CN112324713B - Airflow corner self-adaptive guide blade of axial-flow compressor and design method thereof - Google Patents
Airflow corner self-adaptive guide blade of axial-flow compressor and design method thereof Download PDFInfo
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- CN112324713B CN112324713B CN202011349147.3A CN202011349147A CN112324713B CN 112324713 B CN112324713 B CN 112324713B CN 202011349147 A CN202011349147 A CN 202011349147A CN 112324713 B CN112324713 B CN 112324713B
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
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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
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
Abstract
An airflow corner self-adaptive guide blade of an axial-flow compressor and a design method thereof belong to the technical field of design and manufacture of compressors. The airflow corner self-adaptive guide blade of the axial-flow compressor comprises a blade body, wherein the blade body is provided with a cylindrical cavity, an air inlet channel, an air suction channel and an air exhaust channel, the cavity penetrates through the blade body along the height direction of the blade body, the center of a radial section circle of the cavity is positioned on a camber line of the blade body and is close to one side of a front edge of the blade, the radius of the radial section circle of the cavity is 0.7-0.9 times of the radius of an inscribed circle of the blade body corresponding to the position of the center of the circle, a rotary pump is arranged in the cavity, the air inlet channel is arranged at the front edge of the blade and is communicated with the cavity, the air suction channel is arranged at a blade back and is communicated with the cavity, the air exhaust channel is arranged at a blade basin and is communicated with the cavity, the airflow corner self-adaptive guide blade of the axial-flow type compressor and the design method thereof do not need an external power source, simplify an adjusting system and reduce the power loss of an engine.
Description
Technical Field
The invention relates to the technical field of design and manufacture of a gas compressor, in particular to an airflow corner self-adaptive guide blade of an axial-flow gas compressor and a design method thereof.
Background
The variable guide vane is mainly a traditional mode for preventing surging, and the principle of the variable guide vane is to provide prewhirl for inlet airflow, so that the attack angle of the inlet airflow of the first rotor vane can be restored to be close to the designed state parameter, the airflow separation on the vane back is eliminated, and the surging phenomenon is avoided.
In the prior art, two methods are mainly used for changing the direction of airflow, namely, a variable-camber guide vane has the working principle that the tail part of the guide vane is twisted to ensure that inlet airflow generates prewhirl; and secondly, the guide vanes can be rotated, so that the whole vane body is twisted together, the flow area is reduced while the attack angle of the inlet airflow is changed, and the air flow is reduced.
When the traditional guide vane works, the air inlet efficiency needs to be sacrificed, so that the integral air inlet efficiency of the axial-flow type air compressor is reduced, an external power source is also needed, and the power of the whole engine can be lost.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides an axial-flow compressor airflow corner self-adaptive guide blade and a design method thereof, which do not need an external power source, simplify an adjusting system, reduce the power loss of an engine, and can change according to the flow velocity of incoming flow and automatically adjust the flow velocity of blowing and sucking air so as to relatively change the flow direction.
In order to achieve the purpose, the technical scheme of the invention is as follows:
an airflow corner self-adaptive guide blade of an axial-flow compressor comprises a blade body, wherein the blade body comprises a blade body and a tenon, and the blade body is provided with a cylindrical cavity, an air inlet channel, an air suction channel and an air exhaust channel;
the cavity penetrates through the blade body along the height direction of the blade body, the center of a radial section circle of the cavity is positioned on the camber line of the blade body and is close to one side of the front edge of the blade, and the radius of the radial section circle of the cavity is 0.7-0.9 time of the radius of an inscribed circle of the blade body corresponding to the position of the center of the circle; a rotary pump is arranged in the cavity and is rotationally connected with the tenon;
the air inlet channel is arranged on the front edge of the blade and communicated with the cavity, and the air inlet direction of the air inlet channel is the same as the incoming flow direction;
the air suction channel is arranged on the blade back and communicated with the cavity;
the exhaust passage is arranged on the leaf basin and communicated with the cavity, and the width of the exhaust passage is gradually reduced from the cavity to the leaf basin.
Furthermore, the radial section circle of the cavity takes the center of a first inscribed circle on the camber line of the blade body, close to one side of the front edge of the blade, as the center of a circle and takes 0.8 time of the radius of the first inscribed circle as the radius.
Furthermore, the number of the air inlet channels is 1-3, the height of each air inlet channel is one third of the blade height, the distance from the top end of each air inlet channel to the blade tip is equal to the distance from the bottom end of each air inlet channel to the blade root, and the width of each air inlet channel is not less than 2 mm.
Furthermore, the extension line of the channel wall of the suction channel close to one side of the tail edge of the blade passes through the center of the radial section circle of the cavity, the distance from one end, located at the blade back, of the channel wall of the suction channel close to one side of the tail edge of the blade to the center of the radial section circle of the cavity is 2-2.2R, and R is the radius of an inscribed circle at the center of the blade body; the channel wall of the suction channel close to the front edge of the blade is parallel to the channel wall of the suction channel close to the tail edge of the blade, and the width of the suction channel is more than or equal to 2mm, namely, the distance between the two channel walls is more than or equal to 2 mm.
