CN112960139B - To vortex flow distortion generator - Google Patents
To vortex flow distortion generator Download PDFInfo
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- CN112960139B CN112960139B CN202110222530.0A CN202110222530A CN112960139B CN 112960139 B CN112960139 B CN 112960139B CN 202110222530 A CN202110222530 A CN 202110222530A CN 112960139 B CN112960139 B CN 112960139B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/74—Wind turbines with rotation axis perpendicular to the wind direction
Abstract
A pair of vortex flow distortion generators is provided and includes a blade, a casing, and a ring. The number of the blades is 11, and the blades are respectively as follows: (1) the five blades are arranged in the middle, the shapes, the sizes and the bending degrees of the five blades are different, the blade profile section of each blade is that the blade basin faces downwards, and the blade back faces upwards; the bending angle of the blade is symmetrical left and right about the center of the blade; (2) three pairs of blades (6) which are symmetrically distributed on the left side and the right side, are in mirror image structures, are symmetrically distributed and adopt forward-swept layout; the blade profiles of eleven blades are all CDA blade profiles. The supporting small circular ring and the casing (7) play roles of fixing and supporting the blade. The invention can effectively inhibit the air flow separation, reduce the flow loss, and improve the total pressure recovery coefficient from 0.977 to 0.999; the forward-swept layout effectively reduces the mutual influence among all the blades, so that the flow field distribution is closer to the target flow field.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a distortion generator for generating convection vortex flow.
Background
At high rotational speeds, engine performance is closely related to the quality of the inlet airflow, which makes the problem of compatibility of the inlet with the engine an important research content in aircraft propulsion systems. In order to improve stealth performance and reduce flight resistance, a wing body fusion (HWB) and an S-bend air inlet are commonly adopted in modern fighter aircraft, but such a structure can cause a serious rotational flow distortion at an engine inlet, and seriously affects performance and stability of an air compressor, which is specifically represented as follows: the steady operating margin of the engine is reduced, causing surge and stall of the engine. Therefore, the influence of rotational flow distortion on the performance and stability of the compressor is reduced or even eliminated, and the improvement of the performance of the engine is a main problem of the design of the gas turbine engine.
At the beginning of designing a high-wind fighter, surge occurs in the test flight process due to the influence of rotational flow distortion. Thereafter, in order to avoid the occurrence of similar accidents, researchers design a rotational flow distortion generator capable of generating rotational flow distortion, and perform ground tests to study the influence of the rotational flow distortion on the performance and stability of the engine.
The following representatives exist at home and abroad, and rotational flow distortion generators are designed and related research on rotational flow distortion is carried out:
govardhan designs a vane-type swirl distortion generator that uses turning vanes similar to engine inlet guide vanes to generate the overall swirl flow distortion. South boat ginger jian etc. have designed a blade type vortex generator, can produce the whole vortex of different intensity and skew vortex pair through changing blade configuration and overall arrangement. Butcher front has designed a kind of adjustable blade whirl distortion generator, changes the kind and the intensity of whirl through changing blade group number and blade exit corner.
Sheoran and Bouldin designed a chamber-type rotational flow distortion generator. By varying the baffle in the chamber, it is possible to generate integral vortices, twin vortices and offset twin vortices in general structural form. But the rotational flow distortion generator cannot be precisely controlled to generate rotational flow distortion having a specific structural form.
The two rotational flow distortion generators can only generate general type integral vortex or opposite vortex flow distortion, and the blade type rotational flow distortion generator is complex in adjustment and low in precision; the control difficulty of the chamber type rotational flow distortion generator is high.
The vortex flow distortion net is designed on the basis of a vane type vortex distortion generator in Zhang of the university of air force engineering, and the vortex flow distortion net has the advantages that the vortex distortion net can be designed aiming at a target vortex velocity vector field to generate vortex distortion in an expected structural form, and the problems that the existing vortex flow distortion generator is complex in adjustment, low in precision, large in control difficulty and low in precision of a chamber type vortex flow distortion generator are solved. However, the distortion generator has the following disadvantages by analysis:
1) the flow loss and the total pressure loss are large when the airflow flows through the blades;
2) the reproduction accuracy for the standard to the eddy current field is not high. The distribution of the velocity vector and the swirl angle has a large difference with the target flow field, the velocity vector is not uniformly distributed, and the swirl strength is smaller than the target flow field at the vortex core.
Through analysis, the results are found to be due to the airfoil and the blade layout mode.
