RU2630924C1 - Rotor eighth stage impeller of high-pressure compressor (hpc) of turbojet engine (versions), hpc rotor impeller disc, hpc rotor impeller blade, hpc rotor impeller blade ring - Google Patents

Abstract

FIELD: engine devices and pumps.

SUBSTANCE: rotor eighth stage impeller of TJE HPC contains a disc and rotor blades, forming a blade ring. The disc includes a hub with a central hole, curtain, and rim. Each blade consists of a shank, airfoil with a profile, formed by concave pressure side and convex back, and a root shroud on both sides of the feather, forming a bushing surface of the flow part together with the disc rim. In this case, the chord of the lateral edges of wing in the blade root zone forms, with the axis of the rotor in projection, the angle of installation of the wing α_k, increasing along the radial height of the wing with a gradient of wing twist, constituting G_wt=(170.2÷242.9) [deg/m]. The wing blade is designed with the axial twist, variable relative to the rotor axis, that increases radially receding from the rotor axis. The exterior surface of disc rim has the radius which increases in the axial section of HPC towards the working medium flow. The radius R_D Disk from the rotor axis of the HPC to the upper surface of the rim in the mean radial plane of the web is (0.74÷0.96) of the radius R_P/c , the peripheral contour of the flowing part, and with the ratio of the radius R_D to medium height H_av of the profile of the blade R_D/ H_Wed=(8.3÷12.4). The rim of the disk is provided with annular flanges for releasably connecting to the rim flanges of the rims of the seventh and ninth stages of the rotor of the HPC and combining it into the bag with the discs and with the disk of the labyrinth by means of coupling elements.

EFFECT: increasing the efficiency and increasing gas dynamic stability on all operating modes of the compressor when the service life of the rotor of the sixth stage of high-pressure compressor rotor increases without increasing the material consumption.

24 cl, 9 dwg

Description

The group of inventions relates to the field of aircraft engine manufacturing, namely to high-pressure compressors (HPC) of aircraft turbojet engines (turbojet engines).

The impeller of a multi-stage compressor is known, which has a disk with impellers installed on it, including a feather and a shank (Yu.S. Eliseev et al. Theory and design of gas turbine and combined installations. 2nd ed. Moscow. Publishing House of MSTU named after N. .E. Bauman. 2000. p. 621-624).

Known impeller of a multi-stage compressor having a disk with blades mounted on it, including a feather and a shank. The shank of the blade and the groove in the rim of the disk has a trapezoidal profile. The feather is connected to the shank through an intermediate element - the leg. Between the leg and feather, a shelf is made with the formation of a flow part (A.A. Inozemtsev et al. Fundamentals of designing aircraft engines and power plants. Volume 2. Moscow. Mechanical Engineering, 2008, pp. 39-42).

A compressor impeller is known having a disk with rotor blades installed in a groove, including a feather and a shank. The groove of the disk is made with broadening in depth in the cross section of the groove (US 2013/0171343, 07/04/2013, Fig. 1, 2). Similar solutions are known from US 2005/0025622 A1, FIG. 1, US 2009/0246029 A1, FIG. 5, US 2005/0129522 A1, FIG. 1, US 1606029, FIG. 3, 4.

The disadvantages of the known solutions include the lack of development of a system for selecting the set of necessary parameters for the general configuration of the impeller disk, affecting the formation of the configuration and the area of the bore of the flowing part and the placement of blades in the groove of the rim of the disk of the disk, which form the aerodynamic processes of the interaction of the impeller of the compressor rotor with the flow of the working fluid, due to the lack of specification of the ranges of geometric and aerodynamic parameters of the spatial configuration of the disk and the angular anovki blades in the impeller rotor, making it difficult for an optimum combination of increased efficiency values stocks dynamic stability (CDB) of the compressor, as well as providing optimal strength and an increased dynamic resource with minimum material consumption.

The problem solved by the group of inventions, united by a single creative concept, is to develop the impeller of the eighth stage of the high-pressure compressor rotor of the turbojet engine with improved structural and aerodynamic parameters of the spatial configuration of the disk and blades, providing the possibility of optimizing the profile and the area of the passage sections of the engine ducts, sufficient to increase the flow rate of the compressible working fluid - air, the efficiency in the eighth stage of the HPC, the supply of air flow to the next stage of the HPC with an increased supply of GDU in all modes of operation and engine life without increasing material consumption.

The problem is solved in that the impeller blade of the eighth stage as part of the rotor of a multi-stage high-pressure compressor HPC turbojet engine having a body with a flow part, a low pressure turbine (HPH) with a shaft, a high pressure turbine (HPH) and an HPC rotor including a shaft a drum-disk structure with disks and blade crowns, while the impeller rim of the impeller is provided with a groove for installing blades, according to the invention, the blade contains a feather with a convex-concave profile formed by a vogue with a trough and a convex back, conjugated inlet and outlet edges, as well as a shank and a root flange integrally made with a feather, with a conical surface on both sides of the feather, forming a fragment of the sleeve surface of the flowing part of the engine of the eighth stage of the HPC, and the shank of the blade is made with the possibility of installation in the groove of the rim of the disk and has a configuration of the side and supporting surfaces, congruent to the profile of the mating surfaces of the groove with the formation of the castle connection type "ring groove" and providing an angle a SETTING profile pen to the rotor axis in projection on an axial schematic of the rotor plane normal to the axis of the blade having a root section of the pen _to a value α = (32,4 ÷ 46,6) °, and in a peripheral section of the pen value α _n = ( 37.4 ÷ 53.8) °, while the blade feather is made with an axial twist variable relative to the rotor axis, increasing with radial distance from the rotor axis with a pen twist gradient G _zp defined in the range of the projected axial plane

G _s.p. = (α _p -α _k ) / N _sr = (187.6 ÷ 270.1) [deg / m],

where α _to - the angle of installation of the profile of the feather of the scapula, in the root section; α _p - also, in the peripheral section; N _cf - the average height of the feather blades; in addition, the feather of the blade is made variable in width and height of the feather with a thickness defined in cross section as the difference in height of the back and trough relative to the chord connecting the input and output edges of the feather of the blade, while the maximum thickness of the profile of the feather of the blade is made the largest in the root section and decreasing in height pen to the peripheral end with a gradient G _{of standard fuel} equal to

G _u.t = (C _to -C _p ) / N _sr = (2.7 ÷ 3.9) ⋅10 ^-2 [m / m],

where C _to - the maximum thickness of the profile of the feather blade in the root section; C _p - also in the peripheral section; N _cf - the average height of the feather blades.

In this case, the shank of the blade can have a sole with a longitudinal axis located in a conventional plane normal to the axis of the rotor and contains a broadening in depth made in cross section by two reciprocal mirror-symmetric dihedral protrusions, the upper faces of each of which are inclined to the conventional plane of the base of the shank the angle β ₁ = (29 ÷ 40) °, and the lower faces are counter-inclined and each form an angle β ₂ = (48 ÷ 69) ° with the reference plane of the sole of the shank.

The shank can be made with a ratio of the average height H _{cf of the} blade feather profile to the average height of the shank h _{cp of} H _cf / h _cp = (4.6 ÷ 6.3).

The feather of the blade can be made with a convex-concave profile formed by a concave trough of the profile, facing concavity in the direction of rotation of the rotor counterclockwise (view in np - direction of flight), and a convex back of the pen, convex in the direction of rotation of the rotor and in the direction of rotation clockwise.

Alternatively, the feather of the blade can be made with a convex-concave profile formed by a concave trough facing concavity in the direction of rotation of the rotor clockwise (view in np), and a convex back of the pen, convex in the direction of rotation of the rotor and against the direction of rotation clockwise (view by n.p.).

