CN111649948A - Air inlet system for annular blade cascade performance tester - Google Patents
Air inlet system for annular blade cascade performance tester Download PDFInfo
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- CN111649948A CN111649948A CN202010589558.3A CN202010589558A CN111649948A CN 111649948 A CN111649948 A CN 111649948A CN 202010589558 A CN202010589558 A CN 202010589558A CN 111649948 A CN111649948 A CN 111649948A
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Abstract
The invention provides an air inlet system for an annular cascade performance tester, which is characterized by comprising an air inlet pipeline, a straight pipe section, a diffusion section, a stabilization section, a convergence section, a spray pipe and a cascade test section; the air inlet pipeline comprises a large air inlet pipeline, a small air inlet pipeline and an air outlet pipeline; the large and small air inlet pipelines and the air outlet pipelines are respectively provided with a group of pressure regulating valves and fine adjusting valves; the rear part of the three-way joint is connected with the straight pipe section through an expansion joint; a conical diffusion section is connected behind the straight pipe section; the diffusion section is connected with the stabilization section; the stabilizing section comprises a rectifying section and a voltage stabilizing section; a sintered wire mesh and a honeycomb rectifier are sequentially arranged in the rectifying section; a damping net is arranged in the pressure stabilizing section; the voltage stabilizing section is connected with the convergence section; the convergent section is connected with the cascade test section through a spray pipe; the air inlet system provided by the invention can jointly adjust the air inlet pressure and the air inlet flow, meets the requirements of the annular cascade performance test on the air inlet pressure and the air inlet flow, and has good flow field quality.
Description
Technical Field
The invention relates to the technical field of aero-engine tests, in particular to an air inlet system for an annular cascade tester.
Background
The performance indexes of the aero-engine are directly influenced by the performance of the cascade, complex flow field structures and loss mechanisms in cascade runners are studied in detail, and methods for reducing energy loss in the cascade runners and improving aerodynamic performance of the cascade are explored, so that the method becomes important research content for improving the performance of the aero-engine. Known from the existing cascade theory and test, the flow in the cascade is very complex, the influence factors are very many, the geometrical factors such as airflow corner and consistency influence pneumatic factors, such as the interference of incoming flow Mach number and shock wave boundary layer, and the like, the mutual interference of airflow wake and blade movement is caused by the staggered arrangement of the rotating blades and the static blades, and the interference influence of viscosity action and shock wave in the flow causes the unsteady and extreme complexity of the flow in the cascade and presents the common rotation and three-dimensional characteristics of the rotating machinery; therefore, how to establish a better tester to accurately determine the flow field parameters in the blade cascade is necessary and urgent, wherein the air inlet system of the tester largely determines the flow field quality, and the flow field quality determines whether the test result is accurate enough, so that the air inlet system needs to be optimally designed.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides an air inlet system for an annular cascade tester.
The invention adopts the following technical scheme:
an air inlet system for an annular cascade performance tester comprises an air inlet pipeline, a straight pipe section, a diffusion section, a stabilization section, a convergence section, a spray pipe and a cascade test section, and is characterized in that the air inlet pipeline comprises a large air inlet pipeline, a small air inlet pipeline and an air discharge pipeline; the large and small air inlet pipelines and the air outlet pipeline are connected with the same main air channel, and a group of pressure regulating valves and fine adjustment valves which are connected in parallel are arranged on the large and small air inlet pipelines and the air outlet pipeline; an air inlet gate valve is arranged on the main air path; the large and small air inlet pipelines are connected in a converging way through a three-way joint; the rear part of the three-way joint is connected with the straight pipe section through an expansion joint; a conical diffusion section is connected behind the straight pipe section; the diffusion section is connected with the stabilization section; the stabilizing section comprises a rectifying section and a voltage stabilizing section; the voltage stabilizing section is connected with the convergence section; the convergent section is connected with the cascade test section through a spray pipe; a foundation mounting platform is arranged at the blade grid test section; and the outlet of the cascade test section is connected with an exhaust system.
