CN113029573A - Low-Reynolds-number plane cascade high-altitude flow simulation device - Google Patents
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Abstract
The invention discloses a low Reynolds number plane cascade high-altitude flow simulation device. The device comprises an air inlet gate valve group, an air inlet quick valve group, an air inlet pressure regulating valve group, a straight pipe section, an expansion section, a stabilization section, a contraction section, a test body, an exhaust throttler, a three-stage injection body and a small hole exhaust section in sequence along the air flow direction, wherein a turbine cascade test model or an air compressor cascade test model is installed in the test body, and the test body is connected with a vacuum suction assembly and a secondary flow assembly. The air inlet pressure regulating valve group controls the total pressure of the stable section, and the suction assembly controls the static pressure and the boundary layer in front of the cascade test piece cascade; the three-level injection body and the exhaust restrictor control the back pressure of the ultrasonic speed test body or the subsonic speed test body in the room to realize the regulation of Reynolds number, in particular to the regulation of high-altitude low Reynolds number. The device can realize flow simulation of sub-span supersonic velocity and wide Reynolds number range, and is suitable for carrying out experimental study and technical verification on aerodynamic performance of plane blade grids of aero-engine impellers.
Description
Technical Field
The invention belongs to the field of basic research and test equipment of aero-engines, and particularly relates to a low Reynolds number 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 perform a test study on the aerodynamic characteristics of the cascade channel flow under a real flight condition on the ground, ground equipment capable of simulating parameters such as the mach number, the reynolds number and the like of the cascade flow in actual flight must be built so as to ensure that the test can be performed under a condition close to an actual working state. Especially, the blade profile and the blade cascade which are suitable for the high-altitude environment and supersonic flow are developed, the flow conditions of the blade profile and the blade cascade in the high-altitude low Reynolds number and high-speed flight state are required to be simulated, and a large amount of aerodynamic performance test research and technical verification are carried out so as to analyze and research the flow mechanism, characteristics and rules in the blade cascade channel and verify a new design scheme. For the study of the turbine blade cascade flow with film cooling and internal air cooling, the main flow and the secondary flow of the test equipment are required to have enough temperature difference or temperature ratio regulation capacity and introduction capacity of different media so as to simulate the heat and mass transfer process between two flows of the same or different media and turbine blades.
At present, the flow simulation device commonly adopted for carrying out the blade cascade test of aeroengine impellers (comprising a fan/compressor and a turbine) and gas turbines at home and abroad has the following defects: firstly, when supersonic flow is simulated, a plurality of single-point Mach number solid spray pipes are generally adopted, and when the flow state is changed, the spray pipes need to be frequently replaced, so that the operation is extremely inconvenient and the efficiency is low; secondly, the test section has no room holding structure and no back pressure regulating valve, a vacuum pumping mode is generally adopted for Reynolds number simulation, pumping equipment is complex, the efficiency is low, the sealing is difficult to guarantee, the Reynolds number simulation section is single, the simulation range is narrow, and the high-altitude simulation capability is insufficient; thirdly, the secondary flow system has single function and only has the heat and mass transfer test capability of one medium airflow; and fourthly, the flow simulation device generally adopts an open jet structure, the exhaust collector is simple, the exhaust collecting effect is poor, and the noise pollution is large.
At present, the development of a closed type plane cascade high-altitude flow simulation device which has the sub-span supersonic mach number and reynolds number, particularly the low reynolds number and high-altitude flow independent simulation capability, has the regulation capability of different medium primary/secondary air flow temperature ratios, is convenient and efficient to operate and meets the requirements of basic research and technical verification of advanced aeroengine turbines and gas turbine cascade aerodynamic performance tests is urgently needed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a low Reynolds number plane cascade high-altitude flow simulation device.
