Low-pressure low-density engine sand dust environment simulation device

Abstract

The application provides a low-pressure low-density engine sand-dust environment simulation device, and belongs to the field of wind tunnel test, and solves the problem that the existing environment simulation device is difficult to simulate the wind-sand environment with low density, high wind speed and large sand-dust diameter range span. The device comprises an environment experiment cabin, a refrigeration system, a sand-dust system and a pressure simulation system. The environment experiment cabin comprises a backflow type wind tunnel, a fan, a honeycomb device, an annular sand spraying device, an axial variable angle supporting mechanism and a wind tunnel heat exchange and filter. The environment experiment cabin is connected with the pressure simulation system through an air extraction pipeline. The sand-dust system is connected with the annular sand spraying device in the wind tunnel through a sand conveying pipeline penetrating the wall of the wind tunnel. The refrigeration system is connected with an air compressor in the sand-dust system and a vacuum unit in the pressure simulation system through a water supply pipeline. The application can construct an extreme environment, improve the reliability and safety of an aircraft in each stage of the whole life cycle in the extreme environment, and improve the test efficiency.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of wind tunnel test, and particularly relates to a low-pressure and low-density engine sand environment simulation device. BACKGROUND

[0002] With the increase of global extreme environment and the increase of the frequency of aircraft encountering sand environment, domestic and foreign research institutions pay more and more attention to the adaptability of aircraft sand environment under extreme environment. When the fixed-wing aircraft flies at low altitude near the ground, the sand dust is sucked into the nacelle, which can cause the power system to wear out quickly, cause the engine to fail, and even cause serious consequences. During the take-off and landing of the rotor aircraft in the desert environment, the ground sand and other foreign matters will be sucked into the air inlet under the action of the airflow under the rotor, causing blockage, reducing the performance and reliability of the engine, and causing safety accidents. The flight height of the aircraft is usually 0km-20km. The pressure of the space probe currently exploring planets in outer space is 0.01kpa-5kpa. The ground wind speed varies greatly, and the maximum wind speed can reach 130m / s. The maximum diameter of the sand dust particles is 1000um. The low-pressure and low-density engine sand environment simulation device is mainly aimed at the engine of the aircraft and the space probe. The existing sand environment simulation device is difficult to simulate the wind tunnel sand environment with low density, high wind speed and large sand dust diameter range span. Therefore, a sand environment simulation device is needed to build an extreme environment, so as to carry out extensive research on the adaptability of the aircraft sand environment under the extreme environment. SUMMARY

[0003] To solve the above problems, the application provides a low-pressure and low-density engine sand environment simulation device, which solves the problem that the existing environment simulation device is difficult to simulate the wind tunnel sand environment with low density, high wind speed and large sand dust diameter range span.

[0004] The technical scheme adopted by the present application is as follows: a low-pressure and low-density engine sand dust environment simulation device, comprising an environment experiment cabin, a refrigeration system, a sand dust system and a pressure simulation system, the environment experiment cabin comprises a closed return flow wind tunnel, a fan, a honeycomb device, an annular sand blasting device, an axial variable angle supporting mechanism and a wind tunnel heat exchanger / filter, the fan is installed at the power section of the closed return flow wind tunnel, the model replacement cabin cover is installed at the top of the test section of the closed return flow wind tunnel, the personnel access door is installed on the side of the test section of the closed return flow wind tunnel, the honeycomb device is installed at the inlet of the stable section of the closed return flow wind tunnel, the annular sand blasting device is installed at the stable section of the return flow wind tunnel and located behind the honeycomb device, the axial variable angle supporting mechanism is fixedly connected to the inside of the test section of the closed return flow wind tunnel and located behind the annular sand blasting device, the wind tunnel heat exchanger / filter is fixedly connected with the inner wall of the transition section of the closed return flow wind tunnel and located in front of the fan, the closed return flow wind tunnel is connected with the pressure simulation system, the sand dust system is connected with the annular sand blasting device and provides sand dust particles, the annular sand blasting device disperses sand dust in the air flow, and the refrigeration system is connected with the wind tunnel heat exchanger / filter, the sand dust system and the pressure simulation system respectively to provide a cooling source.

