RU2614709C1 - Low-pressure compressor of gas turbine engine of aviation type - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: compressor pf low pressure (CPV) bypass two-shaft gas turbine engine (GTE) is made of aircraft-type axial, four-stage with the inlet guide vanes (IGV). Stator housing CPV blade rows equipped with guide vanes (ON) of the blade, respectively the first, second and third-stage and dual-straightener. CPV has front and rear bearing of the rotor shaft. Front support fixed in the housing CPV BHA, back support - in the intermediate housing (PC) engine. The rotor shaft includes a reel-disk and cylindrical components, the first of which includes the impellers on the number of rotor stages. Bearings share the supports on the stator and rotor parts. The stator portion includes a front support bearing housing coupled with the bearing housing and the hub of the BHA to form a compact ring cavities. A cavity is provided with an elastic ring. The elastic ring is provided with projections mutually offset circumferentially with the inside and outside of the ring in one angular frequency γ v.u.k.= (2.55÷3.82) [U/rad]. The tape is perforated ring in the form of dispersed holes. Another annular cavity contains the element elastic damping torsional vibration system with elastic cross members arranged at the frequency found in the invention. The rear rotor shaft support comprises a support-thrust bearing and an external coupling element. The back support body is equipped with an additional row of holes for the flow of oil in the oil chamber. Reel-disk component CPV rotor shaft provided with radial and angular configuration of the outer surface of the rim disc impellers at all levels, combined with the inner surface of the engine running on an axial section flow together rims rotor shaft drives the flow of the working fluid. The blades of impellers are made with a spiral twist with respect to the axis of the pen, to create a variable adjustment angle of the pen γ_mouth installation profile stylus between the chord line and the front sections of the lattice in the plane sweep cylindrical section blade row.

EFFECT: invention allows to extend the operating range of the compressor stable damped oscillation of the rotor shaft without entering the resonant frequency.

22 cl, 8 dwg

Description

The invention relates to the field of production and operation of aircraft gas turbine engines (GTE), in particular to the structures and components of a low pressure compressor (LPC).

A GTE compressor is known, including an elastic-damper rotor bearing with an elastic element of a squirrel-wheel bearing (S. A. Vyunov, Yu.I. Gusev, A. V. Karpov and others. Design and engineering of aircraft gas-turbine engines. Moscow. Engineering. 1989, pp. 373-377).

A gas turbine engine compressor is known, including a rotor support made by a support body with an elastic squirrel-type damper (NN Sirotin, AS Novikov, AG Paykin, AN Sirotin. Fundamentals of designing the production and operation of aviation gas turbine engines and power plants in the CALS technology system. Book 1. Moscow. Science 2011. p. 734-736, Fig. 15.4, p. 767).

The disadvantages of these known solutions include the low level of sophistication of the adaptation of a low-pressure compressor to work in stationary ground conditions.

Known rotor shaft of a drum-disk type axial compressor of the engine with disks pairwise combined in stages and arranged sequentially downstream in the longitudinal plane of the drum cross-section. Both disks of each stage are interconnected by means of an annular collar of the first disk and a landing belt in the canvas of the second disk. The annular collar of the second disk forms a tract drum shell, acting as a spacer between the second and first disks of each subsequent working stage. On the rims of the disks, wedge-shaped annular recesses are made, which form an annular dovetail groove for contact with the wedge-shaped annular protrusions at the ends of the shelves of the rotor blades (RU 2269678 C1, publ. 02.10.2006).

A gas turbine engine low-pressure compressor with a rotor shaft comprising a system of four disks, each of which contains a rim for installing and driving rotor blades, is in communication with the low-pressure turbine shaft (LP) (NN Sirotin, A.S. Novikov , AG Paykin, AN Sirotin. Fundamentals of designing the production and operation of aircraft gas turbine engines and power plants in the CALS technology system. Book 1. Moscow. Science 2011. pp. 249-259)

The disadvantages of the known solutions include the lack of a system for selecting the set of necessary disk parameters that form the configuration of the rotor shaft and affecting the area of the flow section of the flow passage and the placement of blades on the disk rim that form the aerodynamic processes of the interaction of the rotor shaft of the drum-disk structure with the flow of the working fluid, due to the lack of specification ranges of geometric and aerodynamic parameters of the spatial configuration of the disks, as well as the difficulty of obtaining a compromise a combination of increased values of efficiency, reserves of gas-dynamic stability (GDU) of the compressor and, as a result, the difficulty of ensuring optimal dynamic strength and increased resource of the rotor shaft with a minimum material consumption of the disks and their connections in the shaft structure.

Known low-pressure compressor GTE, made with the support of the rotor shaft of the compressor, including placed on the shaft of the bearing connected to the bearing housing, the lubrication and cooling system of the bearing and sealing elements (A.A. Inozemtsev, M.A. Nikhamkin, V.L. Sandratsky “Gas turbine engines.” Aviadvigatel OJSC Perm 2007, pp. 196-199, Fig. 4.4.7.1_2).

Known low-pressure compressor GTE, made with the support of the compressor rotor shaft, including a bearing with a housing, connecting elements, seals and a bearing lubrication and cooling system (NN Sirotin, A.S. Novikov, A.G. Paykin, A.N. Sirotin, Fundamentals of Designing the Production and Operation of Aircraft Gas Turbine Engines and Power Plants in the System of CALS Technologies, Book 1. Moscow, Science 2011. pp. 762-763, Fig. 1-5.18, p. 763).

The disadvantages of the known solutions are the low adaptation of the low pressure compressor to long-term continuous operation in a stationary external environment and the low maintainability of the support of the rotor shaft of the low pressure rotor due to the non-optimal arrangement of the connections.

The problem solved by a group of inventions, united by a single creative concept, is to constructively develop a stationary-type low-pressure compressor of a gas turbine engine (GTE) with an improved system of elastic-hydraulic damping of rotor shaft vibrations, a system for supplying a lubricant-cooling fluid to the elements of the rear rotor support, and also in the study of the rotor shaft of the drum and disk construction of the low pressure rotor with impeller disks of improved aerodynamic configuration, spatial stiffness of nodes and the elements of the connection of the rotor shaft disks, necessary to increase the efficiency, gas-dynamic stability and engine life without increasing the material consumption.

The problem is solved in that the low-pressure compressor of a double-circuit twin-shaft gas turbine engine of an aviation type, according to the invention, is made of an axial, no more than four-stage, endowed with an input guide apparatus (VNA) having a body and power profiled racks equipped with adjustable rotary flaps, and also endowed with a connected with VNA the stator of the low pressure switch, in which the blades forming the blade crowns of the guide vanes (HA) of the first, second and third stupas are installed of the stator and the blades of the fourth stage of the stator forming the blade crown of the double straightening device, the LPC has front and rear bearings of the rotor shaft, the first of which is fixed in the VNA KND housing, and the second in the intermediate housing (PC) of the engine, and the KND rotor is installed in these supports with a shaft including drum-disk and cylindrical components, the first of which is equipped with impellers according to the number of rotor steps, each consisting of a disk and blades forming a blade ring of the corresponding stage; the front support of the KND rotor shaft is made containing a roller bearing separating the support into the stator and rotor parts and is equipped with a system of elastic-hydraulic damping of vibrations of the rotor shaft, while the stator part includes a support housing, which is connected to the roller bearing housing and is enclosed by an annular element of the hub of the internal housing of the KND KND with the formation of two compact annular cavities, one of which is filled with liquid and provided with an elastic ring with damping of the oscillations of the shaft by the elastic ring and replace by extending the fluid flows through the wall of the ring ribbon, for which the elastic ring is provided on both sides with protrusions mutually displaced around the circumference through one with an angular frequency of γ _cc in the range of γ _cc = (2.55 ÷ 3 82) [units / rad], and the ring tape is provided with perforations in the form of dispersed holes, in addition, the stator part of the support includes the forming ring elements of the cavities of pressurization, venting and oil with annular labyrinth caps fixed to them and an outer ring fixed in the roller bearing housing of the latter; the second of the annular cavity of the stator part of the support contains an element of elastic damping of the vibrations of the rotor shaft, made in the body of the support in the form of a ring structure of the “squirrel wheel” type, including a system of longitudinally oriented elastic beams separated by parallel slots, with elastic beams located around the perimeter of the support body with angular frequency γ _p.b.k. defined in the range of γ _bp = (7.2 ÷ 14.4) [units / rad], and the slots between them are made wider than the width of the beads by (1.1 ÷ 2.4) times; and the rotor part of the support includes a trunnion of the front support of the rotor shaft, consisting of a hollow cylindrical section equipped with at least one ledge, on which an inner ring of the roller bearing and two multi-row labyrinth rings are installed, which together with the maze response covers separate the oil and soufflé cavities, as well as the venting cavity and cavity of pressurization of air, the volume of which is limited by the third multi-crest ring of the labyrinth mounted on the conical diaphragm of the front axle forming with -cylindrical portion integrally and permanently connected to the drive shaft of the first stage rotor.

Moreover, the number of blades in the blade crowns of the impellers can be made increasing from the first to the third stage of the rotor along the flow of the working fluid and in the blade crown of the Republic of Kazakhstan of the second stage, the number of blades in the blade rim of the impeller of the first stage is not less than 20%, in the third, no less than 50%.

