the wire helix from which the material MP is made.

A method of manufacturing a wire material MP is widely known (see AS 183174 USSR. A method of manufacturing non-woven material MP from metal wire / AM Soifer, VN Buzitsky, VA Pershin. - Pub. 1966, Byul No. 13).

The optimal initial setting of the system “anchorage-blades-damping device with elements of MP”, in most practical cases, can be ensured exactly when the material parameters lie in the above ranges.

The proposed elastic hysteresis elements from the material MP in the proposed device work for cyclic compression in a closed volume and have sufficiently good damping properties (the maximum dispersion coefficient of products from MP working for cyclic compression in a closed volume Ψ _max ≈2.3 ÷ 2.5, see Eskin ID Study of the generalized elastic-friction characteristics of aircraft engine dampers and shock absorbers: dis ... Candidate of Technical Sciences / ID Eskin. - Kuibyshev: KuAI, 1973. - 150 p.).

These elastic hysteresis elements are operable up to a temperature of 500 ° C. At higher temperatures, the stand-up of the stainless wire disappears and the elastic-hardened element loses its elastic properties.

This temperature range may be quite sufficient when using these elastic-hardened elements in the damping devices of the first and second stages of the rotor of a low-pressure compressor, but in many cases it will be insufficient when using them in the first and second stages of the ARC rotor.

The use of a heat-resistant spring wire for the manufacture of MP material allows these elastic-hysteresis elements to be used for damping oscillations of the blades of the first and second stages of high-pressure air-jet engines of powerful aircraft engines.

It is widely known that titanium does not work well for dry friction. When dry friction in a pair of titanium-metal, for example, in a pair of titanium-steel, titanium particles are pulled out of the titanium element and stick to the steel, an intense wear of the titanium element.

Therefore, in order to improve the wear resistance of the blade attachment point in the case of manufacturing working blades and a barrel of titanium alloy, a mounting point for the blade rotors of a low-pressure and high-pressure compressor of fifth generation aircraft is proposed, characterized in that the padlocks made of thin steel steel hardened polished sheet without gaps covering blades locks on all surfaces on which they would contact with the sides of the number An end profiled groove, an elastic hysteresis element installed under the padlock locks, and an elastic hysteresis or elastic elements installed between the ends of the locks under the blade platforms in the absence of shoes.

In the proposed place of attachment of the blades, the presence of the steel intermediate spacer and the steel shoes fixed on the working paddle locks organizes all contacts in which mutual slippage of the contacting surfaces occurs, like steel-to-steel friction pairs. The application of a wear-resistant coating on these surfaces, for example, silvering or a solid lubricant ensures high wear resistance of these surfaces.

A rotor of a low-pressure compressor of an aircraft engine is proposed, made in the form of a barrel with three or more annular protrusions on the inner and outer surfaces of the barrel, in each annular protrusion of which there is a shaped circular groove with a transverse radial cross section, which responds to the paddle blade of the dovetail type, and the blades with their locks are inserted into these grooves and made with platforms that, together with the blades feathers, organize the flow channels of these blades, and the blades of the steps, starting with the second or from the third stage, the platforms rest against each other, and the rotor of the low pressure compressor is rigidly connected to the fan rotor, and the blades of each stage, located near the locks fixing the displacements in the circumferential direction of the blades of these stages, have special notches in the platform in which these locks are located , characterized in that the place of attachment of the working blades of the first or first and second stages of the rotor of the low pressure compressor, is made according to any one of p.p. 1, 2, 3, 4, 5, 6, 7, and 8 claims.

A rotor of the high-pressure compressor of the aircraft engine is proposed, consisting of the following elements: HPC blades; blisches of the first and second stages of the ARC; KVD impeller; disk with labyrinth seal, each blis of HPC is milled from a single blank part, blis of HPC of the first stage of the HPC rotor combines the impeller, the set of blades, labyrinth seals and the HPC shaft and is connected together from the second stage and the impeller from the third to the sixth stage of the HPC rotor with the help of bolts, on the bliska shaft of the second stage of the ARC are made splined grooves for connection with the rear part of the fan shaft, the blades of the third stage of the ARC rotor are mounted on the ARC impeller using the “dovetail x” groove st and are pressed in axial direction by a stop ring attached to the front surface of the dovetail slot with bolts, blisks of the first and second stages of the ARC rotor and the blades of the third stage of the ARC rotor are made of titanium alloy, and the stop ring is made of nickel alloy, the blades with the fourth the sixth stages of the ARC rotor are mounted on the impeller of the ARC rotor using a profiled annular groove and are made with platforms and fixed against displacement in the tangential direction at each of the stages dia. oppositely located locks, platforms of blades from the fifth to the sixth stages of the ARC fit snugly to each other, and the blades of the fifth and sixth stages of the ARC located near the locks fixed in the recesses of the annular shaped groove have special cuts in the platform for these locks, blades with a fourth at the sixth stage of the ARC are made of nickel alloy, both blisers of the ARC are attached to the front flange of the ARC impeller, and a labyrinth seal disc is attached to its back flange, and on the impeller KVD completed k grooves of the dovetail under the blades of the third stage of the rotor of the KVD, three profiled annular grooves for fastening the blades of the fourth, fifth and sixth stages of the KVD and four labyrinth seals to seal the joint with the liners of the abradable seal and the cellular seal of the stator of the KVD, the impeller wheel. nickel alloy in the form of a barrel, made at the same time the whole with the disks, and on the disk with the labyrinth seal, the teeth of the labyrinth seal are made, ensuring the sealing of the joint with the support lotneniya combustion chamber casing, and the disk with the labyrinth seal is made of nickel alloy, characterized in that the mounting location of rotor blades fourth HPC rotor stages performed according to any one of claims 1, 2, 3, 4, 5, 6, 7, and 8 claims.

Note that the vibration strength of the working blades of the blisks and the third stage of the proposed ARC rotor is provided by “detuning” from the resonances of dangerous forms of oscillation of the blades, even when it has to deteriorate the mass characteristics of the ARC rotor, since these blades are not hollow legs and shelves, and the designs of dampers for blisk blades have not yet been developed, and the damping in the “dovetail” lock joint of third-stage blades at low rotor speeds (2000 ÷ 5000 rpm) is small, and Turns (7000 and more) is practically zero (see Skubachevsky, GS Aviation gas turbine engines. Design and calculation of parts / GS Skubachevsky / Fig. 7.31. - From-e 2nd, additional. Textbook for aviation universities. - M .: Mashinostroenie. 1965. - 451 p.).

A known method of assembling the place of attachment of the working blades of the compressor of low and high pressure aircraft engine SaM 146 (aircraft engine SaM 146 (see Kiselev Yu.V. Engine SaM 146. Device of the main units / Yu.V. Kiselev, D.Yu. Kiselev. - Electronic training SSAU, Samara, 2012 - 41 p.), consisting in the fact that the working blades successively install one after another through two diametrically located notches in two diametrically located sectors of the annular profiled groove of the attachment point of the blades, the first and the last each sector install blades with slots in the platforms under the locks, both locks are inserted into the notches and slots so that the vanes of the ends of the platforms are firmly rested against each other, and fasten the locks.

The advantage of this method is its simplicity.