The problem in terms of the blade rim is solved by the fact that the blade rim of the eighth stage impeller as part of the rotor of a multi-stage high-pressure compressor turbojet engine with a housing with a flow part, a high-pressure pump with a shaft, a high-pressure fuel pump and a high-pressure rotor, including a drum-disk design shaft with impeller disks , the rim of which is endowed with a groove for mounting of rotor blades, according to the invention comprises blades evenly spaced around the perimeter of the disc at an angular frequency _l Y = (14,17 ÷ 19,59) [U / rad], wherein each vane blade row the front wheel of the eighth stage of the HPC rotor is made with the configuration and parameters described above, in addition, the ends of the root flange of each blade are made with the possibility of tightly adjoining the counter ends of the adjacent blades of the impeller rim facing them, forming a sleeve surface of the flow part, for which each flange the blades are made oblique with the repetition of the curvature of the inner surface of the engine duct in the zone of the eighth stage of the HPC with an increase in the radius in the direction of flow of the working fluid and the angle ϕ by the clone of the generatrix of the outer surface of the shelf to the axis of the rotor, identical to the generatrix of the outer surface of the rim of the disk and comprising at least 4 °.

The problem in terms of the compressor rotor disk is solved by the fact that the eighth-stage impeller disk as part of the rotor of a multi-stage high-pressure compressor turbofan engine, having a housing with a flow part, a high-pressure pump with a shaft, a high-pressure fuel pump and an HPC rotor, including a drum-disk design shaft with impeller disks provided with blades, comprising a shank, a root shelf and pen according to the invention, the drive is in the form monoelementa comprising a rim, a hub with a central opening and a web, wherein the disk radius R _d from the rotor axis to External Expansion surface of the rim in the central radial plane of the web (0,74 ÷ 0,96) of the radius R _p.ch. the peripheral contour of the flowing part in the indicated plane, - and the rim of the disk is provided with an annular groove along the contour to accommodate the shanks of the working blades in it and is divided by the groove into two asymmetric differently high annular arms with peripheral annular conical shelves with the formation together with the upper surface of the root shelves of the blades of the blades of the sleeve surface of the contour the engine flow part within the axial width of the rim of the disk of the eighth stage of the HPC rotor, while the outer surface of the rim is made with an inclination angle th relative to the axis of the rotor shaft and a radius increasing in the direction of flow of the working fluid in the axial section of the HPC with a gradient of G _R. limited in the range

,

,

where R _max and R _min - the maximum and minimum radii of the generatrix of the upper surface of the disk rim In _rev - the axial width of the disk rim bounded by the interscapular channel; moreover, the front and rear shelves of the rim of the disk of the eighth stage are made with the possibility of detachable connection with the mating shelves of the rim of the disks of the seventh and ninth stages and the formation of the combined annular fragments of the inner contour of the flow path of the HPC with the inclusion of the disk of the eighth stage in the power shell of the drum-disk design of the rotor shaft, and in the area of the detachable joint, sections of the shelves of the indicated disks are made with the possibility of overlapping, in addition, the canvas of the disk of the eighth stage is made with the possibility of power connection in a package with the seventh, ninth and disks with labyrinth disc by the clamping elements.

The radius of the Central hole of the hub R _TSO.s. can be made sufficient to pass the shaft of the theater and optionally component (0.19 ÷ 0.28) from the radius R _{d of the} disk, counting the latter from the axis of the rotor to the outer surface of the rim in the middle radial plane of the web.

The groove of the disk can be equipped with at least one inlet for installing the shanks of the blades and the fixing elements in the groove to fix the position of the blades in the groove.

The disk of the eighth stage can be combined into a package with the seventh, ninth disks and with the labyrinth disk by means of clamping elements such as close-fitting studs and nuts with calibrated tightening torque, for which holes are made in the blade web for coupling studs that are equidistantly spaced relative to the axis of the rotor shaft and conditionally of a circle with an angular frequency defined in the range Y _crepe = (3.18 ÷ 4.46) [u / rad], while the radius of the conditional circle of the location of the centers of these holes is optionally (0.51 ÷ 0.72) of the radius R _d disk in the middle p the adial plane of the blade, in addition, the blade blade is provided with annular flanges on both sides for mounting the interdisk bushings and spacer rings.

The disk blade can be equipped with ventilation air vents to equalize the pressure in the packet region from the seventh to the ninth disk with pressure in other parts of the volume inside the drum-disk shell of the HPC rotor shaft, equidistant radially around the circumference spaced with an angular frequency Y _vent = (3.18 ÷ 5.73) [units / rad].

The groove of the disk rim can be made with double broadening in depth, located respectively in the upper and in the bottom part of the groove and separated by a narrowing formed by two mirror-symmetric mating ring protrusions made with rounded opposed end sections of the profile in the groove cross section located at a distance providing the possibility of supporting the establishment between the shank of the blade, while the lower broadening of the annular groove of the rim of the disk is made with the faces forming the castle config “ring groove” type uration with an angle of mutual inclination of the side faces of (91 ÷ 98) °, and congruent with respect to dominant points of the supporting surfaces to the mating surfaces of the shank of the blade, and the upper groove broadening is made corresponding in configuration, width and axial height difference of the front and back the edges of the groove, the axial inclination of the main part of the area of the upper surface of the root shelf of the scapula extending into the flow part, which in turn is identical to the required slope of the internal contour of the flow part on disk arrangement sowing area eighth stage of the HPC.

The length of the perimeter of the annular groove in the rim of the disk can be sufficient to accommodate the shanks of the blades with an angular frequency of Y _l , defined in the range of values of Y _l = (14.17 ÷ 19.59) [units / rad].

The task in terms of the impeller according to the first embodiment is solved by the fact that the eighth-stage impeller as part of the rotor of a multi-stage high-pressure compressor turbofan engine, having a housing with a flow part, a high-pressure pump with a shaft, a high-pressure fuel pump and an HPC rotor including a drum-and-disk design shaft, according to the invention contains a blade wreath and a disk endowed with an annular groove for installing crown blades, the disk being made in the form of a single element including a hub with a central hole, a blade and a rim, and each blade of the crown contains shank pen formed with a profile formed concave trough and a convex back, and a root shelf tapered surface on both sides of the pen, the radius R _d disk from the axis of the rotor ARCs to conventional conical surface, pine with the rotor shaft and which describes an upper rim surface in the middle radial plane of the web is (0.74 ÷ 0.96) from the radius R _p.h. the peripheral contour of the flowing part in the specified plane, and the radius R _ts.o.s. the central hole of the hub is made sufficient to pass the shaft of the theater and optionally component (0.19 ÷ 0.28) from the radius R _{d of the} disk in the middle radial plane of the disk blade; moreover, the outer surface of the rim is made with an angle of inclination of the generatrix relative to the axis of the rotor shaft and a radius increasing in the direction of movement of the flow of the working fluid in the axial section of the HPC with a gradient of G _R. defined in the range

,

,

where R _max and R _min - the maximum and minimum radii of the generatrix of the upper surface of the disk rim, In _rev - the axial width of the disk rim bounded by the interscapular channel; To ensure the transmission of torque from the theater, the front and rear shelves of the eighth stage disk rim are made with the possibility of detachable connection with the mating shelves of the seventh and ninth stage disks and the formation of the combined annular fragments of the internal contour of the HPC flow path with the inclusion of the eighth stage disk in the drum the disk design of the rotor shaft, in addition, the canvas of the eighth stage disk is made with the possibility of power connection in a package with the seventh, ninth disks and with the disk the labyrinth by means of coupling elements such as tightening studs and nuts with a calibrated tightening torque, for which the disk blade is provided with annular flanges on both sides for installing the interdisk bushings and spacer rings, and the holes for the coupling studs in the disk blade are made equidistant spaced relative to the axis of the rotor and along the circumference with an angular frequency defined in the range Y _crepe = (3.18 ÷ 4.46) [u / rad].