The invention discloses a low Reynolds number plane cascade high-altitude flow simulation device which is characterized by comprising an air inlet gate valve group, an air inlet quick valve group, an air inlet pressure regulating valve group, a straight pipe section, an expansion section, a stabilizing section, a contraction section, a test body, an exhaust restrictor, a three-level injection body and a small hole exhaust section in sequence along the airflow direction, wherein a turbine cascade test model or a compressor cascade test model is installed in the test body, and the test body is connected with a vacuum suction assembly and a secondary flow assembly;
the air inlet gate valve group, the air inlet quick valve group, the air inlet pressure regulating valve group, the straight pipe section and the expansion section are connected through a flange pipeline and an expansion joint and are sealed by metal winding type sealing gaskets; the expansion section, the stable section and the contraction section are connected through flanges and are sealed by metal winding type sealing gaskets;
the contraction section, the test body and the exhaust restrictor are positioned through end face pins and sealed by an inflatable shroud ring;
the exhaust restrictor, the three-stage injection body and the small-hole exhaust section are also connected through flanges and are sealed by metal winding type sealing gaskets;
the expansion section is a conical body and is used for reducing the flow velocity of the stable section and stabilizing the flow field of the stable section;
the contraction section is a round-to-square body, and the round air inlet section is changed into a square air inlet section, so that the flow velocity and the flow field quality of the test section are improved;
the exhaust restrictor has an exhaust function, collects the test model outlet airflow of the test body, and guides the test model outlet airflow into the three-stage injection body, so as to prevent the test model outlet airflow reflection from interfering with the test section flow field in the test body; the exhaust restrictor also has a throttling function and is used for assisting in adjusting test backpressure of a test section in a test body and achieving the purpose of changing the test Reynolds number;
the three-stage injection body adopts a medium-pressure air source injection mode and is used for adjusting test back pressure of a test section in the test body and achieving the purpose of changing the test Reynolds number;
the small-hole exhaust section is used for exhausting gas at the front end of the test body, reducing the flow speed of exhaust gas and reducing exhaust noise;
the vacuum suction assembly is used for adjusting the thickness of a boundary layer of a test section in a test body and assisting in adjusting the Mach number in front of a gate of a test model;
the secondary flow assembly is used for blowing secondary air flows of the same or different media as the primary air flows to the air film blades of the turbine blade cascade model, so that the requirements of mixing and cooling the secondary flows of the turbine blade cascade model are met, and the temperature ratio adjustment of the primary air flows and the secondary air flows of different media of the turbine blade cascade model is realized.
Furthermore, the vacuum suction assembly, the secondary flow assembly and the supersonic speed test body are connected by rubber hoses or metal hoses.
Further, the air inlet gate valve group comprises a main gate valve and a bypass gate valve I; the main gate valve is arranged at the foremost end of an air inlet pipeline of the simulation device along the airflow direction through a flange; a bypass gate valve I is connected to the main gate valve pipeline in parallel, and the bypass gate valve I conducts air guiding and exhausting from the main gate valve pipeline through a flange pipeline.
Furthermore, the quick air inlet valve group comprises a quick valve and a bypass gate valve II; the quick valve is arranged on an air inlet pipeline behind the air inlet gate valve group along the airflow direction of the simulation device through a flange; and a bypass gate valve II is connected in parallel to the quick valve pipeline and conducts air guiding and exhausting from the quick valve pipeline through a flange pipeline.
Furthermore, the air inlet pressure regulating valve group comprises a main pressure regulating valve, an auxiliary pressure regulating valve and an air flow mixer;
the main pressure regulating valve and the airflow mixer are connected through a flange and sealed by a metal winding type sealing gasket to form a connecting body, and the front end and the rear end of the connecting body are installed on an air inlet pipeline behind the air inlet quick valve group along the airflow direction of the simulation device through the flange; the main pressure regulating valve pipeline is connected with an auxiliary pressure regulating valve in parallel, the auxiliary pressure regulating valve guides air from the front end pipeline of the main pressure regulating valve through a flange pipeline, and the exhaust of the auxiliary pressure regulating valve is connected into the airflow mixer.
Further, the stabilizing section comprises a rectifying section and a static flow section which are sequentially connected along the airflow direction.