Furthermore, a flowmeter, a pressure sensor and a temperature sensor are arranged on the large air inlet pipeline and the small air inlet pipeline; and a pressure sensor and a temperature sensor are arranged on the main air path.
Furthermore, the cascade test section comprises an annular cascade test section, a fan-shaped cascade test section and a plane cascade test section, and the two sections are matched with the same basic mounting platform.
Furthermore, the convergent sections corresponding to the annular cascade test section and the fan-shaped test section and the spray pipe are of an integrated structure.
Furthermore, the outlet of the convergent section corresponding to the plane cascade test section is connected with the inlet of the spray pipe through a flange, and the centering spigot is positioned.
Furthermore, the shape of an air outlet of a convergent section corresponding to the annular cascade test section is circular; the shape of an air outlet of a convergent section corresponding to the fan-shaped cascade test section is fan-shaped; and the shape of the air outlet of the convergent section corresponding to the plane blade grid test section is rectangular.
Further, the diffusion section adopts a double-layer structure.
Furthermore, a sintered wire mesh and a honeycomb rectifier are sequentially arranged in the rectifying section; a damping net is arranged in the pressure stabilizing section; and the honeycomb rectifier and the damping net are fixed on the slide rail on the inner side of the stable section through linear slide blocks.
The invention has the following beneficial effects:
(1) the air inlet system provided by the invention is provided with a large air inlet pipeline, a small air inlet pipeline and an air outlet pipeline, the three pipelines are respectively provided with a pressure regulating valve and a fine regulating valve, the three pipelines can jointly regulate the air inlet pressure and the air inlet flow, the regulation range is finer, the regulation precision is higher, the requirements of an annular cascade performance test on different air inlet pressures and different air inlet flows are met, the high Mach number control precision of a flow field in a downstream test section is ensured, and the flow field quality is good.
(2) According to the invention, the large and small air inlet pipelines are connected in a pipeline converging manner by adopting the tee joint, so that the defects of large flow resistance and large flow regulation difficulty of the blender are overcome, and the flow field quality is improved.
(3) The invention can carry out subzero, collapse and supersonic speed tests and blowing tests on an annular cascade test section, a fan-shaped cascade test section and a plane cascade test section by replacing corresponding solid spray pipes and convergence sections.
(4) The diffusion section is of a double-layer structure, and the sintered wire mesh, the honeycomb rectifier and the damping mesh are arranged in the rectifying section, so that the arrangement can play a role in improving the quality of a flow field.
Drawings
FIG. 1 is a schematic view of an air intake system according to the present invention;
FIG. 2 is a schematic diagram of an intake system valve arrangement according to the present invention;
FIG. 3 is a schematic structural view of a stabilization segment;
FIG. 4 is a schematic view of the structure of the nozzle and the nozzle trolley.
Detailed Description
The invention is further described with reference to the following figures and examples. In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "axial," "radial," and the like are used in the indicated orientations and positional relationships based on the orientation shown in the drawings for convenience in describing the invention and simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus are not to be considered as limiting.