Furthermore, the extension line of the channel wall of the exhaust channel close to one side of the tail edge of the blade passes through the center of the radial section circle of the cavity, the distance from one end, located at the blade basin, of the channel wall of the exhaust channel close to one side of the tail edge of the blade to the center of the radial section circle of the cavity is 2.3-2.5R, and R is the radius of an inscribed circle at the center of the blade body; the exhaust channel is obliquely arranged on a channel wall close to one side of the front edge of the blade, the minimum width of the exhaust channel is larger than or equal to 2mm, and the difference between the maximum width and the minimum width of the exhaust channel is 2-4 mm.
Furthermore, the rotary pump comprises a rotating shaft and a plurality of blades which are uniformly arranged along the circumferential direction of the rotating shaft, the diameter of the rotating shaft is 0.15-0.25 times of the diameter of the cavity, and the rotating shaft is rotationally connected with the blade tenon; the number of the blades is 8-10, the distance between each blade and the cavity wall of the cavity is smaller than 1mm, the bending degree of each blade is 15-30 degrees, and the bending direction of each blade is opposite to the rotating direction.
A design method of an airflow corner self-adaptive guide blade of an axial-flow compressor comprises the following steps:
s1, establishing a three-dimensional blade body model, wherein the three-dimensional blade body model comprises a blade tip, a blade root, a blade back, a blade basin, a mean camber line, a blade leading edge and a blade trailing edge;
s2, determining the center O and the radius of a cavity, and determining the center and the radius of a first inscribed circle on the upper surface of the blade tip close to one side of the front edge of the blade, wherein the center O of the cavity is the center of the first inscribed circle, and the radius of the cavity is 0.7-0.9 times of the radius of the first inscribed circle;
s3, designing a cavity, drawing a radial cross-section circle of the cavity on the upper surface of the blade tip according to the circle center O and the radius of the cavity, and penetrating the radial cross-section circle of the cavity through the whole three-dimensional blade body model from the blade tip to the blade root to obtain the cavity;
s4, designing an air inlet channel:
s4.1, establishing a two-dimensional model of the upper surface of the blade tip according to the three-dimensional blade body model with the cavity obtained in the step S3, wherein the two-dimensional model of the upper surface of the blade tip comprises a blade back, a blade basin, a mean camber line, a blade front edge, a blade tail edge and a cavity;
s4.2, establishing an outer flow field area of the two-dimensional model of the upper surface of the blade tip, wherein the outer flow field area comprises an inlet, an outlet, a first side face and a second side face; the vertical distance from the inlet to the outlet of the outer flow field area is greater than 3 times of the arc length of the blade, and the vertical distance between the first side face and the second side face of the outer flow field area is greater than 3 times of the width of the blade;
s4.3, constructing a non-structural grid of the two-dimensional model of the upper surface of the blade tip with the outer flow field area, setting an inlet of the outer flow field area as an inlet of a calculation domain, and setting an outlet, a side face I and a side face II of the outer flow field area as outlets of the calculation domain;
s4.4, setting pressure parameters of an inlet of the calculation domain and an outlet of the calculation domain, selecting a turbulence model as a k-epsilon turbulence model, obtaining a streamline cloud picture of an outer flow field area, and finding a stagnation point A of a front edge of the blade in the streamline cloud picture;
s4.5, on the two-dimensional model of the upper surface of the blade tip, extending the stagnation point A along the incoming flow direction, intersecting the cavity at a point B, and respectively biasing the line segment AB towards two sides by a1mm，a2mm，a3And (5) obtaining 6 line segments with two ends respectively intersected with the front edge of the blade and the cavity by mm distance, wherein the line segments are respectively as follows: a. the1B1、A2B2、A3B3、A4B4、A5B5And A6B6(ii) a The 6 line segments, the blade front edge and the cavity are enclosed to form3 closed curves, respectively: curve A1B1B2A2、A3B3B4A4And A5B5B6A6Respectively stretching 3 curves upwards from one third of the leaf height to two thirds of the leaf height to obtain three air inlet channels;
s5, designing an exhaust passage:
drawing a circle with the center O of the cavity as the center and 2.3 times of the radius of the cavity as the radius, and intersecting the leaf basin at a point C1Connection point C1The connecting line intersects with the cavity at a point D from the center of the cavity1To obtain a line segment C1D1(ii) a Segment C1D1Biasing towards leaf pot direction for 2mm, extending obtained line segment, and crossing with leaf pot at point C2(ii) a Then, the line segment C is divided1D1Biasing towards the leaf basin direction by 4mm, extending the obtained line segment, and intersecting the cavity at a point D2Will close curve C1D1D2C2Stretching upwards from one third of the leaf height to two thirds of the leaf height to obtain an exhaust channel;
s6, designing an air suction channel:
the center O of the cavity is used as the center of the circle, a circle is drawn by taking 2 times of the radius of the cavity as the radius, and the circle intersects with the leaf back at a point C3Connection point C3Intersects the center of the cavity and the connecting line with the cavity and a point D3The obtained line segment C3D3Biasing towards the leaf back for 2mm, extending the obtained line segment, and respectively crossing with the leaf back and the cavity at a point C4And D4Will close curve C3D3D4C4Stretching upwards from one third of the leaf height to two thirds of the leaf height to obtain an air suction channel;
s7, designing a rotary pump:
drawing a circle by taking the circle center O of the cavity as the circle center and taking 0.2 time of the radius of the cavity as the radius to obtain the section of the rotating shaft of the rotary pump; then, the circle center O of the cavity is taken as the circle center, a circle is drawn by taking 0.8 time of the radius of the cavity as the radius, and a point E is selected on the circle, connected with the hollowThe center O of the cavity biases the line segment EO to the direction of the leaf back by 1mm, and the line segment L1Intersects the section of the rotating shaft of the rotary pump at a point F1(ii) a Then, the line segment EO is biased to the direction of the leaf back by 1.5mm to obtain a line segment L2Line segment L2Cross-section of the rotary pump shaft at point F2(ii) a Then, the line segment EO is biased to the direction of the leaf back by 2mm to obtain a line segment L3(ii) a Passing points E and F1Make an arc and combine with L2Tangent to obtain an arc S1(ii) a Passing points E and F2Make an arc and combine with L3Tangent to obtain an arc S2(ii) a By arcs S1, S2 and F1F2The enclosed figure is a geometric model of one blade of the rotary pump, the geometric model of the blade is arrayed into 7 blades in an equiangular mode by taking the circle center O of the cavity as the circle center, the section of a rotating shaft of the rotary pump is stretched from the blade tip to the blade root, and the geometric models of 8 blades are stretched from the position 2mm away from the blade tip to the position 2mm away from the blade root to obtain the rotary pump;
s8, establishing a three-dimensional tenon model, connecting the three-dimensional tenon model with the three-dimensional blade body model of which the air inlet channel, the air outlet channel, the air suction channel and the rotary pump are designed, and rotatably connecting a rotating shaft of the rotary pump with the tenon.
