CN111076888A - Small vertical backflow ice wind tunnel experimental device for measuring ice accretion adhesion - Google Patents
Small vertical backflow ice wind tunnel experimental device for measuring ice accretion adhesion Download PDFInfo
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- CN111076888A CN111076888A CN202010028325.6A CN202010028325A CN111076888A CN 111076888 A CN111076888 A CN 111076888A CN 202010028325 A CN202010028325 A CN 202010028325A CN 111076888 A CN111076888 A CN 111076888A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention provides a small vertical backflow ice wind tunnel experimental device for measuring ice accretion adhesion, which comprises: the device comprises an atomizing nozzle system, an experimental rotating beam part, a low-temperature environment box part and a vertical backflow small wind tunnel system. The beneficial effects of the invention include: 1) the method includes the steps that the flying icing condition of the high-altitude airplane is simulated as much as possible under the ground environment, and an experimental device for measuring the adhesion force of the accumulated ice is provided; 2) the adhesion force measurement experiment controlled by multiple factors is realized, the simulation of ice accretion of the airplane under different environmental temperatures and different wind speeds can be realized, and the ice accretion adhesion force can be accurately measured; 3) the small vertical reflux icing wind tunnel is built, the size is small, the icing state research under the low-temperature environment can be realized, the vertical reflux icing wind tunnel is suitable for schools, laboratories, enterprises and the like to explore the specific change rules of different influence factors on the adhesive force, and the vertical reflux icing wind tunnel has a wide application prospect.
Description
Technical Field
The invention relates to a small vertical backflow icing wind tunnel experimental device for measuring icing adhesion force, which is used for simulating icing of an airplane under atmospheric conditions and realizing icing.
Background
When the airplane flies through the supercooled cloud layer, supercooled water drops and ice crystals in the air collide with the airplane to generate attached ice which is attached to the surface of the airplane, and the icing phenomenon can influence the aerodynamic appearance of the airplane, so that the lift force of the airplane is reduced, the resistance is increased, the performance of the airplane is greatly influenced, and the accident condition of the airplane can be seriously caused. Deicing of aircraft surfaces is therefore an important research context. The ice formed by the aircraft flying at high altitude is impact ice, and the formation of the impact ice is influenced by a series of parameters such as water droplet size, atmospheric environment temperature, liquid water content, aircraft flying speed and the like. The surface icing thereof can be classified into open ice, frost ice and mixed ice. Frost ice generally forms with lower density and loose morphology under conditions of lower temperature and lower liquid water content and is easily removed by air flow blows. The ice is formed under the conditions of higher temperature and liquid water content, has higher density and compact structure, is not easy to remove, and seriously threatens the flight safety of the airplane. Therefore, a series of means are needed to remove ice attached to the surface of the airplane, mechanical deicing is a typical deicing method for the icing on the surface of the airplane, and the adhesion between an ice layer and the skin is damaged by means of vibration, deformation and the like of the skin, so that the deicing effect is achieved. To ensure that the force applied to the aircraft surface is sufficient to completely remove the ice accretion and to minimize the use of energy on the aircraft, it is desirable to have an accurate knowledge of the amount of adhesion of the ice accretion to the aircraft surface. Therefore, the vertical backflow small-sized icing wind tunnel is developed for measuring and researching the adhesion force under different icing conditions of the surface of the airplane, and is used for calculating the adhesion force of the icing surface in order to simulate the icing condition of the surface of the airplane as much as possible.