The drum-disk component of the KND rotor shaft can be made with a radial and angular configuration of the outer surface of the rims of the disks of the impellers of all stages, combined with the inner surface of the engine’s flow part on the axial section of the flow of the body of the rim of the rims of the rotor shaft disks, for which the disks are made in steps increasing along the working fluid in the conditional middle plane of the web with the diameter of the flowing part, with the ratio of the diameters (1.0) :( 1.1 ÷ 1.34) :( 1.18 ÷ 1.44) :( 1.21 ÷ 1 , 48), and with angles of inclination o bauds forming the surface configuration of the flowing part with smooth conjugation of adjacent ends.

The axle of the front support of the KND rotor shaft can be equipped with an end sleeve with a flange for preloading the inner ring of the roller bearing and the scallop labyrinth rings located behind it to the ledge of the cylindrical portion of the axle, and the end sleeve of the axle contains a sealed diaphragm that separates the volume of the sleeve into the oil and air cavities, and in the diaphragm is made protruding on both sides of the last glass, designed to establish a spline sleeve in which the drive shaft of the pump for pumping oil from the oil cavity per days of support.

The back support of the KND rotor shaft can be made thrust and contains a ball bearing separating the support into the stator and rotor parts, while the stator part includes a support housing made integral with the ball bearing housing and passing at the ends into internal and external power rings of different diameters for split connections with mating flanges of the outer ring of the ball bearing and the intermediate housing of the engine, and the rotor part of the rear support includes at the same time the lower part of the conical diaphragm, one-piece the KND rotor shaft component of the KND rotor shaft and the rear axle which is detachably connected to the cylindrical shaft component on which the ball bearing is mounted, two multi-crest labyrinth rings and a multifunctional external clamping element made with the formation of an open manifold for collecting and supplying lubricant coolant to the rolling elements of the ball bearing and the ring of the labyrinth with access to the oil cavity, while on the cylindrical component of the shaft of the multi-row ring rings paired with labyrinth seal mating covers form movable seals of the boost cavities, venting and oil cavity of the rear support, and the third multi-comb ring is located on the conical diaphragm of the rear shaft support and together with the labyrinth seal cover movably closes the boost cavity from the front side.

The number of power profiled racks equipped with adjustable rotary flaps can be taken in VNA KND expressed as a prime number of at least 17 and no more than 23 (units).

The task of the second embodiment is solved in that the low-pressure compressor of a double-circuit twin-shaft gas turbine engine of an aviation type, according to the invention, is made of an axial, not more than four-stage, endowed with an input guide apparatus having a housing and power profiled racks equipped with adjustable rotary flaps, and also endowed with a connected with VNA stator housing KND, in which are installed forming the blade crowns of the guide vanes of the blades, respectively, the first, second and t by a lathe of the stator steps and the blades of the fourth stator stage forming the scapular crown of the double straightening apparatus, the KND has front and rear bearings, the first of which is fixed in the VNA KND housing, and the second in the intermediate engine casing; in these bearings a KND rotor is installed with a shaft including a drum-disk and cylindrical components, the first of which is equipped with impellers according to the number of rotor steps, each of which consists of a disk and blades forming a blade ring of the corresponding stage, while the drum-disk component contains three sections , two of which the first and second are made non-separable, while the first section from the engine input includes a pin in series of the front support of the rotor shaft, disks of the first and second stages and cylinder a single spacer, the second section includes a third-stage disk communicated with the axle of the rear support of the rotor shaft and a cylindrical spacer, and the third section consists of a fourth-stage disk, and the impeller disk of each stage is made in the form of a single element including a rim turning into a blade-reinforced web a Central hole, the rim of each disk is connected to the canvas with the formation of annular conical inclined shelves for power association with the rim of the disks of the previous and subsequent steps and supply slots for rotor working blades that are uniformly distributed over the circumference and are inclined to the axis of the shaft, the radius R of the first stage disk _D1 from the rotor shaft to the outer surface of the rim in the central plane of the web (0,42 ÷ 0,61) of the radius R _pp the peripheral contour of the flowing part in the indicated plane, and the blade web of the first stage disk on the front side of the disk in the zone adjacent to the rim is equipped with a conical ring element located under it for power connection with the conical diaphragm of the axle of the front support, which is made with an angle β of inclining the generatrix to the axis the rotor shaft, exceeding the angle ϕ of inclination of the generatrix of the outer surface of the rim by Δ equal to Δ = (β-ϕ), defined in the range Δ = (39 ÷ 47) °.

In this case, the rear along the flow of the working fluid shelf of the rim of the disk of the first stage can be developed before contact with the mating shelf of the rim of the disk of the next stage and made to extend beyond the size of the pen of the working blade of the first stage to a width sufficient to accommodate the labyrinth seal elements made with the possibility of interaction through the gap with the elements of the fixed end of the blade of the stator guide vane, which ensures interaction with the specified disk of the first rotor stage along the working fluid.

The outer surface of the rim of the disk of the first stage can be made with the angle of inclination of the generatrix relative to the axis of the rotor shaft, coinciding with the angle of inclination of the generatrix of the inner contour of the flow part, the radius of which monotonically changes in the direction of flow of the working fluid with a gradient of radial expansion G _about , defined in the range

, где

where

R _max and R _min - the maximum and minimum radii of the outer surface of the rim of the disk, In _about - the axial width of the rim.

The task of the third option is solved in that the low-pressure compressor of a double-circuit twin-shaft gas turbine engine of an aviation type, according to the invention, is made of an axial, not more than four-stage, endowed with an input guide apparatus having a housing and power profiled racks equipped with adjustable rotary flaps, and also endowed with a connected with VNA stator housing KND, in which are installed forming the blade crowns of the guide vanes of the blades, respectively, the first, second and the third stages of the stator and the blades of the fourth stage of the stator forming the blade crown of the double rectifier apparatus, while the LPC has front and rear supports, the first of which is fixed in the VNA of the LPC, and the second in the intermediate engine casing; in these bearings a KND rotor is installed with a shaft including a drum-disk and cylindrical components, the first of which is endowed with impellers according to the number of rotor steps, each consisting of a disk and blades forming a blade ring of the corresponding stage, and the blade ring of the impeller of the first rotor stage is formed blades that are installed in the grooves of the rotor shaft disk with an angular frequency of γ _l.v. defined in the range of γ _l.v. = (5.1 ÷ 6.8) (u / rad), with each shank and feather containing a convex-concave profile formed by a concave trough and a convex back, conjugated by input and output edges, the blade is made with spiral twist relative to the axis of the pen, a variable adjustment pen angle γ _mouth profile settings pen defined as the angle between the common tangent connecting the inlet and outlet edges, forming a chord of the profile, and the frontal profile line grating in a planar reamer blade row cylindrical section, having the value γ _set in the root section of the pen = (61,5 ÷ 75,5) °, and in a peripheral section of γ value _ust.p. = (36.9 ÷ 44.9) °, moreover, the feather of the blade is made with a variable thickness and width of the feather, defined in cross section as the difference between the heights of the back and trough relative to the chord connecting the input and output edges of the feather of the blade, while the input and the output edges of the pen are made sailing diverging to the peripheral end of the blade with a gradient of G _yx increasing the chords connecting them, equal to

G _u = (L _p.h.- L _k.h. ) / H _cf = (8.4 ÷ 12.1) ⋅10 ^-2 [m / m],

where L _p.h. - the length of the peripheral chord connecting the input and output edges of the feather blade in a conditional plane perpendicular to the axis of the spiral twist of the feather blade; L _c.h. - the same, the length of the root chord; N _cf - the average height of the feather blades; in addition, the blade is made with the ratio of the height h of the input edge of the pen profile to the middle chord L _cf. dividing the area of the working surface of the pen into two equal parts, comprising h / L _cf. = (2.18 ÷ 3.13).

Moreover, each blade of the blade rim of the impeller of the first stage of the rotor can be equipped on both sides of the pen with an anti-vibration shelf located in the region of one third of the height of the pen from the peripheral end of the blade pen.

The castle connection of the grooves of the rim of the disks of each stage with the shanks of the blades can be performed on the type of "dovetail".

The feather of the blade of the blade rim of the impeller of the first stage of the KND rotor can be made with a trough facing concavity in the direction of rotation of the rotor counterclockwise (view along the np - direction of flight), and with the back of the pen convex towards the side of rotation of the rotor and in the direction of rotation clockwise (view in np).

The feather of the blade of the blade of the impeller of the first stage of the KND rotor can be made with a trough facing concavity in the direction of rotation of the rotor clockwise (view in n.p.), and with the back of the pen convex towards the side of rotation of the rotor and against the direction of rotation clockwise (view by n.p.).