Further, in step S2, the specific manner of determining the center and the radius of the first inscribed circle of the top surface of the blade tip on the side close to the leading edge of the blade is as follows: taking any 3 points on the front edge of the blade on the upper surface of the blade tip, respectively connecting the points on the two sides with the middle point to obtain two line segments which are intersected with the middle point, respectively making vertical center lines of the two line segments, taking the intersection point of the two vertical center lines as a circle center, taking the distance from the circle center to any one point of the 3 points as a radius to make a circle, and constraining the circle center to a middle arc line to obtain a first inscribed circle of the upper surface of the blade tip close to one side of the front edge of the blade, namely obtaining the circle center and the radius of the first inscribed circle of the upper surface of the blade tip close to one side of the front edge of the blade.
Further, in step S4.2, an inlet of the outer flow field region is perpendicular to the incoming flow direction, and an outlet of the outer flow field region is parallel to the inlet.
The invention has the beneficial effects that:
1) the invention designs and transforms the guide blades of the air compressor based on a flow control method, utilizes the incoming flow to drive the rotary pump to rotate, and adjusts the corner of the passing air flow by blowing and sucking air to the blade grid channel, thereby achieving the self-adaptive flow guiding function which can be automatically adjusted according to the change of the flow velocity of the inlet air flow;
2) the airflow corner self-adaptive guide blade is not required to be controlled by an external power source, can change the flow velocity direction of airflow flowing through the blade grid channel, and can be used for self-adaptive airflow guide according to the incoming flow;
3) the invention is improved on the basis of the original blade profile, the original blade profile does not need to be redesigned, and a new damage mode is not introduced;
4) compared with the traditional guide vane, the design method can avoid thermal deformation caused by heat exchange between the vane and the airflow, and simplifies the tolerance matching problem during vane processing;
5) the invention relates to a gas turbine and a gas compressor, which are widely applied to the fields of aviation, aerospace, energy and power industries and mainly aim at impeller machinery needing to change the angle of airflow.
Additional features and advantages of the invention will be set forth in part in the detailed description which follows.
Drawings
Fig. 1 is a schematic perspective view of an airflow corner adaptive guide vane of an axial-flow compressor according to an embodiment of the present invention;
FIG. 2 is a cross-sectional top view taken along line a-a of FIG. 1;
FIG. 3 is an enlarged view at B of FIG. 2;
fig. 4 is a schematic perspective view of a second axial-flow compressor airflow corner adaptive guide vane provided in an embodiment of the present invention;
FIG. 5 is a top view of an axial flow compressor airflow corner adaptive guide vane provided by an embodiment of the invention;
FIG. 6 is a top view of a prior art axial flow compressor guide vane (i.e., the vane body of the present invention);
FIG. 7 is a schematic view of a cascade channel flow field of an axial-flow compressor airflow corner adaptive guide vane of the invention;
FIG. 8 is a schematic design diagram of the outer flow field region provided by an embodiment of the present invention;
FIG. 9 is a schematic design of an intake air passage provided by an embodiment of the present invention;
FIG. 10 is a schematic design diagram of the exhaust and intake passages provided by an embodiment of the present invention;
fig. 11 is a schematic design diagram of a rotary pump according to an embodiment of the present invention.
