CN116163997A - Blade root slotting compressor blade grid based on incoming flow quantity control angle zone separation - Google Patents

Blade root slotting compressor blade grid based on incoming flow quantity control angle zone separation Download PDF

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CN116163997A
CN116163997A CN202211643210.3A CN202211643210A CN116163997A CN 116163997 A CN116163997 A CN 116163997A CN 202211643210 A CN202211643210 A CN 202211643210A CN 116163997 A CN116163997 A CN 116163997A
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blade
suction surface
separation
groove wall
channel
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茅晓晨
王昀煜
刘波
王何建
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Northwestern Polytechnical University
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Northwestern Polytechnical University
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses a blade root slotting compressor blade grid based on incoming flow quantity control angle zone separation, belonging to the technical field of internal flow control of impeller machinery; the root of the blade grid is internally provided with a channel, an air inlet of the channel is positioned at the front edge of the blade grid, an air outlet of the channel is positioned at the suction surface, and the front edge of the blade is communicated with the suction surface through the air inlet and the air outlet; the cross section of the channel is formed by a suction surface groove wall molded line and a pressure surface groove wall molded line, the cavity in the channel is formed by stretching two groove wall molded lines forming the cross section along the spreading direction, and the height of the cavity is determined according to the size of the actual angle separation range. The invention can effectively improve the kinetic energy of low-energy fluid on the suction surface through the high-momentum fluid of the incoming flow, increases the kinetic energy of the low-energy fluid on the suction surface, simultaneously blocks the interaction between the secondary flow on the end wall and the surface layer on the suction surface, obviously improves the separation phenomenon of the blade grid angle area, has good attack angle changing characteristic, and is a passive flow control technology with development potential.