The task of the fourth embodiment is solved in that the low-pressure compressor of a double-circuit twin-shaft gas turbine engine of the aviation type, according to the invention, is made axial, no more than four-stage, endowed with an input guide apparatus having a housing and power profiled racks equipped with adjustable rotary flaps, and also endowed with connected with VNA stator housing KND, in which are installed forming the blade crowns of the guide vanes of the blade respectively the first, second and the third stages of the stator and the blades of the fourth stage of the stator forming the blade crown of the double straightening apparatus, while the LPC has front and rear bearings, the first of which is fixed in the HVA of the LPC, and the second in the intermediate engine casing; in these bearings a KND rotor is installed with a shaft including a drum-disk and cylindrical components, the first of which is equipped with impellers according to the number of rotor steps, each of which consists of a disk and blades forming a blade ring of the corresponding stage, while the drum-disk component contains three sections , two of which the first and second are made non-separable, while the first section from the engine input includes a pin in series of the front support of the rotor shaft, disks of the first and second stages and cylinder a single spacer, the second section includes a third-stage disk communicated with the axle of the rear support of the rotor shaft and a cylindrical spacer, and the third section consists of a fourth-stage disk, and the impeller disk of each stage is made in the form of a single element including a rim turning into a blade-reinforced web a Central hole, the rim of each disk is connected to the canvas with the formation of annular conical inclined shelves and provided with grooves for rotor blades that are evenly distributed around the perimeter y and are made inclined to the axis of the shaft, while the radius of the disk R _{d2 of the} second stage from the axis to the outer surface of the rim in the middle plane of the web is (0.54 ÷ 0.77) from the radius R of the _item the peripheral contour of the flowing part in the indicated plane, and the disk rim is made with an angle ϕ of the generatrix of the outer surface of the rim relative to the axis of the rotor shaft, which is ϕ = (12 ÷ 17) ° and identical to the axial angle relative to the same axis of the generatrix of the inner contour of the flowing part, in addition the disk of the second stage is made with the possibility of power association with the shelf of the rim of the disk of the first stage and through a spacer with the blade disk of the third stage.

In this case, the cylindrical spacer can be equipped with a flange for detachable connection with the third stage disk blade, while holes are made in the flange uniformly spaced around the perimeter of the flange with an angular frequency Y _f1 = (5.3 ÷ 7.9) [units / rad], in addition, the cylindrical spacer is made wide enough to accommodate the elements of the labyrinth seal, made with the possibility of interaction through the gap with the elements of the fixed end of the blade of the stator guide vane, providing interaction with the second disk the second rotor stage in the working fluid.

The castle connection of the grooves of the rim of the disk of each stage with the shanks can be performed on the type of "dovetail".

The outer surface of the rim of the disk of the second stage can be made with the angle of inclination of the generatrix relative to the axis of the rotor shaft, coinciding with the angle of inclination of the generatrix of the inner contour of the flow part, the radius of which monotonically changes in the direction of flow of the working fluid with a radial expansion gradient G _ob2 defined in the range

,

,

where R _max and R _min - the maximum and minimum radii of the outer surface of the rim of the disk, In _about - the axial width of the rim.

The task of the fifth embodiment is solved in that the low-pressure compressor of a double-circuit twin-shaft gas turbine engine of an aviation type, according to the invention, is made of an axial, not more than four-stage, endowed with an input guide apparatus having a housing and power profiled racks equipped with adjustable rotary flaps, and also endowed with a connected with VNA stator housing KND, in which are installed forming the blade crowns of the guide vanes of the blades, respectively, the first, second and tr with a series of stator stages and the blades of the fourth stator stage forming the blade crown of the double straightening apparatus, the LPC has front and rear bearings, the first of which is fixed in the VNA of the LPC, and the second in the intermediate engine casing; in these supports, a KND rotor is installed with a shaft including a drum-disk and cylindrical components, the first of which is equipped with impellers according to the number of rotor steps, each of which consists of a disk and blades forming a blade ring of the corresponding stage, and the blade ring of the impeller of the second stage of the rotor is formed blades that are installed by shanks in the grooves of the rotor shaft disk with an angular frequency of γ _l.v. defined in the range of γ _l.v. = (6.0 ÷ 8.2) (u / rad), with the blades containing each shank and feather with a convex-concave profile formed by a concave trough and a convex back, conjugated by the input and output edges, while the feather is made with a spiral twist relative to the axis of the pen, a variable adjustment pen angle γ _mouth profile settings pen defined as the angle between the common tangent connecting the inlet and outlet edges, forming a chord of the profile, and the frontal profile line grating in a planar reamer blade row cylindrical section, having the value γ _set in the root section of the pen = (65,2 ÷ 73,2) °, and in a peripheral section of γ value _ust.p. = (35.8 ÷ 43.8) °, and the feather of the blade is made with a variable thickness and width of the feather, defined in cross section as the difference between the heights of the back and trough relative to the chord connecting the input and output edges of the feather of the blade, while the input and the output edges of the pen are made sailing diverging to the peripheral end of the blade with a gradient of G _u an increase in the connecting chords equal to

G _u = (L _p.h.- L _k.h. ) / H _cp = (7.4 ÷ 10.7) ⋅10 ^-2 [m / m],

where L _p.h. - the length of the peripheral chord connecting the input and output edges of the feather blade in a conditional plane perpendicular to the axis of the spiral twist of the feather blade; L _c.h. - the same, the length of the root chord; N _{cf - the} average height of the feather blades; in addition, the blade is made with the ratio of the height h of the input edge of the pen profile to the middle chord L _cf. , dividing the area of the working surface of the pen into two equal parts, comprising h / L _cp.x. = (1.83 ÷ 2.63).

Moreover, each blade of the blade rim of the impeller of the second stage of the rotor can be equipped on both sides of the pen with an anti-vibration shelf located in the region of one third of the height of the pen from the peripheral end of the blade pen.

The feather of the blade of the blade of the impeller of the impeller of the second stage of the KND rotor can be made with a trough facing concavity in the direction of rotation of the rotor counterclockwise (view in np - direction of flight), and with the back of the pen facing convex in the direction of rotation of the rotor and in the direction of rotation clockwise (view in np).

The feather of the blade of the blade of the impeller of the impeller of the second stage of the KND rotor can be made with a trough facing concavity in the direction of rotation of the rotor clockwise (view in n.p.), and with the back of the pen convex towards the side of rotation of the rotor and against the direction of rotation clockwise (view by n.p.).

The technical result of the group of inventions united by a single creative concept, achieved by the given set of essential features of low pressure gas turbine engine, is to increase the efficiency of the system of elastic-hydraulic damping of rotor shaft vibrations, expand the range of stable compressor operation modes by 2.2% with damping rotor shaft vibrations without entering into resonant frequencies and increasing the engine life by 2 times. This is achieved by increasing the efficiency of the system of elastic-hydraulic damping of shaft oscillations, expanding the range of operating modes of stable operation of the engine with damping oscillations of the rotor shaft without entering the resonant frequencies and reducing the wear of the front support elements of the low pressure valve, which increases the compressor resource by 2 times and the duration of the overhaul by 18-20%. An increase in compressor life is also achieved by adapting KND, as a part of the engine that is more sensitive to the external air flow, intensive work in stationary conditions of ground functioning, as well as optimizing the performance of the rear shaft support of the KND rotor and its elements to these specific conditions, as well as improving the capabilities of installation and dismantling works with semi-automatic or manual techniques, for example, in the field. And due to the improvement of the structural and aerodynamic parameters of the wheels of the impellers of all stages, combined into a drum-disk design of the rotor shaft, they increase the efficiency and expand the range of gas-dynamic stability modes of the engine’s low pressure, as well as reduce the material consumption and increase the bending stiffness of the rotor and the maximum allowable stresses in the elements drive.

The invention is illustrated by drawings, where:

in FIG. 1 shows a low-pressure gas turbine compressor, longitudinal section;

in FIG. 2 - front support shaft rotor KND, a longitudinal section;

in FIG. 3 is a fragment of an elastic ring, side view;

in FIG. 4 - drum-disk component of the shaft of the rotor KND, a longitudinal section;

in FIG. 5 - the impeller of the first stage of the rotor KND, a longitudinal section;

in FIG. 6 - the blade of the impeller of the first stage of the rotor KND, top view;

in FIG. 7 - the impeller of the second stage of the rotor KND, a longitudinal section;

in FIG. 8 - the blade of the impeller of the second stage of the rotor KND, top view.

The low-pressure compressor of the double-circuit twin-shaft gas turbine engine of the aircraft type is made axial, four-stage. KND is endowed with an input guide apparatus 1 having a housing 2 and equipped with adjustable rotary flaps power profiled racks (not shown in the drawings). The compressor is also endowed with a housing 3 of the stator KND, connected to the housing 2 VNA. In the housing 3 of the stator KND installed working blades that form the blade crowns 4 of the guide vanes (ON), respectively, of the first, second and third stages of the stator and form the blade crown 5 of the double straightening apparatus of the blade of the fourth stage of the stator.

KND has front and rear supports 6 and 7. The front support 6 is fixed in the housing 2 VNA KND. The rear support 7 is fixed in the intermediate housing 8 of the engine. In bearings 6 and 7, a KND rotor is installed with a shaft including a drum-disk and cylindrical components of the front and rear rotor bearings. The drum-disk component is endowed with impellers according to the number of rotor steps, each consisting of a disk 9, 10, 11, 12 and blades forming a blade ring 13 of the corresponding stage. The number of blades in the blade rims of the 13 impellers is made increasing from the first to the third stage of the rotor along the flow of the working fluid and in the blade rim of the Republic of Kazakhstan of the second stage the number of blades in the blade rim of the impeller of the first stage is not less than 20%, in the third less than 50%. The disks 9, 10, 11, 12 of the impellers of each stage are made in the form of a single element, including a rim 14, turning into a web 16 reinforced by the hub 15 with a central hole 17.