Reference numerals in the drawings of the specification include:
1-cavity, 2-air inlet channel, 3-air outlet channel, 4-tenon, 5-blade front edge, 6-camber line, 7-air suction channel, 8-blade tail edge, 9-blade tip, 10-blade root, 11-blade basin, 12-blade back, 13-rotary pump, 14-blade body, 15-inlet, 16-outlet, 17-side I, 18-side II.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
In order to solve the problems in the prior art, as shown in fig. 1 to 11, the invention provides an airflow corner self-adaptive guide blade of an axial-flow compressor, which comprises a blade body 14, wherein the blade body 14 comprises a blade body and a tenon 4, and the blade body 14 is provided with a cylindrical cavity 1, an air inlet channel 2, an air suction channel 7 and an air exhaust channel 3;
the cavity 1 penetrates through the blade body 14 along the height direction of the blade body 14, the center of a radial section circle of the cavity 1 is positioned on the camber line 6 of the blade body 14 and close to one side of the blade leading edge 5, and the radius of the radial section circle of the cavity 1 is 0.7-0.9 time of the radius of an inscribed circle of the blade body 14 corresponding to the position of the center of the circle; a rotary pump 13 is arranged in the cavity 1, the rotary pump 13 is rotationally connected with the tenon 4, specifically, the rotary pump 13 is in point contact connection with the blade tenon 4, so that the working stability of the rotary pump 13 is ensured, and the momentum loss caused by friction force is reduced;
the air inlet channel 2 is arranged on the front edge 5 of the blade and communicated with the cavity 1, and the air inlet direction of the air inlet channel 2 is the same as the incoming flow direction;
the air suction channel 7 is arranged on the blade back 12 and communicated with the cavity 1;
the exhaust passage 3 is opened in the blade basin 11 and communicated with the cavity 1, and the width of the exhaust passage 3 is gradually reduced from the cavity 1 to the blade basin 11.
Preferably, the radial section circle of the cavity 1 takes the center of a first inscribed circle on the camber line 6 of the blade body 14 close to the leading edge 5 of the blade as the center of a circle, and takes the radius of 0.8 times the radius of the first inscribed circle as the radius. In this embodiment, the cylindrical cavity 1 is disposed inside the blade body 14 and located on one side close to the leading edge 5 of the blade, and the radius of the cross section of the cavity 1 is 0.7-0.9 times of the radius of the inscribed circle of the blade body 14, so that the cavity 1 can improve the air intake utilization rate while ensuring the rigidity of the blade.
As shown in fig. 1 and 2, 1 to 3 air inlet channels 2 are opened, the height of the air inlet channel 2 is one third of the blade height, the distance from the top end of the air inlet channel 2 to the blade tip 9 is equal to the distance from the bottom end of the air inlet channel 2 to the blade root 10, and the width of the air inlet channel 2 is not less than 2 mm. In this embodiment, 3 air inlet channels 2 are arranged between the blade front edge 5 and the cylindrical cavity 1, the 3 air inlet channels 2 are arranged in parallel, the air inlet direction of each air inlet channel 2 is the same as the incoming flow direction, so that air is introduced into the cavity 1, the height of each air inlet channel 2 is one third of the blade height, the width of each air inlet channel 2 is determined by the thickness of the blade and is greater than or equal to 2mm, and the interval between every two adjacent air inlet channels 2 is not greater than the channel width.
As shown in fig. 3, the extension line of the channel wall of the suction channel 7 close to the blade trailing edge 8 side passes through the center of the radial section circle of the cavity 1, and the distance from one end of the channel wall of the suction channel 7 close to the blade trailing edge 8 side, which is located at the blade back 12, to the center of the radial section circle of the cavity 1 is 2 to 2.2R, where R is the radius of the inscribed circle of the blade body 14 at the center; the channel wall of the suction channel 7 on the side close to the leading edge 5 of the blade is parallel to the channel wall on the side close to the trailing edge 8 of the blade, and the width of the suction channel 7 is 2mm or more, that is, the distance between the two channel walls is 2mm or more. The height of the suction channel 7 is one third of the blade height and the distance from the top end of the suction channel 7 to the blade tip 9 is equal to the distance from the bottom end of the suction channel 7 to the blade root 10.
As shown in fig. 3, the extension line of the channel wall of the exhaust channel 3 close to the blade trailing edge 8 side passes through the center of the radial section circle of the cavity 1, and the distance from one end of the channel wall of the exhaust channel 3 close to the blade trailing edge 8 side, which is located at the blade basin 11, to the center of the radial section circle of the cavity 1 is 2.3 to 2.5R, where R is the radius of the inscribed circle of the blade body 14 at the center; the channel wall of the exhaust channel 3 close to one side of the front edge 5 of the blade is obliquely arranged, the minimum width of the exhaust channel 3 is more than or equal to 2mm, and the difference between the maximum width and the minimum width of the exhaust channel 3 is 2-4 mm, so that good acceleration capability is ensured. In the present embodiment, the channel wall of the exhaust channel 3 near the leading edge 5 of the blade is obliquely arranged, so that the exhaust channel 3 is of a tapered structure with the width gradually decreasing from the cavity 1 to the blade basin 11, the height of the exhaust channel 3 is one third of the blade height, and the distance from the top end of the exhaust channel 3 to the blade tip 9 is equal to the distance from the bottom end of the exhaust channel 3 to the blade root 10.
As shown in fig. 4 and 5, the rotary pump 13 comprises a rotating shaft and a plurality of blades uniformly arranged along the circumferential direction of the rotating shaft, the diameter of the rotating shaft is 0.15-0.25 times of the diameter of the cavity 1, and the rotating shaft is rotatably connected with the blade tenon 4; the number of the blades is 8-10, the distance between each blade and the wall of the cavity 1 is smaller than 1mm, the bending degree of each blade is 15-30 degrees, the bending direction of each blade is opposite to the rotating direction, and the rotary pump 13 is guaranteed to have enough working strength.