This method of assembling the place of attachment of the working blades to the technical essence is closest to the one proposed and adopted as a prototype.

But this method cannot assemble the proposed attachment points of the working blades, since not only the working blades are mounted in these places, but also the damping device, and at the same time the methods of fixing the blades from displacement change both in the circumferential and in the radial direction.

Therefore, the task is to create a method for assembling the place of attachment of rotor blades for low and high pressure compressor rotors suitable for assembling the proposed blade attachment points.

The task is solved by the fact that a method of assembling the place of attachment of working blades made in the form of a barrel of low and high pressure compressor rotors is proposed, consisting in that the working blades are successively installed one after the other through diametrically located notches in the diametrically located sectors of the annular shaped groove of the attachment point blades, characterized in that the low pressure compressor barrel or the high pressure compressor barrel is placed on the table so that its longitudinal The second axis was vertical, and the technological groove was located below the annular profiled groove, two semicircles of the intermediate spacer were diametrically opposed to the annular profiled groove, the semi-rings of the intermediate spacer were shifted to the abutment into the wall of the technological groove, and the intermediate spacer was inserted into the circular profaned pattern. , or wind the cable, alternating, through grooves in the sectors between the grooves of the annular profiled groove and fixing points of the blades, install elastic elements and blades, insert locks into the grooves, at the same time radially force the locks to the positions where they should be fixed, and fix them with the help of a device installed so that its pushers are located in technological holes designed for squeezing one half of the intermediate spacer out of the technological groove, and pivotally connected with a bracket rigidly mounted on the stem of the working cylinder, pressure is applied to the cylinder and extruded using the spacers of the intermediate spacer spacer from the process groove up to the stop into the opposite wall of the annular profiled groove, the pressure from the cylinder is relieved, and the pushers exit the process holes, turn the cylinder together with the bracket 180 ° so that the tappets enter the process holes intended for ejection of the second half-ring of the intermediate spacer, and a small pressure is fed into the cylinder and the pushers enter the technological holes; the pressure in the cylinder and the second half ring of the intermediate spacer is squeezed out in the same way from the process groove, the pressure from the cylinder is released and the pushers exit from the process holes, and press the plugs into the process holes into the intermediate spacer or in the spacer and into the grooves of the elastic section.

With the help of the semicircular grooves in the halves of the intermediate spacer and probes it can be precisely installed in the technological groove. Also, with the help of probes, parts of the elastic hysteresis element - packages can be precisely installed in the annular profiled groove.

When setting locks in the grooves and securing them between the elastic elements and the ends of these locks and the ends of the padlock locks located near these locks, as well as between the elastic elements and the ends of the locks of the adjacent vanes, a tension is created.

When the intermediate spacer is pushed out of the technological groove, a tension is created between the elastic hysteresis element and the padlocks and the locks fixed in the recesses of the annular profiled groove, and the tension between the elastic elements and blade platforms and the elastic hysteresis element is established, and the final value of the tension between the elastic elements and the teeth lock paddles and locks, secured in the grooves.

With simultaneous compression of the package during assembly (see FIG. 19), a longitudinal force acts on each j-th half of the corrugation

where P _j is the force acting on the j-th corrugation in the radial direction, and μ is the coefficient of sliding friction.

It can be seen from the formula that the longitudinal force that the j-th corrugation of the package must overcome so that its tip moves in the circumferential direction relative to the bottom of the annular profiled groove or lock of the working blade increases from the extreme corrugations to the middle (this is the effect of “accumulation” ( summing up the action of the forces of dry friction. It is precisely because of the effect of this effect that the corrugations of the package are simultaneously compressed by one and the same amount of deformation of the rigidity of the corrugations of the package are unequal and increase from extreme corrugations to average.

As already mentioned, the effect of "accumulation" of the friction forces when using an elastic hysteresis element from a cable or elements from an MP material does not practically manifest itself in any of the variants of its radial compression used in the proposed method, and the elastic hysteresis element from a cable has the same heat capacity after assembly, and the elastic hysteresis elements of material MP have the same stiffness.

The design of the proposed device and method of assembly are illustrated by illustrations:

in fig. 1 shows the main view of the proposed attachment point for low-pressure compressor blades with an annular elastic-hysteresis element composed of four parts made in multi-span corrugated packages and elastic elements in the form of round or oval split rings mounted under the platforms of the blades between the ends of the locks fixed in the grooves of the annular profiled kanaki, and the ends of the padlock locks, as well as between the ends of the padlock locks with tension over the annular elastic-hysteresis element, the end face am locks secured in the grooves, padlocks and their platforms;

in fig. 2 shows a fragment of the place of attachment of the blades in section with a lock fixed in the recess;

in fig. 3 shows a section along A-A in FIG. one;

in fig. 4 shows a section along BB in FIG. one;

in fig. 5 is a view of page B of FIG. one;

in fig. 6 shows a fragment of the place of attachment of the working blades with a notch with a lock fixed in it with a protrusion with a part of the semi-ring of the intermediate spacer and parts of the annular elastic hardened element;

in fig. 7 shows an elastic hysteresis fastening element made of one part and assembled from separate pairs of corrugated tapes, in which the junction of the ends of one tape is diametrically opposite to the junction of the ends of the other tape, with the junction of the tape ends of each next pair contacting with the tape of the previous pair, also offset the junction of the ends of this tape to the angle π;

in fig. 8 shows a fragment of the place of attachment of the working blades with additional support of the blades with chamfers, made on the blade lock, on the slopes of the corrugations;

in fig. 9 shows a fragment of the place of attachment of the working blades with a notch with a lock without a protrusion fixed in it with a half-ring of the intermediate spacer and an annular elastic-hardening element wound from the cable segment;

in fig. 10 shows a view along page D of FIG. 9;

in fig. 11 shows a fragment of the place of attachment of working blades with a spatula and an elastic hysteresis element in the form of a corner made of material MP

in fig. 12 shows a fragment of the place of attachment of working blades with a spatula and an elastic hysteresis element in the form of a channel made of material MP;

in fig. 13 shows a section through dd in fig. 11 and 12;

in fig. 14 is a section along E-E in FIG. 11 and 12;

in fig. 15 shows a fragment of the attachment point of the working blades with a blade, an elastic hysteresis element and an elastic element in contact with a shoe fixed on the blade lock;

in fig. 16 shows the rotor of a low-pressure aircraft engine;

in fig. 17 shows the rotor of a high-pressure compressor of an aircraft engine;

in fig. 18 shows a diagram of the operation of extrusion of a half-ring of the intermediate spacer from the technological groove;

in fig. 19 shows a package loading circuit (system of acting forces) with simultaneous compression of its corrugations;

in fig. 20 shows a qualitative view of the hysteresis loop under loading of the working blade by static and dynamic loads.

