CN114658678A - Tongue plate structure of plane cascade test bed of gas compressor - Google Patents
Tongue plate structure of plane cascade test bed of gas compressor Download PDFInfo
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- CN114658678A CN114658678A CN202210157243.0A CN202210157243A CN114658678A CN 114658678 A CN114658678 A CN 114658678A CN 202210157243 A CN202210157243 A CN 202210157243A CN 114658678 A CN114658678 A CN 114658678A
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- tongue plate
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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
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
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Abstract
The invention discloses a tongue plate structure of a plane cascade test bed of a gas compressor, which comprises an upper tongue plate and a lower tongue plate which are arranged at an inlet of a test section in parallel; the inlet of the test section is connected with the side wall blade of the blade grid through a bending section; the blade grid comprises a plurality of arc-shaped blades arranged on the grid plate in an array manner; one end bending section of the tongue plate, which is contacted with the side wall blade, bends at a certain angle towards the inlet flow field of the test section; when a plane cascade test of the gas compressor is carried out, particularly under the working condition that the incoming flow speed is low, the tongue plate walls on the two sides of the test bed are longer, and the boundary layer is thicker when the boundary layer is developed from the inlet of a test section to the inlet of a cascade channel, so that the attack angles of blades on the two side walls are different from that of the middle cascade channel, and on the other hand, the flow separation of local flow fields on the two side wall surfaces of the cascade channel can influence the middle cascade channel to cause the poor periodicity; the flow field at the side wall blades at two sides can be finely adjusted by bending the end part geometry of the tongue plate, so that the flow field of the middle cascade channel is influenced and the periodicity is further improved.
Description
Technical Field
The invention relates to the technical field of performance tests of a plane cascade of a gas compressor, and mainly relates to a tongue plate structure of a plane cascade test bed of the gas compressor.
Background
The plane cascade test of the air compressor of the aero-engine is an important means for researching the design performance parameters of the blade profile of the blade, and a certain flow field periodicity is necessary in the cascade test. However, the flow field at the side wall near the cascade channel often has a large influence on the flow field of the intermediate cascade channel, and the periodicity of the cascade may even be difficult to meet the test requirements under some working conditions, so it is necessary to optimize the flow field at the side wall of the cascade channel to improve the periodicity of the cascade flow field. In methods for improving the periodicity of a flow field in a cascade test, low-energy flow suction of a side plate, adjustment of the structural shape of a tail plate and the like exist, and no method for improving a tongue plate structure and improving the flow field to further improve the periodicity of a cascade channel exists at present.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the problems in the prior art, the invention provides a tongue plate structure of a plane cascade test bed of a gas compressor, which is characterized in that the structure of the contact part of the tongue plate and a side wall blade is improved by changing the tongue plate structure, and the flow field of the contact part is improved by arranging the bending angle of the bending section of the tongue plate and the length of the bending line, so that the periodicity of a cascade channel is improved.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:
a tongue plate structure of a plane cascade test bed of a gas compressor comprises an upper side tongue plate and a lower side tongue plate which are arranged at an inlet of a test section in parallel; the inlet of the test section is connected with the side wall blade of the blade grid through a bending section; the blade grid comprises a plurality of arc-shaped blades arranged on the grid plate in an array manner;
the upper tongue plate at the inlet of the test section is connected with the upper side wall blade through a first bending section; the section of the first bending section is wedge-shaped, the first bending section is bent towards the inner side of the inlet of the test section along the upper tongue plate, a straight line part close to one side of the inlet of the test section is an upper tongue plate bending molded line, the length of the first bending section does not exceed the width of the grid plate, and the bending angle of the upper tongue plate is not higher than 10 degrees;
the lower tongue plate at the inlet of the test section is connected with the lower side wall blade through a second bending section; the section of the second bending section is wedge-shaped, the second bending section is bent towards the inner side of the inlet of the test section along the lower tongue plate, the straight line part close to one side of the inlet of the test section is a bending molded line of the lower tongue plate, the length of the second bending section does not exceed the width of the grid plate, and the bending angle of the lower tongue plate does not exceed 30 degrees.
Further, the thickness of the tongue plate is selected based on the internal and external pressure intensities of the tongue plate, and the height of the tongue plate is smaller than the distance between the end walls of the test bed.
Further, the Mach number at the entrance of the test section was chosen to be 0.7 and the angle of attack was-3.7 °.
Further, the tongue plate structure can be applied to an open type or closed type compressor plane cascade test bed.
Has the beneficial effects that:
the tongue plate structure of the compressor plane cascade test bed provided by the invention is used for solving the problem that two side walls at a cascade channel in the compressor plane cascade test bed are blades, one end, which is in contact with the side wall blades, of the tongue plate is bent towards a flow field, and the bending of the tongue plate enables airflow to enter an expansion channel of the side wall blades to be accelerated, so that the capability of resisting a counter pressure gradient of the airflow at the side wall blades can be reduced, the flow separation is reduced, and meanwhile, a boundary layer at the side wall is controlled to improve an incoming flow attack angle of a near wall surface, and the improvement of the flow periodicity of the cascade channel is facilitated.
