CN119666303A - A suction structure for improving the flow field quality of a plane cascade wind tunnel and its design method - Google Patents
A suction structure for improving the flow field quality of a plane cascade wind tunnel and its design method Download PDFInfo
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- CN119666303A CN119666303A CN202411883616.8A CN202411883616A CN119666303A CN 119666303 A CN119666303 A CN 119666303A CN 202411883616 A CN202411883616 A CN 202411883616A CN 119666303 A CN119666303 A CN 119666303A
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Abstract
The application belongs to the technical field of subsonic plane blade cascade wind tunnel tests, and particularly relates to a suction structure for improving the quality of a plane blade cascade wind tunnel flow field and a design method thereof. The structure comprises an inlet flow passage formed between the movable lower guide wall and the movable upper guide wall, wherein a plurality of blades are arranged on the plane blade grid test piece at equal grid intervals, the upper end wall is a suction surface of the uppermost blade of the plane blade grid test piece, the front edge of the upper end wall is connected with the tail end of the movable upper guide wall, a penetrating suction slit is formed along the normal direction of the surface of the upper end wall, the lower end wall is a suction surface of the lowermost blade of the plane blade grid test piece, and the front edge of the lower end wall is connected with the tail end of the movable lower guide wall. The suction structure for improving the quality of the plane blade grid wind tunnel flow field can partially or completely weaken adverse effects of the flow field quality, further improve the quality of the plane blade grid wind tunnel flow field and ensure the validity of test data.
Description
Technical Field
The application belongs to the technical field of subsonic plane blade cascade wind tunnel tests, and particularly relates to a suction structure for improving the quality of a plane blade cascade wind tunnel flow field and a design method thereof.
Background
The plane blade grid wind tunnel is basic test equipment which is widely applied in the design and research of axial flow impeller machinery. The design of the core components of the aeroengine, namely the compressor and the turbine blades, is widely applied to the verification of blade profile performance, the verification of blade profile design methods, the verification of CFD design programs and the verification of new test measurement technologies without leaving a large number of supports for plane blade grid wind tunnel tests. The cascade wind test database established based on the plane cascade wind tunnel test technology is always the technical core of each large aeroengine company.
When the plane blade cascade test is carried out, the airflow before the cascade is firstly contacted with the upper end wall of the plane blade cascade, obvious turning occurs when the airflow passes through the upper end wall with larger curvature, flow separation is very easy to occur, the channels of the upper end wall are blocked, static pressure before the cascade is increased, mach number is reduced, the airflow is deflected to the side of the lower end wall under the action of the circumferential pressure difference, the flow of each channel of the plane blade cascade is caused to be different, the uniformity of inlet Mach number and airflow angle and the flow field period after the cascade are reduced, and the requirement of the plane blade cascade test cannot be met.
Modern high-load compressor blades are typically characterized by high subsonic speeds and airflow deflection angles, and the inherent influence of the quality of the planar cascade wind tunnel flow field is particularly remarkable. Therefore, the adverse effect of the flow field quality can be partially or completely weakened by a regulation and control technical scheme, so that the flow field quality of the plane blade grid wind tunnel is improved, and the validity of test data is ensured.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a suction structure for improving the quality of a plane blade grid wind tunnel flow field and a design method thereof, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
In a first aspect, the present application provides a suction structure for improving the quality of a planar cascade wind tunnel flow field, comprising:
a movable upper deflector wall;
A movable lower guide wall, an inlet flow channel is formed between the movable lower guide wall and the movable upper guide wall;
the planar blade grid test piece is provided with a plurality of blades at equal grid distances;
The upper end wall is the suction surface of the uppermost blade of the planar cascade test piece, the front edge of the upper end wall is connected with the tail end of the movable upper guide wall, and a penetrating suction slit is formed along the normal direction of the surface of the upper end wall;
The lower end wall is the suction surface of the lowest blade of the planar cascade test piece, and the front edge of the lower end wall is connected with the tail end of the movable lower guide wall.
In at least one embodiment of the application, the planar cascade test piece is mounted on the test section by a rotatable disk.
In at least one embodiment of the present application,
The front edges of a plurality of blades jointly form a front edge line of the plane blade grid test piece;
The trailing edges of a plurality of the blades together form the trailing edge line of the planar cascade test piece.
In at least one embodiment of the application, the suction slots are parallel to the leading and trailing edge lines of the plurality of blades on the planar cascade test piece.
The second aspect of the present application provides a method for designing a suction structure for improving the quality of a planar cascade wind tunnel flow field, for designing a suction structure for improving the quality of a planar cascade wind tunnel flow field as described above, comprising:
Step one, determining the chord direction position of a suction slit;
step two, determining the height B of the suction slit;
Step three, determining the width W of the suction slit;
And step four, realizing the design of a suction structure for improving the quality of the plane cascade wind tunnel flow field according to each parameter.