The proposed mounting location of rotor blades for low-and high-pressure compressor rotors of fifth-generation aircraft engines (see Fig. 1) is designed as an annular protrusion 1 on the inner and outer surfaces of the barrel 2 of the low-pressure compressor rotor or the barrel of the high-pressure compressor rotor 62 (see FIG. 16), in which an annular shaped groove 3 is made on the side of the outer surface of the barrel 2 or barrel 62, in which the working blades 5 with rectangular platforms 6 are fixed with locks “dovetail” 4. In the annular groove 3 Two notches 7 are made in two diametrically opposite places with such a width (see Fig. 2) and a length in the tangential direction so that it can freely accommodate the lock 4 of the vanes 5, with a rectangular transverse radial section with a depth equal to the depth of the ring groove 3 ( see fig. 3). In the grooves 7 (see Fig. 2) and the notches in the platforms 6 (see Fig. 3) with locks 8 fitted washers 9 and self-locking nuts 10 fixed locks 11, limiting the displacement of the blades 5 in the tangential direction. Moreover, the outer diameter of the impeller, measured by the locks 11 (see Fig. 1), is equal to the outer diameter, measured on the platforms 6 of the blades 5. The annular shaped groove 3 is made with a conical bottom 12 (see Fig. 4). Moreover, the axis of the conical surface of the bottom 12 coincides with the longitudinal axis of the barrel 2 of the low-pressure compressor rotor or the barrel of the high-pressure compressor 62, and the angle at the apex of this cone is chosen from the condition for creating the required amount of tension between the locks 4 of the blades 5 and the elastic hysteresis element 13 on which they are . The radial cross-section of the annular shaped groove 3 has the shape of a “dovetail”, connected at the base with a trapezium with vertical side walls, and the height of the trapezium along which it is connected with the figure “dovetail” is in mm

where b is the larger base of the “dovetail” figure, c is its smaller base, and is the value by which the trapezium stands for the larger base of the figure “dovetail” equal in mm

where δ is the tension in mm between the locks 4 blades 5 and the elastic hysteresis element 13, ϕ is the angle at the apex of the bottom cone 12 of the annular shaped groove 3, so that an annular technological groove 14 is formed in one of the side walls of the protrusion of the working vanes highest height measured in radial cross section equal in mm

h = δ + H + 0 ÷ 0.2,

На торце с меньшей толщиной каждого полукольца 16 (см. фиг. 4) у его концов выполнены две полукруглых технологических выемки 17 или три таких выемки, в этом случае одна из выемок находится в средней части полукольца 16. Кольцевая промежуточная проставка 15 установлена на дно 12 кольцевой профилированной канавки 3 (см. фиг. 1 и 4) таким образом, что ее торец с выемками 17 контактирует с боковой стороной выступа 1 места крепления лопаток (см. фиг. 5), в которой нет технологической канавки 14. Между кольцевой промежуточной проставкой 15 и замками 11, установленными в выемках 7, и замками 4 рабочих лопаток 5 с радиальным натягом δ установлен кольцевой упругогистерезисный элемент 13 (см. фиг. 1 и 4) с шириной, измеренной в направлении продольной оси ротора, равной или меньшей ширины меньшего основания «ласточкиного хвоста» кольцевой профилированной канавки 3, составленный из одной, двух и более частей 18 кольца (см. фиг. 1), равнорасположенных по окружности, и между концами этих частей имеются зазоры 19, величина которых либо равна нулю, либо равна или меньше половины допустимой суммарной величины относительных рабочих смещений в окружном направлении концов этой части кольца и предпочтительно равна 0,2÷0,5 мм. Между наружной поверхностью бочки 2 или бочки 62 (см. фиг. 1 и 16) и платформой 6 каждой лопатки 5, а также между торцами платформ 6 соседних лопаток 5 и ответными торцами платформ 6 лопаток 5 и замков 11 имеются зазоры 20, величина которых ограничена величинами допустимых смещений лопатки под действием статических и динамических рабочих нагрузок. Под платформами 6 лопаток 5 между торцами замков 11, закрепленных в выемках 7 кольцевой профилированной канавки 3, и торцами замков 4 лопаток 5, а также между торцами замков 4 лопаток 5 с натягом по кольцевому упругогистерезисному элементу 13, торцам замков 11, замкам 4 лопаток 5 и их платформам 6 установлены упругогистерезисные или упругие элементы 21 (см. фиг. 1). Причем величины этих натягов подобраны таким образом, что при колебаниях лопаток происходят упругие взаимные проскальзывания с сухим трением контактирующих элементов. Причем в выемках в кольцевой канавке 3 закреплены четыре, шесть или более равнорасположенных по окружности замков 11. Боковые стороны замков 11 (см. фиг. 2), закрепленных в выемках 7 в кольцевой профилированной канавке 3, на части своей длины, у дна 12 кольцевой канавки 3, срезаны и образуют заборный клин 22. В боковой стенке с технологической канавкой 14 выступа 1 места крепления рабочих лопаток (см. фиг. 3 и 4) выполнено четыре или шесть отверстий 23, из которых два расположены в районах расположения концов полуколец 16 промежуточной проставки 15, а при выполнении шести отверстий 23 еще по одному в районе средней части каждого полукольца 16. В эти отверстия до упора в кольцевую промежуточную проставку 15 запрессованы заглушки 24. Само место крепления рабочих лопаток собрано по способу п. 11 формулы изобретения, и все трущиеся поверхности деталей предлагаемого места крепления покрыты износостойким покрытием.where H is the greatest height of the transverse radial section of the annular intermediate spacer 15. The annular intermediate spacer 15 (see Fig. 1) is made of two diametrically opposite half-rings 16 with a transverse radial section in the form of a trapezium - a truncated wedge (see Fig. 4), with the greatest height H, the width equal to or smaller than the width of the smaller base of the “dovetail” of the annular shaped groove 3, and the angle of inclination of the wedge is half the angle of the wedge cone equal to

At the end with a smaller thickness of each half-ring 16 (see FIG. 4), two semi-circular process grooves 17 or three such grooves are made at its ends, in this case one of the grooves is located in the middle part of the semi-ring 16. The ring spacer 15 is installed on the bottom 12 annular profiled grooves 3 (see Fig. 1 and 4) in such a way that its end with the notches 17 is in contact with the side of the protrusion 1 of the blade attachment point (see Fig. 5), which does not have a technological groove 14. Between the annular spacer 15 and locks 11, installed A circular elastic hardening element 13 (see Fig. 1 and 4) with a width measured in the direction of the longitudinal axis of the rotor equal to or less than the width of the smaller base of the "dovetail" ring is circular. profiled groove 3 made up of one, two or more ring parts 18 (see FIG. 1) equidistant around the circumference, and there are gaps 19 between the ends of these parts, the value of which is either zero or equal to or less than half of the permissible total relative value GOVERNMENTAL working displacement in the circumferential direction of the end part of the ring, and preferably equal to 0.2 ÷ 0.5 mm. Between the outer surface of the barrel 2 or barrel 62 (see Fig. 1 and 16) and the platform 6 of each blade 5, as well as between the ends of the platforms 6 of the adjacent blades 5 and the counter ends of the platforms 6 of the blades 5 and locks 11, there are gaps 20, the size of which is limited the values of the allowable displacement of the blade under the action of static and dynamic workloads. Under the platforms 6 blades 5 between the ends of the locks 11, fixed in the recesses 7 of the annular profiled groove 3, and the ends of the locks 4 of the blades 5, as well as between the ends of the locks 4 of the blades 5, with an overload along the annular elastic-hysteresis element 13, the ends of the locks 11, the locks 4 of the blades 5 and their platforms 6 are installed elastic hysteresis or elastic elements 21 (see FIG. 1). Moreover, the magnitudes of these tensions are chosen in such a way that, when the blades oscillate, elastic mutual slippage occurs with dry friction of the contacting elements. Moreover, four, six or more equally spaced locks 11 are fixed in the grooves in the annular groove 3. The sides of the locks 11 (see Fig. 2) fixed in the grooves 7 in the annular profiled groove 3, on a part of their length, at the bottom 12 the annular the grooves 3 are cut off and form an intake wedge 22. In the side wall with the process groove 14 of the protrusion 1 of the attachment of the working blades (see Fig. 3 and 4) four or six holes 23 are made, of which two are located in the areas of the ends of the semi-rings 16 intermediate spacers 15, and when you In addition to the six holes 23, one more in the middle part of each half-ring 16. These holes to the stop in the annular intermediate spacer 15 are pressed into the plugs 24. The blade mounting point itself is assembled according to method 11 of the claims, and all the friction surfaces of the parts of the proposed location Mounts are covered with a wear resistant coating.