The drum-disk component of the KND rotor shaft is made with a radial and angular configuration of the outer surface of 18 rims 14 of the disks 9, 10, 11, 12 of the impellers of all stages, combined with the inner surface of the engine’s flowing part on the axial portion of the flow of the rim of the rotor shaft disks of the rotor shaft stream. . For this, the disks 9, 10, 11, 12 are made with stepwise increasing along the working fluid in the conditional middle plane of the blade 16 with the diameter of the flowing part, with the ratio of the diameters (1,0) :( 1,11 ÷ 1,34) :( 1 , 18 ÷ 1.44) :( 1.21 ÷ 1.48), and with the inclination angles of the rims 14, forming the surface configuration of the flowing part with smooth conjugation of adjacent ends.

The number of power profiled racks equipped with adjustable rotary flaps is adopted in the VNA KND expressed as a prime number of at least 17 and no more than 23 units.

The front support 6 of the KND rotor shaft (Fig. 2) is made comprising a roller bearing 19 separating the support into the stator and rotor parts and is equipped with a system of elastic-hydraulic damping of the vibrations of the rotor shaft. The stator part includes a bearing housing 20, which is connected to the housing 21 of the roller bearing 19 and is enclosed on the side surface by an adjacent ring element of the hub 22 of the inner housing 23 of the input low pressure guide apparatus 1 with the formation of two compact peripheral annular cavities 24 and 25 between them. Annular cavity 24 in working condition it is filled with liquid and provided with an autonomous elastic ring 26. The elastic ring 26 divides the annular cavity 24 into unequal volumes on different sides of the ring 26 with damping to of the oscillations of the shaft at the same time with the ring 26 and a constructive slowdown of the return flows of fluid through the wall of the tape 27 of the ring 26. For this, the elastic ring 26 is equipped with one-sided protrusions 28 and 29 made along the perimeter of the tape 27 of the ring from the outside and inside, as well as perforation in the form of dispersed holes ( drawings not shown). The protrusions 28, 29 are mutually offset around the circumference through one with an angular frequency _γ.c. defined in the range

γ _V.O.K. = N _in. / 2π = (2.55 ÷ 3.82) [units / rad],

where N _in. - the total number of protrusions on both sides of the tape of the elastic ring.

The annular cavity 25 contains an element of elastic damping of the vibrations of the rotor shaft, made directly in the body of the housing 20 of the rotor shaft support in the form of an annular squirrel-wheel structure including a system of longitudinally oriented elastic beams 30. The beams 30 are located around the perimeter of the support body 6 with an angular frequency γ _b.p. defined in the range

γ _b.s. = N _b.s. / 2π = (7.2 ÷ 14.4) [units / rad],

where N _b.s. - the number of elastic beams in the "squirrel wheel".

The beams 30 are separated by parallel slots (not shown in the drawings), the width of which (1.1 ÷ 2.4) times exceeds the width of the beams 30.

The stator portion of the support comprises an oil cavity 31, a vent cavity 32 and a boost chamber 33. Cavities 31, 32, 33 are made by forming ring elements 34, 35, 36 with ring covers 37, 38, 39 of labyrinths fixed on them. The stator part of the support also includes an outer ring 40 of the latter fixed in the housing 21 of the roller bearing 19.

The rotor part of the support includes a pin 41 of the front support. The pin 41 consists of a hollow cylindrical section 42 with at least one ledge 43 and a conical diaphragm 44. On the cylindrical section 42 of the pin 41, an inner ring 45 of the roller bearing 19 and two scallop rings 46, 47 of the labyrinth are installed. The rings 46, 47 of the labyrinth together with the counter covers 37, 38 of the labyrinths separate the oil cavity 31 and the cavity 32 venting, as well as the cavity 32 venting and the cavity 33 boost air. The volume of the cavity 33 of the pressurization of air is limited by the third scallop ring 48 of the labyrinth mounted on the conical diaphragm 44 of the pin 41, forming with the cylindrical section 42 integrally and inseparably connected with the disk 9 of the first stage of the drum-disk component of the rotor shaft. The axle 41 of the front support is equipped with an end sleeve 49 with a flange 50 for power supporting the inner ring 45 of the roller bearing 19 and the scallop rings 46, 47 of the labyrinths located behind it, pressing against the ledge 43 on the cylindrical section 42 of the axle 41.

The end sleeve 49 of the pin 41 of the front support of the rotor shaft of the low pressure rotor is multifunctional, axisymmetric with respect to the axis of the rotor shaft. The end sleeve 49 contains a sealed diaphragm 51. The diaphragm 51 divides the volume of the sleeve into an oil cavity 52 and an air cavity 53, which is in communication with a cavity 33 boost support. In the diaphragm 51, a glass 54 protruding to both sides of the diaphragm is made integrally with it. The front part of the glass 54 is made in communication with the oil cavity 52. The rear part of the glass 54 is structurally protruding into the air cavity 53 of the sleeve and designed to make the spline sleeve 55. B spline sleeve 55 mounted shaft 56 of the drive pump for pumping oil from the oil cavity 31 of the front support.

The rear support 7 of the rotor shaft of the low pressure rotor is made thrust and contains a ball bearing 57 that separates the support into the stator and rotor parts. The stator part includes a bearing housing 58, integral with the ball bearing housing 57 and passing at the ends into internal and external power rings 59 and 60 of different diameters for detachable connections by mating flanges of the outer ring 61 of the ball bearing 57 and the intermediate housing 8 of the engine. The rotor part of the rear support includes at the same time a conical diaphragm 62, one-piece connected to the disk 11 of the third stage of the drum-disk component of the KND rotor shaft and a rear pin 63, detachably connected to the cylindrical component 64 of the shaft. A ball bearing 57, two scallop rings 65, 66 labyrinths and a multifunctional external coupling element 67 are formed on the cylindrical component 64 of the shaft with the formation of an open manifold for collecting and supplying coolant to the rolling elements of the ball bearing 57 and the scallop ring 65 of the labyrinth with access to the oil cavity . The scallop rings 65, 66 mounted on the cylindrical component of the shaft 64 together with the maze seal mating covers form movable seals of the boost cavities, venting and oil cavity of the rear support. The third scallop ring 68 is located on the conical diaphragm 62 of the rear shaft support and, together with the labyrinth seal cover, movably closes the boost cavity from the front side.

The drum-disk component (Fig. 4) contains three sections, two of which the first and second are made non-separable. The first section from the engine entrance includes a pin 41 of the front support 7 of the rotor shaft, a disk 9 of the first stage, a disk 10 of the second stage and a spacer 69. The second section includes a disk 11 of the third stage, in communication with the pin 63 of the rear support 7 of the rotor shaft and the cylindrical spacer 70. The third section consists of a disk 12 of the fourth stage. The rim 14 of each disk is connected to the blade 16 with the formation of annular conical inclined shelves 71 for power association with the rim of the disks of the previous and subsequent steps. The rim 14 of each disk is provided with grooves (not shown in the drawings) for rotor blades, which are evenly distributed around the perimeter and made inclined to the axis of the shaft. The castle connection of the grooves of the rim of the disks of each stage with the shanks of the blades is made according to the "dovetail" type.

The radius of the disk 9 of the first stage R _d1 from the axis of the rotor shaft to the outer surface 18 of the rim 14 in the middle plane of the blade 16 is (0.42 ÷ 0.61) from the radius R of the _item the peripheral contour of the flowing part in the specified plane.

The blade 16 of the disk 9 of the first stage (Fig. 5) from the front side of the disk in the area adjacent to the rim 14 is provided with a conical ring element 72 located under it for power connection with the conical diaphragm 44 of the axle 41 of the front support for transmitting radial and axial forces to the elements front rotor support. The annular element 72 is made with an angle β of inclination of the generatrix to the axis of the rotor shaft, exceeding the angle ϕ of inclination of the generatrix of the outer surface 18 of the rim 14 by an amount Δ equal to Δ = (β-ϕ), determined in the range Δ = (39 ÷ 47) °. The rear along the flow of the working fluid shelf 73 of the rim 14 of the disk 9 of the first stage is developed before contact with the mating shelf 74 of the rim 14 of the disk of the second stage and is made to extend beyond the size of the pen blade 75 of the disk 9 of the first stage, sufficient to accommodate the elements in the specified shelf 76 labyrinth seals made with the possibility of interaction through the gap with the elements of the stationary end of the blade of the stator guide apparatus, which ensures interaction with the disk of the first rotor stage along the working fluid.

The outer surface 18 of the rim 14 of the disk 9 of the first stage is made with the angle of inclination of the generatrix relative to the axis of the rotor shaft, coinciding with the angle of inclination of the generatrix of the inner contour of the flow part, the radius of which monotonically changes in the direction of flow of the working fluid with a radial expansion gradient G _ob1 defined in the range

,

,

where R _max and R _min - the maximum and minimum radii of the outer surface of the rim of the disk of the first stage, In _about - the axial width of the rim of the disk of the first stage.