Disclosure of Invention
According to one aspect of the invention, a small vertical backflow ice wind tunnel experimental device for measuring the adhesion force of ice deposition is provided, and is characterized by comprising:
an atomizing nozzle system is arranged on the bottom of the container,
the experimental rotating beam part is used for testing,
the part of the low-temperature environment box,
a small wind tunnel system which flows back vertically,
wherein:
the atomizing nozzle system includes:
an air atomizing nozzle is arranged at the bottom of the air atomizing nozzle,
a gas path portion including:
an air compressor for producing high-pressure air,
an air purifier for removing impurities in high-pressure air,
the air regulator regulates the pressure of the high-pressure air output by the air purifier,
a flow regulating valve for delivering the high-pressure air output by the air regulator to the air channel interface of the nozzle,
a waterway portion, comprising:
a water pump for delivering water to the liquid filter,
the liquid filter is used for removing impurities in water from the water pump,
a liquid regulator for controlling the pressure of the water output by the liquid filter,
a liquid flow regulating valve for regulating the flow of the water output by the liquid regulator and delivering the water to the waterway interface of the nozzle,
the experimental rotating beam part comprises:
the experiment table is fixed at the upper end of the experiment beam,
the experimental beam is completely arranged in the low-temperature environment box,
an experiment beam fixing piece connected with the lower end of the experiment beam,
a motor is arranged on the base plate and is provided with a motor,
a coupler, wherein the experimental beam fixing part is connected with the motor through the coupler,
the frequency converter is used for being matched with the motor for use, the rotating speed of the motor is adjusted by changing the frequency of the frequency converter, so that the control of the rotating speed of the experimental beam is realized,
the low-temperature environment box part comprises:
a stainless steel box body as a main body, wherein the inner surface of the stainless steel box body is stuck with heat preservation cotton for keeping the environmental temperature,
a plurality of finned heat exchangers arranged in the stainless steel box body,
a cooling water circulator arranged outside the stainless steel box body and connected with the plurality of fin type heat exchangers through silica gel hoses,
the small vertical backflow wind tunnel system comprises: power section, first diffusion section, water conservancy diversion section, shrink section, experiment section, second diffusion section, wherein:
the power section comprises a centrifugal fan arranged at the corner of the power section and used for providing a certain amount of stable airflow for experiments,
the flow guide section comprises a straight flow section, a first corner section, a second corner section and a third corner section and is used for changing the direction of the airflow in the flowing process,
the contraction section is used for playing a role of accelerating the airflow,
the experimental section is the section used to perform the experiment,
the experimental section comprises a fracture used for placing the experimental rotating beam in the experimental section to perform ice accumulation simulation and/or adhesion force measurement,
the air flow flowing process in the vertical backflow small wind tunnel system comprises the following steps: the airflow at the outlet of the fan is decelerated after passing through the first soft connecting part and the first diffusion section, then passes through the first corner section, the second corner section and the direct current section, so that the direction of the airflow is changed, then the airflow is rectified in the stable section, then the airflow enters the experiment section after being accelerated by the contraction section, the airflow and the spray formed on the nozzle arranged at the experiment section collide with the surface of the experiment table together to form accumulated ice, the adhesion force between the accumulated ice and the surface of the experiment table is measured by a centrifugal method, the airflow is decelerated after passing through the experiment section and the second diffusion section again, then the airflow passes through the third corner section and the second soft connecting part, and reaches the inlet of the fan to form an integral vertical backflow circulation wind tunnel system.
Drawings
Fig. 1 is a schematic view of the overall configuration of a small vertical backflow ice wind tunnel experimental device for ice accretion adhesion measurement according to an embodiment of the present invention.
Fig. 2 is a schematic diagram of a spray system according to one embodiment of the present invention.
FIG. 3 is a schematic view of a rotating experimental beam system according to one embodiment of the present invention.
FIG. 4 is a schematic view of a cryogenic environment tank according to one embodiment of the present invention.
FIG. 5 is a system diagram of a small vertical return flow icing wind tunnel experimental setup for icing adhesion measurement according to one embodiment of the present invention.
Detailed Description
An overall schematic diagram of a small vertical backflow ice wind tunnel experimental device for ice accretion adhesion measurement according to an embodiment of the present invention is shown in fig. 1 below.
The small vertical reflux icing wind tunnel experimental device for measuring the ice accretion adhesion comprises four system parts: the device comprises an atomizing nozzle system, an experimental rotating beam part, a low-temperature environment box part and a vertical backflow small wind tunnel system. Each part is specifically described below.