It is also proposed a mounting point for rotor blades of low and high pressure compressor rotors of fifth generation aircraft engines (see Fig. 1), characterized in that the elastic elements 21 are made in the form of round, or oval, or round and oval split steel, arranged so that the cut 26, made along the generatrix of the ring, is located at the gap between the ends of the platforms 6 of the adjacent blades 5 in the radial plane of the rotor and at the end on the inner surface of the platform 6 ktiruyuschey with this elastic element 21, made the protrusion 27, with a gap included in the incision of the elastic element 21.

A mounting point for rotor blades for low and high pressure compressor engines of the fifth generation is proposed (see Fig. 1), characterized in that the elastic-hardened element 13 is made of two, four, six, or more parts 18. Each part is made of one, two or more ground, welded or hardened, corrugated tapes 28 (see FIG. 6), made of heat-resistant or heat-resistant stainless steel. And in each part with two or more ribbons 28, in it they are assembled "corrugations in corrugations". Two diametrically located locks 11, installed in the recesses 7 of the annular profiled groove 3, are made with protrusions 29 (see Fig. 1), with which they rest on the bottom of the annular profiled groove 3. Between the protrusions 29 and the counter ends of the parts 18 of the annular elastoresisse element 13 are the gaps 30, the magnitude of which is either zero or equal to or less than half of the allowable total value of the relative working displacements in the circumferential direction of the ends of this part of the annular elastic-hardening element, and preferably avna 0.2 ÷ 0.5 mm. Between these protrusions and the response ends of each of the semi-rings of the intermediate spacer there are gaps 31, the total value of which is equal to or greater than the maximum relative temperature elongation of the semi-rings 16 of the intermediate spacer 15. Each hole 23 made in the wall of the annular shaped groove 3 without the technological groove 14 located at the middle each part 18 of the elastic hysteresis element 13, in the radial section, where the apex of the corrugation of this part rests on the bottom of the annular profiled groove 3, is made with a diameter equal to the sum of the thicknesses of the intermediate spacer 15 and the tape 28 or tapes 28 of the elastic hysteresis element 13. Caps 24 are pressed into the holes 23, which, with their spherical ends without a gap or with a gap equal to the amount of mutual slip of this vertex relative to the bottom of the annular shaped groove 3, enter into reciprocal notches 32 (see Fig. 4), made in the semi-rings 16 of the intermediate spacer 17 and in the lateral side of each part of the elastic-hardened element 13.

In addition, a mounting point for rotor blades of low and high pressure compressor engines of the fifth generation is proposed (see Fig. 7), characterized in that the elastic-hardened fixture element 13 of the mounting point is made of one part 18 and assembled from separate pairs 33 of corrugated ribbons 28, which joint of the ends of one tape is diametrically opposite to the joint of the ends of the other tape. Moreover, the junction of the ends of the tape 28 of each next pair 33, in contact with the tape 28 of the previous pair 33, is also offset from the junction of the ends of this tape by an angle π and the joints of the tapes 28 are located at the tops of the corrugations supported on the semi-rings 16 of the intermediate spacer 15. At the end of each lock 11, facing the bottom of the annular profiled groove 3, are fillets 34, with which δ locks 11 are supported on the tops of the corrugations of the elastic hysteresis element 13. The ends of the semi-rings 16 of the intermediate spacer 15 with the same tension are placed under two diametrically arranged ennymi of these latches and the gap between the ends of the half rings equal to or less than the maximum relative temperature elongation intermediate spacers.

A mounting point for rotor blades for low and high pressure compressor engines of the fifth generation is proposed (see FIG. 8), characterized in that at the ends of the locks there are 4 blades 5, the chamfers 35 are cut at the bottom of the locks so that the blade with these chamfers abuts further the slopes of the corrugations, and the elastic elements 21 located in the depressions of these corrugations lean against the tension either in the bottom of the depression or in the other slope of these corrugations.

It is also proposed to attach the rotor blades of the rotors of the low-pressure and high-pressure engines of the fifth generation (see Fig. 9), characterized in that the elastic-hardened element 13 is made as a piece of cable 36 of one-sided lay without a central wire - from six or eighteen wires wound round to the turn closely in one row over the intermediate spacer 15 so that the width of the winding, measured in the direction of the rotor axis, is equal to the width of the base of the lock 4 of the blade 5, with one end of the cable 36 fixed under one vice com 11 without a protrusion installed in the recess 7 in the annular shaped groove 3, and the second in another such lock 11 (not shown in Fig.), or both ends of the cable 36 are fixed in one of two such locks 11, so that in any radial section blade attachment points had the same number of turns 37 (see Fig. 10).

A mounting point for rotor blades for low and high pressure compressor engines of the fifth generation is proposed (see FIG. 11), characterized in that the elastic hysteresis element located under the locks 4 blades 5 and the elastic hysteresis elements located under the platforms 6 between the ends of the locks 4 blades 5 , made in the form of corners 38, each of which is located so under the lock 4 of its shoulder blade 5, that the smaller shelf 39 of the corner is located between the ends of the locks 4 of the adjacent vanes 5. On the locks 4 of the two blades 5 located at each of the locks 11 installed in the recesses 7 of the annular profiled groove 3 (see FIG. 12), the elastic-hardened elements are in the form of a channel 40, and one channel shelf is located between the ends of the locks 4 of the adjacent vanes 5, and the other between the end of the lock 11 installed in the recess 7, and the end of the lock 4 blades 5. And the part of the elastic hysteresis elements 38 and 40, installed with pressure on the parts in contact with them, located under the locks 4 blades 5 (see FIG. 11 and 12) have a transverse radial cross-section of a rectangular shape with a width measured in the direction of the rotor axis equal to the smaller base of the “dovetail” of the scapula lock, and their parts located between the locks (see Fig. 14) have a cross section in the form a rectangle connected to a “dovetail” that exactly coincides with the “dovetail” of the padlock. The elastic hysteresis elements 38 and 40 themselves are made by cold pressing of high-density MP wire material λ = 2.5 ÷ 4 g / cm ³ and more of welded stainless steel wire with preferred wire diameter d = 0.15 ÷ 0.3 mm, with a ratio D / d = 8 ÷ 10, where D is the diameter of the wire helix from which the material MP is made.