Drawings
FIG. 1 is a schematic diagram of a tongue plate structure of a planar cascade test bed of a gas compressor provided by the invention;
FIG. 2 is a top view of a tongue plate structure of a planar cascade test bed of a gas compressor provided by the invention;
FIG. 3a is a partial enlarged view of a first bending section of a tongue plate structure of a planar cascade test bed of a gas compressor, provided by the invention;
FIG. 3b is a partial enlarged view of a second bending section of a tongue plate structure of a planar cascade test bed of the gas compressor provided by the invention;
FIG. 4a is a contour map of Mach number in the case of a straight tongue plate in an embodiment of the present invention;
FIG. 4b is a contour map of Mach number at the time of bending of the tongue plate in the embodiment of the present invention;
FIG. 5a is a flow chart of the embodiment of the present invention at the upper and lower side walls in the case of a straight tongue plate;
fig. 5b is a flow chart of the upper and lower side walls in the case of bending of the tongue plate in the embodiment of the present invention.
Description of reference numerals:
1-inlet of test section; 2-test section outlet; 3-upper tongue plate; 4-lower tongue plate; 5-grid plate.
Detailed Description
The present invention will be further described with reference to the accompanying drawings. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention designs a tongue plate structure of a compressor plane cascade test bed with a geometrically bent end part, as shown in a figure 1-2, the tongue plate structure comprises an upper side tongue plate 3 and a lower side tongue plate 4 which are arranged at an inlet 1 of a test section in parallel; the inlet 1 of the test section is connected with the side wall blade of the blade grid through a bending section; the blade grid comprises a plurality of arc-shaped blades arranged on the grid plate 5 in an array manner. The grid structure is omitted from fig. 1 for clarity of illustration.
The upper tongue plate at the inlet of the test section is connected with the upper side wall blade through a first bending section; the section of the first bending section is wedge-shaped, the first bending section is bent towards the inner side of the inlet of the test section along the upper tongue plate, the straight line part close to one side of the inlet of the test section is an upper tongue plate bending molded line, and the length of the first bending section is L1。
The lower tongue plate at the inlet of the test section is connected with the lower side wall blade through a second bending section; the section of the second bending section is wedge-shaped, the second bending section is bent towards the inner side of the inlet of the test section along the lower tongue plate, the straight line part close to one side of the inlet of the test section is a bending molded line of the lower tongue plate, and the length of the second bending section is L2。
The test conditions of a cascade test bed of a traditional linear tongue plate and a plane cascade test bed of a gas compressor in the figure 1 are set to be about 0.7 of inlet Mach number and-3.7 of attack angle, and calculation is carried out.
For a conventional straight tongue plate, as shown in fig. 4a and 5a, the suction surface of the blade near the upper sidewall in fig. 4a has a more concentrated mach number contour than the adjacent blade. In fig. 5a, where the upper tongue plate meets the side wall blade, the airflow bends more sharply in the direction behind the leading edge of the impinging end wall blade, creating a large scale flow separation downstream. In fig. 5a, at the contact part of the lower side tongue plate and the end wall guide vane, the flow is separated to a certain degree under the inverse pressure gradient.
In this embodiment, the end portion is adoptedAnd calculating the flow field of the test section by using the bent tongue plate structure. The contact end of the tongue plate and the side wall blade bends towards the side of the flow field of the test section, so that airflow can enter the expansion channel of the side wall blade to accelerate, and for the tongue plate on the upper side wall surface, the geometric adjustment position is positioned at the upstream of the inlet of the blade cascade, so the bending angle alpha of the upper side tongue plate is designed to be not more than 10 degrees, and if the angle is too large, the incoming flow attack angle of other blade cascades is likely to be influenced. For the lower side wall surface tongue plate, the geometric adjustment position is positioned at the downstream of the blade grid inlet, so the bending angle beta range of the lower side tongue plate can be slightly larger, the arranged angle beta is not more than 30 degrees, and large-scale separation vortex can be generated when the angle is too large. Because the local flow field near the side wall blade is adjusted, the length L of the side bending molded line of the tongue plate test section1And L2The length is not required to be too long, and the designed length does not exceed the width of the grid plate.
The Mach number contour line under the condition of geometric bending of the end part of the tongue plate is shown in figure 4b, the shock wave intensity of the suction surface of the blade close to the upper side wall is reduced after the geometric adjustment of the end part of the tongue plate, and the flow separation scale near the blades of the upper side wall and the lower side wall is reduced under the acceleration action of the geometric bending of the end part of the tongue plate on the airflow in figure 5 b.
The above description is only of the preferred embodiments of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the invention and these are intended to be within the scope of the invention.