Further, the test body is an ultrasonic test body;
the supersonic speed test body comprises a variable Mach number spray pipe and a supersonic speed test cabin which are arranged on the mounting platform I and are sequentially connected along the airflow direction;
the variable Mach number spray pipe is a two-dimensional square spray pipe, has a sub-span supersonic spray pipe profile adjusting function of Mach number 1.0-Mach number 2.0, and is used for adjusting the incoming flow Mach number of a supersonic test body test section;
the supersonic speed test cabin is a square body, the center of the supersonic speed test cabin is a test section, a supporting mechanism for mounting a turbine blade cascade test model or a gas compressor blade cascade test model is arranged in the test section, and a test section parking chamber is wrapped outside the test section.
Furthermore, the test body is a subsonic test body, and the subsonic test body comprises a sonic nozzle and a subsonic test chamber which are arranged on the mounting platform II and are sequentially connected along the airflow direction;
the sound velocity spray pipe is square, sequentially comprises a spray pipe contraction section and a spray pipe section along the airflow direction, and is used for realizing subsonic incoming flow in the subsonic velocity test cabin;
the subsonic speed test cabin is a square body, the center of the subsonic speed test cabin is a test section, a supporting mechanism used for mounting a turbine blade cascade test model or a compressor blade cascade test model is arranged in the test section, and a test section parking chamber is wrapped outside the test section.
The low Reynolds number plane blade grid high-altitude flow simulation device can conveniently and quickly realize the flow simulation of the plane blade grid sub-span supersonic velocity and the wide Reynolds number range, in particular to the flow simulation of the supersonic velocity and the high-altitude low Reynolds number. The low Reynolds number plane cascade high-altitude flow simulation device is comprehensive in function, convenient to operate, good in quality of a flow field at a test section, simple in test preparation and high in test accuracy, and can save test preparation time and improve test efficiency.
Drawings
FIG. 1 is a two-dimensional plan view of a low Reynolds number planar cascade high altitude flow simulation apparatus of the present invention;
FIG. 2 is a two-dimensional plan view of an inlet gate valve set in the low Reynolds number planar cascade high altitude flow simulation apparatus of the present invention;
FIG. 3 is a two-dimensional plan view of a fast intake valve set in the low Reynolds number planar cascade high altitude flow simulation apparatus of the present invention;
FIG. 4 is a two-dimensional plan view of an air inlet pressure regulating valve set in the low Reynolds number planar cascade high altitude flow simulation apparatus of the present invention;
FIG. 5 is a three-dimensional perspective view of a stabilization segment in the low Reynolds number planar cascade high altitude flow simulation apparatus of the present invention;
FIG. 6 is a two-dimensional plan view of an supersonic velocity test body in the low Reynolds number planar cascade high altitude flow simulation apparatus of the present invention;
FIG. 7 is a two-dimensional plan view of a subsonic velocity test body in the low Reynolds number planar cascade high altitude flow simulation apparatus of the present invention.
In the figure, 1, an air inlet gate valve group 2, an air inlet quick valve group 3, an air inlet pressure regulating valve group 4, a straight pipe section 5, an expansion section 6, a stable section 7, a contraction section 8, a supersonic speed test body 9, a subsonic speed test body 10, an exhaust restrictor 11, a three-level injection body 12, an orifice exhaust section 13, a vacuum suction assembly 14 and a secondary flow assembly;
101. a main gate valve 102, a bypass gate valve I;
201. a quick valve 202, a bypass gate valve II;
301. a main pressure regulating valve 302, an auxiliary pressure regulating valve 303, an air flow mixer;
601. a rectifying section 602, a stationary flow section;
801. the mounting platform I802, the variable Mach number spray pipe 803, the supersonic speed test chamber;
901. and a mounting platform II 902, a sonic nozzle 903 and a subsonic test chamber.
