CN112964472A - Stabilizing section for plane blade grid high-altitude flow simulation device - Google Patents
Stabilizing section for plane blade grid high-altitude flow simulation device Download PDFInfo
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- CN112964472A CN112964472A CN202110305922.3A CN202110305922A CN112964472A CN 112964472 A CN112964472 A CN 112964472A CN 202110305922 A CN202110305922 A CN 202110305922A CN 112964472 A CN112964472 A CN 112964472A
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Abstract
The invention discloses a stabilizing section for a plane cascade high-altitude flow simulation device. The stabilizing section is a cylindrical body and sequentially comprises a rectifying section and a static flow section from front to back along the airflow direction, and a probe seat is fixed on the static flow section; the rectifying section and the static flow section are positioned by a spigot and connected by a flange; the rectifying section adopts a double-layer sleeve structure, the outer layer is a pressure-bearing shell, and the inner layer sequentially comprises a pressure ring, a sintered wire mesh, a honeycomb device and a damping net from front to back along the airflow direction; a linear slide rail is arranged on the inner wall of the outer layer, a linear slide block is arranged on the outer wall of the inner layer, and the inner layer moves back and forth along the linear slide rail through the linear slide block; the outer layer and the inner layer are positioned through the stop ring and fixed through the hexagon socket head cap screw on the press ring. This stable section simple structure, it is convenient to change, and it is convenient to maintain, can save experimental preparation time, improves test efficiency.
Description
Technical Field
The invention belongs to the field of basic research and test equipment of aeroengines, and particularly relates to a stabilizing section for a plane cascade high-altitude flow simulation device.
Background
The aerodynamic profile of the rotor/stator blades determines the aerodynamic performance of the aircraft turbine (including fan/compressor and turbine) and the gas turbine, which are key components for maintaining the thermodynamic cycle and generating thrust. In order to design high-performance aero jet engines and gas turbines, the design method and flow characteristics of the turbine need to be studied on the cascade (two-dimensional blade profile) level. In order to carry out the test research on the flow aerodynamic characteristics of the cascade channels under the real flight condition on the ground, ground equipment capable of simulating parameters such as the flow Mach number, the Reynolds number and the like of the cascade channels in the actual flight must be built so as to ensure that a large amount of aerodynamic performance test research and technical verification can be carried out under the condition close to the actual working state, so that the flow mechanism, characteristics and rules in the cascade channels can be analyzed and researched, and a new design scheme is verified.
The stabilizing section is one of important components of the plane cascade high-altitude flow simulation device and plays roles in filtering airflow impurities, stabilizing incoming flow, reducing turbulence degree and providing a high-quality flow field for the cascade test section. At present, the stable section for the plane cascade high-altitude flow simulation device at home and abroad has the following defects: 1. a sintering silk screen is not additionally arranged, so that the filtering of incoming fine impurities cannot be carried out, the improvement of the flow field quality of a cascade test section is influenced, and the damage to a cascade test piece and a measuring probe is likely to be caused; 2. the rectification section internal member includes that honeycomb ware, damping net etc. adopt transition fit to install in stabilizing the section casing, and the installation is dismantled very inconveniently, and intensity of labour is big, inconvenient maintenance.
At present, the requirement of developing a stable section which can realize filtering the incoming flow fine impurities, further stabilize the flow field and conveniently detach the maintenance is urgently needed, a high-quality flow field is provided for a cascade test section, and the requirements of basic research and technical verification of advanced aero-engine turbine and gas turbine blade type cascade flow simulation pneumatic performance tests are met.
Disclosure of Invention
The invention aims to provide a stabilizing section for a plane blade grid high-altitude flow simulation device.