Disclosure of Invention
In view of the problems in the prior art, the present invention provides a distortion generator for vortex flow, comprising: blades, casings, rings;
wherein the blades are totally 11, are respectively:
the five blades in the middle are sequentially arranged from top to bottom: the left and right ends of the five blades are fixedly connected with small circular rings 8 on the left and right sides respectively; the shape, size and bending angle of the middle blade 1, the middle blade 2, the middle three blade 3, the middle four blade 4 and the middle five blade 5 are different, the blade profile section of each blade is that the basin faces downwards, the back of the blade faces upwards, and the bending angle of the blade is symmetrical left and right about the center of the blade; the bending angles of the middle blade 1 and the middle blade 5 are increased from the middle to the two sides and then reduced; the bending angles of the middle two blades 2, the middle three blades 3 and the middle four blades 4 are increased along with the increase of the chord length of each blade; the shape and the position of the first blade 1 and the fifth blade 5 are basically symmetrical, the shape and the position of the second blade 2 and the fourth blade 4 are basically symmetrical, and the five blades are all solid blades;
three pairs of blades 6 which are symmetrically distributed on the left and the right sides are sequentially arranged from top to bottom on the left side: the left first blade, the left second blade and the left third blade; the right side is sequentially from top to bottom: a right first blade, a right second blade and a right third blade; wherein, the three pairs of blades at two sides are in mirror image structure, are symmetrically distributed and adopt forward sweep layout; the inner sides of all the blades are fixedly connected with the small supporting circular ring 8, and the outer sides of all the blades are fixedly connected to the casing 7; the shape and the blade bending angle of three pairs of blades 6 which are symmetrically distributed on the left side and the right side are the same, the blades are the same type of blades, the length of the left two blades and the right two blades is the longest, and the lengths of the left one blade, the left three blades, the right one blade and the right three blades are equal and are slightly shorter than the left two blades and the right two blades;
the blade profiles of eleven blades are CDA blade profiles;
from the top view of the convective vortex flow distortion generator, the shapes of the left blade, the left three blades, the right blade and the right three blades are all right trapezoid, the upper bottom of the trapezoid is close to the inner side of the convective vortex flow distortion generator, the lower bottom of the trapezoid is close to the outer side of the distortion generator, the lower bottom of the trapezoid is wider than the upper bottom, the right-angle side of the right trapezoid is close to the rear side of the convective vortex flow distortion generator, and the bevel side is close to the front side of the generator;
the small supporting rings 8 comprise a left ring and a right ring, are symmetrically distributed and are hollow cylinders;
the circular casing 7 is a hollow cylinder, and the supporting small circular ring 8 and the casing 7 play roles in fixing and supporting the blades; the connection mode of the blades and the casing 7 and the connection mode of the blades and the small supporting ring 8 are both fixed connection.
In one embodiment of the invention, the reference line followed by the distribution of 11 blades is: the line of the middle blade and the line of the middle five blades are circular arcs, and the radian of the circular arcs is 171.53-188.69 degrees; the line of the middle two blades and the line of the middle four blades are circular arcs, and the radian of the circular arcs is 83.29-96.89 degrees; the other blade lines are straight line segments.
In one embodiment of the invention, the reference line followed by the distribution of 11 blades is: the line of the middle blade and the line of the middle five blades are arcs with the radius of 300mm, and the radian is 180 degrees; the line of the middle two blades and the line of the middle four blades are arcs with the radius of 300mm, and the radian is 90 degrees; the other blade lines are straight line segments.
In another embodiment of the present invention, the middle blade 1 takes the upper vertexes of the two small supporting rings 8 as the starting point and the end point, and takes the shape of a circular arc; a connecting line between the centers of circles of the two small supporting circular rings 8 is taken as an axis, and the direction is the positive direction towards the right; the middle blade 2 takes a 45-degree point of the left supporting small ring 8 as a starting point and takes a 135-degree point of the right supporting small ring 8 as an end point to present a bilaterally symmetrical circular arc shape; the middle three blades 3 are in a bilaterally symmetrical circular arc shape by taking the 90-degree point of the left supporting small circular ring 8 as a starting point and taking the 90-degree point of the right supporting small circular ring 8 as an end point; the middle four blades 4 are in a bilaterally symmetrical circular arc shape by taking a-45-degree point of the left supporting small circular ring 8 as a starting point and taking a 225-degree point of the right supporting small circular ring 8 as an end point; the five middle blades 5 are arc-shaped with the lower vertex of the left supporting small ring 8 as a starting point and the lower vertex of the right supporting small ring 8 as an end point.