Description

Blade root slotting compressor blade grid based on incoming flow quantity control angle zone separation
Technical Field
The invention belongs to the technical field of internal flow control of impeller machinery, and particularly relates to a blade root slotting compressor blade grid based on incoming flow quantity control corner region separation.
Background
The performance of the compressor as a core component of the aeroengine largely determines the performance of the aeroengine, so the importance of the compressor is self-evident. In recent years, compressors have been continuously developed in the direction of high efficiency and high load, but the compressor blades have been accompanied by a more severe working environment. In particular, complex corner flow, and the interaction of the vortex structures such as an end wall boundary layer, a blade boundary layer, trailing edge falling vortex, corner vortex, channel vortex and the like exists in the corner flow between the suction surface and the end wall, which is a main factor for causing the performance deterioration of the compressor. Therefore, it is very necessary to suppress the flow separation phenomenon in the corner region, to widen the effective working range of the aeroengine, and to improve the aerodynamic performance of the compressor.
At present, the flow control technology for the angular separation phenomenon of the compressor is mainly divided into two forms of active control and passive control. The common active control forms include boundary layer suction technology with a slotted end wall and a jet vortex generator with an open end wall; common vortex generators with passive control of leading edge leaflets, tip jet technology based on leading edge openings for incoming flow, and the like. The control methods obtain benefits to a certain extent, but the active flow control method needs additional auxiliary mechanisms, so that the complexity of the structure is increased, and the passive control method cannot consider the performance under the variable working conditions.
Disclosure of Invention
The technical problems to be solved are as follows:
in order to avoid the defects of the prior art, the blade root slotting air compressor blade grid based on the incoming flow quantity control angle zone separation is provided, no additional device is needed to be introduced, the kinetic energy of low-energy fluid on the suction surface can be effectively improved through the incoming flow high-momentum fluid, the interaction between the secondary flow of the end wall and the surface layer of the suction surface is blocked while the kinetic energy of the low-energy fluid on the suction surface is increased, the blade grid angle zone separation phenomenon is obviously improved, the blade root slotting air compressor blade grid has good attack angle changing characteristics, and the blade root slotting air compressor blade grid is a passive flow control technology with development potential. The structure controls the angular separation based on the fluid with high momentum, has the advantage of easier realization compared with the common active flow control technology, has good attack angle changing characteristic, and enriches the technical means for controlling the angular separation of the compressor.
The technical scheme of the invention is as follows: the utility model provides a blade root slotting compressor cascade based on come flow control angle district separation which characterized in that: the root of the blade grid is internally provided with a channel, an air inlet of the channel is positioned at the front edge of the blade grid, an air outlet of the channel is positioned at the suction surface, and the front edge of the blade is communicated with the suction surface through the air inlet and the air outlet; the cross section of the channel is formed by a suction surface groove wall molded line and a pressure surface groove wall molded line, the cavity in the channel is formed by stretching two groove wall molded lines forming the cross section along the spreading direction, and the height of the cavity is determined according to the size of the actual angle separation range.
The invention further adopts the technical scheme that: the spanwise height of the channel is 15% -25% of the height of the blade.
The invention further adopts the technical scheme that: the channel spanwise height is 20% of the leaf height.
The invention further adopts the technical scheme that: the groove wall profile of the suction surface of the section of the channel consists of two sections of tangent circular arcs, wherein the inlet angle of the first section of circular arc is the geometrical incidence angle of the blade grid, and the included angle between the outlet of the second section of circular arc and the suction surface is 5-8 degrees; the pressure surface groove wall molded line is formed by tangent three sections of circular arcs, the inlet angle of the first section of circular arc is the geometrical incidence angle of the blade grid, and the third section of circular arc outlet is designed based on the Coanda effect, so that jet flow is closer to the suction surface, and the capability of the suction surface low-energy fluid in resisting the reverse pressure gradient is enhanced.
The invention further adopts the technical scheme that: and the included angle between the second section of arc outlet of the groove wall molded line of the suction surface and the suction surface is 6 degrees.
The invention further adopts the technical scheme that: the width between the channels is controlled by a molded line, a structure of increasing and decreasing is adopted from the leading edge to the trailing edge, the throat parts of the leading edge are symmetrically arranged about the camber line of the blade profile, and the width is determined according to the actual size of the leading edge; the width of the outlet throat is equal to that of the front edge throat; the maximum width position is the midpoint position of the groove wall line of the suction surface, and the ratio of the maximum width to the width of the throat of the front edge is 2:1.
the invention further adopts the technical scheme that: the width of the front edge throat is 1% -1.5% of the chord length.
The invention further adopts the technical scheme that: the width of the leading edge throat is 1% of the chord length.
The invention further adopts the technical scheme that: the end point of the groove wall line is positioned on the suction surface of the blade, the position of the end point is determined according to the actual angle division range, and the end point is positioned after the angle division offline starting point and before the tail edge separation line.
The invention further adopts the technical scheme that: the axial length of the groove wall molded line of the suction surface is 70% of the axial chord length, and the axial length of the groove wall molded line of the pressure surface is 86.5% of the axial chord length.
Advantageous effects
The invention has the beneficial effects that: the invention discloses a blade root slotting compressor blade grid based on incoming flow quantity control angle zone separation, wherein an air entraining slot communicated with the front edge and the suction surface of a blade is formed at the root of the blade, the width of a slot is increased from the front edge to the tail edge, and then the slot is reduced. In order to prove the feasibility of the slotted blade cascade of the blade root, numerical verification is carried out on a certain pressure sound velocity plane blade cascade, and the result shows that the slotted blade cascade obviously improves the phenomenon of angular area separation of the blade cascade, reduces the loss of flow and has good attack angle changing characteristic.
Preferably, the included angle between the second section arc outlet of the groove wall line of the suction surface and the suction surface is set to be 5-8 degrees, so that huge blending loss can be caused by the overlarge included angle of the wall surface.
Preferably, the third section of arc outlet of the groove wall line of the pressure surface is designed based on the Coanda effect, so that jet flow is closer to the suction surface, and the capability of the suction surface for resisting the reverse pressure gradient of low-energy fluid is enhanced.
Preferably, the termination point of the groove wall profile is located after the angular separation off-line initiation point and before the trailing edge separation line, since the channel jet is most notable for effective control of the suction side separation vortex, and is most effective when the exit position corresponds to the vicinity of the position of the suction side separation vortex in the development and development stage.