The invention relates to a stabilizing section for a plane blade grid high-altitude flow simulation device, which is characterized in that the stabilizing section is a cylindrical body and sequentially comprises a rectifying section and a static flow section from front to back along the airflow direction, and the rectifying section and the static flow section are positioned through pin holes and connected through flanges; probe seats are uniformly distributed on the static flow section along the airflow direction at a distance L from the end face of the outlet in the circumferential direction, and the probe seats are welded on the position of a measuring hole of a sensor of the static flow section;
the rectifying section adopts a double-layer sleeve structure form, the outer layer of the rectifying section is provided with a rectifying section pressure-bearing shell, a rectifying section front flange and a rectifying section rear flange, and the inner layer of the rectifying section sequentially comprises a front clamp ring, a sintered wire mesh lining assembly, a honeycomb device assembly, a plurality of groups of damping mesh positioning lining assemblies and a rear clamp ring from front to back along the airflow direction; two groups of linear sliding rails are arranged on the inner wall of the outer layer of the rectifying section, linear sliding blocks (110) are arranged on the outer walls of all components on the inner layer of the rectifying section, and all the components on the inner layer of the rectifying section are driven to move back and forth by the linear sliding blocks (110) moving back and forth along the linear sliding rails; the front compression ring, the sintered wire mesh lining assembly, the honeycomb device assembly and the multiple groups of damping mesh lining assemblies are sequentially exposed after moving forwards, so that maintenance is convenient; the inner layer of the rectifying section and the outer layer of the rectifying section are positioned through a linear slide rail, and an inner layer sintering silk screen lining assembly, a honeycomb device assembly and a plurality of groups of damping net positioning lining assemblies are pressed and fixed through inner hexagonal screws on a front pressing ring and a rear pressing ring;
the static flow section also adopts a double-layer sleeve structure, the outer layer of the static flow section is a static flow section pressure-bearing shell, a static flow section front flange and a static flow section rear flange, and the inner layer of the static flow section sequentially comprises a compression ring and a static flow section lining from front to back along the airflow direction; the static flow section inner layer and the static flow section outer layer are positioned through a stop ring, and the static flow section lining is compressed and fixed through the hexagon socket head cap screws on the compression ring.
Further, the distance L is the section position of the static flow section from the outlet end face 1/5-1/2.
Furthermore, a total pressure probe or a total temperature probe is arranged on the probe seat.
Further, the linear slide rail is a V-shaped slide rail or an I-shaped slide rail.
Furthermore, reinforcing ribs are welded outside the rectifying section and the static flow section.
Furthermore, rubber strips are adopted for sealing between the front clamp ring and the sintered wire mesh lining assembly, between the rear clamp ring and the damping mesh assembly, and between the clamp ring and the static flow section lining.
Furthermore, the inner lining components of the multiple groups of damping nets and the inner lining wall surfaces of the static flow section are all provided with straight holes, the aperture size phi is 3-8 mm, the aperture ratio is 2-5%, and the inner lining components and the static flow section are distributed in a star shape.
Furthermore, the static flow section lining is replaced by a turbulence generator for changing the turbulence degree of the flow field.
In order to facilitate maintenance and replacement of the rectifying device, the rectifying section in the stabilizing section of the plane cascade high-altitude flow simulation device adopts a double-layer structure form, the inner shell rectifies, the outer shell bears pressure, the sintered wire mesh, the honeycomb device and the damping net are all in a modular design and are fixed on the outer shell through the linear slide rail, and the installation and the disassembly are convenient.
When the PIV test is carried out, the sintering silk screen used in the stable section of the plane cascade high-altitude flow simulation device can be taken out, and the sintering silk screen is prevented from filtering trace particles to influence the particle concentration of the cascade test section.
When the turbulence degree of the flow field needs to be changed, the static flow section lining in the stable section of the plane blade grid high-altitude flow simulation device can be replaced by the turbulence generators with different grids, so that the turbulence degree index of the downstream flow field is changed.
The stabilizing section for the plane blade grid high-altitude flow simulation device is simple in structure, the inner components are convenient to mount and dismount, and convenient to maintain, the time for replacing, maintaining and maintaining the inner components can be saved, and the flow field quality and the test accuracy of the test section are improved.
Drawings
FIG. 1 is a perspective view of a stabilization segment for a planar cascade high altitude flow simulator of the present invention.
FIG. 2 is a schematic structural diagram of a rectifying section in a stabilizing section of the high-altitude flow simulation device for the planar blade cascade.