In at least one embodiment of the present application, in step one, determining the chordwise location of the suction slit comprises:
s11, determining the positions of the front edge point and the tail edge point of the uppermost blade on the plane blade grid test piece according to the size and the air inlet angle of the plane blade grid test piece;
s12, obtaining the chord length C of the blade;
S13, determining the chord direction position of the suction slit according to the positions of the front edge point and the tail edge point of the uppermost blade on the plane blade grid test piece and the chord length C of the blade.
In at least one embodiment of the present application, in S13, a distance between a center of the suction slit and a front edge point of the uppermost blade is l=0.4 to 0.8c, and the center of the suction slit is located on an inner wall surface of the upper end wall.
In at least one embodiment of the present application, in step two, determining the height B of the suction slit comprises:
acquiring the height H of the blade on the plane blade grid test piece;
Determining the height B of the suction slit from the height H of the blade, comprising:
the distance d between the two ends of the suction slit and the spanwise boundary of the blade is 0.1-0.15H, namely the height B of the suction slit is 0.7-0.8H.
In at least one embodiment of the present application, step three, determining the width W of the suction slit, comprises:
the width W of the suction slit is 0.1-0.3C.
In at least one embodiment of the present application,
When the plane blade grid test piece is in a negative attack angle state, the distance L between the center of the suction slit and the front edge point of the uppermost blade is 0.4-0.6C, and the width W of the suction slit is 0.1-0.2C;
when the plane blade grid test piece is in a positive attack angle state, the distance L between the center of the suction slit and the front edge point of the uppermost blade is 0.6-0.8C, and the width W of the suction slit is 0.2-0.3C.
The invention has at least the following beneficial technical effects:
The suction structure for improving the quality of the plane blade grid wind tunnel flow field can partially or completely weaken adverse effects of the flow field quality, further improve the quality of the plane blade grid wind tunnel flow field and ensure the validity of test data.
Drawings
FIG. 1 is a schematic drawing of a suction structure for improving the quality of a planar cascade wind tunnel flow field according to an embodiment of the present application;
FIG. 2 is a schematic view of an upper end wall of a suction structure for improving the quality of a planar cascade wind tunnel flow field according to an embodiment of the present application;
FIG. 3 is a schematic drawing of a suction slot of a suction structure for improving the quality of a planar cascade wind tunnel flow field according to an embodiment of the present application.
Wherein:
11-movable upper guide wall, 12-movable lower guide wall, 21-plane blade cascade test piece, 22-upper end wall, 23-lower end wall, 24-suction slit, 31-rotatable disk.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The application is described in further detail below with reference to fig. 1 to 3.
In a first aspect the application provides a suction structure for improving the quality of a planar cascade wind tunnel flow field, comprising a movable upper guide wall 11, a movable lower guide wall 12, a planar cascade test piece 21, an upper end wall 22, suction slits 24 and a lower end wall 23.
Specifically, as shown in FIG. 1, an inlet flow channel is formed between a movable lower guide wall 12 and a movable upper guide wall 11, a plane blade grating test piece 21 is arranged on a test section through a rotatable disc 31, a plurality of blades are arranged on the plane blade grating test piece 21 at equal grating distances, the front edges of the blades jointly form a front edge line of the plane blade grating test piece 21, and the tail edges of the blades jointly form a tail edge line of the plane blade grating test piece 21.
The upper end wall 22 is the suction surface of the uppermost blade of the planar cascade test piece 21, the front edge of the upper end wall 22 is connected with the tail end of the movable upper guide wall 11, a penetrating suction slit 24 is formed along the normal direction of the surface of the upper end wall 22, the suction slit 24 is parallel to the front edge line and the tail edge line of a plurality of blades on the planar cascade test piece 21, the lower end wall 23 is the suction surface of the lowermost blade of the planar cascade test piece 21, and the front edge of the lower end wall 23 is connected with the tail end of the movable lower guide wall 12.
According to the suction structure for improving the quality of the plane cascade wind tunnel flow field, the plane cascade model is formed by arranging a plurality of identical blades on the plane cascade test piece 21 and linearly arranging the blades according to a certain distance, so that the periodic flow of the annular element cascade of the compressor or turbine blade is simulated. In order to obtain the blowing test data reflecting the true performance of the blade profile, the planar blade-grid test piece 21 has good flow field periodicity and can meet the flow field quality requirements.
According to the suction structure for improving the quality of the wind tunnel flow field of the plane blade cascade, the plane blade cascade test piece 21 is arranged on the rotatable disc 31 of the test section, the adjustment of the incoming flow inlet angle (attack angle) of the blade cascade is realized through the cooperation of the movable upper and lower guide walls, and in order to seal a flow passage to reduce flow leakage, the movable upper and lower guide walls are connected with the front edges of the upper and lower end walls of the suction surface positions of the two blades at the outermost end of the plane blade cascade test piece 21. Since the air inlet angle of the blade cascade is generally acute, the plane blade cascade test piece 21 is always inclined relative to the axial incoming flow of the wind tunnel, and the larger the air inlet angle is, the more inclined the blade cascade is. The movable upper guide wall 11 is connected with the upper end wall 22 and forms an upper boundary of the test section together with the suction surface of the uppermost blade, and the movable lower guide wall 12 is connected with the lower end wall 23 and forms a lower boundary of the test section together with the pressure surface of the lowermost blade.