[0005] Further, the sand dust system comprises a high-pressure gas storage tank, a buffer tank, an air compressor, a filter / dryer and a high-precision flow scale, the air compressor is connected with the buffer tank, the buffer tank is connected with the filter / dryer, the filter / dryer is connected with the high-pressure gas storage tank, the high-pressure gas storage tank is connected with the high-precision flow scale, and the high-precision flow scale is connected with the annular sand blasting device.

[0006] Further, the pressure simulation system comprises a high-precision sand dust filter, a large-particle sand dust shielding device, a high-precision flow regulating valve group and a vacuum unit, the large-particle sand dust shielding device is connected with the hole flange at the first corner of the closed return flow wind tunnel, the large-particle sand dust shielding device is connected with the high-precision sand dust filter, the high-precision sand dust filter is connected with the high-precision flow regulating valve group, the high-precision flow regulating valve group is connected with the vacuum unit, and the gas outlet of the vacuum unit is connected with the outdoor atmosphere through a silencer.

[0007] Further, the refrigeration system comprises a cooling tower, an underground water pool and a cooling circulating water pump, three water supply pipelines of the cooling circulating water pump are respectively connected with the water inlet interfaces of the vacuum unit, the air compressor and the wind tunnel heat exchanger / filter, and then the water return pipelines of the vacuum unit, the air compressor and the wind tunnel heat exchanger / filter are gathered together to form a total water return pipeline, the total water return pipeline is connected with the cooling tower, and after being cooled by the cooling tower, the total water return pipeline is automatically discharged into the underground water pool, and a water return pipeline is led out from the underground water pool and connected with the cooling circulating water pump.

[0008] Further, the annular sand blasting device is based on the axis of the test section of the closed recirculating wind tunnel, and the annular uniform sand blasting nozzle is arranged.

[0009] Further, the axial variable angle supporting mechanism comprises a hinge, an engine loading and unloading platform, a rear guide device, a rear lifting device, a front lifting device and a front guide device, the rear guide device and the front guide device are fixedly connected with the inner wall of the test section of the recirculating wind tunnel, the rear lifting device is located inside the rear guide device, and the rear lifting device realizes vertical lifting through the lifting push rod inside the rear lifting device; the front lifting device is located inside the front guide device, and the front lifting device realizes vertical lifting through the lifting push rod inside the front lifting device; the upper end of the front lifting device is fixedly connected with the lower mounting plane of the hinge, the upper mounting plane of the hinge is fixedly connected with the front end lower plane of the engine loading and unloading platform, and the upper end of the rear lifting device is fixedly connected with the rear end of the engine loading and unloading platform; the axial position of the engine loading and unloading platform is adjusted by adjusting the lifting height of the rear lifting device and the front lifting device.

[0010] Further, the axial variable angle supporting mechanism provides support for the test engine, and the axial pitch angle range is -30° to 30°

[0011] The beneficial effects and advantages of the present application are as follows: the present application adopts the recirculating wind tunnel mode, takes the fan as a power source, drives the sand dust in the cabin to move, simulates the sand dust environment and atmospheric pressure on the ground, and can carry out extensive research on the sand dust environment adaptability of the aircraft in extreme environments by using the present application, so as to provide sufficient basic data support for the research and development of the aircraft, improve the reliability and safety of the aircraft in each stage of the whole life cycle in extreme environments, and improve the test efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0012] Figure 1 is a structural diagram of the present application;

[0013] Figure 2 is a structural diagram of the present application;

[0014] Figure 3 is a nozzle arrangement diagram of the annular sand blasting device; DETAILED DESCRIPTION

[0015] The specific embodiment is given in combination with the accompanying Figure 1 , the accompanying Figure 2 and the accompanying Figure 3 , and the technical scheme of the present application is further described through the description of the embodiment.