Detailed description of the preferred embodiments
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in fig. 1, the low reynolds number plane cascade high-altitude flow simulation device of the invention sequentially comprises an air inlet gate valve group 1, an air inlet fast valve group 2, an air inlet pressure regulating valve group 3, a straight pipe section 4, an expansion section 5, a stabilization section 6, a contraction section 7, a test body, an exhaust restrictor 10, a three-level injection body 11 and a small hole exhaust section 12 along the air flow direction, wherein a turbine cascade test model or a compressor cascade test model is installed in the test body, and the test body is connected with a vacuum suction assembly 13 and a secondary flow assembly 14;
the air inlet gate valve group 1, the air inlet fast valve group 2, the air inlet pressure regulating valve group 3, the straight pipe section 4 and the expansion section 5 are connected through a flange pipeline and an expansion joint and are sealed by metal winding type sealing gaskets; the expansion section 5, the stable section 6 and the contraction section 7 are connected through flanges and sealed by metal winding type sealing gaskets;
the contraction section 7, the test body and the exhaust restrictor 10 are positioned through end surface pins and sealed by an inflatable shroud ring;
the exhaust restrictor 10, the three-level ejector body 11 and the small-hole exhaust section 12 are connected through flanges and are sealed by metal winding type sealing gaskets;
the expansion section 5 is a conical body and is used for reducing the flow velocity of the stable section 6 and stabilizing the flow field of the stable section 6;
the contraction section 7 is a round-to-square body, and the round air inlet section is changed into a square air inlet section, so that the flow velocity and the flow field quality of the test section are improved;
the exhaust restrictor 10 has an exhaust function, collects the test model outlet airflow of the test body, and guides the test model outlet airflow into the three-stage injection body 11 to prevent the test model outlet airflow reflection from interfering with the test section flow field in the test body; the exhaust restrictor 10 also has a throttling function and is used for assisting in adjusting test backpressure of a test section in a test body and achieving the purpose of changing the test Reynolds number;
the three-stage injection body 11 adopts a medium-pressure air source injection mode and is used for adjusting test back pressure of a test section in the test body and achieving the purpose of changing the test Reynolds number;
the small-hole exhaust section 12 is used for exhausting gas at the front end of the test body, reducing the flow speed of exhaust gas and reducing exhaust noise;
the vacuum suction assembly 13 is used for adjusting the thickness of a boundary layer of a test section in a test body and assisting in adjusting the Mach number in front of a gate of a test model;
the secondary flow assembly 14 is used for blowing secondary air flows of the same or different media as the primary air flows to the air film blades of the turbine blade cascade model, so that the requirements of mixing and cooling the secondary flows of the turbine blade cascade model are met, and the temperature ratio adjustment of the primary air flows and the secondary air flows of different media of the turbine blade cascade model is realized.
Further, the vacuum suction assembly 13, the secondary flow assembly 14 and the supersonic speed test body 8 are connected by a rubber hose or a metal hose.
Further, as shown in fig. 2, the inlet gate valve set 1 includes a main gate valve 101 and a bypass gate valve i 102; the main gate valve 101 is arranged at the foremost end of an air inlet pipeline of the simulation device along the airflow direction through a flange; the pipeline of the main gate valve 101 is connected with a bypass gate valve I102 in parallel, and the bypass gate valve I102 conducts air guiding and air exhausting from the pipeline of the main gate valve 101 through a flange pipeline.
Further, as shown in fig. 3, the intake quick valve group 2 includes a quick valve 201 and a bypass gate valve ii 202; the quick valve 201 is arranged on an air inlet pipeline behind the air inlet gate valve group 1 of the simulation device along the air flow direction through a flange; and a bypass gate valve II 202 is connected in parallel to the pipeline of the quick valve 201, and the bypass gate valve II 202 conducts air guiding and air exhausting from the pipeline of the quick valve 201 through a flange pipeline.
Further, as shown in fig. 4, the intake pressure regulating valve group 3 includes a main pressure regulating valve 301, an auxiliary pressure regulating valve 302 and an airflow mixer 303;
the main pressure regulating valve 301 and the airflow mixer 303 are connected through a flange and sealed by a metal winding type sealing gasket to form a connecting body, and the front end and the rear end of the connecting body are arranged on an air inlet pipeline behind the air inlet fast valve group 2 of the simulation device along the airflow direction through the flange; an auxiliary pressure regulating valve 302 is connected in parallel to the pipeline of the main pressure regulating valve 301, air is introduced from the pipeline at the front end of the main pressure regulating valve 301 through a flange pipeline by the auxiliary pressure regulating valve 302, and exhaust of the auxiliary pressure regulating valve 302 is connected into an airflow mixer 303.