As shown in fig. 1, the invention provides an air inlet system for an annular cascade performance tester, which comprises an air source, an air inlet pipeline, a straight pipe section 13, a diffuser section 14, a stabilizer section 15, a convergence section 16, a nozzle and a cascade test section 17 which are connected in sequence; the air inlet pipeline comprises a large air inlet pipeline 11, a small air inlet pipeline 12 and an air discharge pipeline 10, as shown in fig. 2, the large air inlet pipeline 11, the small air inlet pipeline 12 and the air discharge pipeline 10 are connected with the same main air path, and a group of pressure regulating valves (112, 122 and 102 in the figure) and fine regulating valves (111, 121 and 101 in the figure) which are connected in parallel are arranged on the large air inlet pipeline, the small air inlet pipeline and the air discharge pipeline; an air inlet gate valve is arranged on the main air path; the large and small air inlet pipelines are provided with flow meters and thermometers 114 and 124 which are connected together through a three-way joint 18, and the rear part of the three-way joint 18 is connected with the straight pipe section 13 through an expansion joint; the rear part of the straight pipe section 13 is connected with a conical diffusion section 14, the diffusion section 14 is used for connecting the straight pipe section 13 with a stable section 15 to carry out speed reduction and pressurization so as to stabilize a flow field to a certain extent, and the diffusion section 14 with a double-layer structure is adopted in the embodiment so as to achieve better flow field quality; as shown in fig. 3, the stabilizing section 15 includes a rectifying section and a voltage stabilizing section, the first half is the rectifying section, and the second half is the voltage stabilizing section; the inside of the rectifying section is sequentially provided with a sintered wire mesh 151 and a honeycomb rectifier 152, the honeycomb rectifier 152 and the damping mesh 153 are in modular design and are fixed on the shell of the stabilizing section 15 through linear sliding rails so as to be convenient for installation, disassembly and maintenance, wherein the honeycomb rectifier 152 is positioned at the position 0.2 times of the inner diameter behind the inlet of the stabilizing section; 4 layers of damping nets 153 are arranged in the pressure stabilizing section, each layer of damping net is arranged at equal intervals, a total temperature and total pressure mounting seat is arranged near an outlet of the pressure stabilizing section, and 2 total pressure comb-shaped probes with 5 points, 2 total temperature probes with 5 points and 8 static pressure measuring points are arranged on the same plane; the pressure stabilizing section is connected with the converging section, the converging section is connected with the cascade test section through the spray pipe, the cascade test section comprises an air inlet section and an air outlet section, inlet and outlet measuring sections are respectively arranged, and 4 total pressure probes with 5 points, 4 total temperature probes with 5 points and 8 static pressure measuring points are uniformly distributed.
The cascade test section 17 comprises an annular cascade test section, a fan-shaped cascade test section and a plane cascade test section, which are all adapted to the same basic mounting platform and can be replaced, and different cascade test sections 17 are selected for different tests; the test section of the annular blade cascade is mainly used for subsonic tests of the supercharging blade cascade and the turbine blade cascade, the test section of the fan-shaped blade cascade is used for subsonic tests of the supercharging blade cascade and the turbine blade cascade, and the test section of the plane blade cascade is mainly used for subsonic tests of the supercharging blade cascade and the turbine blade cascade; considering the difference of the structural forms of the three cascade test sections, in order to facilitate quick replacement, the convergence section 16 corresponding to the annular cascade test section and the fan-shaped test section and the spray pipe are of an integrated structure; the outlet of the convergent section 16 corresponding to the plane cascade test section is connected with the inlet of the spray pipe through a flange, the centering spigot is positioned, the spray pipe adopts a two-dimensional spray pipe flow channel and is composed of a spray pipe box body 161 and a trolley 162, the spray pipe box body 161 is used for installing and fixing a spray pipe block, and the spray pipe trolley 162 is used for supporting the spray pipe box body 161, as shown in fig. 4; the air outlet of the blade grid test section 17 is connected with an exhaust device, and the exhaust device comprises a horizontal exhaust collector 22 fixed along the horizontal direction and a movable exhaust collector 23 movable along the circumferential direction, and the horizontal exhaust collector 22 and the movable exhaust collector 23 are connected with the same exhaust silencing tower 23.
The specific working mode of the invention is as follows:
the gate valve on the main gas path is opened, the gas is sent into the gas inlet pipeline 10, the opening degrees of three groups of pressure regulating valves (112, 122 and 102 in the figure) and fine regulating valves (111, 121 and 101 in the figure) on the large and small gas inlet pipelines and the gas discharge pipelines 12 and 13 can be respectively or synchronously adjusted, the gas inlet flow and pressure can be controlled, therefore, the fluid with changed parameters is conveyed through the straight pipe section 13, is decelerated and pressurized at the diffusion section 14, is stabilized at the stabilization section, is then sent into the cascade test section 17 through the convergence section 16 and the spray pipes, and forms a flow field meeting the requirements of the cascade test at the cascade test section 17.