[0016] Example 1

[0017] As Figure 1The low-pressure low-density engine sand dust environment simulation device is characterized in that the environment experiment cabin comprises a closed return flow wind tunnel 1, a fan 2, a honeycomb device 3, an annular sand spraying device 4, an axial variable angle supporting mechanism 7 and a wind tunnel heat exchanger / filter 20, the fan 2 is installed at the power section of the closed return flow wind tunnel 1, a model replacement cabin cover 5 is installed at the top of the test section of the closed return flow wind tunnel 1, a personnel access door 6 is installed at the side of the test section of the closed return flow wind tunnel 1, the honeycomb device 3 is installed at the inlet of the stable section of the closed return flow wind tunnel 1, the annular sand spraying device 4 is installed at the stable section of the closed return flow wind tunnel 1 and located behind the honeycomb device 3, the axial variable angle supporting mechanism 7 is located at the test section of the closed return flow wind tunnel 1, fixedly connected with the inner wall of the test section and located behind the annular sand spraying device 4, the wind tunnel heat exchanger / filter 20 is fixedly connected with the inner wall of the transition section of the closed return flow wind tunnel 1 and located in front of the fan 2, the transition section has a large size and can reduce the airflow speed in the transition section, therefore, the wind tunnel heat exchanger / filter 20 can intercept most of the sand dust particles and protect the fan 2, and the wind tunnel heat exchanger / filter 20 can cool the inside of the wind tunnel and ensure that the environment temperature in the wind tunnel is not higher than 47 DEG C; the flange opening of the first corner of the closed return flow wind tunnel 1 is connected with the pressure simulation system, and the sand dust system is connected with the annular sand spraying device 4 through a sand dust conveying pipeline penetrating through the wall of the closed return flow wind tunnel 1 and provides sand dust particles, Figure 3The nozzle outlet structure of the annular sand blasting device 4 adopts the structure of air bag sand, CFD analysis and calculation are carried out in advance, and the sand dust is uniformly diffused by using the mutual superposition of the diffusion angles of the annular sand blasting. The annular sand blasting device 4 disperses the sand dust in the air flow, and the refrigeration system is connected with the wind tunnel heat exchanger / filter 20, the sand dust system and the pressure simulation system to provide a cooling source. The closed recirculating wind tunnel 1 is a completely closed low-pressure recirculating wind tunnel, which can provide the space, pressure and measuring equipment required for simulation tests at the test section. The closed recirculating wind tunnel 1 can flow air, and simulate wind speed at the test section. The test piece and the axial variable angle support mechanism 7 are hoisted into the test section by the model replacement hatch cover 5 at the top of the test section, and the relevant operators can enter the test section through the personnel access door 6 to install the test piece and perform related operations. The fan 2 is the power source of the wind tunnel, which controls the simulation of different wind speeds at low pressure by controlling the rotating speed of the fan blades; the sand dust system controls the amount of sand dust entering the wind tunnel to realize different sand dust concentrations under different working conditions. The closed recirculating wind tunnel includes a second transition section (including a wind tunnel heat exchanger / filter 20), a collector, a stable section (including a honeycomb 3 and a damping net), a contraction section, a test section, a first diffusion section, a first corner, a first transition section, a second corner, a power section, a second diffusion section, a large-angle diffusion section, etc. The annular sand blasting device 4 is based on the axis of the test section of the closed recirculating wind tunnel 1, and the sand dust sprayed by the annular uniformly distributed sand blasting nozzle is conical and superimposed on each other, and flows with the air flow in the tunnel, thereby forming a relatively uniform sand dust airflow with a certain concentration at the test section.

[0018] The sand dust system includes a high-pressure gas tank 11, a buffer tank 12, an air compressor 13, a filter / dryer 14 and a high-precision flow scale 15. The air compressor 13 is connected with the buffer tank 12 through a high-pressure air pipeline, the buffer tank 12 is connected with the filter and the dryer 14 through a high-pressure air pipeline, the filter / dryer 14 is connected with the high-pressure gas tank 11 through a high-pressure air pipeline, the high-pressure gas tank 11 is connected with the high-precision flow scale 15 through a high-pressure air pipeline, and the high-precision flow scale 15 is connected with the annular sand blasting device 4 through a sand dust conveying pipeline passing through the wall of the closed recirculating wind tunnel 1.

[0019] The pressure simulation system comprises a high-precision sand dust filter 16, a large-particle sand dust shielding device 17, a high-precision flow regulating valve group 18 and a vacuum unit 19. The large-particle sand dust shielding device 17 is connected with the hole body flange at the first corner of the backflow type wind tunnel 1 through an air extraction pipeline. The large-particle sand dust shielding device 17 is connected with the high-precision sand dust filter 16 through an air extraction pipeline. The high-precision sand dust filter 16 is connected with the high-precision flow regulating valve group 18 through an air extraction pipeline. The high-precision flow regulating valve group 18 is connected with the vacuum unit 19 through an air extraction pipeline. The air outlet of the vacuum unit 19 is connected with the outdoor atmosphere through a silencer. The air in the hole is extracted by the vacuum unit 19 to simulate a low-pressure environment. The air extraction amount is adjusted in real time by the large, medium and small three kinds of pneumatic sleeve regulating valves of the high-precision flow regulating valve group 18 to maintain the air pressure in the hole.