FIG. 3 is a schematic structural diagram of a static flow section in a stable section of the high-altitude flow simulation device for the planar blade cascade of the invention.
In the figure, 1, a rectifying section 2, a static flow section 3 and a probe seat;
101. the structure comprises a rectifying section pressure-bearing shell 102, a rectifying section front flange 103, a rectifying section rear flange 104, a front compression ring 105, a sintering wire mesh lining assembly 106, a honeycomb assembly 107, a damping mesh assembly 108, a rear compression ring 109, a linear slide rail 110 and a linear slide block;
201. the static flow section comprises a static flow section pressure-bearing shell 202, a static flow section front flange 203, a static flow section rear flange 204, a clamp ring 205 and a static flow section lining.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in fig. 1, the stabilizing section of the plane cascade high-altitude flow simulation device is a cylindrical body, and sequentially comprises a rectifying section 1 and a static flow section 2 from front to back along the airflow direction, wherein the rectifying section 1 and the static flow section 2 are positioned through a pin hole and connected through a flange; the probe seats 3 are uniformly distributed at the position of the static flow section 2, which is away from the outlet end face by a distance L in the air flow direction, in the circumferential direction, and the probe seats 3 are welded at the position of a sensor measuring hole of the static flow section 2;
as shown in fig. 2, the rectifying section 1 adopts a double-layer sleeve structure, the outer layer of the rectifying section 1 is a rectifying section pressure-bearing shell 101, a rectifying section front flange 102 and a rectifying section rear flange 103, and the inner layer of the rectifying section 1 sequentially comprises a front clamp ring 104, a sintered wire mesh lining assembly 105, a honeycomb device assembly 106, a plurality of damping mesh positioning lining assemblies 107 and a rear clamp ring 108 from front to rear along the airflow direction; two groups of linear sliding rails 109 are arranged on the inner wall of the outer layer of the rectifying section 1, linear sliding blocks 110 are arranged on the outer walls of all components on the inner layer of the rectifying section 1, and all the components on the inner layer of the rectifying section 1 are driven to move back and forth along the linear sliding rails 109 through the linear sliding blocks 110; the front pressing ring 104, the sintering wire mesh lining assembly 105, the honeycomb device assembly 106 and a plurality of groups of damping mesh lining assemblies 107 are exposed in sequence by moving forwards, so that maintenance is facilitated; the inner layer of the rectifying section 1 and the outer layer of the rectifying section 1 are positioned through a linear slide rail 109, and an inner layer sintering wire mesh lining assembly 105, a honeycomb device assembly 106 and a plurality of groups of damping mesh positioning lining assemblies 107 are pressed and fixed through inner hexagon screws on a front pressing ring 104 and a rear pressing ring 108;
as shown in fig. 3, the static flow section 2 also adopts a double-layer sleeve structure, the outer layer of the static flow section 2 is a static flow section pressure-bearing shell 201, a static flow section front flange 202 and a static flow section rear flange 203, and the inner layer of the static flow section 2 sequentially comprises a compression ring 204 and a static flow section lining 205 from front to back along the airflow direction; the inner layer of the static flow section 2 and the outer layer of the static flow section 2 are positioned by a stop ring, and the static flow section lining 205 is compressed and fixed by an inner hexagon screw on the compression ring 204.
Further, the distance L is the section position of the static flow section 2 from the outlet end face 1/5-1/2.
Furthermore, a total pressure probe or a total temperature probe is arranged on the probe seat 3.
Further, the linear slide rail 109 is a V-shaped slide rail or an i-shaped slide rail.
Furthermore, reinforcing ribs are welded outside the rectifying section 1 and the static flow section 2.
Further, rubber strips are used for sealing between the front clamp ring 104 and the sintered wire mesh lining assembly 105, between the rear clamp ring 108 and the damping mesh assembly 107, and between the clamp ring 204 and the static flow section lining 205.