In this case, the disk blade can be equipped with ventilation air passage holes for balancing the pressure in the packet region from the seventh to the ninth disk with pressure in other parts of the volume inside the drum-disk shell of the HPC rotor shaft, equidistant radially around the circumference spaced with an angular frequency Y _vent = (3, 18 ÷ 5.73) [units / rad].

The blades can be evenly spaced around the perimeter of the disk with an angular frequency of Y _l = (14.17 ÷ 19.59) [units / rad], while for radial-angular fixation of the position of the blades, an annular groove is made with contact protrusions, the lower face of each of which is located at an angle to the conditional plane in the bottom part of the groove, identical to the angle of inclination of the counter face of the shank of the blade to the sole of the shank, β ₁ = (29 ÷ 40) °, and from the circumferential displacement in the annular groove of the blade is fixed by at least five locking elements which enes as liner prismatic configuration in cross section, congruent profile of the annular groove, and each endowed with a through threaded hole for the fixing screw.

The feather of the blade can be performed with an axial twist variable with respect to the rotor axis, increasing with radial distance from the rotor axis with a pen twist gradient G _zp defined in the projection onto the conditional axial plane in the range

G _s.p. = (α _p -α _k ) / N _sr = (187.6 ÷ 270.1) [deg / m],

where α _to - the angle of installation of the profile of the feather of the scapula, in the root section; α _p - also, in the peripheral section; H _cf - the average height of the feather blades; in addition, the feather of the blade is made variable in width and height of the feather with a thickness defined in cross section as the difference in height of the back and trough relative to the chord connecting the input and output edges of the feather of the blade, while the maximum thickness of the profile of the feather of the blade is made the largest in the root section and decreasing in height pen to the peripheral end.

The annular shelves of the disk rim can be made protruding beyond the size of the pen of the working blade to a width sufficient for interaction along the working fluid with the blades of the stator guide apparatus.

The task in terms of the impeller according to the second embodiment is solved by the fact that the impeller of the eighth stage as part of the rotor of a multi-stage high-pressure compressor turbofan engine, having a housing with a flow part, a high-pressure pump with a shaft, a high-pressure fuel pump and an HPC rotor including a drum-and-disk design shaft, according to the invention contains a blade wreath and a disk endowed with an annular groove for installing crown blades, the disk being made in the form of a single element including a hub with a central hole, a blade and a rim, and each blade of the crown contains a shank, a feather made with a profile formed by a concave trough and a convex back, and a root shelf with a conical surface on both sides of the feather, while the shank of the blade is configured to fit into the groove of the disc rim and has a configuration of the side and supporting surfaces, congruent to the profile of the mating surfaces a groove with the formation of a lock connection of the "annular groove" type and providing an angle a of the installation of the profile of the pen to the axis of the rotor in the projection onto the conditional axial plane of the rotor normal to the axis of the pen blade with the cross-section of the pen, the value of α _k = (32.4 ÷ 46.6) °, and in the peripheral section of the pen, the value of α _p = (37.4 ÷ 53.8) °, while the feather of the blade is made with a variable axial twist relative to the axis of the rotor growing with radial distance from the axis of the rotor with a gradient of twist of the pen G _s.p. defined in the projection onto the conditional axial plane in the range

G _s.p. = (α _p -α _k ) / H _cf = (187.6 ÷ 270.1) [deg / m],

where α _to - the angle of installation of the profile of the feather of the scapula, in the root section; α _p - also, in the peripheral section; H _cf - the average height of the feather blades; while the blades are uniformly spaced around the perimeter of the disk with an angular frequency of Y _l = (14.17 ÷ 19.59) [units / rad], and the rim of the disk is divided by an annular groove into two asymmetric differently high annular arms, the peripheral sections of the annular shelves of which together with the outer the surface of the root shelves of the blades form the sleeve surface of the contour of the engine duct within the axial length of the rim of the disk of the eighth stage of the HPC rotor with an angle ϕ of inclination of the outer surface of the rim to the axis of the rotor identical to the outer surface of the root molasses; To ensure the transmission of torque from the theater, the front and rear shelves of the eighth stage disk rim are made with the possibility of detachable connection with the mating shelves of the seventh and ninth stage disks and the formation of the combined annular fragments of the internal contour of the HPC flow path with the inclusion of the eighth stage disk in the drum the disk design of the rotor shaft, in addition, the canvas of the eighth stage disk is made with the possibility of power connection in a package with the seventh, ninth disks and with the disk the labyrinth by means of clamping elements, in addition, the impeller is made with a ratio of the radius R _{d of the} disk from the axis of the HPC rotor shaft to the conditional conical surface, pine with the rotor shaft and describing the upper surface of the disk rim in the middle radial plane of the disk web to the average height H _{cf of the} blade feather profile comprising R _d / H _cf = (8.3 ÷ 12.4).

In addition, the disk can be made with a radius R _d from the axis of the HPC rotor to the conditional conical surface describing the upper surface of the rim in the middle radial plane of the web is (0.74 ÷ 0.96) from the radius R _P.s. the peripheral contour of the flowing part in the specified plane.

In this case, the eighth-stage disk can be combined into a package with the seventh, ninth disks and with the labyrinth disk by means of clamping elements such as close-fitting studs and nuts with calibrated tightening torque, for which holes are made in the blade web for coupling studs that are equidistantly spaced relative to the axis of the rotor shaft and along a conditional circle with an angular frequency defined in the range Y _crepe = (3.18 ÷ 4.46) [u / rad], while the radius of the conditional circle of the centers of these holes is optionally (0.51 ÷ 0.72) of the radius R _d disk Independent user radial plane of the web, in addition equipped with a disk blade on both sides of an annular shoulder for installation interdisk bushings and spacer rings.

For radial-angular fixation of the position of the blades, an annular groove can be made with contact protrusions, the lower face of each of which is located at an angle to the reference plane in the bottom part of the groove, identical to the angle of inclination of the mating face of the shank of the blade to the sole of the shank, which is β ₁ = (29 ÷ 40) °, and from the circumferential displacement in the annular groove of the blade, the blades are fixed by at least five locking elements, which are made in the form of a prismatic insert with a cross-sectional configuration congruent to the profile annular groove, and each endowed with a through threaded hole for the fixing screw.

The disk blade can be equipped with ventilation air vents to equalize the pressure in the packet region from the seventh to the ninth disk with pressure in other parts of the volume inside the drum-disk shell of the HPC rotor shaft, equidistant radially around the circumference spaced with an angular frequency Y _vent = (3.18 ÷ 5.73) [units / rad].

The annular shelves of the disk rim can be made protruding beyond the size of the pen of the working blade to a width sufficient to interact along the working fluid with the blades of the stator guide apparatus, and the sections of the ring shelves in the area of the split joint with the seventh and ninth stage disks are overlapable.

The technical result of the invention, achieved by the given set of essential features of the impeller of the eighth stage of the rotor of the high-pressure turbojet engine, including the disk and rotor blades, together making up the blade rim of the impeller, consists in increasing the efficiency and expanding the range of regimes of gas-dynamic stability of the compressor by 2.5% with increasing resource impeller 2 times.

The invention is illustrated by drawings, where:

in FIG. 1 shows the impeller of the eighth stage of the rotor KVD TRD, a longitudinal section;

in FIG. 2 - a fragment of the rim of the disk of the impeller with blades, side view;

in FIG. 3 - fragment of the blade rim of the impeller, top view;

in FIG. 4 - impeller blade, top view;

in FIG. 5 - feather blades of the impeller, a cross section;

in FIG. 6 - shank of the blade of the impeller, front view;

in FIG. 7 - the rim of the disk of the impeller, a longitudinal section;

in FIG. 8 - a fragment of the rim of the disk with the inlet for installation in the groove of the shanks of the blades, a longitudinal section;

in FIG. 9 - a fragment of the rim of the disk with a locking element for fixing the position of the blades in the groove, a longitudinal section.