The scapula of the impeller of the first stage of the rotor is formed by blades 75, which are installed in the grooves of the disk 9 of the rotor shaft with an angular frequency of γ _l. defined in the range

γ _l.v. = N _l.v. / 2π = (5.1 ÷ 6.8) (unit / rad),

where N _lv - the number of blades in the blade rim of the impeller of the first stage of the KND rotor.

The blades 75 of the impeller of the first stage (Fig. 6) contain each shank 77 and feather 78 with a convex-concave profile formed by a concave trough and a convex back, conjugated by input and output edges 79 and 80. Pen 78 is made with a spiral twist relative to the axis of the pen, New variable adjustment pen angle γ _mouth profile settings pen defined as the angle between the common tangent connecting the inlet and outlet edges 79 and 80 forming a chord of the profile 81, 82 and the front line of the lattice plane unfolding profiles cylindrical cross section Ia blade row having a root section pen value γ _ust.k. = (67.5 ÷ 75.5) °, and in the peripheral section the value of γ _st. = (36.9 ÷ 44.9) °. The feather 78 of the blade 75 is made with a thickness varying in width and height of the feather, defined in cross section as the difference between the heights of the back and trough relative to the chord connecting the inlet and outlet edges 79 and 80 of the blade feather. The input and output edges 79 and 80 of the pen 78 are made sailing diverging to the peripheral end face 83 of the blade with a gradient of G _u an increase in the connecting chords equal to

G _u = (L _p.h.- L _k.h. ) / H _cp = (8.4 ÷ 12.1) ⋅10 ^-2 [m / m],

where L _p.h. - the length of the peripheral chord connecting the input and output edges of the feather blade in a conditional plane perpendicular to the axis of the spiral twist of the feather blade; L _c.h. - the same, the length of the root chord; N _cf - the average height of the feather blades.

The blade 75 of the impeller of the first stage is made with the ratio of the height h of the input edge 79 of the profile of the pen 78 to the middle chord L _cf. dividing the area of the working surface of the pen into two equal parts, comprising h / L _cf. = (2.18 ÷ 3.13).

Each blade 75 of the blade rim of the impeller of the first stage of the rotor is equipped on both sides of the pen 78 with an anti-vibration shelf 84 located in the region of one third of the height of the pen from the peripheral end 83 of the blade pen.

Feather 78 of the blade 75 of the blade root of the impeller of the first stage of the KND rotor is made with a trough facing concavity in the direction of rotation of the rotor counterclockwise (view in np - direction of flight), and with the back of the pen facing convex in the direction of rotation of the rotor and in the direction of rotation clockwise (view in np).

Variant feather 78 of the blade 75 of the blade wheel of the impeller of the first stage of the KND rotor is made with a trough facing concavity in the direction of rotation of the rotor clockwise (np view), and with the back of the feather convex to the side against rotation of the rotor and against direction clockwise rotation (np view).

The radius R _{d2 of the} disk 10 of the second stage (Fig. 7) in the drum-disk component from the axis of the rotor shaft to the outer surface 18 of the rim 14 in the middle plane of the web is (0.54 ÷ 0.77) from the radius R of the _item the peripheral contour of the flowing part in the specified plane. The rim 14 of the disk 10 of the second stage is made with an angle ϕ forming the outer surface 18 of the rim relative to the axis of the rotor shaft, component ϕ = (12 ÷ 17) ° and identical to the axial angle relative to the same axis forming the inner contour of the flow part. The rim 14 of the disk 10 of the second stage is made with the possibility of power integration of the front shelf 74 with the rear shelf 73 of the rim of the disk 9 of the first stage and the rear shelf 85 through a cylindrical spacer 69 with the blade 16 of the disk 11 of the third stage for transmitting torque from the high-pressure pump and radial-axial forces from aggregates of rotor shaft stages combined into a drum-disk design.

The cylindrical spacer 69 is provided with a flange 86 for detachable connection with the blade 16 of the disk 11 of the third stage. Holes are made in flange 86 uniformly spaced around the perimeter of the flange with an angular frequency

Y _f1 = N / 2π = (5.3 ÷ 7.9) [units / rad],

where N is the number of holes in the spacer flange.

The cylindrical spacer 69 is made wide enough to accommodate the elements of the labyrinth seal 87 made with the possibility of interaction through the gap with the elements of the stationary end of the blade of the stator guide apparatus, which ensures interaction with the disk of the second rotor stage along the working fluid.

The outer surface 18 of the rim 14 of the disk 10 of the second stage is made with the angle of inclination of the generatrix relative to the axis of the rotor shaft, coinciding with the angle of inclination of the generatrix of the inner contour of the flow part, the radius of which monotonously changes in the direction of flow of the working fluid with a radial expansion gradient G _ob2 defined in the range

,

,

where R _max and R _min - the maximum and minimum radii of the outer surface of the rim of the disk of the second stage, In _about - the axial width of the rim of the disk of the second stage.

The blade wheel of the impeller of the second stage of the rotor is formed by the blades 88, which are installed by the shanks in the grooves of the disk of the rotor shaft with an angular frequency of γ _l.v. defined in the range

γ _l.v. = N _l.v. / 2π = (6.0 ÷ 8.2) (units / rad),

where N _lv - the number of blades in the blade rim of the impeller of the second stage of the KND rotor.

The blades 88 of the impeller of the second stage (Fig. 8) contain each shank 89 and feather 90 with a convex-concave profile formed by a concave trough and a convex back, conjugated by the input and output edges 91 and 92. The feather 90 of the blade 88 is made with a spiral twist about the axis pen, a variable adjustment pen angle γ _mouth profile settings pen defined as the angle between the common tangent connecting the inlet and outlet edges 91 and 92 forming a chord of the profile 93, 94 and the front line of the lattice plane unfolding profiles CYLINDRICAL cross section of the scapular crown, having the value γ _mouth in the root section of the pen = (65,2 ÷ 73,2) °, and in a peripheral section of γ value _ust.p. = (35.8 ÷ 43.8) °.

The feather 90 of the blade 88 is made with a thickness varying in width and height of the feather, defined in cross section as the difference between the heights of the back and the trough relative to the chord connecting the input and output edges 91 and 92 of the feather of the blade. The input and output edges 91 and 92 of the pen 90 are made sailing diverging to the peripheral end face 95 of the blade with a gradient of G _u an increase in the connecting chords equal to

G _u = (L _p.h.- L _k.h. ) / H _cp = (7.4 ÷ 10.7) ⋅10 ^-2 [m / m],

where L _p.h. - the length of the peripheral chord connecting the input and output edges of the feather blade in a conditional plane perpendicular to the axis of the spiral twist of the feather blade; L _c.h. - the same, the length of the root chord; N _cf - the average height of the feather blades.

The blade 88 is made with a ratio of the height h of the input edge 92 of the profile of the pen 90 to the middle chord L _cf. dividing the area of the working surface of the pen into two equal parts, comprising h / L _cf. = (1.83 ÷ 2.63).

Each blade 88 of the blade rim of the impeller of the second stage of the rotor is equipped on both sides of the pen 90 with an anti-vibration shelf 96 located in the region of one third of the height of the pen from the peripheral end 95 of the blade pen.

The feather 90 of the blade 88 of the blade of the impeller of the second stage of the low pressure rotor is made with a trough facing concavity in the direction of rotation of the rotor counterclockwise (view in np - direction of flight), and with the back of the feather facing in convex direction against rotation of the rotor and in the direction of rotation clockwise (view in np).

Variant feather 90 of the blade 88 of the blade root of the impeller of the second stage of the low pressure rotor is made with a trough facing concavity in the direction of rotation of the rotor clockwise (view in np), and with the back of the feather convex towards the side of rotation of the rotor and against the direction clockwise rotation (np view).

An example implementation of the invention

The rotor shaft of the low-pressure compressor of a gas turbine engine is made of a four-stage, drum-disk design, including impellers according to the number of rotor steps, each consisting of a disk and blades forming a blade ring of the corresponding stage.

The disks 9, 10, 11, 12 of each stage of the low pressure rotor rotor shaft are made by die forging from a forgings in the form of a single element, which includes a solid massive hub 15, the web 16 and the rim 14. The profiles of the web 16 and the hub 15 are formed by turning the workpiece with subsequent polishing. On the outer side of the rim 14 is performed by pulling the locking grooves for mounting the blades of the impellers. The rims 14 of the disks form the front and rear shelves 71 relative to the middle plane of the web 16. Directly by the shelves 71 or through the cylindrical spacers 69, 70, the disks are combined in the power shell of the drum-disk design of the rotor shaft, communicated with the supports of the low-pressure rotor and with the high pressure pump with the possibility of transmission from the latter torque.

