RU155498U1 - GAS-TURBINE ENGINE LOW PRESSURE ROTOR WHEEL BLADE - Google Patents

Abstract

1. The blade of the impeller of the fourth stage of the rotor, comprising a grooved disk, a low pressure compressor (LPC) of a gas turbine engine containing a flow part, having a low pressure turbine, a high pressure turbine and a power turbine, characterized in that the blade contains a feather, which is made with a radial axis, a convex-concave profile formed by a concave trough and a convex back, conjugated in the direction of flow of the working fluid by the input and output edges, and with a spiral twist of the profile along the height of the pen, and also a shank with a longitudinal axis, designed to be installed in any of the grooves of the fourth-stage impeller disk with 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 radial axis of the blade’s pen, which has α in the root section of the pen = (19.7 ÷ 32.3) °, and in the peripheral section of the pen, the value α = (52 ÷ 62) °, and the feather of the blade is made variable in width and height of the feather with a thickness defined in the cross section as the difference in height of the back and trough relative to conditional chord connecting the edges of the feather blade, the maximum thickness of the profile of the feather blade is made the largest in the root section and decreasing in height of the feather to the peripheral end with a gradient G equal to G = (C-C) / H = (l, 48 ÷ 1.76) 10 [m / m], where C · is the maximum thickness of the root section of the blade feather profile; C is the maximum thickness of the peripheral section of the blade feather profile; H is the average height of the blade feather. 2. The impeller blade of the fourth stage of the rotor according to claim 1, characterized in that the blade is made with the angle of the profile of the pen relative to the axis of the rotor,

Description

The utility model relates to the field of aircraft engine manufacturing, namely, to low-pressure axial compressors of aircraft gas turbine engines.

Known profiled compressor blade for the impeller disk having axial, tangential and radial orthogonal axes, containing high and low pressure sides, extending in the radial direction from the shank to the apex and in the axial direction between the front and rear edges, cross sections having corresponding chords and bending lines extending between the leading and trailing edges, and centers of gravity aligned along a pivot axis having a double bend. The low pressure side is curved along the trailing edge near the liner to reduce the separation of the flow on it (RU 2000130594 A, publ. 01.27.2003).

Known compressor blades, including a feather and a shank. The shank of the blade is located horizontally, and the feather is connected to the shank through an intermediate element - the leg. Between the leg and the feather there is a shelf forming the engine flow part (NN Sirotin, AS Novikov, AG Paykin, AN Sirotin. Fundamentals of designing the production and operation of aircraft gas turbine engines and power plants in the CALS system technologies. Book 1. Moscow. Science 2011. p. 257-263).

The disadvantages of the known solutions include the uncertainty of achieving effective interaction of the blades 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 pen and the angular installation of the blades in the impeller of the fourth stage of the rotor, as well as the difficulty of obtaining a compromise combination of increased values of efficiency, gas-dynamic stability (GDU ) compressor and, as a consequence, the difficulty of ensuring optimal dynamic strength and Vyshen blade resource.

The objective of the utility model is to develop the blades of the impeller of the fourth stage of the rotor of the low pressure compressor (KND) of the gas turbine engine (GTE) with improved structural and aerodynamic parameters of the spatial configuration and the stiffness of the feather blade, providing the possibility of increasing the flow rate of the compressible working fluid - air in the fourth stage at all engine operating modes, as well as an increase in gas-dynamic stability and resource without increasing the material consumption of the blade.