In another embodiment of the present invention, the left blade 6, the left blade, the right blade, the left blade, the right blade, the distortion generator, and the distortion generator.
In one embodiment of the invention, the chord length of one blade 1 increases linearly from two ends to the center, the value is 26.78 mm-148.14 mm, the bending angle of the blade increases linearly from two ends to the center and then decreases linearly, the value is 5.5-9.7-8.1 degrees; the chord length of the middle two blades 2 increases linearly from the two ends to the center, the value is 26.78 mm-126.44 mm, the bending angle of the blades increases linearly from the two ends to the center, and the value is 7.6-14.3 degrees; the chord length of the middle three blades 3 increases linearly from the two ends to the center, the value is 26.78 mm-104.75 mm, the bending angle of the blades increases linearly from the two ends to the center, and the value is 8.5-16.7 degrees; the chord length of the middle four blades 4 increases linearly from the two ends to the center, the value is 26.78 mm-126.44 mm, the bending angle of the blades increases linearly from the two ends to the center, and the value is 7.6-14.3 degrees; the chord length of the five middle blades 5 increases linearly from the two ends to the center, the value is 26.78-148.14 mm, the bending angle of the blades increases linearly from the two ends to the center and then decreases linearly, and the value is 5.5-9.7-8.1 degrees.
In another embodiment of the invention, the blades 6 are mirror-symmetric about the central plane of the distortion generator, taking the right group of blades as an example, the chord length of the right blade increases linearly from the joint with the small supporting ring 8 to the circular casing 7, the value is 26.78mm to 199.74mm, the bending angle of the blade increases linearly from the joint with the small supporting ring 8 to the circular casing 7 and then decreases linearly, the value is 3.0 to 6.3 to 5.2 degrees; the chord length of the right two blades is linearly increased from the small supporting ring 8 to the circular casing 7, the numerical value is 26.78-100.59 mm, the bending angle of the blades is linearly increased from the small supporting ring 8 to the circular casing 7 and then linearly decreased, and the numerical value is 3.0-6.3-5.8 degrees; the chord length of the right three blades is increased linearly from the position of the small supporting ring 8 to the position of the circular casing 7, the numerical value is 26.78-199.74 mm, the bending angle of the blades is increased linearly from the position of the small supporting ring 8 to the position of the circular casing 7 and then is decreased linearly, and the numerical value is 3.0-6.3-5.2 degrees.
In another embodiment of the invention, the thickness of the circular casing 7 is 3 mm-10 mm, and the radius is 200-400 mm; the outer diameter of the small internal supporting ring 8 is 16 mm-92 mm, and the thickness is 2 mm-10 mm.
In one embodiment of the invention, the circular case 7 has a thickness of 5mm and an outer diameter of 300 mm; the inner support small ring 8 has a diameter of 46.78mm and a thickness of 5 mm.
The working process of the vortex flow distortion generator is also provided, and the working process specifically comprises the following steps:
step 1: arranging a convective vortex flow distortion generator in an air inlet channel of an air compressor experiment table;
step 2: starting an axial-flow type compressor experiment table;
and step 3: flowing the gas stream through a distortion generator;
and 4, step 4: the distortion generator deflects the incoming flow to generate a standard pair vortex distortion flow field; the method comprises the following specific steps: when the airflow flows through the distortion generator, the blades of the distortion generator enable the airflow to be disturbed and deflected, the deflection direction of the airflow is perpendicular to the blades, the blade back points to the blade basin, and the airflow flowing direction deviates from the axial direction; the airflow flowing through the left blade is disturbed to generate a circumferential speed, the airflow rotates clockwise, a clockwise vortex is generated near the left supporting small ring 8, and a vortex core of the vortex is positioned at the circle center of the left supporting small ring 8; the airflow flowing through the right blade is disturbed to generate a circumferential speed, the airflow rotates anticlockwise, an anticlockwise vortex is generated near the right supporting small ring 8, and the vortex core is positioned at the center of the right supporting small ring 8;
and 5: the swirling flow distortion flow field is rotated by the rotating distortion generator model.
The invention is based on the swirl distortion generator designed by the spanwise epitaxy of the air force engineering university, optimizes the blade profile, adopts the CDA blade profile, improves the layout mode, adopts the forward-swept layout of the blades at two sides, and has the following advantages compared with the spanwise distortion generator:
(1) effectively inhibits the air flow separation, reduces the flow loss, and increases the total pressure recovery coefficient from 0.977 to 0.999.