A multi-stage high-pressure compressor of a turbojet engine includes a housing with a flowing part, a low-pressure turbine with a shaft, a high-pressure turbine and an HPC rotor, including a drum-disk design shaft with a front support and with a tubular part of the rotor shaft on the other side.

In the group of inventions, united by a single creative concept, the impeller of the eighth stage of the compressor rotor (Fig. 1) contains a disk 1, endowed with a groove 2 for installing the rotor blades 3, which together comprise the blade rim of the impeller.

The blades of the blade rim contain each complete shank 4, feather 5 and root shelf 6 with a conical surface on both sides of feather 5. Disc 1 of the impeller is made in the form of a single element including a hub 7 with a central hole 8, web 9 and rim 10, endowed with a groove 2 for installing the shanks of 4 blades. The blades 3 are evenly spaced around the perimeter of the disk 1 with an angular frequency of Y _l = (14.17 ÷ 19.59) [units / rad]. The blade feather 5 is made with a convex-concave profile formed by a concave trough 11 and a convex back 12, conjugated by the input and output edges 13 and 14.

The shank of the 4 blades is made for installation in the groove 2 of the rim 10 of the disk 1. The shank of the 4 blades is made with the configuration of the side and supporting surfaces, congruent to the profile of the mating surfaces of the groove 2 with the formation of the castle connection type "annular groove" and providing the angle and the installation profile of the pen 5 to the axis 15 of the rotor in the projection onto the conditional axial plane of the rotor normal to the axis of the feather of the blade with α _k = (32.4 ÷ 46.6) ° in the root section of the pen, and α _p = (37.4 ÷ in the peripheral section of the pen 53.8) °.

The blade feather 5 (Fig. 4) is made with an axial twist variable relative to the axis of the rotor 15, increasing with radial distance from the rotor axis with the gradient of the twist of the pen G _zp defined in the projection onto the conditional axial plane in the range

G _s.p. = (α _p -α _k ) / H _cf = (187.6 ÷ 270.1) [deg / m],

where α _to - the angle of installation of the profile of the feather of the scapula, in the root section; α _p - also, in the peripheral section; H _cf - the average height of the feather blades.

The blade feather 5 (FIG. 5) is made variable in width and height of the feather thickness, defined in cross section as the difference between the heights of the back 12 and the trough 11 relative to the chord 16 connecting the input and output edges 13 and 14 of the blade feather. The maximum thickness of the blade profile of the pen 5 is made greatest at the root section and decreasing in height to the peripheral end of the pen 17 with a gradient G _{of fuel equivalent} equal to

G _ut = (C _to -C _p ) / N _cf = (2.7 ÷ 3.9) ⋅10 ^-2 [m / m],

where C _to - the maximum thickness of the profile of the feather of the scapula in the root section; With _p - also in the peripheral section; N _cf - the average height of the feather blades.

The shank 4 of the blade (Fig. 6) has a sole 18 with a longitudinal axis located in a conventional plane normal to the axis 15 of the rotor, and contains a broadening in depth, made in cross section by two reciprocal mirror-symmetric dihedral protrusions. The upper faces 19 of each protrusion are inclined to the conditional plane of the sole of the shank 18 at an angle β ₁ = (29 ÷ 40) °. The lower faces 20 are made obliquely inclined and each form an angle β ₂ = (48 ÷ 69) ° with the conditional plane of the sole 18 of the shank.

The ends 21 of the root shelf 6 of each blade (Fig. 3) are made with the possibility of tight adjacency to facing the response ends of the shelf of adjacent blades of the rim of the impeller, forming a sleeve surface of the flow part. For this, the root shelf 6 of the blade 3 is made inclined with the repetition of the curvature of the inner surface of the engine duct in the eighth stage of the HPC with an increase in the radius in the direction of flow of the working fluid and the angle ϕ of inclination of the outer surface of the shelf 6 to the axis of the rotor, which is identical to the generatrix of the outer surface of the rim 10 of the disk and components of at least ϕ≥4 °.

The blade 3 is made with a ratio of the average height H _{cf of the} profile of the feather 5 of the scapula to the average height h _{cf of the} shank 4 constituting H _cf / h _cp = (4.6 ÷ 6.3).

The feather 5 of the blade is made with a convex-concave profile formed by a concave trough 11 of the profile, facing concavity in the direction of rotation of the rotor counterclockwise (view in np - direction of flight), and a convex back of the pen 12, convex in the direction of rotation of the rotor and clockwise.

Variant feather blade is made with a convex-concave profile formed by a concave trough facing concavity in the direction of rotation of the rotor clockwise (np view), and a convex back of the pen convex in side against rotation of the rotor and counterclockwise rotation (view by n.p.).

The disk 1 of the impeller of the eighth step is made with a radius R _d from the axis 15 of the rotor of the HPC to the conditional conical surface, pine with the shaft of the rotor and describing the upper surface of the rim 10 in the middle radial plane of the blade 9, comprising (0.74 ÷ 0.96) from the radius R _pp the peripheral contour of the flowing part in the specified plane. Radius R _ts.o.s. the central hole of the hub is sufficient to accommodate the front support of the HPC and optionally component (0.19 ÷ 0.28) from the radius R _{d of the} disk from the axis 15 of the HPC rotor to the upper surface of the rim 10 in the middle radial plane of the blade web 9.

To accommodate the shanks of the blades 3, the rim 10 of the disk 1 is provided with an annular groove 2 along the contour. The rim 10 is divided by a groove 2 into two asymmetric uneven annular arms 22, 23 with peripheral annular conical shelves 24 and 25, respectively, with the formation of 6 blades 3 together with the upper surface of the root shelves the sleeve surface of the flow path of the engine within the axial width of the rim of the disk of the eighth stage of the HPC rotor.

The outer surface of the rim 10 is made with an angle of inclination of the generatrix 26 relative to the axis 15 of the rotor and a radius increasing in the direction of flow of the working fluid in the axial section of the HPC with a gradient of G _{R rev.} defined in the range

,

,

where R _max and R _min are the maximum and minimum radii of the generatrix of the upper surface of the disk rim, B _rev is the axial width of the disk rim bounded by the interscapular channel.

The impeller is made with a ratio of the radius R _{d of the} disk 1 from the axis 15 of the HPC rotor to the conditional conical surface describing the upper surface of the rim 10 of the disk in the middle radial plane of the blade web 9 of the disk to the average height H _{cf of} the feather profile 5 of the blade, which is R _d / H _cp = (8.3 ÷ 12.4).

The groove 2 of the rim 10 of the disk (Fig. 7) is made with double broadening in depth, located respectively in the upper and in the bottom parts 27 and 28 of the groove and separated by a narrowing, which is formed by two mirror-symmetric mating ring protrusions 29. The protrusions 29 are made with rounded opposed end faces sections of the profile in the cross section of the groove located at a distance providing the possibility of supporting the establishment between them of the shank 4 of the scapula. The broadening in the bottom bottom part 28 of the groove 2 of the rim of the disk is made with faces 30 with the formation of the castle configuration of the type of "ring groove" with an angle of mutual inclination of the side faces 30 of (91 ÷ 98) °, and congruent with respect to the dominant points of the supporting surfaces to the response faces 19 and 20 shanks 4 shovels. The broadening in the upper part 27 of the groove 2 is made corresponding to the configuration, width and axial height difference of the front and rear edges of the groove 2, to the axial inclination of the main part of the upper surface area of the root shelf 6 of the blade, which extends into the flow part, which in turn is identical to the required inclination of the inner the contour of the flowing part on the axial portion of the disk of the eighth stage of the HPC.