The problem is solved in that the impeller blade of the fourth stage of the rotor, including the grooved disk, a low-pressure compressor of a gas turbine engine containing a flow part, which is limited along the peripheral contour of the engine casing having a low pressure turbine (HPH), high pressure turbine (HPD) and a power turbine (ST), according to a utility model, comprises a feather, which is formed with a radial axis, a convex-concave profile, formed by a concave trough and a convex back, mated in the direction the working fluid flow inlet and outlet edges, and a helical twist of the profile height of the pen, as well as a shank with a longitudinal axis intended to be installed in any of the grooves of the impeller disc of the fourth stage with providing angle α _{to the} profile settings of the pen to the rotor axis in the projection onto the conditional axial plane of the rotor normal to the radial axis of the feather of the blade with α _k = (19.7 ÷ 32.3) ° in the root section of the pen, and α _p = (52 ÷ 62) ° in the peripheral section of the pen, and the pen the blades are made variable in width and height of the pen thickness, defined in cross-section as the difference backrest heights and troughs relative to the conventional chord joining the edge of the blade, the maximum thickness of the profile of the blade is made greatest at the root section and decreasing in height to the peripheral end of the pen with a gradient G _{of fuel equivalent} equal to

G _ut = (C _to -C _p ) / H _cf = (1.48 ÷ 1.76) · 10 ^-2 [m / m], where

where C _to - the maximum thickness of the root section of the profile of the pen blade;

With _p - the maximum thickness of the peripheral section of the profile of the pen blade;

N _cf - the average height of the feather blades.

In this case, the blade can be made with the angle of the profile of the pen relative to the axis of the rotor, increasing in height of the blade with a radial distance from the said axis of the rotor with a gradient of G _u.p changes in the specified angle of installation of the profile, which has a projection on the conditional axial plane of the rotor with values in the range

G _U.P. = (α _π -α _k ) / H _cf = (151.7 ÷ 274.0) [deg / m],

where α _κ is the projection of the angle of the profile of the pen in the root section of the blade relative to the axis of the rotor on the conditional axial plane of the rotor, normal to the radial axis of the pen of the blade; α _p - projection of the angle of the profile of the pen in the peripheral section of the blade relative to the axis of the rotor on the conditional axial plane of the rotor, normal to the radial axis of the pen blade; N _cf - the average height of the feather blades.

The blade blade can be made with input and output edges diverging to the peripheral end face with a gradient of increasing chords G _u.x. ,

G _u = (L _p.h.- L _k.h. ) / H _cp = (2.2 ÷ 3.2) · 10 ^-2 [m / m],

where L _p.x is the length of the peripheral chord connecting the input and output edges of the blade feather in a conventional plane parallel to the axial plane of the rotor and the normal radial axis of the blade feather; L _c.h. - the length of the root chord connecting the input and output edges of the feather blade in a conventional plane parallel to the axial plane of the rotor and the normal radial axis of the feather blade; N _cf - the average height of the feather blades.

The blade feather can be made with a convex-concave profile with a concave trough facing concavity in the direction of rotation of the rotor counterclockwise (view along the np - direction of flight) and with a convex back of the feather facing in convexity towards the side of rotation of the rotor and in the direction of rotation clockwise, while the chord connecting the input and output edges of the pen in the root zone forms, with the rotor axis, an angle α _{to the} installation of the profile of the pen of at least the angle α _{0 of the} installation of the shank of the blade in the projection onto the said conventional plane.

The blade feather can be made convex-concave with a concave trough facing concave in the direction of rotation of the rotor in a clockwise direction (view in n.p.) and with a convex back of the feather facing in convexity in the direction of rotation of the rotor and counterclockwise rotation direction (view by n.p.).

The peripheral end face of the blade pen is beveled with the repetition of the curvature of the inner surface of the engine duct in the zone of the fourth KND with a decrease in the radius in the direction of flow of the working fluid with a height sufficient for unobstructed rotation of the impeller blades in the KND rotor of the engine.

The technical result achieved by the above set of essential features of the impeller blades of the fourth stage of the rotor KND GTE rotor consists in increasing the efficiency and expanding the range of compressor gas-dynamic stability modes by 2.2% with a 2-fold increase in the resource of the blade.

The essence of the utility model is illustrated by drawings, where:

in FIG. 1 shows a blade of the impeller of the fourth stage, side view;

in FIG. 2 - the blade of the impeller of the fourth stage, top view;

in FIG. 3 - feather blades of the impeller of the fourth stage, a cross section;

in FIG. 4 - a fragment of the disk of the impeller of the fourth stage with grooves for installing the shanks of the blades, frontal projection.