(2) The forward-swept layout effectively reduces the mutual influence among all the blades, so that the flow field distribution is closer to the target flow field.
Drawings
FIG. 1 shows a front view of a pair of vortex flow distortion generators of the present invention;
FIG. 2 shows a left side view of the distortion generator for a vortex flow and a vane schematic of the present invention, wherein FIG. 2(a) shows the left side view of the distortion generator for a vortex flow and FIG. 2(b) shows the vane schematic;
FIG. 3 shows a top view of the present invention versus a vortex flow distortion generator;
FIG. 4 shows the present invention for a vortex flow distortion generator blade line.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
The present invention provides a distortion generator for a vortex flow, comprising: blades, casings, rings, as shown in fig. 1. The method specifically comprises the following steps:
the number of the blades is 11, and the blades are respectively as follows:
five blades (a middle blade 1, a middle blade 2, a middle three blade 3, a middle four blade 4 and a middle five blade 5 from top to bottom) are arranged in the middle, and the left and right ends of the five blades are fixedly connected with the small circular rings 8 on the left and right sides respectively. The first blade 1, the second blade 2, the third blade 3, the fourth blade 4 and the fifth blade 5 are different in shape, size and blade bending angle (the blade bending angle refers to an included angle between a front edge tangent line and a rear edge tangent line of a camber line of the blade profile) and are totally five types of blades. The shape of the profile section of each blade is shown in fig. 2(b), the profile sections of the blades are all that the basin faces downwards, and the back faces upwards; the bending angle of the blade is symmetrical left and right about the center of the blade; the bending angles of the middle blade 1 and the middle blade 5 are increased from the middle to the two sides and then reduced; the bending angles of the middle two blades 2, the middle three blades 3 and the middle four blades 4 are increased along with the increase of the chord length of each blade. The shape and the position of the first blade 1 and the fifth blade 5 are basically symmetrical, the shape and the position of the second blade 2 and the fourth blade 4 are basically symmetrical, and the five blades are all solid blades.
Three pairs of blades 6 (a left blade, a left two blades and a left three blades are sequentially arranged on the left side from top to bottom, and a right blade, a right two blades and a right three blades are sequentially arranged on the right side from top to bottom) are symmetrically distributed on the left side and the right side, wherein the three pairs of blades on the two sides are of mirror image structures and are symmetrically distributed and adopt a forward-swept layout. The inner sides of all the blades are fixedly connected with the small supporting circular ring 8, and the outer sides of all the blades are fixedly connected to the casing 7. The shape and the blade bending angle of three pairs of blades 6 which are symmetrically distributed on the left side and the right side are the same, the blades are the same type, the length of the left two blades and the length of the right two blades are the longest, and the lengths of the left one blade, the left three blades, the right one blade and the right three blades are equal and are slightly shorter than those of the left two blades and the right two blades.
Fig. 2(b) shows the profile section of each blade, and the profiles of eleven blades are CDA profiles.
Fig. 3 is a top view of the distortion generator, the blade profiles of the upper and lower sides of the left (right) side group are right trapezoid, the upper end of the trapezoid is close to the inner side of the distortion generator (i.e. close to the small ring 8), the lower end of the trapezoid is close to the outer side of the distortion generator (i.e. close to the casing 7), the lower end of the trapezoid is wider than the upper end, the right-angled side of the right trapezoid is close to the rear side of the vortex flow distortion generator, and the oblique side is close to the front side of the generator.
The reference line followed by the distribution of the 11 blades is shown in fig. 4, the line of the middle blade and the line of the middle five blades are circular arcs, the radius of the circular arcs is 200-400 mm, the preferred value is 300mm, the radian of the circular arcs is 171.53-188.69 degrees, and the preferred value is 180 degrees; the middle two-blade line and the middle four-blade line are circular arcs, the radius of the circular arcs is 200-400 mm, the preferred value is 300mm, the radian of the circular arcs is 83.29-96.89 degrees, and the preferred value is 90 degrees; the other blade lines are straight line segments, the length of the middle three blade line is 154-368 mm, and the preferred value is 253.22 mm; the length of the left two-blade line is 100 mm-200 mm, the preferred value is 150mm, and the right two-blade line is the same as the left one-blade line; the length of the left blade line is 159.97 mm-319.93 mm, the optimal value is 239.95mm, and the lengths of the left three, the right one and the right two blade lines are equal to the length of the left blade line.