Furthermore, the wall surfaces of the multiple groups of damping net lining 107 components and the static flow section lining 205 are provided with straight holes, the aperture size phi is 3 mm-phi 8mm, the aperture ratio is 2% -5%, and the damping net lining and the static flow section lining are distributed in a star shape.
Further, the static segment liner 205 is replaced with a turbulence generator to change the turbulence of the flow field.
Example 1
The total length of the stabilizing section for the plane blade cascade high-altitude flow simulation device is 3000mm, wherein the length of a rectifying section is 1mm, the length of a static flow section is 2mm, and the effective inner diameter of the stabilizing section is phi 1600 mm. The sintering silk screen adopts a Weiwen punching sintering net, and the filtering precision range is 2-200 mu m. The honeycomb pipe length of the honeycomb device is 150mm, the wall thickness is 0.15mm, the opposite side distance is 10mm, the damping nets are totally arranged in 5 layers, the interval between the first layer of damping net and the honeycomb device is 200mm, the interval between each layer of damping net is 1mm, the damping nets are 20-mesh stainless steel wire square hole screen nets, the square hole size of the square hole screen net is 0.85mm, the wire diameter is 0.2mm, and the opening rate of the screen net is 64%. The distance L between the probe seat 3 and the outlet end face L of the static flow section is 350 mm.
Although embodiments of the present invention have been disclosed above and described in considerable detail, this is not to be understood as a limitation of the scope of the invention. It will be apparent to those skilled in the art that various changes and modifications can be made without departing from the spirit and scope of the invention. It is therefore intended that the invention not be limited to the exact details and illustrations described and illustrated herein, but fall within the scope of the appended claims and equivalents thereof.
Claims (8)
1. A stabilizing section for a plane blade grid high-altitude flow simulation device is characterized in that the stabilizing section is a cylindrical body and sequentially comprises a rectifying section (1) and a static flow section (2) from front to back along the airflow direction, and the rectifying section (1) and the static flow section (2) are positioned through pin holes and connected through flanges; probe seats (3) are uniformly distributed on the static flow section (2) along the airflow direction at a distance L from the end face of the outlet in the circumferential direction, and the probe seats (3) are welded on the position of a sensor measuring hole of the static flow section (2);
the rectifying section (1) adopts a double-layer sleeve structure, the outer layer of the rectifying section (1) is a rectifying section pressure-bearing shell (101), a rectifying section front flange (102) and a rectifying section rear flange (103), and the inner layer of the rectifying section (1) sequentially comprises a front clamp ring (104), a sintered wire mesh lining assembly (105), a honeycomb device assembly (106), a plurality of groups of damping mesh positioning lining assemblies (107) and a rear clamp ring (108) from front to back along the airflow direction; two groups of linear sliding rails (109) are arranged on the inner wall of the outer layer of the rectifying section (1), linear sliding blocks (110) are arranged on the outer walls of all components on the inner layer of the rectifying section (1), and all the components on the inner layer of the rectifying section (1) are driven to move back and forth along the linear sliding rails (109) through the linear sliding blocks (110); the front pressing ring (104), the sintering wire mesh lining assembly (105), the honeycomb device assembly (106) and a plurality of groups of damping mesh lining assemblies (107) are sequentially exposed after moving forwards, and maintenance is facilitated; the inner layer of the rectifying section (1) and the outer layer of the rectifying section (1) are positioned through a linear sliding rail (109), and an inner layer sintering wire mesh lining assembly (105), a honeycomb device assembly (106) and a plurality of groups of damping mesh positioning lining assemblies (107) are pressed and fixed through inner hexagon screws on a front pressing ring (104) and a rear pressing ring (108);
the static flow section (2) also adopts a double-layer sleeve structure form, the outer layer of the static flow section (2) is a static flow section pressure-bearing shell (201), a static flow section front flange (202) and a static flow section rear flange (203), and the inner layer of the static flow section (2) sequentially comprises a compression ring (204) and a static flow section lining (205) from front to back along the airflow direction; the inner layer of the static flow section (2) and the outer layer of the static flow section (2) are positioned through a stop ring, and the static flow section lining (205) is compressed and fixed through an inner hexagon screw on the compression ring (204).