It is also proposed to attach the working blades of the rotors of the low and high pressure compressor of fifth generation aircraft engines (see Fig. 15), characterized in that the padlocks 41, made of a thin steel hardened or tempered ground stainless steel sheet, are fixed on the locks of 4 blades 5, without gaps covering the locks 4 blades 5 on all surfaces on which they would contact with the sides of the annular profiled groove 3, the elastic hysteresis element 13, set under the lock E blades 4, 5 and uprugogisterezisnymi or the elastic members 21 mounted between the ends of the locks 4 and 11 under the platforms 6 of the blades 5 without shoes.

A rotor of a low-pressure compressor of an aircraft engine is proposed (see FIG. 16), made in the form of a barrel 2 with three or more annular projections 1 on the inner and outer surfaces of the barrel. In each annular protrusion 1, there is a profiled annular groove 3 with a transverse radial section, which responds to the lock 4 of the working blade 5 of the “dovetail” type. Working blades 5 with their locks 4 are inserted into these grooves 3 and made with platforms 6, which together with feathers of 42 blades 5 organize channels of flow around these blades. The blades of 5 stages, starting with the second 43 (or the third stage 44) platforms 6 abut each other. The rotor of the low pressure compressor is rigidly connected to the fan rotor (not shown in FIG.). The blades 5 of each stage, located at the locks 11, fixing the displacements in the circumferential direction of the blades of these stages, have special notches in platform 6 (see Fig. 3), in which these locks are placed, characterized in that the fixing point of the working blades is the first or the first and second stages of the rotor of the low pressure compressor, made according to any one of p.n. 1, 2, 3, 4, 5, 6, 7, and 8 claims.

A rotor of the high-pressure compressor of the aircraft engine is proposed (see FIG. 17), consisting of the following elements: HPC blades 5; bliski first 45 and second 46 steps KVD; KVD 47 impeller; disc with labyrinth seal 48. Each blisk KVD is milled from a single piece of detail. Blis the ARC of the first stage 45 of the ARC rotor combines the impeller 49, a set of blades 5, labyrinth seals 50 and the ARC shaft 51 and is connected together with the second stage 46 and the impeller 47 from the third to the sixth stage of the ARC rotor using bolts 52. On the shaft 51 The bliska of the second stage 46 of the ARC is made of slotted grooves 53 for connection with the back of the fan shaft (not shown in the figure). The blades 5 of the third stage 54 of the ARC rotor (see Fig. 17) are mounted on the impeller 47 of the ARC by means of a dovetail groove and axially pressed by the stop ring 55 attached to the front surface of the dovetail groove using bolts 52. The bliski of the first 45 and second 46 stages of the rotor of the ARC and the blades 5 of the third stage 54 of the ARC rotor are made of titanium alloy, and the stop ring 55 is made of nickel alloy. The blades 5 of the fourth 56, fifth 57 and sixth 58 steps of the ARC rotor are mounted on the impeller 47 of the ARC rotor using a profiled annular groove 3 and are made with platforms 6 and fixed from displacement in the tangential direction at each of the stages by two diametrically opposed locks 11. Platforms 6 blades 5 from the fifth 57 to the sixth 58 steps of the ARC fit snugly together. Four blades 5 of the fifth and four blades 5 of the sixth stage of the ARC have special cuts in platform 6 for two locks 11 (see Fig. 3). The blades 5 from the fourth 56 to the sixth stage 58 of the ARC are made of nickel alloy. To the front flange 59 of the KVD impeller 47 both KVD blisks are attached, and a disk with a labyrinth seal 48 is attached to its back flange 60 also with the help of bolts 52. The kVa dovetail grooves for the blades are made on the KVD impeller 47 (see Fig. 17) 5 of the third stage 54 of the ARC rotor, three profiled annular grooves 3 for fastening the blades of the fourth, fifth and sixth stages of the ARC and four labyrinth seals 61 for sealing the joint with the liners of the abrasive seal and the honeycomb seal of the ARC stator (not shown). The impeller 47 KVD (see Fig. 17) is made of nickel alloy in the form of a barrel 62, which is integrally formed with disks 63. The labyrinth seal disc 48 has labyrinth seal teeth, which seal the joint with the seal support of the combustion chamber casing ( Fig. not shown). The labyrinth seal disc 48 is made of nickel alloy. The proposed rotor of the ARC is characterized in that the place of attachment of the blades of the fourth stage 56 of the rotor of the ARC is made according to any one of pp 1, 2, 3, 4, 5, 6, 7, and 8 claims.

A method for assembling the place of attachment of working blades made in the form of a barrel of low and high pressure compressor rotors is proposed, consisting in that a barrel 2 of a low pressure compressor or a barrel 62 of a high pressure compressor (see Fig. 16 and 17) is placed on table 64 (see Fig. 18) so that its longitudinal axis was vertical, and the process groove 14 was located below the annular profiled groove 3, two semi-rings 16 of the intermediate spacer 15, shifted diametrically opposite to the annular profiled groove 3 half-rings 16 of the intermediate spacer 15 are pressed up to the stop in the wall of the technological groove 14, 3 intermediate parts are installed in the annular shaped spacer 3 parts of the elastic-hardened element — bags 18, or the cable 36 is wound (see FIG. 9), alternating through notches 7 into sectors between the grooves of the annular profiled groove 3 of the place of attachment of the blades, install the elastic elements 21 and blades 5 (see Fig. 18), insert the locks 11 into the notches. Simultaneously, the radial forces displace the locks 11 to the positions where they should be fixed, and they are heated with fitting bolts 8, washers 9 and self-locking nuts 10. With the aid of the device 65, which is installed so that its pushers 66 are located in technological holes 23 intended for squeezing one half-ring 16 of the intermediate spacer 15 out of the technological groove 14, and are hingedly connected to the bracket 67, rigidly mounted on the rod of the working cylinder 68, serves to pressurize the cylinder 68 and squeeze out the semi-ring 16 of the intermediate spacer 15 from the technological groove 14 until it stops against the opposite wall front profiled groove 3. The pressure from cylinder 68 is relieved, and the pushers 66 emerge from the technological holes 23. The cylinder 68 with the bracket 67 is rotated 180 ° in the support 69 of the device 65 so that the pushers 66 enter the technological holes 23 intended to push the second half spacer 16 of the intermediate spacer 15. A small pressure is fed into the cylinder 68 and the pushers 66 enter these technological holes 23. The working pressure is supplied to the cylinder 68 and the second half ring 16 of the intermediate spacer 15 is extruded en logically from the process of the groove 14. The pressure cylinder 68 is vented, and the pushers 66 come out of the holes 23. The process technological holes 23 is pressed against the stop plug 26 into the intermediate piece 15 or a separate part 18 uprugogisterezisnogo element 13.

Assembling the proposed attachment points for rotor blades of low and high pressure compressor rotors according to item 1, 2, 3, 4 and 5 of the claims described in the proposed method for their assembly. Differences in the assembly of the attachment points of the blades according to claims 6 and 7, the claims are clear and do not require additional description. A feature of the assembly of the attachment site according to claim 8 is only that the blades 5 (see Fig. 15) are fed to the assembly with 4 shoes 41 already fixed on their locks

The assembly of the proposed rotors of the low and high pressure compressor is clear from the description of their design and with the exception of the assembly of the attachment points for the working blades, in which the elastic hysteresis element and elastic elements are installed, are no different from the prototype and are not specifically described.