The blade layout mode is as follows: the blade layout mode of the invention refers to the blade layout mode of the vortex flow distortion generator in the paper design and simulation research of novel vortex flow distortion net published by the university of air force engineering, and is improved on the basis. The concrete improvement is as follows:
1. the blade profile of eleven blades adopts a CDA blade profile;
2. the three pairs of blades 6 on the two sides adopt a forward-swept layout.
The small supporting rings 8 are symmetrically distributed and are hollow cylinders.
The circular casing 7 is a hollow cylinder, and the supporting small ring 8 and the casing 7 play roles in fixing and supporting the blades. The connection mode of the blade and the casing 7 and the connection mode of the blade and the circular ring 8 are both fixed connection.
The whole rotational flow distortion generator is of a mechanical structure, and does not contain any electronic equipment inside.
The working principle of the distortion generator is as follows: when the airflow flows through the distortion generator, the airflow is disturbed by the blades to deflect, the deflection direction of the airflow is perpendicular to the blades, the airflow points to the blade basin from the blade back, the airflow flowing through the left side blade generates a circumferential speed by being disturbed, the airflow rotates in the clockwise direction, a clockwise vortex is generated near the left side supporting small circular ring 8, and the vortex core is positioned at the circle center of the left side supporting small circular ring 8; the airflow flowing through the right blade is disturbed to generate a circumferential speed, the airflow rotates in the anticlockwise direction, an anticlockwise vortex is generated near the right supporting small ring 8, and the vortex core of the airflow is positioned at the circle center of the right supporting small ring 8. The purpose is to simulate the eddy distortion flow field so as to carry out numerical simulation research on eddy distortion of the air inlet channel.
In one embodiment of the invention, as shown in fig. 1, the external circular casing 7 has a thickness of 3mm to 10mm, preferably 5mm, and a radius of 200mm to 400mm, preferably 300 mm; the small inner supporting ring 8 has an outer diameter of 16mm to 92mm, preferably 46.78mm, and a thickness of 2mm to 10mm, preferably 5 mm. The middle blade 1 takes the upper vertexes of the two small supporting rings 8 as a starting point and an end point and is in an arc shape; the connecting line between the centers of the two small supporting rings 8 is taken as an axis and the direction is the right direction. The middle two blades 2 are in a bilaterally symmetrical circular arc shape with a 45-degree point of the left supporting small circular ring 8 as a starting point and a 135-degree point of the right supporting small circular ring 8 as an end point. The middle three blades 3 are in a bilateral symmetry arc shape by taking a 90-degree point of the left supporting small circular ring 8 as a starting point and taking a 90-degree point of the right supporting small circular ring 8 as an end point. The middle four blades 4 are in a bilaterally symmetrical circular arc shape with a-45-degree point of the left supporting small circular ring 8 as a starting point and a 225-degree point of the right supporting small circular ring 8 as an end point. The five middle blades 5 are arc-shaped with the lower vertex of the left supporting small ring 8 as a starting point and the lower vertex of the right supporting small ring 8 as an end point. The left blade, the left blade and the left blade on the left side 6 are respectively in bilateral symmetry with the center line of the distortion generator about the left three blades and the right three blades, wherein the points of 135 degrees, 180 degrees and 225 degrees of the left supporting small circular ring are taken as starting points from top to bottom, the end points are positioned on the circular case, the blades are in linear distribution, and the left three blades and the right three blades are in bilateral symmetry.
In one embodiment of the present invention, as shown in fig. 2(a), the chord length of one blade 1 increases linearly from two ends to the center, and the value is: 26.78 mm-148.14 mm, the bending angle of the blade is increased from two ends to the center according to linearity and then decreased according to linearity, and the value is as follows: 5.5 to 9.7 to 8.1 degrees. The chord length of the middle and the two blades 2 is increased linearly from the two ends to the center, and the value is as follows: 26.78 mm-126.44 mm, the bending angle of the blade increases from two ends to the center according to linearity, and the value is as follows: 7.6 to 14.3 degrees. The chord length of the three middle blades 3 is increased linearly from the two ends to the center, and the value is as follows: 26.78 mm-104.75 mm, the bending angle of the blade increases from two ends to the center according to linearity, and the value is as follows: 8.5 to 16.7 degrees. The chord length of the middle four blades 4 increases linearly from the two ends to the center, and the value is as follows: 26.78 mm-126.44 mm, the bending angle of the blade increases from two ends to the center according to linearity, and the value is as follows: 7.6 to 14.3 degrees. The chord length of the five vanes 5 increases linearly from the two ends to the center, and the value is as follows: 26.78 mm-148.14 mm, the bending angle of the blade is increased from two ends to the center according to linearity and then decreased according to linearity, and the value is as follows: 5.5 to 9.7 to 8.1 degrees.