Experiments prove that under different attack angle characteristics, the slotted vane cascade can still maintain good flow control effect, and the total pressure loss coefficient is respectively reduced by 6.47%, 11.21% and 12.13% at attack angles of 0 degrees, 2 degrees and 4 degrees, so that the stable working range of the compressor vane cascade is widened.
As shown in fig. 5, the slotted vane cascade significantly reduced the total pressure loss coefficient over the 0-30% vane height range as compared to the prototype vane cascade. The primary analysis is due to: the high momentum jet ejected from the channel improves the capability of the suction surface low energy fluid to resist the reverse pressure gradient, blocks the interaction between the end wall secondary flow and the suction surface auxiliary surface layer, prevents the suction surface low energy fluid from climbing on the suction surface, and realizes the purpose of inhibiting the separation of corner areas.
As shown in fig. 6 and 7, by comparing flow charts of the prototype blade cascade and the slotted blade cascade at 10% of the blade height, the slotted blade cascade can effectively reduce the separation area of the suction surface of the blade cascade, further reduce the loss caused by corner separation, realize the purpose of inhibiting corner separation, and improve the performance and stability of the compressor.
Drawings
FIG. 1 is a three-dimensional blade schematic of a blade root slotted compressor cascade based on incoming flow control angular separation.
FIG. 2 is a two-dimensional blade profile schematic of a blade root slotted compressor cascade based on incoming flow control angular separation.
Fig. 3 is a schematic diagram of prototype cascade geometry.
Fig. 4 is a graph comparing the total pressure loss coefficients of prototype and slotted cascades at different angles of attack for example one and example two.
Fig. 5 is a graph comparing the total pressure loss coefficients of a prototype cascade and a slotted cascade in the spanwise direction for an angle of attack of 4 deg. for an example.
Fig. 6 is a flow chart of an example blade root slotted compressor cascade blade height of 10% based on the separation of the incoming flow control angle zones.
Fig. 7 is a flow chart of a prototype cascade leaf height of 10%.
Reference numerals illustrate: 1. suction side groove wall profile (AC), pressure side groove wall profile (DG), leading edge throat (AD), maximum width position (BE), outlet throat (CF), 6. Channel spanwise height.
Detailed Description
The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Example one:
referring to fig. 1 to 2, the present invention is a blade root slotted compressor blade cascade based on incoming flow control angular separation, wherein the channels of the blade cascade are positioned in the root of the blade, and are formed by stretching one suction surface groove wall profile (AC) and the other pressure surface groove wall profile (DG), so that the front edge of the blade can be communicated with the suction surface, the height of the blade can be determined according to the size of the actual angular separation range, and in the present example, the spreading height of the channels is 8mm.
The channel wall profile consists of a plurality of continuous tangential circular arcs. In the example, the groove wall profile (AC) of the suction surface consists of an Arc (AB) and an arc (BC), wherein the inlet angle of a first section of the profile Arc (AB) is 42 degrees, and the included angle between the outlet of a second section of the profile arc (BC) and the suction surface is 6 degrees; the pressure surface groove wall molded line consists of three arc tangents, namely a pressure surface groove wall molded line (DG) consists of an arc (DE), an arc (EF) and an arc (FG), wherein the inlet angle of the first section of the molded line arc (DE) is 42 degrees, and particularly, the arc (FG) is designed based on the Coanda effect, so that jet flow is closer to the suction surface, and the capability of the suction surface low-energy fluid for resisting the reverse pressure gradient is enhanced.
The width between the channels is controlled by a profile, with a first increasing and then decreasing design from leading edge to trailing edge, where the leading edge throats (AD) are symmetrically arranged about the airfoil mean camber line to give better variable angle of attack characteristics and higher momentum jets. In this example, the width of the leading edge throat (AD) is 0.45mm; the width of the outlet throat (AD) is equal to the width of the front edge throat (CF); the maximum width position (BE) is a position close to the midpoint of the groove wall profile (AC); the maximum width (BE) width is 0.9mm.
The termination point C of the suction side pocket wall line (AC) is located after the start of the angular separation line and before the trailing edge separation line, and the termination point G of the pressure side pocket wall line (DG) is located before the trailing edge separation line. In this example, the suction side groove wall profile (AC) has an axial length of 26mm and the pressure side groove wall profile (DG) has an axial length of 32mm.
The implementation of the invention is applied to a certain subsonic plane blade cascade as shown in figure 3, and the main design parameters of the blade cascade are shown in the table
TABLE 1 principal design parameters for a planar blade grid of subsonic velocity
Figure BDA0004008607680000051
In order to verify the effect of the invention, numerical simulation is carried out on the prototype blade grating and the slotted blade grating, and the specific implementation process is as follows:
1. and (5) meshing the blade root channels by using an Autogrid5/IGG module in NUMECA.
2. Numerical calculation adopts NUMECA/FINE, jameson finite volume differential format is applied and combined with S-A turbulence model to solve se:Sup>A three-dimensional Reynolds average Navier-Stokes equation, space items adopt central differential format dispersion, time items adopt 4-order range-Kuttse:Sup>A method for iterative solution, and meanwhile an implicit residual error fairing method and se:Sup>A multiple grid technology are adopted to accelerate convergence process.
3. And obtaining a numerical simulation result and carrying out data processing to obtain the reduction percentage of the total pressure loss coefficient of the slotted blade cascade.
As shown in fig. 4, under different attack angle characteristics, the slotted vane cascade can still maintain good flow control effect, and the total pressure loss coefficient is respectively reduced by 6.47%, 11.21% and 12.13% at attack angles of 0 °,2 ° and 4 °, so that the stable working range of the compressor vane cascade is widened.
As shown in fig. 5, the slotted vane cascade significantly reduced the total pressure loss coefficient over the 0-30% vane height range as compared to the prototype vane cascade. The primary analysis is due to: the high momentum jet ejected from the channel improves the capability of the suction surface low energy fluid to resist the reverse pressure gradient, blocks the interaction between the end wall secondary flow and the suction surface auxiliary surface layer, prevents the suction surface low energy fluid from climbing on the suction surface, and realizes the purpose of inhibiting the separation of corner areas.
As shown in fig. 6 and 7, by comparing flow charts of the prototype blade cascade and the slotted blade cascade at 10% of the blade height, the slotted blade cascade can effectively reduce the separation area of the suction surface of the blade cascade, further reduce the loss caused by corner separation, realize the purpose of inhibiting corner separation, and improve the performance and stability of the compressor.
Example two:
to illustrate that the invention can be modified appropriately within its scope, the prototype cascade used in this example is identical to that used in example one, except that the individual parameters are changed, specifically: the channel has a spanwise height of 6mm, a leading edge throat (AD) width of 0.5mm, a maximum width (BE) width of 1mm, a suction side groove wall profile (AC) axial length of 24mm, and a pressure side groove wall profile (DG) axial length of 30mm.
As shown in fig. 4, under different attack angle characteristics, the slotted vane cascade can still maintain good flow control effect, and the total pressure loss coefficient is respectively reduced by 4.83%, 8.67% and 8.11% at attack angles of 0 °,2 ° and 4 °, so that the stable working range of the compressor vane cascade is widened.
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.
Although embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations may be made in the above embodiments by those skilled in the art without departing from the spirit and principles of the invention.