[0020] The refrigeration system comprises a cooling tower 8, an underground water pool 9 and a cooling circulating water pump 10. Three water supply pipelines of the cooling circulating water pump 10 are connected with the water inlet interfaces of the vacuum unit 19, the air compressor 13 and the wind tunnel heat exchanger / filter 20 respectively. The water return pipelines of the vacuum unit 19, the air compressor 13 and the wind tunnel heat exchanger / filter 20 are combined together to form a total water return pipeline. The total water return pipeline is connected with the cooling tower 8. The water cooled by the cooling tower 8 is automatically discharged into the underground water pool 9. A water return pipeline is led out from the underground water pool 9 and connected with the cooling circulating water pump 10.

[0021] As Figure 2As shown, the axial variable angle support mechanism 7 includes a hinge 7-1, an engine loading and unloading platform 7-2, a rear guide device 7-3, a rear lifting device 7-4, a front lifting device 7-5, and a front guide device 7-6. The rear guide device 7-3 and the front guide device 7-6 are fixedly connected with the inner wall of the test section of the closed return wind tunnel 1. The rear lifting device 7-4 is located inside the rear guide device 7-3. The rear guide device 7-3 is provided with a compression wheel for radially positioning the rear lifting device 7-4. The rear lifting device 7-4 is vertically lifted along the axial direction by the lifting push rod inside the rear lifting device 7-4. The front lifting device 7-5 is located inside the front guide device 7-6. The front guide device 7-6 is provided with a compression wheel for radially positioning the front lifting device 7-5. The front lifting device 7-5 is vertically lifted along the axial direction by the lifting push rod inside the front lifting device 7-5. The upper end of the front lifting device 7-5 is fixedly connected with the lower mounting plane of the hinge 7-1. The upper mounting plane of the hinge 7-1 is fixedly connected with the front end lower plane of the engine loading and unloading platform 7-2. The upper end of the rear lifting device 7-4 is fixedly connected with the rear end of the engine loading and unloading platform 7-2. The axial position of the engine loading and unloading platform 7-2 is adjusted by adjusting the lifting height of the rear lifting device 7-4 and the front lifting device 7-5. The axial variable angle support mechanism 7 provides support and force measurement for the test engine. The maximum support weight is 10 tons. The axial pitch angle range is -30° to 30°.

[0022] The simulation environment that can be realized by the embodiment includes: (1) the air environment on the earth's surface; (2) the air pressure range in the wind tunnel is 0.01 kPa to 101 kPa, which is continuously adjustable; (3) the wind speed is 10 to 130 m / s, which is continuously adjustable; (4) the sand dust particle size is 1 to 1000 μm, and the concentration range is 0.1 to 2.2 g / m 3 ; (5) the continuous test time is 1 to 6 hours; (6) the ability to measure the lift, drag, and pitch moment of the test piece.

Claims

1. A low pressure and low density engine sand dust environment simulation device, comprising an environment experiment cabin, a refrigeration system, a sand dust system and a pressure simulation system, characterized in that: The environmental test chamber comprises a closed return wind tunnel (1), a fan (2), a honeycomb device (3), a ring-shaped sand blasting device (4), an axial variable angle supporting mechanism (7) and a wind tunnel heat exchanger / filter (20), the power section of the closed return wind tunnel (1) is provided with the fan (2), the top of the test section of the closed return wind tunnel (1) is provided with a model replacement cabin cover (5), the side of the test section of the closed return wind tunnel (1) is provided with a personnel access door (6), the honeycomb device (3) is arranged at the inlet of the stable section of the closed return wind tunnel (1), the ring-shaped sand blasting device (4) is arranged at the stable section of the closed return wind tunnel (1) and located behind the honeycomb device (3), the axial variable angle supporting mechanism (7) is fixedly connected to the inside of the test section of the closed return wind tunnel and located behind the ring-shaped sand blasting device (4), the wind tunnel heat exchanger / filter (20) is fixedly connected to the inner wall of the transition section of the closed return wind tunnel (1) and located in front of the fan (2), the closed return wind tunnel (1) is connected with a pressure simulation system, a sand dust system is connected with the ring-shaped sand blasting device (4) and provides sand dust particles, the ring-shaped sand blasting device (4) disperses the sand dust in the air flow, and a refrigeration system is connected with the wind tunnel heat exchanger / filter (20), the sand dust system and the pressure simulation system respectively to provide a cooling source.