2. The stabilizing section for the planar cascade high altitude flow simulator as claimed in claim 1, wherein the distance L is a cross sectional position of the static flow section (2) from the outlet end face 1/5-1/2.
3. The stabilizing section for the planar cascade high altitude flow simulation device according to claim 1, wherein a total pressure probe or a total temperature probe is installed on the probe seat (3).
4. The stabilizing section for a planar cascade high altitude flow simulator according to claim 1, wherein the linear slide (109) is a V-shaped slide or an i-shaped slide.
5. The stabilizing section for the planar cascade high altitude flow simulation device according to claim 1, wherein reinforcing ribs are welded outside the rectifying section (1) and the static flow section (2).
6. The stabilizing section for the planar cascade high altitude flow simulation device according to claim 1, wherein rubber strips are used for sealing between the front clamp ring (104) and the sintered wire mesh lining assembly (105), between the rear clamp ring (108) and the damping mesh assembly (107), and between the clamp ring (204) and the static flow section lining (205).
7. The stabilizing section for the planar cascade high altitude flow simulation device according to claim 1, wherein the wall surfaces of the multiple sets of damping net lining (107) components and the static flow section lining (205) are provided with straight holes, the aperture size is phi 3 mm-phi 8mm, the aperture ratio is 2% -5%, and the damping net lining components and the static flow section lining are distributed in a star shape.
8. The stabilizer section for a planar cascade high altitude flow simulator as defined in claim 1 wherein the static flow section liner (205) is replaced with a turbulence generator to vary the turbulence of the flow field.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110305922.3A CN112964472B (en) | 2021-03-23 | 2021-03-23 | Stabilizing section for plane blade grid high-altitude flow simulation device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110305922.3A CN112964472B (en) | 2021-03-23 | 2021-03-23 | Stabilizing section for plane blade grid high-altitude flow simulation device |
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| CN112964472A true CN112964472A (en) | 2021-06-15 |
| CN112964472B CN112964472B (en) | 2022-02-15 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115931368A (en) * | 2023-03-09 | 2023-04-07 | 中国航发四川燃气涡轮研究院 | Flow field uniform device capable of adapting to use environment and used for improving air inlet quality |
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| US10545069B1 (en) * | 2015-04-07 | 2020-01-28 | United States Of America As Represented By The Secretary Of The Air Force | Cascade wind tunnel turbulence grid |
| CN111649948A (en) * | 2020-06-24 | 2020-09-11 | 湖南汉能科技有限公司 | Air inlet system for annular blade cascade performance tester |
| CN111649947A (en) * | 2020-06-24 | 2020-09-11 | 湖南汉能科技有限公司 | Annular cascade performance tester |
| CN112525478A (en) * | 2020-12-18 | 2021-03-19 | 大连海事大学 | Electric adjustment plane cascade experimental system |
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2021
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US10545069B1 (en) * | 2015-04-07 | 2020-01-28 | United States Of America As Represented By The Secretary Of The Air Force | Cascade wind tunnel turbulence grid |
| CN110319999A (en) * | 2019-07-31 | 2019-10-11 | 中国航发沈阳发动机研究所 | Carry out the system and method for turbulent flow screen honeycomb PIV optical test based on cascade wind tunnel |
| CN111649948A (en) * | 2020-06-24 | 2020-09-11 | 湖南汉能科技有限公司 | Air inlet system for annular blade cascade performance tester |
| CN111649947A (en) * | 2020-06-24 | 2020-09-11 | 湖南汉能科技有限公司 | Annular cascade performance tester |
| CN112525478A (en) * | 2020-12-18 | 2021-03-19 | 大连海事大学 | Electric adjustment plane cascade experimental system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115931368A (en) * | 2023-03-09 | 2023-04-07 | 中国航发四川燃气涡轮研究院 | Flow field uniform device capable of adapting to use environment and used for improving air inlet quality |
| CN115931368B (en) * | 2023-03-09 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Flow field uniformity device for improving air intake quality and self-adapting use environment |
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| CN112964472B (en) | 2022-02-15 |
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