The proposed attachment points for rotor blades of low and high pressure compressor rotors at the engine operating modes work as follows: as mentioned above, the blades are elastically fixed at the attachment point and under static and dynamic loads by the workers, they overcome the dry friction forces on the contact surfaces of elastically deformed elements of the attachment point created by the pressure - a compressive load between them, obtained during assembly and as a result of the action of centrifugal forces. The oscillation energy of the system “place of attachment of blades-working blades-damping device” is dissipated due to the work of the dry friction forces in the case of mutual elastic slipping of the contacting elements. For example, when used as the elastic hysteresis element 13 multi-layer multi-span packages 18 (see Fig. 6) - locks 4 blades 5 on the tops of the corrugations of the packages 18, the tops of the corrugations of the packages 18 on the locks 11 and the semi-rings 16 of the intermediate spacer 15 and on the elastic elements 21 and between ribbons 30 of packages 18, elements 21 along platforms 6, and the ends of locks 4 blades 5 and ends of locks 11. When installed in an annular shaped groove 3, a resistive-elastic element 13 made of a cable (see Fig. 9) or resistive-elastic elements 38 and 40 of wire MP material energy inside the elastic hysteresis elements is dissipated due to the mutual elastic slip with dry friction of the wires of the cable or the contacting coils of the material.

In addition, the oscillation energy of the system “place of attachment of blades-working blades-damping device” is dissipated due to aerodynamic damping of oscillations of working blades 5 and dissipation in the material of working blades and barrel, and disks (if any) of the rotor of the low and high pressure compressor. The latter type of damping is very small in comparison with the structural damping in the proposed attachment points of the working blades, and it can be neglected.

Note that for the proposed blade attachment points, the damping devices effectively quench any form of oscillation of the working blades.

The qualitative nature of the loading of the working blade of the proposed attachment point with the elastic hysteresis element 13 in the form of separate multi-span corrugated packages 18 and elastic elements 21 working constant and cyclic dynamic load - torque or force in the simple case when the load component acting in the direction of the rotor axis does not overcome forces friction acting on the bottom of the lock 4 of the blade 5 is shown in FIG. 20. In the initial linear section 69 of the first workload loading 71, the blade is loaded like an elastic body, without reciprocal elastic slippage of the lock 4 and blade platform 6 along the surfaces in contact with them. With further growth of the load, the blade is loaded along the nonlinear section 72 of the process 71 with a gradual expansion of the zone of mutual slippage of the lock 4 of the blade along the side surfaces of the annular profiled groove 3 and the tops of the corrugations of the package 18 in contact with the lock, and the blade in contacting with two elements 21. Then with further growth of the load, the zone gradually expands, where, due to the rotation of the blade (lock), the tension on the sides of its lock is zeroed, and in this zone the friction forces on the sides with zero torona castle. At point 73, these friction forces become equal to zero on the entire surface of the sides of the lock 4, and the blade becomes elastically suspended on the package 18 of two elements 21. Further loading of the blade is described by a non-linear section 74, which during deformation of the package 18 continues to slip with dry friction its tops corrugations, both on locks 4 blades 5, and on half rings 16 intermediate spacer 15, locks 11 and elements 21, and the blade itself elastically slips relative to elements 21. At some time, the oscillation rate becomes equals zero and changes its direction. The blade is loaded by the second working unloading process 75. In the initial linear section 76 of this process, “the system of the working blade-package 18, the elastic elements 21 ″ elastically deformed without mutual slippings on the contact surfaces. Upon further unloading of this system, it is deformed by a nonlinear section 77, in which the blade detaches from elements 21 and the package 18 is deformed with a gradual spreading of its tip peaks from extreme to the central top of the package and then the system is deformed with the least rigidity with a fully layered package 18, along the tops of the corrugations, and along the layers of the package, while at point 78 the lock 4 blades along its side surfaces will come into contact with the annular shaped groove 3. At the same time, the rigidity of the newly formed The “fastening-working-blade-damping device” system greatly increases and its further loading, which again creates tension on the sides of the blade lock, is described by the unloading process section 75 75. Again, at some point 80, the blade oscillation speed will become zero, and speed will change the sign. Further, the system will be loaded by a repeated load process 81, containing qualitatively similar sections of the first load process sections 71 until the hysteresis loop closes at point 82.

It should be noted that the actual loading processes are much more complicated than in the considered example, since a sufficiently large number of blades that oscillate with different amplitudes and in different phases and the laws of exciting loads acting on the blades, can significantly differ from the harmonic, and the load component acting in the direction of the rotor axis can overcome the friction forces acting on the bottom of the castle 4 blades 5 (see above).

But the considered simple example, in our opinion, convincingly proves the possibility of effective damping of oscillations of compressor blades of low and high pressure in practical use of the proposed mounting points without reducing the engine performance - specific thrust and efficiency, resource and maintainability with a slight increase in its mass.

The main advantages of the proposed structures are described above.

Moreover, we emphasize once again that the proposed design of the mounting points of the working blades with dovetail locks installed in the annular grooves of the barrel of the impeller with damping devices suitable for effective damping of the working blades are in essence pioneering solutions. These devices are fairly simple structurally, compact and slightly degrade the mass characteristics of the impellers and the rotors of the turbomachine in general, do not spoil the laws of the flow of the blades of gas and do not impair the sealing conditions of the individual stages of the rotors of the turbomachine, do not reduce the efficiency of the impellers and the turbomachine as a whole.

The proposed design with proper selection of materials of their parts can operate at high temperatures, in the absence of lubrication and aggressive environment, and have a sufficiently large operating time between repairs and fairly good maintainability, at least not less than the "classic" impellers of aviation rotors GTE of the fourth generation, since the working blades and elastic hysteresis and elastic elements of the damping devices can be replaced with new ones in case of their unacceptable wear or breakage.

The positive qualities of the proposed blade attachment points should also include the possibility of changing the sufficiently wide range of the elastic hysteresis properties of a package without changing the design of parts of the attachment site and the process equipment (stamp for making the package and accessories for assembling the place of attachment) only by changing the size of the tension of the corrugations of the package or packages by replacing part of corrugated tapes with smooth ones or installing additional smooth tapes. Smooth tapes are installed under the bag or bags.

The elastic hysteresis elements of the proposed attachment points have high damping properties (as already mentioned, Ψ _max = 2.3 ÷ 2.5 for elastic hysteresis elements of MP material, which work for cyclic compression in a closed volume, and Ψ _max = 3.5 ÷ 3.7 for multi-layered multi-span corrugated package, working for cyclic compression in the mode of one-sided elastic hardening stop).

In conclusion, we note that it is already possible to develop a methodology for conducting a virtual experiment to determine the parameters of all the proposed attachment points, ensuring optimal and final configuration of these systems.