2. The low pressure, low density engine dust environment simulation device of claim 1, wherein: The sand dust system comprises a high-pressure gas storage tank (11), a buffer tank (12), an air compressor (13), a filter / dryer (14) and a high-precision flow scale (15), the air compressor (13) is connected with the buffer tank (12), the buffer tank (12) is connected with the filter / dryer (14), the filter / dryer (14) is connected with the high-pressure gas storage tank (11), the high-pressure gas storage tank (11) is connected with the high-precision flow scale (15), and the high-precision flow scale (15) is connected with the ring-shaped sand blasting device (4).

3. The low pressure, low density engine dust environment simulation device of claim 2, wherein: The pressure simulation system comprises a high-precision sand dust filter (16), a large-particle sand dust shielding device (17), a high-precision flow regulating valve group (18) and a vacuum unit (19), the large-particle sand dust shielding device (17) is connected with the hole flange at the first corner of the closed return wind tunnel (1), the large-particle sand dust shielding device (17) is connected with the high-precision sand dust filter (16), the high-precision sand dust filter (16) is connected with the high-precision flow regulating valve group (18), the high-precision flow regulating valve group (18) is connected with the vacuum unit (19), and the gas outlet of the vacuum unit (19) is connected with the outdoor atmosphere through a silencer.

4. The low pressure, low density engine dust environment simulation device of claim 3, wherein: The refrigeration system comprises a cooling tower (8), an underground pool (9) and a cooling circulating water pump (10), three water supply pipes of the cooling circulating water pump (10) are connected with water inlet interfaces of a vacuum unit (19), an air compressor (13) and a wind tunnel heat exchanger / filter (20) respectively, and then water return pipes of the vacuum unit (19), the air compressor (13) and the wind tunnel heat exchanger / filter (20) are combined together to form a total water return pipe, the total water return pipe is connected with the cooling tower (8), and after being cooled by the cooling tower (8), the water is automatically discharged into the underground pool (9), and a water return pipe is led out from the underground pool (9) and connected with the cooling circulating water pump (10).

5. The low pressure, low density engine dust environment simulation device of claim 1, wherein: The annular sand blasting device (4) is arranged on the axis of the test section of the closed recirculating wind tunnel (1) as a reference, and the annular sand blasting nozzles are uniformly distributed.

6. The low pressure, low density engine dust environment simulation device of claim 1, wherein: The axial variable angle supporting mechanism (7) comprises a hinge (7-1), an engine loading and unloading platform (7-2), a rear guide device (7-3), a rear lifting device (7-4), a front lifting device (7-5) and a front guide device (7-6), the rear guide device (7-3) and the front guide device (7-6) are fixedly connected with the inner wall of the test section of the recirculating wind tunnel (1), the rear lifting device (7-4) is located inside the rear guide device (7-3), and the rear lifting device (7-4) realizes vertical lifting through a lifting push rod inside the rear lifting device (7-4); the front lifting device (7-5) is located inside the front guide device (7-6), and the front lifting device (7-5) realizes vertical lifting through a lifting push rod inside the front lifting device (7-5); the upper end of the front lifting device (7-5) is fixedly connected with the lower mounting plane of the hinge (7-1), the upper mounting plane of the hinge (7-1) is fixedly connected with the front lower plane of the engine loading and unloading platform (7-2), and the upper end of the rear lifting device (7-4) is fixedly connected with the rear end of the engine loading and unloading platform (7-2); the axial position of the engine loading and unloading platform (7-2) is adjusted by adjusting the lifting heights of the rear lifting device (7-4) and the front lifting device (7-5).

7. The low pressure, low density engine dust environment simulation device of claim 6, wherein: The axial variable angle supporting mechanism (7) provides support for the test engine, and the axial pitch angle range is-30° to 30°.

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