1. An atomizing nozzle system:
the atomizing nozzle system comprises an air atomizing nozzle and an air circuit water path, as shown in fig. 2. The gas path produces high-pressure air through an air compressor 101, the high-pressure air removes impurities through an air purifier 102, and the high-pressure air is conveyed to a gas path interface of a nozzle 105 through a flow regulating valve 104 after the air pressure is regulated through an air regulator 103. The water path part conveys water to a liquid filter 108 through a water pump 109 with the lift of 5m and the flow rate of 2200L/h to remove impurities in the water, and then the water is conveyed to a water path interface of a nozzle 105 through a liquid flow regulating valve 106 after the pressure of the water is controlled by a liquid regulator 107. In one embodiment, the nozzle 105 is an official atomizing nozzle of spraying corporation, the model is SU 121/4J, two ends of the official atomizing nozzle respectively correspond to the two interfaces of the water path and the air path, and two nuts at two ends are used for adjusting the threshold values of the water path and the air path, changing the flow supply and adjusting the spray flow and the spray droplet diameter. At 2.8bar, the flow rate is 2.08 to 220L/h, and the larger the flow rate of the spray liquid drops generated by the atomizing nozzle 105 is in positive correlation with the flow rate of the atomizing nozzle, the larger the diameter of the generated liquid drops is. According to the official data about the nozzle, the median diameter of the spray droplet volume at 2.8bar of the experimental nozzle is 15-200 μm
2. Experimental rotating beam section:
the design of the experimental walking beam section is shown in fig. 3, where: the experiment table 201 is fixed at the upper end of the experiment beam 202 through bolts, the whole experiment beam is arranged in the low-temperature environment box, and the lower end of the experiment beam 202 is connected with the experiment beam fixing piece 203. The experiment beam fixing piece 203 is connected with the motor 205 through the coupler 204, the motor 205 is matched with the frequency converter 206 for use, and the rotating speed of the motor 205 is adjusted by changing the frequency of the frequency converter 206, so that the rotating speed of the experiment beam 202 is controlled, and the rotating speed adjustable range is 0-8000 rpm.
3. Low temperature environment box part:
as shown in fig. 4, according to an embodiment of the present invention, the low temperature environment box portion includes a stainless steel box 301 of 650mm x 600mm x 450mm as a main body, and an insulating cotton 302 of 30mm thickness is attached to an inner surface thereof to stabilize an ambient temperature. The stainless steel box 301 includes 8 200mm 230mm 40mm finned heat exchangers 303 inside, which are connected to an external cooling water circulator 306 through a silicone hose 307. According to one embodiment of the invention, a controlled low temperature environment with a minimum temperature of-17 ℃ can be achieved within the low temperature environment chamber.
4. Vertical backflow small wind tunnel system:
as shown in fig. 5, a small vertical return flow wind tunnel system according to an embodiment of the present invention includes five parts: a power section, a diffusion section, a flow guide section, a contraction section and an experiment section. The power section includes a centrifugal fan 401 mounted at its corners to provide a certain amount of steady airflow for the experiment. The flow guide section comprises a straight flow section 405 and three corner sections 404, 406 and 411 and is used for changing the direction of the airflow in the flow process; the contraction section 408 plays a role in accelerating the airflow, and the contraction section 408 is designed and selected with a dimensional curve to ensure the stability of the airflow field; the experiment section 409 is an experiment performing part, and a fracture with the height of 75mm exists in the experiment section 409, and is used for placing the experiment rotating beam 202 in the experiment section 409 to perform ice accumulation simulation and measure the adhesion force. The whole airflow flow process in the wind tunnel is as follows: the airflow at the outlet of the fan 401 is decelerated after passing through the flexible connection 402 and the diffuser section 403, then passes through two corner sections 404 and 406 and a direct current section 405, so that the direction of the airflow is changed, then the airflow is rectified in the stabilizing section 407, and then the airflow is accelerated through the contraction section 408 to enter the experimental section. The gas flow, together with the spray formed on the nozzle 105 (fig. 2) installed at the experimental section 409, impinges on the surface of the experimental bench 201 (fig. 3) to form ice accretion, and the adhesion thereof is measured by a centrifugal method. After passing through the experimental section 409, the airflow is decelerated again through a diffuser section 410, then flows through a corner 411 and a flexible connection 412, and reaches the inlet of the fan 401, so that an integral vertical backflow circulation wind tunnel system is formed.
The advantages and beneficial effects of the invention include:
1) the method includes the steps that the flying icing condition of the high-altitude airplane is simulated as much as possible under the ground environment, and an experimental device for measuring the adhesion force of the accumulated ice is provided;
2) the adhesion force measurement experiment controlled by multiple factors is realized, the simulation of ice accretion of the airplane under different environmental temperatures and different wind speeds can be realized, and the ice accretion adhesion force can be accurately measured;
3) the small vertical reflux icing wind tunnel is built, the size is small, the icing state research under the low-temperature environment can be realized, the vertical reflux icing wind tunnel is suitable for schools, laboratories, enterprises and the like to explore the specific change rules of different influence factors on the adhesive force, and the vertical reflux icing wind tunnel has a wide application prospect.