The gas turbine engine includes a low pressure compressor, a low pressure turbine, a high pressure compressor, a high pressure turbine and a power turbine. The blade of the impeller of the fourth stage of the rotor of the low pressure compressor of the gas turbine engine, containing the flow part, limited by the peripheral contour of the engine housing, contains a feather 1 and a shank 2. The feather 1 of the blade is made with a radial axis, a convex-concave profile formed by a concave trough 3 and a convex back 4 mated in the direction of flow of the working fluid by the input and output edges 5 and 6, respectively, and with a spiral twist of the profile along the height of the pen 1. The shank 2 is made with a longitudinal axis and is intended for installation in Juba of the grooves 7 Disc 8 impeller fourth stage ensuring the angle α _{to the} profile settings of the pen 1 to the rotor axis in a projection on a notional axial rotor plane normal to the radial pen axis 1 of the blade having a root section of the pen 1 the value of α _k = (19 , 7 ÷ 32.3) °, and in the peripheral section of pen 1, the value α _p = (52 ÷ 62) °.

The feather 1 of the blade is made variable in width and height of the feather thickness, defined in cross section as the difference between the heights of the back 4 and trough 3 relative to the chord 9 connecting the input and output edges 5 and 6 of the feather 1 of the blade.

The maximum thickness of the profile of the pen 1 of the scapula is made the largest in the root section and decreasing in height of the pen 1 to the peripheral end face 10 with a gradient of G _weight equal to

G _ut = (C _to -C _p ) / N _cf = (1.48 ÷ 1.76) · 10 ^-2 [m / m],

where C _to - the maximum thickness of the root section of the profile of the pen 1 of the scapula;

With _p - the maximum thickness of the peripheral section of the profile of the pen 1 of the scapula;

H _cf - the average height of the pen 1 scapula.

The blade is made with the angle of installation of the profile of the pen 1 relative to the axis of the rotor, increasing along the height of the blade with a radial distance from the said axis of the rotor with a gradient of G _y.p. changes in the specified angle α _{to the} installation profile, which has a projection on the conditional axial plane of the rotor with values in the range

G _U.P. = (α _π -α _k ) / H _cf = (151.7 ÷ 274.0) [deg / m],

where α _to - the projection angle of the profile of the pen 1 in the root section of the blade relative to the axis of the rotor on the conditional axial plane of the rotor, normal to the radial axis of the blade; α _p - the projection angle of the profile of the pen 1 in the peripheral section of the blade relative to the axis of the rotor on the conditional axial plane of the rotor, normal to the radial axis of the blade; Η _cf - the average height of the pen 1 scapula.

The feather 1 of the blade is made with the input and output edges 5 and 6, respectively, diverging to the peripheral end face 10 with a gradient of increase in the chord G _u.kh. ,

G _u = (L _p.h. -L _k.h. ) / H _cf = (2.2 ÷ 3.2) · 10 ^-2 [m / m],

where L _p.x is the length of the peripheral chord connecting the input and output edges 5 and 6 of the pen 1 of the blade in a conventional plane parallel to the axial plane of the rotor and the normal radial axis of the feather of the blade; L _c.h. - the length of the root chord connecting the input and output edges 5 and 6 of the pen 1 of the blade in a conditional plane parallel to the axial plane of the rotor and the normal radial axis of the blade feather; H _cf - the average height of the pen 1 scapula.

The feather 1 of the blade is made convex-concave profile. The concave surface of the pen profile in the form of a trough 3 is made by facing concavity in the direction of rotation of the rotor counterclockwise (view in np - direction of flight). The convex surface of the profile of the pen 1, forming the back 4 of the pen, is made convex to the side against the rotation of the rotor and in the direction of rotation of the clockwise direction (view on n.p.). The chord 9 connecting the inlet and outlet edges 5 and 6 of pen 1 in the root zone 11 forms an angle α with the axis of the rotor projected onto said conditional plane _to set the profile of pen 1 to at least the installation angle α _{0 of} the shank 2 of the blade.