As shown in fig. 6, the vane body 14 of the present invention is a complete guide vane of the prior art, and the cavity 1 is concentric with the rotary pump 13.
As shown in fig. 7, the working principle of the airflow corner adaptive guide vane of the axial-flow compressor of the invention is as follows:
incoming flow gas with high kinetic energy enters the cavity 1 from the gas inlet channel 2 to drive the rotary pump 13 to work;
because the airflow rotates in the cavity 1, a negative pressure area is formed at the position, close to the cavity 1, of the air suction channel 7, the main flow airflow in the blade grid channel is sucked into the cavity 1, a reverse flow area is formed at the position, close to the blade back 12, of the main flow, and a shear layer is generated between the main flow and the reverse flow area due to the existence of viscosity, so that the main flow can entrain the static atmosphere around through the shear layer, and the main flow generates an airflow corner in the direction of the blade back 12;
meanwhile, the rotary pump 13 discharges the airflow of the cavity 1 into the main flow through the acceleration of the tapered design of the exhaust channel 3, and due to the viscosity of the airflow and the flow speed difference between the airflow passing through the exhaust channel 3 and the main flow, a shear layer is formed between the airflow discharged into the main flow and the main flow, and the shear layer guides the main flow to the side far away from the blade basin 11, so that the main flow generates an airflow turning angle towards the direction of the blade back 12;
when the flow velocity of the incoming flow gas is increased, the kinetic energy is increased, the corresponding incoming flow gas drives the rotary pump 13 to rotate in an accelerating manner, so that the speeds of the reverse flow region and the same flow region are increased, the entrainment effect of the boundary layer between the two regions and the main flow on the main flow is enhanced, and the flow turning angle is correspondingly increased, so that the capability of adaptively changing the flow turning angle according to the change of the incoming flow gas speed is achieved.
As shown in fig. 8 to 11, a method for designing an airflow corner adaptive guide vane of an axial-flow compressor includes the following steps:
s1, establishing a three-dimensional blade body model, wherein the three-dimensional blade body model comprises a blade tip 9, a blade root 10, a blade back 12, a blade basin 11, a mean camber line 6, a blade leading edge 5 and a blade trailing edge 8; specifically, a three-dimensional blade body model is established according to design parameters of guide blades of the existing axial-flow type compressor.
S2, determining the center O and the radius of the cavity 1, and determining the center O and the radius of a first inscribed circle on the upper surface of the blade tip 9 close to one side of the front edge 5 of the blade, wherein the center O of the cavity 1 is the center of the first inscribed circle, and the radius of the cavity 1 is 0.7-0.9 times of the radius of the first inscribed circle;
in step S2, the specific manner of determining the center and radius of the first inscribed circle on the upper surface of the blade tip 9 close to the leading edge 5 of the blade is as follows: taking any 3 points on the blade front edge 5 on the upper surface of the blade tip 9, respectively connecting the points on the two sides with the middle point to obtain two line segments which are intersected with the middle point, respectively making vertical center lines of the two line segments, taking the intersection point of the two vertical center lines as a center of a circle, taking the distance from the center of the circle to any one of the 3 points as a radius to make a circle, and constraining the center of the circle to a middle arc line 6 to obtain a first inscribed circle of the upper surface of the blade tip 9 close to one side of the blade front edge 5, namely obtaining the center of the first inscribed circle of the upper surface of the blade tip 9 close to one side of the blade front edge 5 and the radius.
S3, designing a cavity 1, drawing a radial section circle of the cavity 1 on the upper surface of the blade tip 9 according to the circle center O and the radius of the cavity 1, and enabling the radial section circle of the cavity 1 to penetrate through the whole three-dimensional blade body model from the blade tip 9 to the blade root 10 to obtain the cavity 1.