The assembled compressor shaft has the following geometric parameters: total length - 605 mm, drum-disk construction length - 378 mm, inlet diameter along the flowing part - 364 mm, outlet diameter on the flowing part - 528 mm, average diameters on the flowing part of the disks 1, 2 , 3, 4 respectively 391, 477, 513 and 528 mm. The blade wheel of the impeller of each of the stages of the rotor is formed by blades that are installed in the grooves of the shaft disk. The number of blades in the blade crowns of the impellers is made increasing from the first to the third stage of the rotor along the flow of the working fluid and in the blade crown of the second stage of the Republic of Kazakhstan is made to exceed the number of blades in the blade crown of the impeller of the first stage by not less than 20%, in the third not less than by 50%. The angle of rotation of the air flow, i.e. the degree of increase in pressure in the crown and, accordingly, the stall border. The greater the density, the greater the maximum flow deflection angle. An increase in the density of the lattice is favorable for increasing the range of operation of the crown without a developed separation of the flow, but leads to an increase in profile losses.

When mounting the front support 6 of the rotor shaft of the low-pressure compressor of a gas turbine engine, a roller bearing 19 with inner and outer rings 45 and 40 with rolling bodies in the form of rollers and a separator between them is used. The outer ring 40 is installed in the roller bearing housing 21, combined with an annular element 34 for separating the oil cavity 31 and the venting cavity 32 provided with a maze cover 37. Behind the inner ring 45 of the roller bearing 19, the scallop rings 46 and 47 of the labyrinths are sequentially mounted on the cylindrical portion 42 of the front axle 41. The scallop maze ring 46 separates the oil cavity 31 and the vent cavity 32. The scallop ring 47 of the labyrinth separates the vent cavity 33 with the boost air cavity 34. The third scallop ring 48 of the labyrinth is mounted on the conical diaphragm 44 of the pin 41, movably limiting in combination with the cap 39 of the labyrinth the cavity 33 of the pressurization of air.

The housing 20 of the front support is connected to the housing 21 of the roller bearing 19 and is enclosed on the side surface by an adjacent ring element of the hub 22 of the inner housing 23 of the BHA KND with the formation of two compact peripheral annular cavities 24 and 25 between them. An elastic ring 26 is installed in the annular cavity 24 and filled liquid type aviation engine oil. The elastic ring 26 is made of steel in the form of a tape 27. The elastic ring 26 is provided with one-sided protrusions 28, 29 made around the perimeter of the ring tape from the outer and inner sides of the ring, mutually offset around the circumference through one with an angular frequency of 1.6 [units / rad]. The tape 27 of the ring 26 is provided with perforation in the form of groups of holes in the amount of 4 pieces per section between two adjacent protrusions. The annular cavity 25 contains an element of elastic damping of the vibrations of the rotor shaft, made directly in the body of the rotor shaft support body in the form of an “squirrel wheel” type ring structure including a system of longitudinally oriented elastic beams 30 separated by longitudinal slots.

The end sleeve 49 of the front axle 41 of the rotor shaft is made with a housing in the form of a cylinder of variable diameter, the conditional surface described which is congruently inscribed in the mating inner surface of the axle. The wall of the body of the sleeve 49 is turned in one piece with a sealed diaphragm 51, in which it is made integrally protruding on both sides of the diaphragm glass 54. The back of the glass 54 is made with an insert splined sleeve 55 with a flexible pump 56 of the pumping oil pump installed therein. The sleeve 49 is fixed against rotation in the cup body 54 with an insert pin. An annular groove of the oil manifold and an annular groove for the o-ring are made in the housing of the sleeve 49 from the outside.

When mounting the rear support of the rotor shaft (not shown in the drawings) of the low-pressure compressor of a gas turbine engine, the ring holders of the cover of three labyrinths separating the oil cavity and the venting cavity are flanged onto the flange of the support housing. The entire package of parts is tightened with fixing screws. On the cylindrical component of the KND shaft, the scallop rings of two labyrinths are sequentially installed. Then the previously assembled support housing is lowered onto the shaft. After installing the support housing, the assembled ball bearing is installed on the shaft, after which the package of parts installed on the shaft is tightened with an external coupling element. After tightening the nut, the fixing screws of the outer ball bearing ring are installed. Next, a gear (not shown) of the drive of the speed sensor unit is mounted on the shaft and fixed on the shaft with its own nut. Subsequently, a block of gears for driving speed sensors with an oil-injecting nozzle mounted on them is mounted on the corresponding flanges of the support housing, after which a drive spring is installed in the internal cavity of the shaft.

The low-pressure gas turbine compressor operates as follows.

When the engine starts, the rotor shaft, which combines the disks 9, 10, 11, 12 of the impellers of the four stages of the low pressure switch, is driven by the torque transmitted from the low pressure pump. From the low-pressure turbine (LPH), the rotational force (torque) is transmitted through the cylindrical component to the drum-disk part of the compressor. The torque from the low pressure pump is transmitted through the spring to the cylindrical component of the rotor. The cylindrical component of the rear shaft support and the coupling bolt, spline and coupling pipes located inside it practically do not have elements asymmetrically located relative to the axis of rotation of the shaft, which allows them to avoid natural oscillations during rotation.

From the cylindrical component of the rear support, the torque is transmitted to the drum-disk component, which, among other things, interacts with the fixed stator part of the rear support of the CPV shaft through a system of three labyrinths of seals. The labyrinths of seals prevent particles of oil from entering the oil cavity into the drum-disk part of the low pressure oil that works with the air flow.

Oil from an open reservoir under the influence of centrifugal forces is supplied and, through a system of longitudinal and radial channels, the cutting fluid enters the rolling element of the ball bearing to the ring of the labyrinth of the oil cavity. Thus, the stator and rotor parts of the rear support interact in a single oil medium, which, as a result, undergoes intensive mixing.

The rims 14 of the disks 9, 10, 11, 12 of four stages combined into the power drum-disk component of the rotor shaft of the low pressure rotor include four blades of the impellers. As a result, the flow of the working fluid in the CPV is forced. At the same time, the KND rotor shaft ensures the stability of the design form and the position of the disks of all stages in the drum-disk structure at all possible operating modes of the turbojet engine due to the perception by the shaft sheath of the combination of loads arising during the compressor operation and transfers radial and axial through the conical ring elements loads on the rotor shaft bearings with less energy loss and lower vibrations.

When the shaft rotates, the oscillations of the rotor are damped by the elastic-hydraulic system of the front support, which includes an elastic ring 26 enclosed in an annular cavity 24 filled with engine oil under pressure. With dynamic radial vibrational pressure of the shaft on the elastic ring 26 operating in the compression zone as an elastic curvilinear beam on two supports, part of the vibrational energy is damped due to the elastic resistance of the ring tape 27, the vibrational energy absorbing the vibrational energy is structurally slowed down from the compression zone into the discharge zone through calibrated holes , which also extinguishes the energy of vibration of the shaft. When transferring the pressing of the shaft to other parts of the ring 26, the oscillation damping process is repeated, and in the previous zone, the fluid return flow, which is also structurally slowed down by the ring ribbon perforation, also creates additional damping of the shaft oscillations.

In the other annular cavity 25 of the bearing housing containing the system of elastic beams 30, during the rotation of the shaft and the dynamic change of rotation modes, the critical frequencies of the shaft oscillations change and through the system of beams the critical frequencies are output below the limit of the range of operating modes of the shaft, thereby improving safe operation compressor. The stator part of the rear support of the rotor shaft of the low pressure rotor is fixed around the perimeter in the intermediate motor housing and through the ball bearing ensures the stability of the rotor part when the shaft rotates relative to the axis of rotation of the shaft.

Thus, by improving the design and aerodynamic parameters of the disks of all stages, combined into a drum-disk design of the rotor shaft, they increase the efficiency and expand the range of the gas-dynamic stability modes of the low-pressure motor, as well as reduce the material consumption and increase the bending stiffness of the rotor and the maximum allowable stresses in the elements drive. Due to the structurally designed housing of the front support of the rotor shaft with an elastic ring installed in the housing with an improved system for damping the vibrations of the rotor shaft, they expand the range of stable operation modes of the engine with damping the rotor shaft vibrations without entering the resonant frequencies, and increase the life of the compressor and the engine as a whole . Due to the structurally designed housing of the rear support of the rotor shaft with an installed cascade of oil cavity seals, sequentially including three labyrinth seals, they provide improved operation of the lubricating-cooling system of the rear support, thereby increasing the efficiency, increasing the safe operation and resource of the compressor and the engine as a whole in the process gas turbine engine operation, including as part of gas pumping units for gas transportation or a gas turbine power plant.