The groove 2 of the rim 10 of the disk 1 is equipped with at least one inlet 31 for installation in the groove of the shanks 4 of the blades (Fig. 8) and the fixing elements 32 for fixing the position of the blades in the groove. For radial-angular fixation of the position of the blades 3 in the rim 10 of the disk, the annular groove 2 is made with contact protrusions 29 with the possibility of holding the blades from moving in the radial direction from the action of centrifugal forces. The lower edge of the protrusion 29 is located at an angle to the conventional plane of the bottom of the groove, identical to the angle β _{1 of the} inclination of the counter face 20 of the shank 4 of the blade to its sole 18. From the displacement in the circumferential direction (Fig. 9) in the annular groove 2 of the blade is fixed by at least five the locking elements 32. The locking elements 32 are made in the form of a prismatic insert with a configuration in cross section, congruent to the profile of the annular groove 2, and each endowed with a through threaded hole for the fixing screw 33.

To ensure the transmission of torque from the theater, the rim 10 of the disk 1 is made with the possibility of detachable connection of the front and rear shelves 24 and 25 with the mating shelves of the rim of the drives of the seventh and ninth steps, respectively (not shown in the drawings) and the formation of the combined annular fragments of the internal circuit of the flow passage of the HPC with the inclusion of the disk of the eighth stage in the power shell of the drum-disk design of the rotor shaft. In the area of the detachable joint, sections of the shelves of the indicated disks are lapped.

Disk 1 of the eighth stage is combined in a package with the seventh, ninth disks and with the labyrinth disk by means of clamping elements (not shown in the drawings) such as tightening studs and nuts with a calibrated tightening torque. Why in the blade web 9 holes 34 are made under the tie rods, equidistantly spaced relative to the axis of the rotor and along a conditional circle with an angular frequency defined in the _crepe range Y = (3.18 ÷ 4.46) [u / rad]. The radius R _{article of the} circumference of the location of the centers of these holes 34 is optionally (0.51 ÷ 0.72) from the radius R _{d of the} disk in the middle radial plane of the web. Cloth 9 of the disk is equipped on both sides with annular flanges 35 for installing interdisk bushings and spacer rings (not shown in the drawings).

Cloth 9 of the disk is equipped with ventilation air passage openings 36 for balancing the pressure in the package region from the seventh to ninth disk with pressure in other parts of the volume inside the drum-disk shell of the HPC rotor shaft, equidistant radially around the circumference spaced with an angular frequency Y _vent = (3.18 ÷ 5.73) [units / rad].

The annular shelves 24, 25 of the rim 10 of the disk are made protruding beyond the size of the pen 5 of the working blades 3 to a width sufficient for interaction along the working fluid with the blades of the stator guide vane.

An example implementation of the invention.

The impeller of the eighth stage of the HPC engine consists of a disk 1 and rotor blades 3 mounted on it. Disk 1 is made by die-forging from a forging in the form of a single element, which includes a complete massive hub 7, web 9 and rim 10.

The manufactured disk has the following geometric parameters: overall width of the hub - 24 mm; diameter of the central hole of the hub - 145 mm; web thickness - 3.5 mm; the width of the rim bounded by the interscapular channel is 14 mm; minimum and maximum diameters of the outer surface of the rim of the disk - 548 mm and 551 mm, respectively; the angle ϕ of the inclination of the outer surface of the rim of the disk is 5 °.

The blade 3 of the impeller of the eighth stage of the rotor KVD TRD is stage-by-stage made from the bar of an aircraft alloy. At the first stage, a fragment of the rod of the required length is cut, from which the blade is prepared by electric upsetting, followed by machining, with local thickenings in the areas of the root shelf 6. In the next step, the workpiece is subjected to general heating in an electric furnace to the state of thermoplasticity and hot stamping is performed using a stamp, consisting of two reciprocal profiled half-matrices. The working surface of one of the die semi-matrices includes a section whose shape is made of the mating spatial surface of the back 12 of the pen 5 of the scapula. The working surface of the other half-matrix of the stamp includes a section whose shape is made of the mating spatial surface of the trough 11 of the pen 5 of the scapula. After that, the blade is subjected to machining, including grinding the flap milling, pulling the shank 4.

The refinement of the streamlined surfaces of the profiles of the pen 5 and the root shelf 6 is performed by milling with subsequent polishing. The contact ends 21 of the root shelves 6 are strengthened by applying a high-strength layer to them.

The blade made in this way consists of a single pen 5 with a shank 4 and a root shelf 6, made as a segment of the assembled ring of the blade ring of the impeller of the eighth stage of the turbine engine compressor rotor.

The profile of the pen 9 of the scapula has the following geometric parameters:

- in the root section, the profile of the blade feather is made with a maximum profile thickness C _max = 1.45 mm; the length of the chord 16 connecting the input and output edges 13 and 14 of the blade pen - 16.5 mm; the angle α _{to the} installation profile of the pen to the axis of the rotor is 39.6 °;

- in the peripheral section, the profile of the feather blade is made with a maximum thickness of the profile With _max = 0.59 mm; the length of the chord of the pen is 16.5 mm; the angle α _p setting the profile of the pen is 46 °;

- the average height H _{cp of the} profile of the pen is 24.8 mm;

- the average height h _{cp of the} shank is 5 mm

The root shelf 6 of the blade is made with a circumferential width of 16 mm with contact ends 21 made parallel to the axis of the rotor and the angle ϕ of inclination of the generatrix of the outer surface of the shelf 6 to the axis 15 of the rotor ϕ = 5 °.

On the outside of the rim 10 is performed by pulling an annular groove 2 for mounting the blades. The groove is made with two inlet holes 31. The blades 3 are kept from moving in the radial direction from the action of centrifugal forces using contact tabs 29. The blades 3 are kept in the disk 1 from moving in the circumferential direction 2 with the help of the locking elements 32. The blades 3 are mated at the return ends 21 adjacent root shelves.

During the operation of the turbojet engine, the eighth-stage impeller disk 1 is rotated by transmitting torque from the turbine engine through the drum-disk design of the compressor rotor shaft with the blades 3 of the impeller turned on. As a result, air flow is forced into the compressor. On the concave surface in the form of the trough 11 of the feather 5 of the blade 3, an increased pressure zone is created, and on the convex surface forming the back 12 of the feather 5, a reduced pressure zone is created, which enhances the formation of a directed air flow. Rotating blades 3 of the rotor impeller transmit energy to the air flow, directing the compressible flow to the stator vanes of the eighth stage, and after alignment in the last, the flow enters the last stage of the compressor. At the same time, the disk 1 accepts centrifugal loads and, through the ring shelves 24 and 25 of the rim 10, transfers radial and axial loads to the rotor shaft supports.

The technical result of the present invention is achieved by a combination of the design solutions and geometric parameters of the main elements of the disk of the impeller of the eighth stage of the compressor rotor, namely, the radial parameters of the disk, the geometric configuration of the rim 10, the combination of the tapering web 9 and the axial width of the hub 7, compensating for the weakening of the web 9 of the disk by the central hole 8, which leads to a decrease in material consumption and increase in maximum allowable forces in the disk elements . The diameter of the hole 8 in the hub 7 is accepted sufficient for the passage of the shaft of the theater and repair and technological access to the connections of the compressor shaft. On the outer side of the disk rim 10, an annular groove 2 is held for fixing the blades, while providing the possibility of installing the shank and feather of the blade at an angle that creates the greatest pressure difference at the inlet and outlet of the working fluid flow from the impeller of the eighth stage of the compressor rotor and the most favorable conditions are created works that increase the supply of gas turbine, efficiency and resource with minimal material consumption. Exceeding the stated range of the angle α will lead to a significant limitation of the GDU stock during multi-mode operation of the compressor, a decrease in the efficiency of the rotor stage and an increase in the risk of an accidentally dangerous airflow disruption from the blades 3 of the impeller 3 of the 8th impeller of the eighth stage of the compressor rotor with the resulting loss of the GDU . With an increase in the angle α, the voltage in the blades unreasonably increases at all compressor operating modes, which leads to a decrease in the resource of the disk-blade-wreath system, an increase in the material consumption of the blades installed on the disk, and, ultimately, to a heavier compressor and a decrease in engine operating efficiency. The technical result of the invention is provided by saturating the blade rim with the number of blades arranged with an angular frequency taken from the range found in the invention. When the number of blades decreases below the lower limit of the specified range Y _l <14.17 [units / rad], the lag of the flow from the rotation of the blade rim increases and the risk of loss of the HLD in the indicated compressor stage increases. Exceeding the upper limit of the specified range Y _l > 19.59 [units / rad] and a corresponding increase in the number of blades in the scapular blade formed on the eighth stage disk leads to an unjustified deterioration in efficiency and the risk of premature blocking of the working fluid flow with the scapular crown. In addition, the claimed geometry of the groove provides increased concentration under the action of operational loads and increases the resource of the impeller.