Claims (17)

1. The mounting position of rotor blades for low and high pressure compressor rotors of fifth generation aircraft engines, made in the form of an annular protrusion on the inner and outer surfaces, made in the form of a barrel of rotors of the low and high pressure compressor, in which an annular shaped groove is made on the outer surface of the barrel, in which working blades with platforms are fixed with dovetail locks, grooves with such width and length are made in an annular groove in diametrically opposite places tangential direction so that it can easily accommodate the blade lock, with a rectangular transverse radial section with a depth equal to the depth of the annular groove, and locks in the grooves and notches in the platforms that limit the displacement of the blades in the tangential direction, and the outer diameter of the impeller measured along locks, equal to the outer diameter, measured on the platforms of the blades, characterized in that the annular profiled groove is made with a conical bottom, and the axis of the conical bottom surface with falls with the longitudinal axis of the rotor of the compressor of low and high pressure, and the angle at the apex of this cone is selected from the condition of creating the required amount of tension between the padlocks and the elastic hysteresis element on which they rest, and the radial cross section of the ring shaped groove has the shape of a dovetail, connected at the base with a trapezoid with vertical side walls, and the height of the trapezium along which it is connected to the figure “dovetail” is equal in mm

where b is the larger base of the “dovetail” figure, c is its smaller base, and is the value by which the trapezium stands for the larger base of the figure “dovetail” equal in mm

where δ is the amount of tension in mm between the padlocks and the elastic hysteresis element, ϕ is the angle at the top of the cone of the bottom of the annular shaped groove, so that an annular groove with the greatest height measured in the radial cross section equal in mm h = δ + H + 0 ÷ 0.2, where H is the greatest height of the transverse radial section of the annular intermediate spacer, and the annular intermediate spacer is made of two diametrically opposite semirings with a transverse radial section in the form of a trapezium - a truncated wedge, with the greatest height H, width equal to or smaller than the width of the smaller base “dovetail” "Annular profiled groove, and the angle of the wedge is half the wedge cone angle equal to