Variant feather 1 of the blade is made of a convex-concave profile with a concave surface - a trough 3, facing concavity in the direction of rotation of the rotor clockwise (view in n.p.) and with a convex surface forming the back 4 of feather 1, facing convex in the direction of rotation rotor and counterclockwise rotation direction (view on n.p.).

The peripheral end face 10 of the pen 1 of the blade is made beveled with a repetition of the curvature of the inner surface of the engine duct in the zone of the fourth stage of the low pressure valve with a decrease in the radius in the direction of flow of the working fluid with a height sufficient for unobstructed rotation of the blade of the impeller in the rotor of the low pressure sensor.

The blade of the impeller of the fourth stage of the rotor KND GTD 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 blank with local thickenings is performed by electric upsetting with local thickenings on the location of the shank 2. In the next step, the blank is subjected to general heating in an electric furnace to the state of thermoplasticity and hot die forging is performed using a stamp consisting of of two responding 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 4 of the pen 1 of the blade. The working surface of the other die half-matrix includes a section whose shape is made of the mating spatial surface of the trough 3 of the pen 1 of the scapula. After that, the blade is subjected to mechanical processing, including grinding the flap milling, pulling the shank 2.

The refinement of the streamlined surfaces of the profiles of the pen 1 is performed by milling with subsequent polishing.

The blade made in this way consists of a single pen 1 with a shank 2, made as a segment of the assembled ring of the blade ring of the impeller of the fourth stage of the rotor KND GTD.

The profile of the pen 1 of the scapula has the following geometric parameters:

- in the root section, the profile of the pen 1 of the scapula is made with a maximum thickness of the profile With _max = 4.16 mm; pen chord length - 49.8 mm; the angle α _{to the} installation of the profile of the pen 1 to the axis of rotation of the rotor in the projection onto the axial plane of the latter, normal to the axis of the pen blade, is 26.5 °;

- in the peripheral section, the profile of the feather blade is made with a maximum thickness of the profile With _max = 2.15 mm; pen chord length adopted 53.5 mm; the angle α _{κ of the} installation of the profile of the pen to the axis of rotation of the rotor in the projection onto the axial plane of the latter, normal to the axis of the pen blade, is 56 °;

- the average height H _cf pen profile 1 is 125.9 mm

The blade is made for fixing on the disk of the impeller of the rotor shaft by installing the shank 2 in the groove 7 of the rim of the disk 8.

When the compressor is operating, each blade of the impeller of the fourth stage of the KND rotor interacts with the working fluid, transferring the kinetic and potential energy to the latter. The result is a flow of a compressible working fluid directed towards the exit from the impeller rim of the impeller, which flows from the interscapular channels of the impeller rim of the rotor impeller to the blades and into the interscapular channels of the stator of the fourth stage stator. After alignment in the guiding apparatus, the flow then enters the inlet guiding apparatus of the high-pressure compressor.

In the process of implementation of the design of the impeller blade of the fourth stage of the KND rotor developed in a utility model, the technical result is achieved only when the blade is installed in the impeller with the profile of the pen 1 in the root section of the blade at an angle α _to the axis of the rotor in the projection onto the conditional axial plane of the rotor, normal to the radial axis of pen 1, in the specified angular range of values α _к = (19.7 ÷ 32.3) °, in combination with the simultaneous coordinated satisfaction of the matching conditions found in the utility model of geometric and aerodynamic parameters of the spatial configuration and their gradients of change along the height of the scapula. When assigning the angle α _to the root section of the blade, taken from the interval of values α _to = (19.7 ÷ 32.3) °, found in the utility model taking into account the installation angles of the pen profile of the previous stages of the compressor rotor, the highest values of efficiency, GDU compressor and blade life.

With a decrease in the angle α _to <19.7 °, the range of gas-dynamic stability of the compressor operation is significantly limited, the efficiency of the stage decreases and the risk of an accidentally dangerous disruption of the air flow from the convex back of the 4 blades with the resulting loss of HLD increases. With an increase in the angle α _to > 32.3 °, the risk of disruption of the air flow from the trough 3 of the pen 1 of the scapula increases and the efficiency decreases. In addition, with an increase in the angle α _to > 32.3 °, the voltage in the blade increases unjustifiably at all KND operation modes, which leads to a decrease in the resource, an increase in the material consumption of the blades, and ultimately to a heavier compressor and lower operational efficiency of the engine.