S4, design intake passage 2:
s4.1, establishing a two-dimensional model of the upper surface of the blade tip 9 according to the three-dimensional blade body model with the cavity 1 obtained in the step S3, wherein the two-dimensional model of the upper surface of the blade tip 9 comprises a blade back 12, a blade basin 11, a mean camber line 6, a blade front edge 5, a blade tail edge 8 and the cavity 1;
s4.2, establishing an outer flow field area of the two-dimensional model of the upper surface of the blade tip 9, wherein the outer flow field area comprises an inlet 15, an outlet 16, a first side face 17 and a second side face 18; the vertical distance from the inlet 15 to the outlet 16 of the outer flow field region is greater than 3 times the blade arc length, and the vertical distance between the first side 17 and the second side 18 of the outer flow field region is greater than 3 times the blade width;
in step S4.2, the inlet 15 of the outer flow field region is perpendicular to the incoming flow direction, and the outlet 16 of the outer flow field region is parallel to the inlet 15;
s4.3, constructing a non-structural grid of the two-dimensional model of the upper surface of the blade tip 9 with the outer flow field area, setting an inlet 15 of the outer flow field area as an inlet of a calculation domain, and setting an outlet 16, a first side face 17 and a second side face 18 of the outer flow field area as outlets of the calculation domain; specifically, a two-dimensional model of the upper surface of the blade tip 9 with the outer flow field area is led into the cem to construct an unstructured grid;
s4.4, setting pressure parameters of an inlet of the calculation domain and an outlet of the calculation domain, selecting a turbulence model as a k-epsilon turbulence model, obtaining a streamline cloud picture of an outer flow field area, and finding a stagnation point A of the front edge 5 of the blade in the streamline cloud picture; specifically, the unstructured grid generated in the step S4.3 is imported into fluent software, pressure parameters of an inlet of a calculation domain and an outlet of the calculation domain are set to be correspondingly consistent with a design working condition of the compressor, a k-epsilon turbulence model is selected, flow field data obtained through calculation is imported into tecplot software, and a stagnation point a of a blade leading edge 5 is found according to a streamline cloud chart of an outer flow field region;
s4.5, on the two-dimensional model of the upper surface of the blade tip 9, extending the stagnation point A along the incoming flow direction, intersecting the cavity 1 at a point B, and respectively biasing the line segment AB towards two sides by a1mm，a2mm，a3And (5) obtaining 6 line segments with two ends respectively intersected with the front edge 5 of the blade and the cavity 1 by mm distance, wherein the line segments are respectively as follows: a. the1B1、A2B2、A3B3、A4B4、A5B5And A6B6(ii) a The 6 line segments, the blade front edge 5 and the cavity 1 enclose 3 closed curves, which are respectively as follows: curve A1B1B2A2、A3B3B4A4And A5B5B6A6Respectively stretching 3 curves upwards from one third of the leaf height to two thirds of the leaf height to obtain three air inlet channels 2; in this example, a1＝1，a2＝2.5，a3＝4.5；
S5, design exhaust passage 3:
a circle is drawn by taking the circle center O of the cavity 1 as the circle center and 2.3 times of the radius of the cavity 1 as the radius, and the circle intersects with the leaf basin 11 at a point C1Connection point C1At the center of the cavity 1, the connecting line intersects with the cavity 1 at a point D1To obtain a line segment C1D1(ii) a Segment C1D1Is offset by 2mm towards the direction of the leaf pot 11, and the obtained line segment is extended to intersect with the leaf pot 11 at a point C2(ii) a Then, the line segment C is divided1D1Is offset by 4mm towards the direction of the leaf basin 11, and the obtained line segment is extended to intersect with the cavity 1 at a point D2Will close curve C1D1D2C2Stretching upwards from one third of the leaf height to two thirds of the leaf height to obtain an exhaust channel 3;
s6, designing the suction passage 7:
a circle is drawn by taking the circle center O of the cavity 1 as the center and 2 times of the radius of the cavity 1 as the radius, and the circle intersects with the leaf back 12 at a point C3Connection point C3The connecting line intersects the cavity 1 and the point D at the center of the circle of the cavity 13The obtained line segment C3D3Is biased for 2mm towards the direction of the blade back 12, and the obtained line segment is extended to respectively intersect with the blade back 12 and the cavity 1 at a point C4And D4Will close curve C3D3D4C4Stretching upwards from one third of the leaf height to two thirds of the leaf height to obtain a suction channel 7;
s7, designing the rotary pump 13:
drawing a circle by taking the circle center O of the cavity 1 as the circle center and taking 0.2 time of the radius of the cavity 1 as the radius to obtain the section of the rotating shaft of the rotary pump 13; then, the circle center O of the cavity 1 is taken as the center of the circle, a circle is drawn by taking 0.8 time of the radius of the cavity 1 as the radius, a point E is selected on the circle, the point E is connected with the center O of the cavity 1, the line segment EO is biased to the direction of the blade back 12 by 1mm, and the line segment L is offset towards the direction of the blade back 121Intersects the cross section of the rotating shaft of the rotary pump 13 at a point F1(ii) a Then, the line segment EO is biased to the 12 direction of the leaf back by 1.5mm to obtain a line segment L2Line segment L2Cross-section of the rotary shaft of the rotary pump 13 at a point F2(ii) a Then, the line segment EO is biased to the 12 direction of the leaf back by 2mm to obtain a line segment L3(ii) a Passing points E and F1Make an arc and combine with L2Tangent to obtain an arc S1(ii) a Passing points E and F2Make an arc and combine with L3Tangent to obtain an arc S2(ii) a By arcs S1, S2 and F1F2The enclosed figure is a geometric model of one blade of the rotary pump 13, the geometric model of the blade is arrayed into 7 blades in an equiangular mode by taking the center O of the cavity 1 as the center, the section of a rotating shaft of the rotary pump 13 is stretched from the blade tip 9 to the blade root 10, and the geometric models of 8 blades are stretched from the position 2mm away from the blade tip 9 to the position 2mm away from the blade root 10, so that the rotary pump 13 is obtained;
s8, establishing a three-dimensional tenon 4 model, connecting the model with the three-dimensional blade body models of the designed air inlet channel 2, the air outlet channel 3, the air suction channel 7 and the rotary pump 13, and rotatably connecting the rotating shaft of the rotary pump 13 with the tenon 4.
Finally, it should be noted that the above embodiments are only used to supplement and illustrate the technical solutions of the present invention, and are not limited. The technical solution of the present invention is modified or replaced equivalently in the actual design and production process without departing from the spirit and scope of the technical solution of the present invention, and the technical solution of the present invention is covered by the claims of the present invention.