Similar processes take place with obtaining a positive result when observing and negative when going beyond the boundaries of the gradient range found in the group of inventions G _zp = (187.6 ÷ 270.1) [deg / m] along the height H _{cf of the} pen 5 of the scapula. When performing a three-dimensional profile of the blade pen with gradient values G _zp <187.6 [deg / m], the range of the GDU of the compressor operation is significantly limited, the efficiency of the stage decreases and the risk of an accidentally dangerous stall of the air flow from the convex back 12 of feather 5 of the blade with the resulting loss of GDU. An increase in the ratio of the difference in the angles of installation of the chord 16 of the pen 5 along the height of the scapula to the values of the gradient G _zp exceeding the upper limit leads to an unacceptable decrease in the opening angle of the peripheral section of the pen 9 of the scapula, which in turn leads to a decrease in efficiency and a negative decrease in the range of the compressor GDU and unacceptable mismatch of the eighth stage of the rotor with the previous and subsequent stages of the compressor.

The technical result increasing the impeller resource twice achieved under condition the thickness difference ratio to the average height of the blade 5, Feather received within found in invention _{reference fuel} specified gradient G value range = (2.7 ÷ 3.9) ⋅10 ^-2 [m / m] due to the provision of the required static and dynamic stiffness with optimal material consumption of the blade profile of the blade. When the gradient values G _{reference fuel} <2.7⋅10 ^-2 [m / m] an excessive increase in material consumption occurs due to the increase in the thickness of the peripheral part of the blade feather unjustified by real load combinations, which leads to an overestimation of the compressor mass and a decrease in engine efficiency. When the gradient values G _{reference fuel} > 3.9⋅10 ^-2 [m / m] the required increase in blade life is not achieved due to a decrease in dynamic strength during operation of the compressor due to an unjustified increase in the parameters of bending vibrations of the pen profile with an unacceptable decrease in the maximum thickness of the profile in the most loaded peripheral part of the length of the pen shoulder blades.

The technical result of the group of inventions is also achieved when implementing the invention with the claimed range of ratios (R _d / R _pk ) and (R _d / H _cf ), because a decrease in the values of these relations will lead to an unjustified decrease in the radius of the disk, an unaccounted increase in the radial height of the blades, which as a result will violate the inlet and outlet aerodynamic parameters of the design of the impeller and the flow of the working fluid — air, and will also worsen gas-dynamic stability during transient engine operation. An increase in the values of these relations will lead to an aerodynamically unacceptable decrease in the area of the flow passage of the engine in the zone of the eighth stage of the turbojet compressor, which will violate the required dynamic balance of the flow of the working fluid and will require redesigning the geometric parameters of the flow of the subsequent stages of the HPC. In addition, a decrease in the gradient G _{R. about} below the declared value will lead to an unacceptable negatively small increase in the radius of the disk of the eighth stage and, accordingly, will not provide the required decrease in the flow section in the axial section of the width of the rim of the disk, which will not allow to obtain the necessary increase in pressure of the working fluid, which should be obtained in the zone of the eighth stage of the HPC turbojet engine to achieve a technical result in the implementation of the invention.

Thus, by improving the design and aerodynamic parameters of the eighth stage impeller, an increase in efficiency and an expansion of the range of gas-dynamic stability modes of the engine compressor are achieved without increasing the material consumption.

Claims (36)

1. The blade of the impeller of the eighth stage, having a disk whose rim is endowed with a groove, and a blade rim, as part of the rotor of a multi-stage high pressure compressor (HPC) of a turbojet engine (turbojet engine), comprising a housing with a flow part, a shaft of the HPC rotor and a high pressure turbine ( TVD), characterized in that the blade contains a feather with a convex-concave profile formed by a concave trough and a convex back, conjugated by the input and output edges, as well as a shank and root shelf made in one piece with the feather the surface on both sides of the pen, forming a fragment of the sleeve surface of the flowing part of the engine of the eighth stage of the HPC, and the shank of the blade is made with the possibility of installation in the groove of the rim of the disk and has the configuration of the side and supporting surfaces, congruent to the profile of the mating surfaces of the groove with the formation of a lock connection type "ring groove "And ensuring the angle α of the installation of the profile of the pen to the axis of the rotor in the projection onto the conditional axial plane of the rotor, normal to the axis of the pen blade, having in the root section of the pen the value α _к = (32.4 ÷ 46.6) °, and in the peripheral section of the pen, the value α _п = (37.4 ÷ 53.8) °, while the feather of the blade is made with a variable axial twist relative to the rotor axis, increasing with radial distance from the axis of the rotor with a pen twist gradient G _zp defined in the projection onto the conditional axial plane in the range G _s.p. = (α _p -α _k ) / N _sr = (187.6 ÷ 270.1) [deg / m], where α _to - the angle of installation of the profile of the feather of the scapula, in the root section; α _p - also, in the peripheral section; N _cf - the average height of the feather blades; in addition, the feather of the blade is made variable in width and height of the feather with a thickness defined in cross section as the difference in height of the back and trough relative to the chord connecting the input and output edges of the feather of the blade, while the maximum thickness of the profile of the feather of the blade is made the largest in the root section and decreases along the height of the peripheral end of the pen with a gradient G _{of standard fuel} equal to G _ut = (C _to -C _p ) / N _cf = (2.7 ÷ 3.9) ⋅10 ^-2 [m / m], where C _to - the maximum thickness of the profile of the feather of the scapula in the root section; With _p - also in the peripheral section; N _cf - the average height of the feather blades. 2. The blade of the impeller of the eighth stage of the rotor of the HPC according to claim 1, characterized in that the shank of the blade has a sole with a longitudinal axis located in a conventional plane normal to the axis of the rotor and contains a broadening in depth made in cross section by two mirror-symmetrical reciprocal two-sided protrusions, the upper faces of each of which are inclined to the conditional plane of the base of the shank by an angle β ₁ = (29 ÷ 40) °, and the lower faces are made counter-inclined and form each angle with the conditional plane of the sole of the shank, angle β ₂ = (48 ÷ 69 ) °. 3. The blade of the impeller of the eighth stage of the HPC rotor according to claim 1, characterized in that the shank is made with a ratio of the average height H _{cf of the} blade feather profile to the average height of the shank h _cp , comprising H _cp / h _cp = (4.6 ÷ 6, 3). 4. The impeller blade of the eighth stage of the HPC rotor according to claim 1, characterized in that the blade feather is made with a convex-concave profile formed by a concave trough of the profile, facing concavity in the direction of rotation of the rotor counterclockwise (view in n.p. - direction flight), and the convex back of the pen, convex to the side against the rotation of the rotor and in the direction of rotation of the clockwise. 5. The impeller blade of the eighth stage of the HPC rotor according to claim 1, characterized in that the feather of the blade is made with a convex-concave profile formed by a concave trough facing the concavity in the direction of rotation of the rotor clockwise (np view), and the convex back of the pen, convex to the side against the rotation of the rotor and against the direction of rotation of the clockwise direction (view in np). 6. The scapular crown of the eighth-stage impeller, having a disk, the rim of which is endowed with a groove for installing the rotor blades, as a part of a multistage high-pressure turbine engine rotor, comprising a housing with a flow part, a rotor shaft and high-pressure turbine rotor, characterized in that it contains blades uniformly spaced along the perimeter of the disk with an angular frequency of Y = (14.17 ÷ 19.59) [units / rad], while each blade of the blade rim of the impeller of the eighth stage of the HPC rotor is made according to any one of paragraphs. 1-5, in addition, the ends of the root flange of each blade are made with the possibility of tightly adjoining the counter ends of the adjacent blade blades of the impeller rim facing them, forming a sleeve surface of the flowing part, for which the shelf of each blade is made inclined with the curvature of the inner surface of the flowing part engine in the zone of the eighth stage of HPC with increasing radius in the direction of flow of the working fluid and the angle ϕ of inclination of the generatrix of the outer surface of the shelf to the axis of the rotor, identical to the generatrix of the outer surface ty rim of a disk and components not less than 4 °. 7. The disk of the impeller of the eighth stage as part of the rotor of a multi-stage high pressure compressor (HPC) of a turbojet engine (turbojet engine) having a housing with a flow part, a low pressure turbine (HPH) with a shaft, a high pressure turbine (HPH) and a rotor including a shaft with front and rear supports and disks with rotor blades having a shank, a root shelf and a feather, characterized in that the disk is made in the form of a single element including a rim, a hub with a central hole and a web, with the radius of the disk R _d from the axis of the rotor to the outside the rim surface of the rim in the middle radial plane of the web is (0.74 ÷ 0.96) from the radius R _{p.h of the} peripheral contour of the flow part in the specified plane, and the rim of the disk is provided with an annular groove along the contour to accommodate the shanks of the working blades in it and is divided by a groove on two asymmetric differently high annular shoulders with peripheral annular conical shelves with the formation together with the upper surface of the root shelves of the blades of the sleeve surface of the contour of the engine duct within the axial width of the rim of the disk the fifth stage of the HPC rotor, while the outer surface of the rim is made with an angle of inclination of the generatrix relative to the axis of the rotor shaft and a radius increasing in the direction of flow of the working fluid in the axial section of the HPC with a gradient of _R.R. defined in the range