Similar processes take place with obtaining a positive result when observed and a negative one when going beyond the limits of the gradient ranges G in. Found in the utility model _. height H _cf pen 1 scapula. When performing three-dimensional profile of the blade with the gradient values G _{uniformizing parameter} <151.7 [deg / m], the range of GDU operation of the low pressure switch is significantly limited, the efficiency of the stage drops and the risk of an accidentally dangerous stall of the air flow from the convex back of the 4 blades with the resulting loss of the GDU increases. Increasing the ratio of the difference in the angles of installation of the chord 9 of pen 1 along the height of the scapula to the values of the gradient G _у.х. exceeding the upper limit of G _у.х. > 274.0 [deg / M], leads to an unacceptable decrease in the opening angle of the peripheral section 12 of the pen 1 of the blade, which in turn leads to a decrease in efficiency, a negative decrease in the range of the GDU of the compressor and an unacceptable mismatch of the fourth stage of the rotor with subsequent stages of the low pressure compressor .

Gradient G _WH the increase in the chord 9 of the pen 1 of the scapula along the average height H _{cp of the} pen 1 of the scapula characterizes the windage of pen 1, formed as a result of the angular divergence of the input and output edges 5 and 6 of pen 1 from the sleeve to the peripheral end 10.

Sailing of pen 1 along the height of the scapula is profiled according to the mentioned gradient G _{у.х of the} angular expansion of the chord 9 of the pen with the stated range of G. _у.х. = (2.2 ÷ 3.2) · 10 ^-2 [m / m], which provides a technical result of a utility model. A decrease in the ratio of the difference between the lengths of the peripheral and root chords of the pen 1 to the average height H _{cp of the} pen (G _uh <2.2 · 10 ^-2 ) leads to the formation of insufficient density of filling the peripheral annular section 12 of the cross-sectional area of the flowing part of the scapular crown with peripheral sections 12 pen 1 blades in a projection on a conditional plane normal to the axis of the rotor. As a result, an unacceptable decrease in the GDU stock occurs, a narrowing of the range of gas-dynamic stability of the compressor and a significant decrease in efficiency due to the possible disruption of the air flow from the back of the 4 blades. The increase (G _yx > 3.2 · 10 ^-2 ) leads to an unjustified increase in losses from friction of the flow on the profile of the pen 1 of the blade and to reduce the efficiency of the compressor.

The technical result of increasing the resource of the blade by two times is achieved subject to the condition of the ratio of the difference in thickness to the average height of the pen 1 of the blade, accepted within the specified range of the gradient values of G _weight found in the utility model. = (1.48 ÷ 1.76) · 10 ^-2 [m / m] due to the provision of the required static and dynamic stiffness with optimal material consumption of the profile of the pen 1 of the blade.

When the gradient values G _{reference fuel} <1.48 · 10 ^-2 [m / m] there is an excessive increase in material consumption due to the increase in the thickness of the peripheral part of the blade unreasonable by real load combinations, which leads to an overestimation of the mass of the compressor and a decrease in engine efficiency -

When the gradient values G _{reference fuel} > 1.76 · 10 ^-2 [m / m] the required increase in the resource of the blade 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 pen profile 1 with an unacceptable decrease in the maximum thickness of the profile in the most loaded peripheral part of the length feather scapula.

Thus, by improving the design and aerodynamic parameters of the blades of the impeller of the fourth stage, an increase in efficiency and an expansion of the range of regimes of gas-dynamic stability of the KND of the engine without increasing the material consumption of the blade are achieved.