Claims (9)
1. An airflow corner self-adaptive guide blade of an axial-flow compressor comprises a blade body, wherein the blade body comprises a blade body and a tenon;
the cavity penetrates through the blade body along the height direction of the blade body, the center of a radial section circle of the cavity is positioned on the camber line of the blade body and is close to one side of the front edge of the blade, and the radius of the radial section circle of the cavity is 0.7-0.9 time of the radius of an inscribed circle of the blade body corresponding to the position of the center of the circle; a rotary pump is arranged in the cavity and is rotationally connected with the tenon;
the air inlet channel is arranged on the front edge of the blade and communicated with the cavity, and the air inlet direction of the air inlet channel is the same as the incoming flow direction;
the air suction channel is arranged on the blade back and communicated with the cavity;
the exhaust passage is arranged on the leaf basin and communicated with the cavity, and the width of the exhaust passage is gradually reduced from the cavity to the leaf basin.
2. The airflow corner adaptive guide vane of an axial flow compressor as claimed in claim 1, wherein the radial section circle of the cavity is centered at the center of the first inscribed circle on the camber line of the vane body near the leading edge of the vane, and the radius of the first inscribed circle is 0.8 times the radius of the first inscribed circle.
3. The airflow corner self-adaptive guide blade of an axial-flow compressor as claimed in claim 1, wherein the number of the air inlet channels is 1-3, the height of the air inlet channel is one third of the blade height, the distance from the top end of the air inlet channel to the blade tip is equal to the distance from the bottom end of the air inlet channel to the blade root, and the width of the air inlet channel is not less than 2 mm.
4. The airflow corner self-adaptive guide blade of the axial flow compressor as claimed in claim 2, wherein the extension line of the channel wall of the air suction channel close to the blade trailing edge side passes through the center of the cavity radial cross-section circle, the distance from the end of the channel wall of the air suction channel close to the blade trailing edge side at the blade back to the center of the cavity radial cross-section circle is 2-2.2R, and R is the first inscribed circle radius close to the blade leading edge side on the camber line of the blade body; the channel wall of the suction channel close to the front edge of the blade is parallel to the channel wall of the suction channel close to the tail edge of the blade, and the width of the suction channel is more than or equal to 2 mm.
5. The airflow corner self-adaptive guide blade of the axial-flow compressor as claimed in claim 2, wherein the extension line of the channel wall of the exhaust channel close to the blade trailing edge side passes through the center of the cavity radial cross-section circle, and the distance from the end of the channel wall of the exhaust channel close to the blade trailing edge side at the blade basin to the center of the cavity radial cross-section circle is 2.3-2.5R, wherein R is the radius of the first inscribed circle on the blade body camber line close to the blade leading edge side; the exhaust channel is obliquely arranged on a channel wall close to one side of the front edge of the blade, the minimum width of the exhaust channel is larger than or equal to 2mm, and the difference between the maximum width and the minimum width of the exhaust channel is 2-4 mm.
6. The self-adaptive turning vane of the airflow corner of an axial flow compressor as claimed in claim 1, wherein the rotary pump comprises a rotating shaft and a plurality of vanes uniformly arranged along the circumferential direction of the rotating shaft, the radius of the rotating shaft is 0.15-0.25 times of the radius of a radial section circle of the cavity, and the rotating shaft is rotationally connected with a vane tenon; the number of the blades is 8-10, the distance between each blade and the cavity wall of the cavity is smaller than 1mm, the bending degree of each blade is 15-30 degrees, and the bending direction of each blade is opposite to the rotating direction.
7. The method for designing the airflow corner adaptive guide vane of the axial flow compressor as claimed in claim 1, is characterized by comprising the following steps:
s1, establishing a three-dimensional blade body model, wherein the three-dimensional blade body model comprises a blade tip, a blade root, a blade back, a blade basin, a mean camber line, a blade leading edge and a blade trailing edge;
s2, determining the center O and the radius of a cavity, and determining the center and the radius of a first inscribed circle on the upper surface of the blade tip close to one side of the front edge of the blade, wherein the center O of the cavity is the center of the first inscribed circle, and the radius of the cavity is 0.7-0.9 times of the radius of the first inscribed circle;
s3, designing a cavity, drawing a radial cross-section circle of the cavity on the upper surface of the blade tip according to the circle center O and the radius of the cavity, and penetrating the radial cross-section circle of the cavity through the whole three-dimensional blade body model from the blade tip to the blade root to obtain the cavity;
s4, designing an air inlet channel:
s4.1, establishing a two-dimensional model of the upper surface of the blade tip according to the three-dimensional blade body model with the cavity obtained in the step S3, wherein the two-dimensional model of the upper surface of the blade tip comprises a blade back, a blade basin, a mean camber line, a blade front edge, a blade tail edge and a cavity;
s4.2, establishing an outer flow field area of the two-dimensional model of the upper surface of the blade tip, wherein the outer flow field area comprises an inlet, an outlet, a first side face and a second side face; the vertical distance from the inlet to the outlet of the outer flow field area is greater than 3 times of the arc length of the blade, and the vertical distance between the first side face and the second side face of the outer flow field area is greater than 3 times of the width of the blade;