where R _max and R _min - the maximum and minimum radii of the generatrix of the upper surface of the disk rim, In _rev - the axial width of the disk rim bounded by the interscapular channel; moreover, the front and rear shelves of the rim of the disk of the eighth stage are made with the possibility of detachable connection with the mating shelves of the rim of the disks of the seventh and ninth stages and the formation of the combined annular fragments of the inner contour of the flow path of the HPC with the inclusion of the disk of the eighth stage in the power shell of the drum-disk design of the rotor shaft, and in the area of the detachable joint, sections of the shelves of the indicated disks are made with the possibility of overlapping, in addition, the canvas of the disk of the eighth stage is made with the possibility of th power connection in a package with the seventh, ninth disks and with the labyrinth disk through the clamping elements. 8. The impeller disk of the eighth stage of the HPC rotor according to claim 7, characterized in that the radius of the central hole of the hub R _t.o.s. made sufficient to pass the shaft of the theater and optionally component (0.19 ÷ 0.28) from the radius R _{d of the} disk, counting the latter from the axis of the rotor to the outer surface of the rim in the middle radial plane of the web. 9. The impeller disk of the eighth stage of the HPC rotor according to claim 7, characterized in that the groove of the disk is provided with at least one inlet hole for installing the shanks of the blades and fixing elements in the groove to fix the position of the blades in the groove. 10. The impeller disk of the eighth stage of the HPC rotor according to claim 7, characterized in that the disk of the eighth stage is combined into a package with the seventh, ninth disks and the labyrinth disk by means of coupling elements such as tightening studs and nuts with calibrated tightening torque, for which purpose in the canvas of the disk, holes for the tie rods are made, equidistantly spaced relative to the axis of the rotor shaft and along a conditional circle with an angular frequency defined in the range Y _crepe = (3.18 ÷ 4.46) [u / rad], while the radius of the conditional circle of the location of the centers of these about Verstov alternatively with amounts (0,51 ÷ 0,72) _d from the radius R disc in the middle radial plane of the web, moreover, the web drive is provided on both sides of an annular bead for mounting interdisk bushings and spacer rings. 11. The impeller disk of the eighth stage of the HPC rotor according to claim 7, characterized in that the disk blade is provided with ventilation air bypass holes for balancing pressure in the packet region from the seventh to ninth disk with pressure in other parts of the volume inside the drum-disk shell of the shaft of the HPC rotor, equidistant radially circumferentially spaced with an angular frequency Y _vent = (3.18 ÷ 5.73) [units / rad]. 12. The impeller disk of the eighth stage of the HPC rotor according to claim 7, characterized in that the groove of the rim of the disk is made with double broadening in depth, located respectively in the upper and in the bottom part of the groove and divided by a narrowing formed by two mirror-symmetric mating ring protrusions made with rounded opposite end sections of the profile in the cross section of the groove located at a distance providing the possibility of supporting the shank of the blade between them, while the lower broadening is annular about the groove of the rim of the disk is made with faces that form a locking configuration of the "annular groove" type with an angle of mutual inclination of the side faces of (91 ÷ 98) °, and congruent with respect to the dominant points of the supporting surfaces to the mating surfaces of the blade root, and the upper groove broadening is made corresponding to configuration, width and axial height difference of the front and back edges of the groove, axial inclination of the main part of the upper surface area of the root shelf of the scapula, which extends into the flow part, which in turn is made ideally the required slope of the internal contour of the flow part on the axial portion of the disk of the eighth stage of the HPC. 13. The impeller disk of the eighth stage of the HPC rotor according to claim 7, characterized in that the circumference of the annular groove in the rim of the disk is sufficient to accommodate the shanks of the blades with an angular frequency of Y _l , defined in the range of values of Y _l = (14.17 ÷ 19.59) [units / rad]. 14. The impeller of the eighth stage as part of the rotor of a multi-stage high-pressure compressor turbofan engine, having a housing with a flowing part, a low-pressure turbine of the high-pressure turbine with a shaft, a high-pressure turbine and an HPC rotor, including a drum-disk design shaft, characterized in that it contains a blade ring and a disk, endowed with an annular groove for installing the crown blades, and the disk is made in the form of a single element including a hub with a central hole, the blade and the rim, and the crown blades contain each shank, a feather made with a profile, images nnym concave trough and a convex back, and a root shelf tapered surface on both sides of the pen, the radius R _d disk rotor axis ARCs to conventional conical surface coaxial with the rotor shaft and which describes the upper rim surface of the middle radial plane of the web is ( 0,74 ÷ 0,96) of the radius R _p.ch. the peripheral contour of the flowing part in the specified plane, and the radius R _ts.o.s. the central hole of the hub is made sufficient to pass the shaft of the theater and optionally component (0.19 ÷ 0.28) from the radius R _{d of the} disk in the middle radial plane of the disk blade; moreover, the outer surface of the rim is made with an angle of inclination of the generatrix relative to the axis of the rotor shaft and a radius increasing in the direction of movement of the flow of the working fluid in the axial section of the HPC with a gradient of G _R. defined in the range