Claims (10)

1. The utility model provides a blade root slotting compressor cascade based on come flow control angle district separation which characterized in that: the root of the blade grid is internally provided with a channel, an air inlet of the channel is positioned at the front edge of the blade grid, an air outlet of the channel is positioned at the suction surface, and the front edge of the blade is communicated with the suction surface through the air inlet and the air outlet; the cross section of the channel is formed by a suction surface groove wall molded line and a pressure surface groove wall molded line, the cavity in the channel is formed by stretching two groove wall molded lines forming the cross section along the spreading direction, and the height of the cavity is determined according to the size of the actual angle separation range.
2. The blade root slotted compressor cascade based on incoming flow control angular zone separation of claim 1, wherein: the spanwise height of the channel is 15% -25% of the height of the blade.
3. The blade root slotted compressor cascade based on incoming flow control angular zone separation of claim 2, wherein: the channel spanwise height is 20% of the leaf height.
4. A slotted vane compressor cascade based on incoming flow control angular sector separation as claimed in any one of claims 1-3, wherein: the groove wall profile of the suction surface of the section of the channel consists of two sections of tangent circular arcs, wherein the inlet angle of the first section of circular arc is the geometrical incidence angle of the blade grid, and the included angle between the outlet of the second section of circular arc and the suction surface is 5-8 degrees; the pressure surface groove wall molded line is formed by tangent three sections of circular arcs, the inlet angle of the first section of circular arc is the geometrical incidence angle of the blade grid, and the third section of circular arc outlet is designed based on the Coanda effect, so that jet flow is closer to the suction surface, and the capability of the suction surface low-energy fluid in resisting the reverse pressure gradient is enhanced.
5. The blade root slotted compressor cascade based on incoming flow control angular zone separation of claim 4, wherein: and the included angle between the second section of arc outlet of the groove wall molded line of the suction surface and the suction surface is 6 degrees.
6. A slotted vane compressor cascade based on incoming flow control angular sector separation as claimed in any one of claims 1-3, wherein: the width between the channels is controlled by a molded line, a structure of increasing and decreasing is adopted from the leading edge to the trailing edge, the throat parts of the leading edge are symmetrically arranged about the camber line of the blade profile, and the width is determined according to the actual size of the leading edge; the width of the outlet throat is equal to that of the front edge throat; the maximum width position is the midpoint position of the groove wall line of the suction surface, and the ratio of the maximum width to the width of the throat of the front edge is 2:1.
7. the flow control angle zone separation based blade root slotted compressor cascade of claim 6, wherein: the width of the front edge throat is 1% -1.5% of the chord length.
8. The flow control corner separation-based vane root slotted compressor cascade of claim 7 wherein: the width of the leading edge throat is 1% of the chord length.
9. A slotted vane compressor cascade based on incoming flow control angular sector separation as claimed in any one of claims 1-3, wherein: the end point of the groove wall line is positioned on the suction surface of the blade, the position of the end point is determined according to the actual angle division range, and the end point is positioned after the angle division offline starting point and before the tail edge separation line.
10. The blade root slotted compressor cascade based on incoming flow control corner separation of claim 9, wherein: the axial length of the groove wall molded line of the suction surface is 70% of the axial chord length, and the axial length of the groove wall molded line of the pressure surface is 86.5% of the axial chord length.
CN202211643210.3A 2022-12-20 2022-12-20 Blade root slotting compressor blade grid based on incoming flow quantity control angle zone separation Pending CN116163997A (en)

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