at the end with a smaller thickness of each half-ring, two half-round technological grooves or three such grooves are made at its ends, in this case one of the grooves is located in the middle part of the semi-ring, and the annular intermediate spacer is installed on the bottom of the annular grooved in such a way that its end with grooves in contact with the side of the protrusion of the place of attachment of the blades, in which there is no technological grooves, between the annular intermediate spacer and the locks installed in the grooves, and locks working blades with for An elastic tension hysteresis element with a width measured in the direction of the longitudinal axis of the rotor equal to or smaller than the width of the smaller dovetail base of the annular shaped groove made of one, two or more ring parts that are equally spaced around the circumference and between the ends of these parts there are gaps, the magnitude of which is either zero or equal to or less than half the permissible total value of the relative working displacements in the circumferential direction of the ends of this part of the ring and is equal to 0.2 ÷ 0 , 5 mm, and between the outer surface of the barrel and the platform of each blade, as well as between the ends of the platforms of adjacent blades and the response ends of the blades and lock platforms there are gaps, the magnitude of which is limited by the values of allowable blade displacements under the action of static blades and blades between the ends of the locks fixed in the grooves of the annular profiled groove, and the ends of the padlock locks, as well as between the ends of the padlocks of the blades with tension over the annular elastic-hardened element, the ends of MKs fixed in grooves in an annular shaped groove, locks of blades and their platforms are fitted with elastic hysteresis or elastic elements, and the values of these tensions are chosen in such a way that, when the blades oscillate, elastic mutual slippage occurs with dry friction of the contacting elements, and in the grooves in the ring groove fixed four, six or more locks equally spaced around the circumference, and the sides of the locks secured in recesses in the annular shaped groove, on part of their length, at the bottom of the annular groove, cut off and form an intake wedge, and in the side wall with the technological groove of the protrusion of the place of attachment of the working blades four or six holes are made, of which two are located in the regions of the ends of the semi-rings of the intermediate spacer, around the middle part of each half-ring, and into these holes all the way into the annular intermediate spacer, the plugs are pressed in, and the point of attachment of the working blades is assembled according to method 11 of the claims, and all uschiesya surface of the proposed site of attachment of parts coated with a wear resistant coating. 2. The place of attachment of rotor blades for low-and high-pressure compressor rotors of fifth-generation aircraft engines according to claim 1, characterized in that the elastic elements are made in the form of round, or oval, or round and oval split steel, hardened and ground rings arranged so that the incision site made along the generatrix of the ring is located at the gap between the ends of the platforms of adjacent blades in the radial plane of the rotor and at the end on the inner surface of the platform of one of the blades in contact with this elastic element entom, made the protrusion, with a gap included in the cut of the elastic element. 3. The mounting point of the working blades of the rotors of the compressor of low and high pressure aircraft engines of the fifth generation according to any one of paragraphs. 1 and 2, characterized in that the elastic hysteresis element is made of two, four, six or more parts, each of which is made of one, two or more ground, hardened or hardened corrugated tapes made of heat-resistant or heat-resistant stainless steel, each parts with two or more tapes in it, they are assembled "corrugation into corrugation", and two diametrically located locks, installed in the grooves of the annular profiled groove, are made with projections with which they rest on the bottom of the annular profiled ditch ki, and between the protrusions and the counter ends of the parts of the annular elastic hysteresis element there are gaps, the magnitude of which is either zero or equal to or less than half of the allowable total value of the relative working displacements in the circumferential direction of the ends of this part of the annular elastic hitherto element and preferably 0.2 ÷ 0, 5 mm, and between these protrusions and the response ends of each of the half-rings of the intermediate spacer there are gaps, the total value of which is equal to or greater than the maximum relative temperature elongation of the semi-intermediate spacer, and each hole made in the wall of the annular profiled groove without a process groove, located at the middle of each part of the elastic hysteresis element, in radial section, where the top of the corrugation of this part rests on the bottom of the annular shaped groove, has a diameter equal to the thickness of the intermediate spacer and the tape or ribbons of the elastic-hardened element, and into these holes are inserted the plugs, which with their spherical ends without a gap or with zorom equal to the value of mutual slipping of the top relative to the bottom ring shaped groove included in the response recesses formed in the half-rings in the intermediate spacer and the side of each part uprugogisterezisnogo element. 4. The mounting point of the working blades of the rotors of the compressor of low and high pressure aircraft engines of the fifth generation according to any one of paragraphs. 1 and 2, characterized in that the elastic hysteresis element of the attachment place is made of one part and assembled from separate pairs of corrugated tapes, in which the junction of the ends of one tape is diametrically opposed to the junction of the ends of the other tape, and the junction of the tape ends of each next pair in contact with the previous tape the pairs are also offset from the junction of the ends of this tape by an angle π and the joints of the tapes are located at the tops of the corrugations resting on the semiring of the intermediate spacer, and at the end of each of the locks facing the bottom there is an annular shaped grooves formed fillets that with interference δ locks rest on top of the corrugations uprugogisterezisnogo element and the ends of half-rings intermediate spacers with the same preload placed under two diametrically disposed from these latches and the gap between the ends of the half rings equal to or less than the maximum relative temperature elongation intermediate spacers. 5. The mounting point of the working blades of the rotors of the compressor of low and high pressure aircraft engines of the fifth generation according to any one of paragraphs. 3 and 4, characterized in that at the ends of the padlock locks, chamfers were cut at the bottom of the locks at such an angle that the blade with these chamfers rests further on the slopes of the corrugations, and the elastic elements located in the depressions of these corrugations either lean against the bottom of the depression or another slope of these corrugations. 6. The mounting point of the working blades of the rotors of the compressor low and high pressure aircraft engines of the fifth generation according to any one of paragraphs. 1 and 2, characterized in that the elastic hysteresis element is made in the form of a single-sided cable without a central wire - from six or eighteen wires wound to the coil closely in one row over the intermediate spacer so that the winding width measured in the direction of the rotor axis, equal to the width of the blade lock base, with one end of the cable secured under one lock without a protrusion installed in a recess in an annular shaped groove, and the second in another such lock, or both ends of the cable secured in one of Vuh such locks so that in any radial section attachment points of the blades had the same number of turns. 7. The mounting point of the working blades of the rotors of the compressor of low and high pressure aircraft engines of the fifth generation according to any one of paragraphs. 1 and 2, characterized in that the elastic hysteresis element located under the padlocks and the elastic hysteresis elements located under the platforms between the ends of the padlocks are made in the form of separate elastic hysteresis elements having the shape of a corner, each of which is located so under the lock of its blade that a smaller corner shelf is located between the ends of the locks of the adjacent blades, and the locks of the two blades located at each of the locks installed in the recesses of the annular profiled groove are fitted with elastica Steresis elements having the form of a channel and one channel of the channel is located between the ends of the locks of adjacent blades, and the other between the end of the lock installed in the recess and the end of the lock of the blade, with parts of the elastic-hardened elements installed with tension on the parts in contact with them located under blade padlocks, have a transverse radial cross-section of a rectangular shape with a width measured in the direction of the axis of the rotor, equal to the base of the "dovetail" of the paddle blade, and their parts located between the locks have pepper-section as a rectangle connected to the "dovetail" exactly coincident with "dovetail" lock blade and uprugogisterezisnye elements themselves are made by cold pressing of the wire material MP high density λ = 2,5 ÷ 4 g / cm ³ or more of welded stainless steel wire with preferred wire diameter d = 0.15 ÷ 0.3 mm, with the ratio D / d = 8 ÷ 10, where D is the diameter of the wire helix from which the material MP is made. 8. The mounting point of the working blades of the rotors of the compressor low and high pressure aircraft engines of the fifth generation according to any one of paragraphs. 1, 2, 3, 4, 5, 6 and 7, characterized in that on the padlocks of the blades are fixed stamped shoes made of thin steel hardened or hardened polished stainless steel sheet, without gaps covering the padlocks of the blades over all surfaces along which they would contact with the sides of the annular shaped groove, the elastic hysteresis element installed under the padlocks, and the elastic hysteresis or elastic elements installed between the ends of the locks under the blade platforms in the absence of the bash What are the. 9. The rotor of the low-pressure compressor of the aircraft engine, made in the form of a barrel with three or more annular protrusions on the inner and outer surfaces of the barrel, in each annular protrusion of which there is a profiled annular groove with a transverse radial section responding to the paddle blade of the “dovetail” type, and working blades with their locks are inserted into these grooves and made with platforms, which together with the blades feathers organize channels of flow around these blades, and the blades of steps starting from the second or third from The platforms rest against each other, and the rotor of the low pressure compressor is rigidly connected to the fan rotor, and the blades of each stage, located near the locks that fix the blades from the displacements in the circumferential direction, have special notches in the platform, in which these locks are placed, which differ the fact that the mounting location of the working blades of the first or first and second stages of the rotor of the low pressure compressor is made according to any one of claims. 1, 2, 3, 4, 5, 6, 7, and 8 claims. 10. Rotor of the high-pressure compressor of the aircraft engine, consisting of the following elements: HPC blades; blisches of the first and second stages of the ARC; KVD impeller; disk with labyrinth seal, each blis of HPC is milled from a single blank part, blis of HPC of the first stage of the HPC rotor combines the impeller, the set of blades, labyrinth seals and the HPC shaft and is connected together from the second stage and the impeller from the third to the sixth stage of the HPC rotor with the help of bolts, on the bliska shaft of the second stage of the ARC are made splined grooves for connection with the rear part of the fan shaft, the blades of the third stage of the ARC rotor are mounted on the ARC impeller using the “dovetail x” groove st and are pressed in axial direction by a stop ring attached to the front surface of the dovetail groove with bolts, blisks of the first and second stages of the ARC rotor and the blades of the third stage of the ARC rotor are made of titanium alloy, and the stop ring is made of nickel alloy, blades from the fourth to the sixth stages of the ARC rotor are mounted on the impeller wheel of the ARC rotor using a profiled annular groove and are made with platforms and fixed against displacement in the tangential direction at each of the stages dia etrarally opposite locks, platforms of blades from the fifth to the sixth stages of the ARC fit snugly to each other, and the blades of the fifth and sixth stages of the ARC, located near the locks fixed in the grooves of the annular shaped groove, have special cuts in the platform for these locks, blades with a fourth at the sixth stage of the ARC are made of nickel alloy, both blisers of the ARC are attached to the front flange of the ARC impeller, and a labyrinth seal disc is attached to its back flange, and to the working collar All KVDs made k grooves “dovetail” for the blades of the third stage of the rotor of the KVD, three profiled annular grooves for fastening the blades of the fourth, fifth and sixth stages of the KVD and four labyrinth seals KVD is made of nickel alloy in the form of a barrel, made in one piece with the discs, and on the disc with a labyrinth seal, the teeth of the labyrinth seal are made, ensuring the sealing of the joint with oh seal the combustion chamber casing, and the disk with the labyrinth seal is made of nickel alloy, characterized in that the mounting location of rotor blades fourth HPC rotor stages performed according to any of claims. 1, 2, 3, 4, 5, 6, 7, and 8 claims. 11. The method of assembling the place of attachment of the working blades, made in the form of a barrel of rotors of the compressor of low and high pressure, consisting in that the working blades sequentially one after the other are installed through diametrically located notches in the diametrically located sectors of the annular profiled groove of the attachment point of the blades, characterized by that the barrel of the low pressure compressor or the barrel of the high pressure compressor is installed on the table so that its longitudinal axis is vertical and the technological ditch and located below the annular profiled groove, two semicircles of the intermediate spacer are installed diametrically opposite to the annular profiled groove; through the grooves in the sector between the grooves of the annular profiled grooves of the attachment of the blades, establish elastic elements and blades insert locks into the notches, simultaneously with radial forces displace locks into positions where they should be fixed, and fix them with the help of a device installed so that its pushers are located in technological holes intended to extrude one half-ring intermediate spacer from technological grooves, and pivotally connected with the bracket rigidly mounted on the rod of the working cylinder, apply pressure to the cylinder and squeeze out the semi-rings of the intermediate spacer and of the technological groove up to the stop into the opposite wall of the annular profiled groove, the pressure from the cylinder is released and the pushers go out of the technological holes, turn the cylinder together with the bracket 180 ° in the fixture support so that the pushers fit into the technological holes designed to push the second half-ring of the intermediate spacer, and a small pressure is fed into the cylinder and the pushers enter the technological holes, the working pressure is supplied to the cylinder and the second half ring is spaced hydrochloric spacer is extruded in a similar manner from the process groove of the cylinder pressure is vented and the pushers emerge from the technological holes, and in technological hole plugs molded against the stop in an intermediate spacer or the intermediate spacer and the recess portions uprugogisterezisnogo element.

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