where R _max and R _min - the maximum and minimum radii of the generatrix of the upper surface of the disk rim, In _rev - the axial width of the disk rim bounded by the interscapular channel; To ensure the transmission of torque from the theater, the front and rear shelves of the eighth stage disk rim are made with the possibility of detachable connection with the mating shelves of the seventh and ninth stage disks and the formation of the combined annular fragments of the internal contour of the HPC flow path with the inclusion of the eighth stage disk in the drum the disk design of the rotor shaft, in addition, the blade of the eighth stage is made with the possibility of power connection in a package with the seventh, ninth disks and disco the labyrinth by means of coupling elements such as tightening studs and nuts with a calibrated tightening torque, for which the disk blade is provided with annular flanges on both sides for installing the interdisk bushings and spacer rings, and the holes for the coupling studs in the disk blade are made equidistant spaced relative to the axis of the rotor and along the circumference with an angular frequency defined in the range Y _crepe = (3.18 ÷ 4.46) [u / rad]. 15. The impeller of the eighth stage of the HPC rotor according to claim 14, characterized in that the disk blade is provided with ventilation air bypass holes for balancing the pressure in the packet region from the seventh to the ninth disk with pressure in other parts of the volume inside the drum-disk shell of the shaft of the HPC rotor, equidistantly radially around the circumference spaced with an angular frequency Y _vent = (3.18 ÷ 5.73) [units / rad]. 16. The impeller of the eighth stage of the HPC rotor according to claim 14, characterized in that the blades are uniformly spaced around the perimeter of the disk with an angular frequency of Y _l = (14.17 ÷ 19.59) [units / rad], while for radial-angular the fixation of the position of the blades of the annular groove is made with contact protrusions, the lower face of each of which is located at an angle to the reference plane in the bottom part of the groove, identical to the angle of inclination of the mating face of the shank of the blade to the sole of the shank, making β ₁ = (29 ÷ 40) °, and from circular displacements in the annular groove of the blade are fixed anes not less than five retaining elements, which are constructed as a prismatic configuration with the insert in cross-section, congruent profile of the annular groove, and each endowed with a through threaded hole for the fixing screw. 17. The impeller of the eighth stage of the rotor of the HPC wheel according to claim 14, characterized in that the feather of the blade is made with an axial twist variable relative to the axis of the rotor, increasing with radial distance from the rotor axis with a pen twist gradient G _z defined in the projection on the conditional axial plane in the range G _s.p. = (α _p -α _k ) / N _sr = (187.6 ÷ 270.1) [deg / m], where α _to - the angle of installation of the profile of the feather of the scapula, in the root section; α _p - the same in the peripheral section; N _cf - the average height of the feather blades; in addition, the feather of the blade is made variable in width and height of the feather with a thickness defined in cross section as the difference in height of the back and trough relative to the chord connecting the input and output edges of the feather of the blade, while the maximum thickness of the profile of the feather of the blade is made the largest in the root section and decreases along pen height to the peripheral end. 18. The impeller of the eighth stage of the HPC rotor according to claim 14, characterized in that the annular shelves of the disk rim are made protruding beyond the size of the pen of the working blade to a width sufficient for interaction along the working fluid with the blades of the stator guide apparatus. 19. The impeller of the eighth stage as part of the rotor of a multi-stage high-pressure compressor turbofan engine, having a housing with a flowing part, a low-pressure turbine of the high-pressure turbine with a shaft, a high-pressure turbine and an HPC rotor, including a drum-disk design shaft, characterized in that it contains a blade ring and a disk, endowed with an annular groove for installing the crown blades, and the disk is made in the form of a single element including a hub with a central hole, the blade and the rim, and the crown blades contain each shank, a feather made with a profile, images a concave trough and a convex back, and a root shelf with a conical surface on both sides of the feather, while the shank of the blade is configured to fit into the groove of the rim of the disk and has a configuration of the lateral and supporting surfaces, congruent to the profile of the mating surfaces of the groove with the formation of a lock connection of the type “ring” groove ”and ensuring the angle α of setting the profile of the pen to the axis of the rotor in the projection onto the conditional axial plane of the rotor, normal to the axis of the pen of the blade, which has α _k = (32.4 ÷ 46.6) ° in the root section of the pen and the peripheral cross section of the pen, the value α _p = (37.4 ÷ 53.8) °, while the feather of the blade is made with an axial twist variable relative to the rotor axis, increasing with radial distance from the rotor axis with a pen twist gradient G _z defined in the projection on a conditional axial plane in the range G _s.p. = (α _p -α _k ) / N _sr = (187.6 ÷ 270.1) [deg / m], where α _to - the angle of installation of the profile of the feather of the scapula, in the root section; α _p - the same in the peripheral section; N _cf - the average height of the feather blades; while the blades are uniformly spaced around the perimeter of the disk with an angular frequency of Y _l = (14.17 ÷ 19.59) [units / rad], and the rim of the disk is divided by an annular groove into two asymmetric differently high annular arms, the peripheral sections of the annular shelves of which together with the outer the surface of the root shelves of the blades form the sleeve surface of the contour of the engine duct within the axial length of the rim of the disk of the eighth stage of the HPC rotor with an angle ϕ of inclination of the outer surface of the rim to the axis of the rotor identical to the outer surface of the root molasses; To ensure the transmission of torque from the theater, the front and rear shelves of the eighth stage disk rim are made with the possibility of detachable connection with the mating shelves of the seventh and ninth stage disks and the formation of the combined annular fragments of the internal contour of the HPC flow path with the inclusion of the eighth stage disk in the drum the disk design of the rotor shaft, in addition, the canvas of the eighth stage disk is made with the possibility of power connection in a package with the seventh, ninth disks and with the disk the labyrinth by means of clamping elements, in addition, the impeller is made with a ratio of the radius R _{d of the} disk from the axis of the rotor shaft of the HPC to the conditional conical surface, pine with the shaft of the rotor and describing the upper surface of the rim of the disk in the middle radial plane of the blade web to the average height H _{cf of the} blade feather profile comprising R _d / N _sr = (8.3 ÷ 12.4). 20. The impeller of the eighth stage of the HPC rotor according to claim 19, characterized in that the disk is made with a radius R _d from the axis of the HPC rotor to a conditional conical surface describing the upper surface of the rim in the middle radial plane of the web is (0.74 ÷ 0.96 ) of the radius R _p.ch. the peripheral contour of the flowing part in the specified plane. 21. The impeller of the eighth stage of the HPC rotor according to claim 19, characterized in that the disk of the eighth stage is combined into a package with the seventh, ninth disks and the labyrinth disk by means of coupling elements such as tightening studs and nuts with calibrated tightening torque, for which purpose in the disk blade holes are made under the tie rods equidistantly spaced relative to the rotor shaft axis and along the hypothetical circle with angular frequency determined in the range _crepe Y = (3,18 ÷ 4,46) [U / rad], the radius of the notional circle centers of said hole location s is alternatively with (0,51 ÷ 0,72) _d from the radius R disc in the middle radial plane of the web, moreover, the web drive is provided on both sides of an annular bead for mounting interdisk bushings and spacer rings. 22. The impeller of the eighth stage of the HPC rotor according to claim 19, characterized in that for the radial-angle fixation of the position of the blades, the annular groove is made with contact protrusions, the lower face of each of which is located at an angle to the reference plane in the bottom of the groove, identical to the angle of inclination mating faces the blade root to the sole of the liner constituting β ₁ = (29 ÷ 40) °, and the displacement in the circumferential direction in the annular groove of the blade are fixed by at least five retaining elements, which are constructed as a prismatic contribution sha configuration in cross section, congruent profile of the annular groove, and each endowed with a through threaded hole for the fixing screw. 23. The impeller of the eighth stage of the HPC rotor according to claim 19, characterized in that the disk blade is provided with ventilation air bypass holes for balancing the pressure in the package region from the seventh to ninth disk with pressure in other parts of the volume inside the drum-disk shell of the shaft of the HPC rotor, equidistantly radially around the circumference spaced with an angular frequency Y _vent = (3.18 ÷ 5.73) [units / rad]. 24. The impeller of the eighth stage of the rotor of the HPC according to claim 19, characterized in that the annular shelves of the disk rim are made protruding beyond the size of the pen of the working blade to a width sufficient to interact along the working body with the blades of the stator guide apparatus, and sections of the annular shelves in the area of the split joints with discs of the seventh and ninth stages are made with the possibility of overlapping.

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