Claims (30)

1. The low-pressure compressor (KND) of the double-circuit twin-shaft gas turbine engine (GTE) of the aviation type, characterized in that it is made of an axial, not more than four-stage, endowed with an input guide apparatus (VNA) having a housing and power profiled racks equipped with adjustable rotary flaps, and also endowed with a VND stator housing connected to the VNA, in which the blades forming the blade crowns of the guide vanes (ON) are installed, respectively, of the first, second and third stages of the stator and the image the blades of the double straightening apparatus of the blades of the fourth stage of the stator, the KND has front and rear bearings of the rotor shaft, the first of which is fixed in the VNA KND housing, and the second in the intermediate housing (PC) of the engine, and the KND rotor with the shaft is installed in the said supports, including drum-disk and cylindrical components, the first of which is endowed with impellers according to the number of rotor steps, each consisting of a disk and blades forming a blade ring of the corresponding stage; the front support of the KND rotor shaft is made containing a roller bearing separating the support into the stator and rotor parts, and is equipped with a system of elastic-hydraulic damping of the vibrations of the rotor shaft, while the stator part includes a support housing that is connected to the roller bearing housing and is surrounded by an annular element of the hub of the internal housing of the KND KND with the formation two compact annular cavities, one of which is filled with liquid and provided with an elastic ring to ensure damping of the oscillations of the shaft by the elastic ring and replace dlenie fluid flows through the wall of the ring belt, which elastic ring is provided on both sides of the projections are mutually offset circumferentially through one angular frequency γ _v.u.k. in the range of γ _w.s. = (2.55 ÷ 3.82) [u / rad], and the ring tape is provided with perforations in the form of dispersed holes, in addition, the stator part of the support includes the forming ring elements of the cavities of pressurization, venting and oil with annular labyrinth covers fixed to them and the outer ring of the latter fixed in the roller bearing housing; the second of the annular cavity of the stator part of the support contains an element of elastic damping of the vibrations of the rotor shaft, made in the body of the support in the form of a ring structure of the “squirrel wheel” type, including a system of longitudinally oriented elastic beams separated by parallel slots, with elastic beams located around the perimeter of the support body with angular frequency γ _p.b.k. defined in the range of γ _bp = (7.2 ÷ 14.4) [units / rad], and the slots between them are made wider than the width of the beads by (1.1 ÷ 2.4) times; and the rotor part of the support includes a trunnion of the front support of the rotor shaft, consisting of a hollow cylindrical section equipped with at least one ledge, on which an inner ring of the roller bearing and two multi-row labyrinth rings are installed, which together with the maze response covers separate the oil and soufflé cavities, as well as the venting cavity and cavity of pressurization of air, the volume of which is limited by the third multi-crest ring of the labyrinth mounted on the conical diaphragm of the front axle forming with -cylindrical portion integrally and permanently connected to the drive shaft of the first stage rotor. 2. The low-pressure compressor according to claim 1, characterized in that the number of blades in the blade rims of the impellers is made increasing from the first to the third stage of the rotor along the flow of the working fluid and in the blade rim of the second stage RK is made larger than the number of blades in the blade rim of the impeller the first stage is not less than 20%, in the third - not less than 50%. 3. The low-pressure compressor according to claim 1, characterized in that the drum-disk component of the KND rotor shaft is made with a radial and angular configuration of the outer surface of the rims of the disks of the impellers of all stages, combined with the inner surface of the duct part of the engine on the axial section of the flow around the set of rims of the disks the rotor shaft by the flow of the working fluid, for which the disks are made with stepwise increasing along the working fluid in the conditional middle plane of the blade with the diameter of the flowing part, with the ratio of the diameters ditch (1.0) :( 1.1 ÷ 1.34) :( 1.18 ÷ 1.44) :( 1.21 ÷ 1.48) and with the inclination angles of the rims forming the surface configuration of the flowing part with smooth conjugation adjacent ends. 4. The low-pressure compressor according to claim 1, characterized in that the axle of the front support of the rotor shaft of the low-pressure rotor is equipped with an end sleeve with a flange for pressing the inner ring of the roller bearing and the scallop labyrinths located behind it to the ledge of the cylindrical portion of the axle, and the end sleeve of the axle contains a sealed diaphragm that separates the volume of the sleeve into the oil and air cavities, and in the diaphragm a protruding cup is made on both sides of the last, designed to establish a spline sleeve in which the drive shaft is mounted Yes, the pump for pumping oil from the oil cavity of the front support. 5. The low-pressure compressor according to claim 1, characterized in that the rear bearing support of the low-pressure rotor rotor shaft is made thrust and contains a ball bearing separating the support into the stator and rotor parts, while the stator part includes a bearing housing made integral with the ball bearing housing and passing at the ends, in the internal and external power rings of different diameters for detachable connections with mating flanges of the outer ring of the ball bearing and the intermediate housing of the engine, and the rotor part of the rear support includes the rear part of the conical diaphragm, one-piece connected to the third-stage disk of the drum-disk component of the KND rotor shaft, and the rear axle, which is detachably connected to the cylindrical shaft component, on which the ball bearing is mounted, two multi-combs of the labyrinths and a multifunctional external coupling element made with the formation of an open collector for collecting and pressurizing supply of cutting fluid to the rolling elements of the ball bearing and the labyrinth ring with access to the oil cavity, while installed e on the cylindrical component of the shaft, the multi-comb rings paired with the maze seal covers form movable seals of the boost, venting and oil cavities of the rear support, and the third multi-comb ring is located on the conical diaphragm of the rear shaft support and, together with the labyrinth seal cover, movably closes the front side boost 6. The low-pressure compressor according to claim 1, characterized in that the number of power profiled racks equipped with adjustable rotary flaps is adopted in the HPA KND expressed as a prime number of at least 17 and not more than 23 (units). 7. A low-pressure compressor of a double-circuit twin-shaft gas turbine engine of an aviation type, characterized in that it is made of an axial, not more than four-stage, endowed with an input guide apparatus having a housing and power profiled racks equipped with adjustable rotary flaps, and also endowed with a KND stator housing connected to the VNA, in which the blades forming the blade crowns of the guide vanes of the stator, respectively, of the first, second and third stages of the stator and forming the blade blade are installed ec dual flow straightener vanes fourth stator stage, the CPV has front and rear support, the first of which is fixed in the housing BHA CPV, and the second intermediate in the motor housing; in these bearings a KND rotor is installed with a shaft including a drum-disk and cylindrical components, the first of which is equipped with impellers according to the number of rotor steps, each of which consists of a disk and blades forming a blade ring of the corresponding stage, while the drum-disk component contains three sections , two of which, the first and second, are non-separable, while the first section from the engine input includes a pin connected to the front support of the rotor shaft, disks of the first and second stages and qi an indigenous spacer, the second section includes a third-stage disk connected to the axle of the rear support of the rotor shaft and a cylindrical spacer, and the third section consists of a fourth-stage disk, and the impeller disk of each stage is made in the form of a single element, including a rim, turning into a hub-reinforced web a Central hole, the rim of each disk is connected to the canvas with the formation of annular conical inclined shelves for power association with the rim of the disks of the previous and subsequent stages and n slots for rotor working blades that are uniformly distributed over the circumference and are inclined to the axis of the shaft, the radius R of the first stage disk _D1 from the rotor shaft to the outer surface of the rim in the central plane of the web (0,42 ÷ 0,61) from radius R _p.ch. the peripheral contour of the flowing part in the indicated plane, and the blade web of the first stage disk on the front side of the disk in the zone adjacent to the rim is equipped with a conical ring element located under it for power connection with the conical diaphragm of the axle of the front support, which is made with an angle β of inclining the generatrix to the axis the rotor shaft, exceeding the angle ϕ of inclination of the generatrix of the outer surface of the rim by Δ equal to Δ = (β-ϕ), defined in the range Δ = (39 ÷ 47) °. 8. The low pressure compressor according to claim 7, characterized in that the rear along the flow of the working fluid shelf of the rim of the disk of the first stage is developed before contact with the mating shelf of the rim of the disk of the next stage and is made to extend beyond the size of the pen of the working blade of the first stage to a width sufficient placing in the indicated shelf elements of the labyrinth seal, made with the possibility of interaction through the gap with the elements of the fixed end of the blade of the stator guide apparatus, providing interaction with the specified disk the first rotor stage in the working fluid. 9. The low-pressure compressor according to claim 7, characterized in that the outer surface of the rim of the disk of the first stage is made with an angle of inclination of the generatrix relative to the axis of the rotor shaft, coinciding with the angle of inclination of the generatrix of the internal contour of the flow part, the radius of which monotonously changes in the direction of flow of the working fluid with gradient radial expansion G _about defined in the range