Further, as shown in fig. 5, the stabilizing section 6 includes a rectifying section 601 and a static flow section 602 which are connected in series along the airflow direction.
Further, as shown in fig. 6, the test body is a supersonic test body 8;
the supersonic speed test body 8 comprises a variable Mach number spray pipe 802 and a supersonic speed test cabin 803 which are arranged on the installation platform I801 and are sequentially connected along the airflow direction;
the variable Mach number spray pipe 802 is a two-dimensional square spray pipe, has a sub-span supersonic spray pipe profile adjusting function of Mach number 1.0-Mach number 2.0, and is used for adjusting the incoming flow Mach number of a supersonic test body test section;
the supersonic speed test cabin 803 is a square body, the center of the supersonic speed test cabin 803 is a test section, a support mechanism for mounting a turbine blade cascade test model or a compressor blade cascade test model is arranged in the test section, and a test section parking chamber is wrapped outside the test section.
Further, as shown in fig. 7, the test body is a subsonic test body 9, and the subsonic test body 9 includes a sonic nozzle 902 and a subsonic test chamber 903 which are installed on an installation platform ii 901 and sequentially connected in the airflow direction;
the sonic velocity nozzle 902 is square, and sequentially comprises a nozzle contraction section and a nozzle section along the airflow direction, and is used for realizing the subsonic velocity inflow in the subsonic velocity test chamber 903;
the subsonic velocity test cabin 903 is a square body, the center of the subsonic velocity test cabin 903 is a test section, a supporting mechanism used for mounting a turbine blade cascade test model or a compressor blade cascade test model is arranged in the test section, and a test section parking chamber is wrapped outside the test section.
Example 1
The test section of the test body of the low Reynolds number planar cascade high-altitude flow simulation device is 190mm in width, 445mm in height, the Mach number range is 0.3-1.8, and the Reynolds number range is 0.4, 105～22.5×105(calculated by chord length of 75 mm), the test back pressure in the test section can reach 7.5kPa at the lowest.
The flow field calibration shows that the deviation of the flow field core region of the test section in the subsonic velocity test body 9 at the Mach number of 0.8 is superior to 0.003, and the advanced index of the low-speed wind tunnel and high-speed wind tunnel flow field quality requirement GJB 1179A-2012 is reached.
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. The low Reynolds number plane cascade high-altitude flow simulation device is characterized by comprising an air inlet gate valve group (1), an air inlet quick valve group (2), an air inlet pressure regulating valve group (3), a straight pipe section (4), an expansion section (5), a stabilization section (6), a contraction section (7), a test body, an exhaust throttler (10), a three-level injection body (11) and a small hole exhaust section (12) in sequence along the air flow direction, wherein a turbine cascade test model or a gas compressor cascade test model is installed in the test body, and the test body is connected with a vacuum suction assembly (13) and a secondary flow assembly (14);
the air inlet gate valve group (1), the air inlet quick valve group (2), the air inlet pressure regulating valve group (3), the straight pipe section (4) and the expansion section (5) are connected through a flange pipeline and an expansion joint and are sealed by a metal winding type sealing gasket; the expansion section (5), the stable section (6) and the contraction section (7) are connected through flanges and are sealed by metal winding type sealing gaskets;
the contraction section (7), the test body and the exhaust restrictor (10) are positioned through end surface pins and sealed by an inflatable shroud ring;
the exhaust restrictor (10), the three-level injection body (11) and the small-hole exhaust section (12) are also connected through flanges and are sealed by metal winding type sealing gaskets;
the expansion section (5) is a conical body and is used for reducing the flow velocity of the stable section (6) and stabilizing the flow field of the stable section (6);
the contraction section (7) is a round-to-square body, and the round air inlet section is changed into a square air inlet section, so that the flow velocity and the flow field quality of the test section are improved;
the exhaust restrictor (10) has an exhaust function, collects the test model outlet airflow of the test body, and guides the test model outlet airflow into the three-stage injection body (11) to prevent the test model outlet airflow reflection from interfering with the test section flow field in the test body; the exhaust restrictor (10) also has a throttling function and is used for assisting in adjusting test backpressure of a test section in a test body and achieving the purpose of changing the test Reynolds number;
the three-stage injection body (11) adopts a medium-pressure air source injection mode and is used for adjusting test back pressure of a test section in the test body and achieving the purpose of changing the test Reynolds number;
the small-hole exhaust section (12) is used for exhausting gas at the front end of the test body, reducing the flow speed of exhaust gas and reducing exhaust noise;
the vacuum suction assembly (13) is used for adjusting the thickness of a boundary layer of a test section in a test body and assisting in adjusting the Mach number in front of a gate of a test model;
the secondary flow assembly (14) is used for blowing secondary air flows of the same or different media as the primary air flows to the air film blades of the turbine blade cascade model, so that the requirements of mixing and cooling of the secondary flows of the turbine blade cascade model are met, and the temperature ratio adjustment of the primary air flows and the secondary air flows of different media of the turbine blade cascade model is realized.