The blades 6 are mirror symmetric with respect to the central plane of the distortion generator, so that for the right blade set, the chord length of the right blade increases linearly from the point where it is fixed to the support ring 8 to the circular casing, and the values are: 26.78 mm-199.74 mm, the bending angle of the blade is increased linearly from the fixed joint with the supporting ring 8 to the circular casing and then decreased linearly, the value is: the chord length of the right two blades of 3.0 degrees to 6.3 degrees to 5.2 degrees is increased from the position of the supporting ring 8 to the position of the circular casing according to the linearity, and the numerical value is as follows: 26.78 mm-100.59 mm, the bending angle of the blade is increased linearly from the position of the supporting ring 8 to the position of the circular casing and then decreased linearly, and the value is as follows: 3.0 to 6.3 to 5.8 degrees. The chord length of the right three blades is increased from the position of the supporting ring 8 to the position of the circular casing according to the linearity, and the numerical value is as follows: 26.78 mm-199.74 mm, the bending angle of the blade is increased linearly from the position of the supporting ring 8 to the position of the circular casing and then decreased linearly, and the value is as follows: 3.0 to 6.3 to 5.2 degrees.
The working process of the rotational flow distortion generator specifically comprises the following steps:
step 1: arranging a convective vortex flow distortion generator in an air inlet channel of an air compressor experiment table;
and 2, step: starting the gas compressor experiment table;
and step 3: flowing the gas stream through a distortion generator;
and 4, step 4: the distortion generator deflects the incoming flow to generate a standard pair vortex distortion flow field. The method comprises the following specific steps: when the airflow flows through the distortion generator, the blades of the distortion generator enable the airflow to be disturbed and deflected, the deflection direction of the airflow is perpendicular to the blades, the blade back points to the blade basin, and the airflow flowing direction deviates from the axial direction. The airflow flowing through the left blade is disturbed to generate a circumferential speed, the airflow rotates clockwise, a clockwise vortex is generated near the left supporting small ring 8, and a vortex core of the vortex is positioned at the circle center of the left supporting small ring 8; the airflow flowing through the right blade is disturbed to generate a circumferential speed, the airflow rotates anticlockwise, an anticlockwise vortex is generated near the right supporting small ring 8, and the vortex core is positioned at the center of the right supporting small ring 8;
and 5: the swirling flow distortion flow field is rotated by the rotating distortion generator model.
The blade bend angle of the invention can be adjusted according to the strength of the vortex flow distortion field to be simulated, thereby ensuring that the required vortex flow distortion field is simulated.
Claims (10)
1. A distortion generator for a swirling flow, comprising: blades, casings, rings; wherein
The number of the blades is 11, and the blades are respectively as follows:
the five blades in the middle are sequentially arranged from top to bottom: the left end and the right end of the first blade (1), the second blade (2), the third blade (3), the fourth blade (4) and the fifth blade (5) are fixedly connected with the small circular rings (8) on the left side and the right side respectively; the shapes, sizes and bending angles of the first middle blade (1), the second middle blade (2), the third middle blade (3), the fourth middle blade (4) and the fifth middle blade (5) are different, and the blade profile section of each blade is that the basin faces downwards and the back faces upwards; the bending angle of the blade is symmetrical left and right about the center of the blade; the bending angles of the middle blade (1) and the middle blade (5) are increased from the middle to the two sides and then reduced; the bending angles of the middle two blades (2), the middle three blades (3) and the middle four blades (4) are increased along with the increase of the chord length of each blade; the shape and the position of the first blade (1) and the fifth blade (5) are basically symmetrical, the shape and the position of the second blade (2) and the fourth blade (4) are basically symmetrical, and the five blades are all solid blades;
three pairs of blades (6) which are symmetrically distributed are positioned on the left side and the right side, and the left side is sequentially from top to bottom: the left first blade, the left second blade and the left third blade; the right side is sequentially from top to bottom: a right first blade, a right second blade and a right third blade; wherein, the three pairs of blades at two sides are in mirror image structure, are symmetrically distributed and adopt forward sweep layout; the inner sides of all the blades are fixedly connected with a small supporting ring (8), and the outer sides of all the blades are fixedly connected to a casing (7); the shape and the blade bending angle of three pairs of blades (6) which are symmetrically distributed on the left side and the right side are the same, the blades are the same type, the left two blades and the right two blades have the longest length, and the left one blade, the left three blades, the right one blade and the right three blades have the same length and are slightly shorter than the left two blades and the right two blades;