s4.3, constructing a non-structural grid of the two-dimensional model of the upper surface of the blade tip with the outer flow field area, setting an inlet of the outer flow field area as an inlet of a calculation domain, and setting an outlet, a side face I and a side face II of the outer flow field area as outlets of the calculation domain;
s4.4, setting pressure parameters of an inlet of the calculation domain and an outlet of the calculation domain, selecting a turbulence model as a k-epsilon turbulence model, obtaining a streamline cloud picture of an outer flow field area, and finding a stagnation point A of a front edge of the blade in the streamline cloud picture;
s4.5, on the two-dimensional model of the upper surface of the blade tip, extending the stagnation point A along the incoming flow direction, intersecting the cavity at a point B, and respectively biasing the line segment AB towards two sides by a1mm，a2mm，a3And (5) obtaining 6 line segments with two ends respectively intersected with the front edge of the blade and the cavity by mm distance, wherein the line segments are respectively as follows: a. the1B1、A2B2、A3B3、A4B4、A5B5And A6B6(ii) a The 6 line segments, the blade front edge and the cavity enclose 3 closed curves, which are respectively: curve A1B1B2A2、A3B3B4A4And A5B5B6A6Respectively stretching 3 curves upwards from one third of the leaf height to two thirds of the leaf height to obtain three air inlet channels;
s5, designing an exhaust passage:
drawing a circle with the center O of the cavity as the center and 2.3 times of the radius of the cavity as the radius, and intersecting the leaf basin at a point C1Connection point C1The connecting line intersects with the cavity at a point D from the center of the cavity1To obtain a line segment C1D1(ii) a Segment C1D1Biasing towards leaf pot direction for 2mm, extending obtained line segment, and crossing with leaf pot at point C2(ii) a Then, the line segment C is divided1D1Biasing towards the leaf basin direction by 4mm, extending the obtained line segment, and intersecting the cavity at a point D2Will close curve C1D1D2C2Stretching upwards from one third of the leaf height to two thirds of the leaf height to obtain an exhaust channel;
s6, designing an air suction channel:
the center O of the cavity is used as the center of the circle, a circle is drawn by taking 2 times of the radius of the cavity as the radius, and the circle intersects with the leaf back at a point C3Connection point C3Intersects the center of the cavity and the connecting line with the cavity and a point D3The obtained line segment C3D3Biasing towards the leaf back by 2mm, and extending the obtained line segmentLong, intersecting the leaf back and the cavity at points C4And D4Will close curve C3D3D4C4Stretching upwards from one third of the leaf height to two thirds of the leaf height to obtain an air suction channel;
s7, designing a rotary pump:
drawing a circle by taking the circle center O of the cavity as the circle center and taking 0.2 time of the radius of the cavity as the radius to obtain the section of the rotating shaft of the rotary pump; then, the circle center O of the cavity is taken as the circle center, a circle is drawn by taking 0.8 time of the radius of the cavity as the radius, a point E is selected on the circle, the point E is connected with the circle center O of the cavity, the line segment EO is biased towards the blade back direction by 1mm, and a line segment L is obtained1Line segment L1Intersects the section of the rotating shaft of the rotary pump at a point F1(ii) a Then, the line segment EO is biased to the direction of the leaf back by 1.5mm to obtain a line segment L2Line segment L2Cross-section of the rotary pump shaft at point F2(ii) a Then, the line segment EO is biased to the direction of the leaf back by 2mm to obtain a line segment L3(ii) a Passing points E and F1Make an arc and combine with L2Tangent to obtain an arc S1(ii) a Passing points E and F2Make an arc and combine with L3Tangent to obtain an arc S2(ii) a By arcs S1, S2 and F1F2The enclosed figure is a geometric model of one blade of the rotary pump, the geometric model of the blade is arrayed into 7 blades in an equiangular mode by taking the circle center O of the cavity as the circle center, the section of a rotating shaft of the rotary pump is stretched from the blade tip to the blade root, and the geometric models of 8 blades are stretched from the position 2mm away from the blade tip to the position 2mm away from the blade root to obtain the rotary pump;
s8, establishing a three-dimensional tenon model, connecting the three-dimensional tenon model with the three-dimensional blade body model of which the air inlet channel, the air outlet channel, the air suction channel and the rotary pump are designed, and rotatably connecting a rotating shaft of the rotary pump with the tenon.
8. The method for designing the airflow corner adaptive guide vane of the axial flow compressor as recited in claim 7, wherein in the step S2, the center and the radius of the first inscribed circle of the top surface of the blade tip on the side close to the leading edge of the blade are determined as follows: taking any 3 points on the front edge of the blade on the upper surface of the blade tip, respectively connecting the points on the two sides with the middle point to obtain two line segments which are intersected with the middle point, respectively making vertical center lines of the two line segments, taking the intersection point of the two vertical center lines as a circle center, taking the distance from the circle center to any one point of the 3 points as a radius to make a circle, and constraining the circle center to a middle arc line to obtain a first inscribed circle of the upper surface of the blade tip close to one side of the front edge of the blade, namely obtaining the circle center and the radius of the first inscribed circle of the upper surface of the blade tip close to one side of the front edge of the blade.
9. The method of claim 7, wherein in step S4.2, the inlet of the outer flow field region is perpendicular to the incoming flow direction, and the outlet of the outer flow field region is parallel to the inlet.
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