Claims (6)

1. The blade of the impeller of the fourth stage of the rotor, comprising a grooved disk, a low pressure compressor (LPC) of a gas turbine engine containing a flow part, having a low pressure turbine, a high pressure turbine and a power turbine, characterized in that the blade contains a feather, which is made with a radial axis, a convex-concave profile formed by a concave trough and a convex back, conjugated in the direction of flow of the working fluid by the input and output edges, and with a spiral twist of the profile along the height of the pen, and a shank having a longitudinal axis designed to be placed in any of the impeller disk slots fourth stage ensuring the angle α _{to the} profile settings of the pen to the rotor axis in a projection on a notional axial rotor plane normal to the radial axis of the blade having a root section pen value α _к = (19.7 ÷ 32.3) °, and in the peripheral section of the pen, the value α _п = (52 ÷ 62) °, and the feather of the blade is made variable in width and height of the feather with a thickness defined in the cross section as the difference in height of the back and trough relatively conditional chords connecting the edges of the feather of the scapula, while the maximum thickness of the profile of the feather of the scapula is made the largest in the root section and decreasing in height of the pen to the peripheral end with a gradient of G _y.t. equal to G _y.t. = (C _to -C _p ) / N _sr = (l, 48 ÷ 1.76) · 10 ^-2 [m / m], where C _to · is the maximum thickness of the root section of the profile of the feather blade; With _p - the maximum thickness of the peripheral section of the profile of the pen blade; N _cf - the average height of the feather blades. 2. The blade of the impeller of the fourth stage of the rotor according to claim 1, characterized in that the blade is made with the angle of the profile of the pen relative to the axis of the rotor, increasing in height of the blade with a radial distance from the said axis of the rotor with a gradient of G _y.p. changes in the specified angle of installation of the profile, having in the projection onto said conditional axial plane of the rotor values in the range G _y.p. = (α _p -α _k ) / N _sr = (151.7 ÷ 274.0) [deg / m], where α _to is the projection of the angle of the profile of the pen in the root section of the blade relative to the axis of the rotor on the conditional axial plane of the rotor normal to the radial axis of the feather of the blade; α _p - projection of the angle of the profile of the pen in the peripheral section of the blade relative to the axis of the rotor on the conditional axial plane of the rotor, normal to the radial axis of the pen blade; N _cf - the average height of the feather blades. 3. The blade of the impeller of the fourth stage of the rotor according to claim 1, characterized in that the feather of the blade is made with input and output edges diverging to the peripheral end with a gradient of increasing chord G _y.x. , G _y.x. = (L _p.x.- L _k.h. ) / H _cp = (2.2 ÷ 3.2) · 10 ^-2 [m / m], where L _p.x. - the length of the peripheral chord connecting the input and output edges of the feather blade in a conventional plane parallel to the axial plane of the rotor and the normal radial axis of the feather blade; L _c.x. - the length of the root chord connecting the input and output edges of the feather blade in a conventional plane parallel to the axial plane of the rotor and the normal radial axis of the feather blade; N _cf - the average height of the feather blades. 4. The blade of the impeller of the fourth stage of the rotor according to claim 1, characterized in that the feather of the blade is made of a convex-concave profile with a concave trough facing concavity in the direction of rotation of the rotor counterclockwise (view in np - direction of flight), and with a convex back of the pen, convex to the side against the rotation of the rotor and in the direction of rotation of the clockwise direction, while the chord connecting the input and output edges of the pen in the root zone forms an angle α _{to the} installation of the rotor axis in the projection onto the said conventional plane Ofila pen not less than the angle α ₀ installation of the shank of the scapula. 5. The blade of the impeller of the fourth stage of the rotor according to claim 1, characterized in that the feather of the blade is convex-concave with a concave trough, facing concavity in the direction of rotation of the rotor clockwise (view in np) and with a convex 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). 6. The blade of the impeller of the fourth stage of the rotor according to claim 1, characterized in that the peripheral end of the feather of the blade is made beveled with repetition of the curvature of the inner surface of the engine duct in the zone of the fourth stage of the low pressure valve with a decrease in radius in the direction of flow of the working fluid with a height sufficient for unhindered rotation of the blades of the impeller in the rotor of the KND engine.

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