, where R _max and R _min - the maximum and minimum radii of the outer surface of the rim of the disk, In _about - the axial width of the rim. 10. A low-pressure compressor of a double-circuit twin-shaft gas turbine engine of an aviation type, characterized in that it is made of an axial, no more than four-stage, endowed with an input guide apparatus having a housing and power profiled racks equipped with adjustable rotary flaps, and also endowed with a KND stator housing connected to the VNA, in which the blades forming the blade crowns of the guide vanes of the stator, respectively, of the first, second and third stages of the stator and forming the blade blade are installed the center of the double straightening apparatus of the blade of the fourth stage of the stator, while the low pressure switch has front and rear bearings, the first of which is fixed in the VNA KND housing, and the second in the intermediate engine casing; in these bearings a KND rotor is installed with a shaft including a drum-disk and cylindrical components, the first of which is endowed with impellers according to the number of rotor steps, each consisting of a disk and blades forming a blade ring of the corresponding stage, and the blade ring of the impeller of the first rotor stage is formed blades that are installed in the grooves of the rotor shaft disk with an angular frequency of γ _l.v. defined in the range of γ _l.v. = (5.1 ÷ 6.8) (u / rad), with the blades containing each shank and feather with a convex-concave profile formed by a concave trough and convex back, conjugated by the input and output edges, while the feather is made with a spiral twist relative to the axis of the pen, a variable adjustment pen angle γ _mouth profile settings pen defined as the angle between the common tangent connecting the inlet and outlet edges, forming a chord of the profile, and the frontal profile line grating in a planar reamer blade row cylindrical section, having the value γ _set in the root section of the pen = (67.5 ÷ 75.5) °, and in the peripheral section the value of γ _st. = (36.9 ÷ 44.9) °, moreover, the feather of the blade is made with a variable thickness and width of the feather, defined in cross section as the difference between the heights of the back and trough relative to the chord connecting the input and output edges of the feather of the blade, while the input and the output edges of the pen are made sailing diverging to the peripheral end of the blade with a gradient of G _yx increasing the chords connecting them, equal to G _yx = (L _p.x.- L _k.h. ) / H _cp = (8.4 ÷ 12.1) ⋅10 ^-2 [m / m], where L _p.x is the length of the peripheral chord connecting the input and output edges of the feather blade in a conditional plane perpendicular to the axis of the spiral twist of the feather blade; L _c.h. - the same, the length of the root chord; N _cf - the average height of the feather blades; in addition, the blade is made with the ratio of the height h of the input edge of the pen profile to the middle chord L _cp.x. , dividing the area of the working surface of the pen into two equal parts, comprising h / L _cp.x. = (2.18 ÷ 3.13). 11. The low-pressure compressor according to claim 10, characterized in that each blade of the blade rim of the impeller of the first stage of the rotor is equipped on both sides of the pen with an anti-vibration shelf located in the region of one third of the height of the pen from the peripheral end of the blade pen. 12. The low-pressure compressor according to claim 10, characterized in that the interlocking connection of the grooves of the rim of the disks of each stage with the shanks of the blades is made according to the dovetail type. 13. The low-pressure compressor according to claim 10, characterized in that the feather of the blade of the blade of the impeller of the first stage of the KND rotor is made with a trough facing concavity in the direction of rotation of the rotor counterclockwise (view in np - direction of flight), and with the back of the pen, convex to the side against the rotation of the rotor and in the direction of rotation of the clockwise direction (view in np). 14. The low-pressure compressor according to claim 10, characterized in that the feather of the blade of the blade of the impeller of the first stage of the KND rotor is made with a trough facing concavity in the direction of rotation of the rotor clockwise (view in np), and with the back of the pen turned convex to the side against the rotation of the rotor and against the direction of rotation of the clockwise direction (view in np). 15. The low-pressure compressor of a double-circuit twin-shaft gas turbine engine of an aircraft type, characterized in that it is made of an axial, not more than four-stage, endowed with an input guide apparatus having a housing and power profiled racks equipped with adjustable rotary flaps, and also endowed with a KND stator housing connected to the VNA, in which the blades forming the blade crowns of the guide vanes of the stator, respectively, of the first, second and third stages of the stator and forming the blade blade are installed the center of the double straightening apparatus of the blade of the fourth stage of the stator, while the low pressure switch has front and rear bearings, the first of which is fixed in the VNA KND housing, and the second in the intermediate engine casing; in these bearings a KND rotor is installed with a shaft including a drum-disk and cylindrical components, the first of which is equipped with impellers according to the number of rotor steps, each of which consists of a disk and blades forming a blade ring of the corresponding stage, while the drum-disk component contains three sections , two of which, the first and second, are non-separable, while the first section from the engine input includes a pin connected to the front support of the rotor shaft, disks of the first and second stages and qi an indigenous spacer, the second section includes a third-stage disk connected to the axle of the rear support of the rotor shaft and a cylindrical spacer, and the third section consists of a fourth-stage disk, and the impeller disk of each stage is made in the form of a single element, including a rim, turning into a hub-reinforced web a central hole, the rim of each disk being connected to the web to form annular conical inclined shelves and provided with grooves for rotor blades that are evenly distributed around the perimeter ru and are made inclined to the axis of the shaft, while the radius of the disk R _{d2 of the} second stage from the axis to the outer surface of the rim in the middle plane of the web is (0.54 ÷ 0.77) from the radius R of the _item the peripheral contour of the flowing part in the indicated plane, and the disk rim is made with an angle ϕ of the generatrix of the outer surface of the rim relative to the axis of the rotor shaft, ϕ = (12 ÷ 17) ° and identical to the axial angle relative to the same axis of the generatrix of the inner contour of the flowing part, in addition the disk of the second stage is made with the possibility of power association with the shelf of the rim of the disk of the first stage and through a spacer with the blade disk of the third stage. 16. The low-pressure compressor according to claim 15, characterized in that the cylindrical spacer is provided with a flange for detachable connection with the third-stage disk blade, while holes are made in the flange uniformly spaced around the perimeter of the flange with an angular frequency of Υ _f1 = (5.3 ÷ 7.9) [units / rad], in addition, the cylindrical spacer is made wide enough to accommodate the elements of the labyrinth seal, made with the possibility of interaction through the gap with the elements of the fixed end of the blade of the stator guide vane, echivayuschego engagement with the second drive rotor stage of the working fluid. 17. The low-pressure compressor according to claim 15, characterized in that the locking connection of the grooves of the rim of the disk of each stage with the shanks is made according to the dovetail type. 18. The low-pressure compressor according to claim 15, characterized in that the outer surface of the rim of the second-stage disk is made with an angle of inclination of the generatrix relative to the axis of the rotor shaft, coinciding with the angle of inclination of the generatrix of the internal contour of the flow part, the radius of which monotonously changes in the direction of flow of the working fluid with gradient radial expansion of G _{about 2} , defined in the range

where R _max and R _min - the maximum and minimum radii of the outer surface of the rim of the disk, B _about - the axial width of the rim. 19. A low-pressure compressor of a double-circuit twin-shaft gas turbine engine of an aviation type, characterized in that it is made of an axial, not more than four-stage, endowed with an input guide apparatus having a housing and power profiled racks equipped with adjustable rotary flaps, and also endowed with a KND stator housing connected to the VNA, in which the blades forming the blade crowns of the guide vanes of the stator, respectively, of the first, second and third stages of the stator and forming the blade blade are installed the center of the double straightening apparatus of the blade of the fourth stage of the stator, while the low pressure switch has front and rear bearings, the first of which is fixed in the VNA KND housing, and the second in the intermediate engine casing; in these supports, a KND rotor is installed with a shaft including a drum-disk and cylindrical components, the first of which is equipped with impellers according to the number of rotor steps, each of which consists of a disk and blades forming a blade ring of the corresponding stage, and the blade ring of the impeller of the second stage of the rotor is formed blades that are installed by shanks in the grooves of the rotor shaft disk with an angular frequency of γ _l.v. defined in the range of γ _l.v. = (6.0 ÷ 8.2) (u / rad), with the blades containing each shank and feather with a convex-concave profile formed by a concave trough and a convex back, conjugated by the input and output edges, while the feather is made with a spiral twist relative to the axis of the pen, a variable adjustment pen angle γ _mouth profile settings pen defined as the angle between the common tangent connecting the inlet and outlet edges, forming a chord of the profile, and the frontal profile line grating in a planar reamer blade row cylindrical section, having the value γ _set in the root section of the pen = (65,2 ÷ 73,2) °, and in a peripheral section of γ value _ust.p. = (35.8 ÷ 43.8) °, and the feather of the blade is made with a variable thickness and width of the feather, defined in cross section as the difference between the heights of the back and trough relative to the chord connecting the input and output edges of the feather of the blade, while the input and the output edges of the pen are made sailing diverging to the peripheral end of the blade with a gradient of G _yx increasing the chords connecting them, equal to G _yx = (L _p.x. -L _c.x. ) / H _cp = (7.4 ÷ 10.7) ⋅10 ^-2 [m / m], where L _p.x is the length of the peripheral chord connecting the input and output edges of the feather blade in a conditional plane perpendicular to the axis of the spiral twist of the feather blade; L _c.h. - the same, the length of the root chord; N _cf - the average height of the feather blades; in addition, the blade is made with the ratio of the height h of the input edge of the pen profile to the middle chord L _cp.x. , dividing the area of the working surface of the pen into two equal parts, comprising h / L _cp.x. = (1.83 ÷ 2.63). 20. The low-pressure compressor according to claim 19, characterized in that each blade of the blade rim of the impeller of the second stage of the rotor is equipped on both sides of the pen with an anti-vibration shelf located in the region of one third of the height of the pen from the peripheral end of the blade pen. 21. The low-pressure compressor according to claim 19, characterized in that the feather of the blade of the blade of the impeller of the second stage of the KND rotor is made with a trough facing concavity in the direction of rotation of the rotor counterclockwise (view in the np-direction of flight), and with the back of the pen, convex to the side against the rotation of the rotor and in the direction of rotation of the clockwise direction (view in np). 22. The low-pressure compressor according to claim 19, characterized in that the feather of the blade of the blade of the impeller of the second stage of the KND rotor is made with a trough facing concavity in the direction of rotation of the rotor clockwise (view in np), and with the back of the pen turned convex to the side against the rotation of the rotor and against the direction of rotation of the clockwise direction (view in np).

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