In the embodiment, mass flowmeters with the accuracy of +/-1.0% FS and the ranges of 10-36 kg/s and 0-12 kg/s are respectively arranged on the large air inlet pipeline and the small air inlet pipeline to measure the flow; a group of pressure regulating valves and fine adjusting valves are arranged on the large air inlet pipeline, the small air inlet pipeline and the air discharge pipeline respectively to ensure that the flow field in the downstream test section has high Mach number control precision.
It should be understood that the above examples are only for clearly illustrating the technical solutions of the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (8)
1. An air inlet system for an annular cascade performance tester comprises an air inlet pipeline, a straight pipe section, a diffusion section, a stabilization section, a convergence section, a spray pipe and a cascade test section, and is characterized in that the air inlet pipeline comprises a large air inlet pipeline, a small air inlet pipeline and an air discharge pipeline; the large and small air inlet pipelines and the air outlet pipeline are connected with the same main air channel, and a group of pressure regulating valves and fine adjustment valves which are connected in parallel are arranged on the large and small air inlet pipelines and the air outlet pipeline; an air inlet gate valve is arranged on the main air path; the large and small air inlet pipelines are connected in a converging way through a three-way joint; a straight pipe section is connected behind the three-way joint; a conical diffusion section is connected behind the straight pipe section; the diffusion section is connected with the stabilization section; the stabilizing section comprises a rectifying section and a voltage stabilizing section; the voltage stabilizing section is connected with the convergence section; the convergent section is connected with the cascade test section through a spray pipe; a foundation mounting platform is arranged at the blade grid test section; and the outlet of the cascade test section is connected with an exhaust system.
2. The air inlet system for the annular blade cascade performance tester as claimed in claim 1, wherein the large and small air inlet pipelines are provided with a flowmeter, a pressure sensor and a temperature sensor; and a pressure sensor and a temperature sensor are arranged on the main air path.
3. The air intake system for the annular cascade performance tester of claim 1, wherein the cascade test section comprises an annular cascade test section, a fan-shaped cascade test section and a plane cascade test section, which are all adapted to the same basic mounting platform.
4. The air inlet system for the annular cascade performance tester as claimed in claim 3, wherein the convergent sections corresponding to the annular cascade test section and the fan-shaped test section are of an integral structure with the nozzle.
5. The air inlet system of the annular cascade performance tester as claimed in claim 3, wherein the outlet of the convergent section corresponding to the planar cascade test section is connected with the inlet of the nozzle through a flange, and the centering spigot is positioned.
6. The air inlet system for the annular blade cascade performance tester as claimed in claim 3, wherein the shape of the air outlet of the convergent section corresponding to the annular blade cascade test section is circular; the shape of an air outlet of a convergent section corresponding to the fan-shaped cascade test section is fan-shaped; and the shape of the air outlet of the convergent section corresponding to the plane blade grid test section is rectangular.
7. The air intake system for the annular cascade performance tester of claim 1, wherein the diffuser section has a double-layer structure.