2. The low Reynolds number plane cascade high altitude flow simulation device according to claim 1, wherein the vacuum suction assembly (13), the secondary flow assembly (14) and the supersonic velocity test body (8) are connected by rubber hoses or metal hoses.
3. The low Reynolds number plane cascade high altitude flow simulation apparatus according to claim 1, wherein the air inlet gate valve set (1) comprises a main gate valve (101) and a bypass gate valve I (102); the main gate valve (101) is arranged at the foremost end of an air inlet pipeline of the simulation device along the airflow direction through a flange; a bypass gate valve I (102) is connected in parallel to the pipeline of the main gate valve (101), and air is introduced into and exhausted from the pipeline of the main gate valve (101) through a flange pipeline by the bypass gate valve I (102).
4. The low reynolds number plane cascade high altitude flow simulation apparatus according to claim 1, wherein the inlet fast valve set (2) comprises a fast valve (201) and a bypass gate valve ii (202); the quick valve (201) is arranged on an air inlet pipeline behind the air inlet valve group (1) of the simulation device along the air flow direction through a flange; and a bypass gate valve II (202) is connected in parallel on the pipeline of the quick valve (201), and the bypass gate valve II (202) guides air and exhausts air from the pipeline of the quick valve (201) through a flange pipeline.
5. The low Reynolds number planar cascade high altitude flow simulation apparatus according to claim 1, wherein the inlet pressure regulating valve set (3) comprises a main pressure regulating valve (301), an auxiliary pressure regulating valve (302) and an airflow mixer (303);
the main pressure regulating valve (301) is connected with the airflow mixer (303) through a flange, and is sealed by a metal winding type sealing gasket to form a connecting body, and the front end and the rear end of the connecting body are arranged on an air inlet pipeline behind the air inlet quick valve group (2) of the simulation device along the airflow direction through the flange; an auxiliary pressure regulating valve (302) is connected in parallel to the pipeline of the main pressure regulating valve (301), air is led from the front end pipeline of the main pressure regulating valve (301) through a flange pipeline by the auxiliary pressure regulating valve (302), and exhaust of the auxiliary pressure regulating valve (302) is connected into an airflow mixer (303).
6. The low Reynolds number planar cascade high altitude flow simulation apparatus according to claim 1, wherein the stationary section (6) comprises a rectifying section (601) and a static flow section (602) connected in series in the airflow direction.
7. The low reynolds number planar cascade high altitude flow simulation apparatus according to claim 1, wherein the test body is a supersonic test body (8);
the supersonic speed test body (8) comprises a variable Mach number spray pipe (802) and a supersonic speed test cabin (803) which are arranged on the mounting platform I (801) and are sequentially connected along the airflow direction;
the variable Mach number spray pipe (802) is a two-dimensional square spray pipe, has a sub-span supersonic spray pipe profile adjusting function of Mach number 1.0-Mach number 2.0, and is used for adjusting the incoming flow Mach number of a supersonic test body test section;
the supersonic speed test cabin (803) is a square body, the center of the supersonic speed test cabin (803) is a test section, a supporting mechanism for mounting a turbine blade cascade test model or a compressor blade cascade test model is arranged in the test section, and a test section parking chamber is wrapped outside the test section.