Claims (4)
1. The tongue plate structure of the planar cascade test bed of the gas compressor is characterized by comprising an upper side tongue plate and a lower side tongue plate which are arranged at an inlet of a test section in parallel; the inlet of the test section is connected with the side wall blade of the blade cascade through a bending section; the blade grid comprises a plurality of arc-shaped blades arranged on the grid plate in an array manner;
the upper tongue plate at the inlet of the test section is connected with the upper side wall blade through a first bending section; the section of the first bending section is wedge-shaped, the first bending section is bent towards the inner side of the inlet of the test section along the upper tongue plate, a straight line part close to one side of the inlet of the test section is an upper tongue plate bending molded line, the length of the first bending section does not exceed the width of the grid plate, and the bending angle of the upper tongue plate is not higher than 10 degrees;
the lower tongue plate at the inlet of the test section is connected with the lower side wall blade through a second bending section; the section of the second bending section is wedge-shaped, the second bending section is bent towards the inner side of the inlet of the test section along the lower tongue plate, the straight line part close to one side of the inlet of the test section is a bending molded line of the lower tongue plate, the length of the second bending section does not exceed the width of the grid plate, and the bending angle of the lower tongue plate does not exceed 30 degrees.
2. The structure of the tongue plate of the compressor planar cascade test bed according to claim 1, wherein the thickness of the tongue plate is selected based on the internal and external pressure intensities of the tongue plate, and the height of the tongue plate is smaller than the distance between the end walls of the test bed.
3. The structure of the flat cascade test bed tongue plate of the compressor according to any one of claims 1 to 2, wherein the Mach number at the inlet of the test section is selected to be 0.7, and the attack angle is-3.7 °.
4. The structure of the tongue plate of the compressor planar cascade test bed according to any one of claims 1 to 2, wherein the structure of the tongue plate can be applied to an open or closed compressor planar cascade test bed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210157243.0A CN114658678B (en) | 2022-02-21 | 2022-02-21 | Tongue plate structure of plane cascade test bed of gas compressor |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210157243.0A CN114658678B (en) | 2022-02-21 | 2022-02-21 | Tongue plate structure of plane cascade test bed of gas compressor |
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| CN114658678A true CN114658678A (en) | 2022-06-24 |
| CN114658678B CN114658678B (en) | 2022-12-06 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07279889A (en) * | 1994-04-08 | 1995-10-27 | Ishikawajima Harima Heavy Ind Co Ltd | Cascade pressure ratio adjusting device for two-dimensional cascade tunnel |
| CN110186688A (en) * | 2019-04-28 | 2019-08-30 | 南京航空航天大学 | Hole slot structure drawing-in type transonic turbine cascade turbine test platform leaf grating is bent tailgate |
| CN110530595A (en) * | 2019-07-19 | 2019-12-03 | 南京航空航天大学 | A kind of plane cascade test platform test section inlet system of the adjustable angle of attack |
| CN112304556A (en) * | 2020-11-16 | 2021-02-02 | 大连海事大学 | Combined pumping system for improving periodicity of plane blade cascade and quality of outlet flow field |
| CN112747929A (en) * | 2020-11-30 | 2021-05-04 | 南京航空航天大学 | Flow channel adjusting mechanism of cascade test bed for expanding adjusting range of cascade attack angle |
| CN113188748A (en) * | 2021-04-30 | 2021-07-30 | 中国空气动力研究与发展中心空天技术研究所 | Supersonic velocity plane cascade flow field starting and uniformity adjusting device |
| CN113738451A (en) * | 2021-09-15 | 2021-12-03 | 西安交通大学 | Test system for measuring cooling characteristics of cascade air film |
| CN113758670A (en) * | 2021-09-10 | 2021-12-07 | 中国民航大学 | Suction and flow guide tail plate combined planar cascade flow field quality improving system |
-
2022
- 2022-02-21 CN CN202210157243.0A patent/CN114658678B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07279889A (en) * | 1994-04-08 | 1995-10-27 | Ishikawajima Harima Heavy Ind Co Ltd | Cascade pressure ratio adjusting device for two-dimensional cascade tunnel |
| CN110186688A (en) * | 2019-04-28 | 2019-08-30 | 南京航空航天大学 | Hole slot structure drawing-in type transonic turbine cascade turbine test platform leaf grating is bent tailgate |
| CN110530595A (en) * | 2019-07-19 | 2019-12-03 | 南京航空航天大学 | A kind of plane cascade test platform test section inlet system of the adjustable angle of attack |
| CN112304556A (en) * | 2020-11-16 | 2021-02-02 | 大连海事大学 | Combined pumping system for improving periodicity of plane blade cascade and quality of outlet flow field |
| CN112747929A (en) * | 2020-11-30 | 2021-05-04 | 南京航空航天大学 | Flow channel adjusting mechanism of cascade test bed for expanding adjusting range of cascade attack angle |
| CN113188748A (en) * | 2021-04-30 | 2021-07-30 | 中国空气动力研究与发展中心空天技术研究所 | Supersonic velocity plane cascade flow field starting and uniformity adjusting device |
| CN113758670A (en) * | 2021-09-10 | 2021-12-07 | 中国民航大学 | Suction and flow guide tail plate combined planar cascade flow field quality improving system |
| CN113738451A (en) * | 2021-09-15 | 2021-12-03 | 西安交通大学 | Test system for measuring cooling characteristics of cascade air film |
Non-Patent Citations (1)
| Title |
|---|
| 向宏辉等: "附面层抽吸技术在跨声速平面叶栅试验中的应用探索", 《燃气涡轮试验与研究》 * |
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| CN114658678B (en) | 2022-12-06 |
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