8. The air inlet system for the annular blade grid performance tester as claimed in claim 1, wherein a sintered wire mesh and a honeycomb rectifier are sequentially arranged in the rectifying section; a damping net is arranged in the pressure stabilizing section; and the honeycomb rectifier and the damping net are fixed on the slide rail on the inner side of the stable section through linear slide blocks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010589558.3A CN111649948A (en) | 2020-06-24 | 2020-06-24 | Air inlet system for annular blade cascade performance tester |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010589558.3A CN111649948A (en) | 2020-06-24 | 2020-06-24 | Air inlet system for annular blade cascade performance tester |
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| CN111649948A true CN111649948A (en) | 2020-09-11 |
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| CN202010589558.3A Pending CN111649948A (en) | 2020-06-24 | 2020-06-24 | Air inlet system for annular blade cascade performance tester |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112781825A (en) * | 2020-12-30 | 2021-05-11 | 中国航发沈阳发动机研究所 | Suction structure for improving flow field quality of plane cascade wind tunnel and design method thereof |
| CN112964472A (en) * | 2021-03-23 | 2021-06-15 | 中国空气动力研究与发展中心空天技术研究所 | Stabilizing section for plane blade grid high-altitude flow simulation device |
| CN112964448A (en) * | 2021-03-23 | 2021-06-15 | 中国空气动力研究与发展中心空天技术研究所 | Airflow mixer for plane blade grid high-altitude flow simulation device |
| CN112964473A (en) * | 2021-03-23 | 2021-06-15 | 中国空气动力研究与发展中心空天技术研究所 | Exhaust restrictor for planar cascade flow simulation device |
| CN113029573A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Low-Reynolds-number plane cascade high-altitude flow simulation device |
| CN113029577A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Expansion section for planar cascade flow simulation device |
| CN113029575A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Height-adjustable plane cascade test section |
| CN114034460A (en) * | 2021-11-10 | 2022-02-11 | 中国人民解放军空军工程大学 | Secondary flow generating device |
| CN114689329A (en) * | 2022-05-09 | 2022-07-01 | 北京航空航天大学 | Annular cascade test bench and aeroelasticity test system thereof |
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2020
- 2020-06-24 CN CN202010589558.3A patent/CN111649948A/en active Pending
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112781825A (en) * | 2020-12-30 | 2021-05-11 | 中国航发沈阳发动机研究所 | Suction structure for improving flow field quality of plane cascade wind tunnel and design method thereof |
| CN113029575A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Height-adjustable plane cascade test section |
| CN112964448A (en) * | 2021-03-23 | 2021-06-15 | 中国空气动力研究与发展中心空天技术研究所 | Airflow mixer for plane blade grid high-altitude flow simulation device |
| CN112964473A (en) * | 2021-03-23 | 2021-06-15 | 中国空气动力研究与发展中心空天技术研究所 | Exhaust restrictor for planar cascade flow simulation device |
| CN113029573A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Low-Reynolds-number plane cascade high-altitude flow simulation device |
| CN113029577A (en) * | 2021-03-23 | 2021-06-25 | 中国空气动力研究与发展中心空天技术研究所 | Expansion section for planar cascade flow simulation device |
| CN112964472A (en) * | 2021-03-23 | 2021-06-15 | 中国空气动力研究与发展中心空天技术研究所 | Stabilizing section for plane blade grid high-altitude flow simulation device |
| CN113029573B (en) * | 2021-03-23 | 2021-11-12 | 中国空气动力研究与发展中心空天技术研究所 | Low-Reynolds-number plane cascade high-altitude flow simulation device |
| CN112964448B (en) * | 2021-03-23 | 2022-02-15 | 中国空气动力研究与发展中心空天技术研究所 | Airflow mixer for plane blade grid high-altitude flow simulation device |
| CN113029575B (en) * | 2021-03-23 | 2022-04-26 | 中国空气动力研究与发展中心空天技术研究所 | Height-adjustable plane cascade test section |
| CN114034460A (en) * | 2021-11-10 | 2022-02-11 | 中国人民解放军空军工程大学 | Secondary flow generating device |
| CN114034460B (en) * | 2021-11-10 | 2023-08-22 | 中国人民解放军空军工程大学 | Secondary flow generating device |
| CN114689329A (en) * | 2022-05-09 | 2022-07-01 | 北京航空航天大学 | Annular cascade test bench and aeroelasticity test system thereof |
| CN114689329B (en) * | 2022-05-09 | 2023-07-21 | 北京航空航天大学 | Annular blade grid test bed and pneumatic elasticity test system thereof |
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