the blade profiles of eleven blades are CDA blade profiles;
from the top view of the convective vortex flow distortion generator, the shapes of the left blade, the left three blades, the right blade and the right three blades are all right trapezoid, the upper bottom of the trapezoid is close to the inner side of the convective vortex flow distortion generator, the lower bottom of the trapezoid is close to the outer side of the distortion generator, the lower bottom of the trapezoid is wider than the upper bottom, the right-angle side of the right trapezoid is close to the rear side of the convective vortex flow distortion generator, and the bevel side is close to the front side of the generator;
the small supporting circular rings (8) comprise a left circular ring and a right circular ring, are symmetrically distributed and are hollow cylinders;
the circular casing (7) is a hollow cylinder, and the supporting small circular ring (8) and the casing (7) play roles in fixing and supporting the blades; the connection mode of the blade and the casing (7) and the connection mode of the blade and the small supporting ring (8) are both fixed connection.
2. A distortion generator for swirling flow as claimed in claim 1, wherein the 11 vanes are distributed along a datum line: the line of the middle blade and the line of the middle five blades are circular arcs, and the radian of the circular arcs is 171.53-188.69 degrees; the line of the middle two blades and the line of the middle four blades are circular arcs, and the radian of the circular arcs is 83.29-96.89 degrees; the other blade lines are straight line segments.
3. A distortion generator for swirling flow as claimed in claim 2, wherein the 11 vanes are distributed along a datum line: the line of the middle blade and the line of the middle five blades are arcs with the radius of 300mm, and the radian is 180 degrees; the line of the middle two blades and the line of the middle four blades are arcs with the radius of 300mm, and the radian is 90 degrees; the other blade lines are straight line segments.
4. A distortion generator for a vortex flow according to claim 1, wherein the middle blade (1) has a circular arc shape starting from and ending at the upper vertices of the two small supporting rings (8); the connecting line between the circle centers of the two small supporting circular rings (8) is taken as an axis, and the right direction is taken as the positive direction; the middle two blades (2) take a 45-degree point of the left supporting small circular ring (8) as a starting point and a 135-degree point of the right supporting small circular ring (8) as an end point to form a bilaterally symmetrical circular arc shape; the middle three blades (3) take the 90-degree point of the left supporting small circular ring (8) as a starting point and the 90-degree point of the right supporting small circular ring (8) as an end point to form a bilaterally symmetrical circular arc shape; the middle four blades (4) take a-45-degree point of the left supporting small circular ring (8) as a starting point and a 225-degree point of the right supporting small circular ring (8) as an end point to form a bilaterally symmetrical circular arc shape; the five middle blades (5) take the lower vertex of the left supporting small circular ring (8) as a starting point and the lower vertex of the right supporting small circular ring (8) as an end point to form an arc shape.
5. A distortion generator for swirling flow according to claim 1, wherein a line connecting centers of two supporting small rings (8) is an axis, and a positive direction is toward the right; the left blade, the left blade and the left blade on the left side (6) and the right blade and the left three blades on the left side are respectively in bilateral symmetry about the center line of the distortion generator from top to bottom by taking 135 degrees, 180 degrees and 225 degrees of the left supporting small circular ring (8) as starting points and the end points on the circular case (7), wherein the three blades on the left side and the right side are in linear distribution.
6. A convective vortex distortion generator according to claim 1, wherein the chord length of one of the vanes (1) increases linearly from both ends to the center, and has a value of 26.78mm to 148.14mm, and the vane bending angle increases linearly from both ends to the center and then decreases linearly, and has a value of 5.5 ° to 9.7 ° to 8.1 °; the chord length of the middle two blades (2) increases linearly from the two ends to the center, the value is 26.78-126.44 mm, the bending angle of the blades increases linearly from the two ends to the center, and the value is 7.6-14.3 degrees; the chord length of the middle three blades (3) is increased linearly from two ends to the center, the value is 26.78-104.75 mm, the bending angle of the blades is increased linearly from two ends to the center, and the value is 8.5-16.7 degrees; the chord length of the middle four blades (4) is increased linearly from the two ends to the center, the value is 26.78-126.44 mm, the bending angle of the blades is increased linearly from the two ends to the center, and the value is 7.6-14.3 degrees; the chord length of the five middle blades (5) increases linearly from the two ends to the center, the value is 26.78-148.14 mm, the bending angle of the blades increases linearly from the two ends to the center and then decreases linearly, and the value is 5.5-9.7-8.1 degrees.