The second aspect of the present application provides a design method of a suction structure for improving the quality of a planar cascade wind tunnel flow field, which is used for designing the suction structure for improving the quality of the planar cascade wind tunnel flow field, and the design method comprises:
step one, determining the chord-wise position of the suction slit 24;
Step two, determining the height B of the suction slit 24;
step three, determining the width W of the suction slit 24;
And step four, realizing the design of a suction structure for improving the quality of the plane cascade wind tunnel flow field according to each parameter.
In the design method for the suction structure for improving the quality of the plane cascade wind tunnel flow field, in the first step, the chord direction position of the suction slit 24 is determined, and the method comprises the following steps:
s11, determining the positions of the front edge point and the tail edge point of the uppermost blade on the plane blade grid test piece 21 according to the size and the air inlet angle of the plane blade grid test piece 21;
s12, obtaining the chord length C of the blade;
s13, determining the chord direction position of the suction slit 24 according to the positions of the front edge point and the tail edge point of the uppermost blade on the plane blade cascade test piece 21 and the chord length C of the blade.
In a preferred embodiment of the present application, in S13, the distance between the center of the suction slit 24 and the leading edge point of the uppermost blade is l=0.4 to 0.8c, and the center of the suction slit 24 is located on the inner wall surface of the upper end wall.
In the second step, the design method for improving the quality of the planar cascade wind tunnel flow field of the application determines the height B of the suction slit 24, and comprises the following steps:
acquiring the height H of the blade on the plane blade cascade test piece 21;
Determining the height B of the suction slit 24 from the height H of the blade includes:
The distance d between the two ends of the suction slit 24 and the spanwise boundary of the blade ranges from 0.1 to 0.15h, i.e., the height B of the suction slit 24 ranges from 0.7 to 0.8h.
The application relates to a design method of a suction structure for improving the quality of a plane blade grid wind tunnel flow field, which comprises the following steps:
The width W of the suction slit 24 is in the range of 0.1 to 0.3C.
In the embodiment, when the width W of the suction slit 24 is determined, the range of the distance L between the center of the suction slit 24 and the front edge point of the uppermost blade is 0.4-0.6C when the planar cascade test piece 21 is in the negative attack angle state, the range of the width W of the suction slit 24 is 0.1-0.2C, and the range of the distance L between the center of the suction slit 24 and the front edge point of the uppermost blade is 0.6-0.8C when the planar cascade test piece 21 is in the positive attack angle state, and the range of the width W of the suction slit 24 is 0.2-0.3C.
According to the design method for the suction structure for improving the quality of the plane cascade wind tunnel flow field, the suction slits 24 are arranged on the surface of the upper end wall 22 and serve as the suction structure for suction, so that the suction structure can act on a core area of the upper end wall 22 with deteriorated flow field more directly or more closely, the improvement effect on flow separation and blockage in the upper end wall 22 channel is more prominent, low-energy fluid in the upper end wall 22 channel can be pumped away under the condition of consuming smaller suction flow, the blockage degree of the upper end wall 22 channel is relieved, and the uniformity of the plane cascade inlet flow field and the periodicity of the outlet flow field are effectively improved. The suction applied to the surface of the upper end wall 22 has less interference with the planar cascade inlet flow field than the suction applied to the aft portion of the movable upper guide wall 11, and better inlet flow field uniformity can be achieved with less suction flow consumption. In addition, the tail part of the movable upper guide wall 11 has small improvement effect on the plane cascade outlet flow field, the quality of the outlet flow field is indirectly improved mainly by improving the quality of the inlet flow field, the surface of the upper end wall 22 is sucked close to the cascade outlet, the scattering of airflow to the surrounding atmosphere after the airflow is separated from the cascade can be directly weakened by sucking, and the interference on the outlet atmosphere boundary is obviously inhibited, so that the periodicity of the cascade outlet Mach number and the airflow angle is directly improved.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411883616.8A CN119666303A (en) | 2024-12-19 | 2024-12-19 | A suction structure for improving the flow field quality of a plane cascade wind tunnel and its design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411883616.8A CN119666303A (en) | 2024-12-19 | 2024-12-19 | A suction structure for improving the flow field quality of a plane cascade wind tunnel and its design method |
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| Publication Number | Publication Date |
|---|---|
| CN119666303A true CN119666303A (en) | 2025-03-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202411883616.8A Pending CN119666303A (en) | 2024-12-19 | 2024-12-19 | A suction structure for improving the flow field quality of a plane cascade wind tunnel and its design method |
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| Country | Link |
|---|---|
| CN (1) | CN119666303A (en) |
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- 2024-12-19 CN CN202411883616.8A patent/CN119666303A/en active Pending
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