8. The low Reynolds number plane cascade high altitude flow simulation device of claim 1, wherein the test body is a subsonic velocity test body (9), and the subsonic velocity test body (9) comprises a sonic velocity nozzle (902) and a subsonic velocity test chamber (903) which are installed on a mounting platform II (901) and are sequentially connected in an airflow direction;
the sound velocity spray pipe (902) is square, sequentially comprises a spray pipe contraction section and a spray pipe section along the airflow direction, and is used for realizing the subsonic velocity inflow in the subsonic velocity test cabin (903);
the subsonic velocity test cabin (903) is a square body, the center of the subsonic velocity test cabin (903) is a test section, a supporting mechanism used for mounting a turbine blade cascade test model or a compressor blade cascade test model is arranged in the test section, and a test section parking chamber is wrapped outside the test section.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114279714A (en) * | 2021-12-27 | 2022-04-05 | 北京航空航天大学 | Aeroengine turbine test bed under high altitude and low Reynolds number, simulation method and application |
| CN115560945A (en) * | 2021-07-01 | 2023-01-03 | 南方科技大学 | Multi-mode variable Reynolds number cascade wind tunnel |
| CN115824560A (en) * | 2023-02-21 | 2023-03-21 | 中国空气动力研究与发展中心空天技术研究所 | Planar cascade wind tunnel PIV experiment slit tracer particle distribution device and distribution method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104390762A (en) * | 2014-11-24 | 2015-03-04 | 哈尔滨工业大学 | Experimental device for fine mechanical flow field measurement for fluid |
| CN104897406A (en) * | 2015-06-04 | 2015-09-09 | 大连海事大学 | Rotary stamping compressed rotor plane cascade experimental system |
| 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 |
| CN112284675A (en) * | 2020-10-26 | 2021-01-29 | 中国航天空气动力技术研究院 | Wind tunnel for multi-body separation dynamics research |
-
2021
- 2021-03-23 CN CN202110305900.7A patent/CN113029573B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104390762A (en) * | 2014-11-24 | 2015-03-04 | 哈尔滨工业大学 | Experimental device for fine mechanical flow field measurement for fluid |
| 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 |
| CN104897406A (en) * | 2015-06-04 | 2015-09-09 | 大连海事大学 | Rotary stamping compressed rotor plane cascade experimental system |
| 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 |
| CN112284675A (en) * | 2020-10-26 | 2021-01-29 | 中国航天空气动力技术研究院 | Wind tunnel for multi-body separation dynamics research |
Non-Patent Citations (2)
| Title |
|---|
| SASIPRABA, T 等: "Optimizations of Small Horizontal-Axis Wind Turbine Rotors at Low Reynolds Number", 《3RD INTERNATIONAL CONFERENCE ON FRONTIERS IN AUTOMOBILE AND MECHANICAL ENGINEERING (FAME 2020)》 * |
| 凌代军等: "低雷诺数平面叶栅试验方法研究", 《燃气涡轮试验与研究》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115560945A (en) * | 2021-07-01 | 2023-01-03 | 南方科技大学 | Multi-mode variable Reynolds number cascade wind tunnel |
| CN115560945B (en) * | 2021-07-01 | 2024-03-15 | 南方科技大学 | Multi-mode variable Reynolds number cascade wind tunnel |
| CN114279714A (en) * | 2021-12-27 | 2022-04-05 | 北京航空航天大学 | Aeroengine turbine test bed under high altitude and low Reynolds number, simulation method and application |
| CN114279714B (en) * | 2021-12-27 | 2022-10-25 | 北京航空航天大学 | Aeroengine turbine test bed under high altitude and low Reynolds number, simulation method and application |
| CN115824560A (en) * | 2023-02-21 | 2023-03-21 | 中国空气动力研究与发展中心空天技术研究所 | Planar cascade wind tunnel PIV experiment slit tracer particle distribution device and distribution method |
| CN115824560B (en) * | 2023-02-21 | 2023-04-14 | 中国空气动力研究与发展中心空天技术研究所 | Planar cascade wind tunnel PIV experiment slit tracer particle distribution device and distribution method |
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