7. A convective vortex flow distortion generator according to claim 1, wherein the vanes (6) are mirror symmetric about the central plane of the distortion generator, and in the case of the right set of vanes, the chord length of the right vane increases linearly from the joint with the supporting small ring (8) to the circular casing (7) and has a value of 26.78mm to 199.74mm, and the vane bending angle increases linearly from the joint with the supporting small ring (8) to the circular casing (7) and then decreases linearly, and has a value of 3.0 ° to 6.3 ° to 5.2 °; the chord length of the right two blades is linearly increased from the small supporting ring (8) to the circular casing (7), the numerical value is 26.78-100.59 mm, the bending angle of the blades is linearly increased from the small supporting ring (8) to the circular casing (7) and then linearly decreased, and the numerical value is 3.0-6.3-5.8 degrees; the chord length of the right three blades is increased linearly from the position of the small supporting ring (8) to the position of the circular casing (7), the numerical value is 26.78-199.74 mm, the bending angle of the blades is increased linearly from the position of the small supporting ring (8) to the position of the circular casing (7) and then is reduced linearly, and the numerical value is 3.0-6.3-5.2 degrees.
8. The distortion generator of a convective vortex flow according to claim 1, wherein the circular casing (7) has a thickness of 3mm to 10mm and a radius of 200mm to 400 mm; the small internal supporting ring (8) has an outer diameter of 16-92 mm and a thickness of 2-10 mm.
9. A distortion generator for swirling flow according to claim 8, characterized in that the circular casing (7) has a thickness of 5mm and an outer diameter of 300 mm; the small inner supporting ring (8) has an outer diameter of 46.78mm and a thickness of 5 mm.
10. A method of operating a vortex flow distortion generator as claimed in any one of claims 1 to 8, including the steps of:
step 1: arranging a convective vortex flow distortion generator in an air inlet channel of an air compressor experiment table;
step 2: starting an axial-flow type compressor experiment table;
and step 3: the airflow passes through the distortion generator;
and 4, step 4: the distortion generator deflects the incoming flow to generate a standard pair vortex distortion flow field; the method comprises the following specific steps: when the airflow flows through the distortion generator, the blades of the distortion generator enable the airflow to be disturbed and deflected, the deflection direction of the airflow is perpendicular to the blades, the blade back points to the blade basin, and the airflow flowing direction deviates from the axial direction; the airflow flowing through the left blade is disturbed to generate a circumferential speed, the airflow rotates clockwise, a clockwise vortex is generated near the left supporting small ring (8), and the vortex core is positioned at the circle center of the left supporting small ring (8); the airflow flowing through the right blade is disturbed to generate a circumferential speed, the airflow rotates anticlockwise, an anticlockwise vortex is generated near the right support small circular ring (8), and a vortex core of the airflow is positioned at the circle center of the right support small circular ring (8);
and 5: and rotating the eddy current distorted flow field through the rotating distortion generator model.
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| BRPI0700765A (en) * | 2007-02-15 | 2007-12-04 | Embraer Aeronautica Sa | vortex generator to improve performance of recessed air intakes |
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| CN108691583A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Casing among turbogenerator |
| CN108953232A (en) * | 2018-07-20 | 2018-12-07 | 大连海事大学 | A kind of non-axisymmetric distribution stator blade axial-flow compressor |
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2021
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|---|---|---|---|---|
| BRPI0700765A (en) * | 2007-02-15 | 2007-12-04 | Embraer Aeronautica Sa | vortex generator to improve performance of recessed air intakes |
| CN103835810A (en) * | 2012-11-27 | 2014-06-04 | 中航商用航空发动机有限责任公司 | Acoustic liner for air-inlet nacelle of aircraft engine and aircraft engine |
| CN104912668A (en) * | 2015-04-24 | 2015-09-16 | 南京航空航天大学 | Variable camber vane type spiral flow distortion generator |
| CN108691583A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Casing among turbogenerator |
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