Claims (4)
1. A small-size perpendicular backward flow ice wind tunnel experimental apparatus for accumulated ice adhesion measurement, its characterized in that includes:
an atomizing nozzle system is arranged on the bottom of the container,
the experimental rotating beam part is used for testing,
the part of the low-temperature environment box,
a small wind tunnel system which flows back vertically,
wherein:
the atomizing nozzle system includes:
an air atomizing nozzle (105),
a gas path portion including:
an air compressor (101) for producing high-pressure air,
an air cleaner (102) for removing impurities from the high pressure air,
an air regulator (103) for regulating the pressure of the high-pressure air output from the air purifier (102),
a flow regulating valve (104) for delivering the high-pressure air output by the air regulator (103) to the air passage interface of the nozzle (105),
a waterway portion, comprising:
a water pump (109) for delivering water to the liquid filter (108),
the liquid filter (108) for removing impurities from the water pump (109),
a liquid regulator (107) for controlling the pressure of the water output by the liquid filter (108),
a liquid flow regulating valve (106) for regulating the flow of water outputted from the liquid regulator (107) and delivering the water to the waterway interface of the nozzle (105),
the experimental rotating beam part comprises:
a test bench (201) fixed on the upper end of the test beam (202),
the experimental beam (202), which is entirely placed in a low-temperature environment chamber,
an experiment beam fixing member (203) connected to a lower end of the experiment beam (202),
a motor (205) for rotating the motor,
a coupler (204), wherein the experimental beam fixing part (203) is connected with the motor (205) through the coupler (204),
the frequency converter (206) is used for being matched with the motor (205) for use, the rotating speed of the motor (205) is adjusted by changing the frequency of the frequency converter (206), so that the control of the rotating speed of the experimental beam (202) is realized,
the low-temperature environment box part comprises:
a stainless steel box body (301) as a main body, wherein the inner surface of the stainless steel box body (301) is stuck with heat insulation cotton (302) for keeping the environmental temperature,
a plurality of finned heat exchangers (303) arranged in the stainless steel box body (301),
a cooling water circulator (306) arranged outside the stainless steel box body (301) and connected with the plurality of fin type heat exchangers (303) through silica gel hoses (307),
the small vertical backflow wind tunnel system comprises: power section, first diffusion section, water conservancy diversion section, shrink section, experiment section, second diffusion section, wherein:
the power section comprises a centrifugal fan (401) mounted at its corners for providing a certain amount of steady airflow for the experiment,
the flow guiding section comprises a straight flow section (405), a first corner section (404), a second corner section (406) and a third corner section (411) and is used for changing the direction of the airflow in the flowing process,
the contraction section (408) is used for increasing the speed of the airflow,
experimental section (409) is the section used to perform the experiment,
the experimental section (409) comprises a break for placing the experimental rotation beam (202) within the experimental section (409) for ice accretion simulation and/or adhesion magnitude measurement,
the air flow flowing process in the vertical backflow small wind tunnel system comprises the following steps: the airflow at the outlet of the fan (401) is decelerated after passing through the first soft connection part (402) and the first diffusion section (403), then passes through a first corner section (404) and a second corner section (406) and a straight section (405) so that the direction of the airflow is changed, and then the airflow is rectified in a stable section (407), then the airflow is accelerated to the experimental section through a contraction section (408), the airflow and the spray formed on a nozzle (105) arranged at the experimental section (409) are collided on the surface of the experimental table (201) together to form accumulated ice, the adhesion force between the accumulated ice and the surface of the experimental table (201) is measured through a centrifugal method, the airflow is decelerated through a second diffusion section (410) after passing through the experimental section (409), then flows through the third corner section (411) and the second soft connecting part (412) to reach the inlet of the fan (401), and an integral vertical backflow circulating wind tunnel system is formed.
2. The small vertical backflow ice wind tunnel experiment device for ice accretion adhesion measurement according to claim 1, characterized in that:
the larger the flow rate of the spray droplets generated by the atomizing nozzle (105) and the flow rate of the atomizing nozzle have positive correlation, the larger the diameter of the generated droplets is,
the atomizing nozzle (105) sprays droplets having a median volume diameter of 15 to 200 microns at 2.8 bar.
3. The small vertical backflow ice wind tunnel experiment device for ice accretion adhesion measurement according to claim 1, characterized in that:
the contraction section (408) adopts a dimensional curve to ensure the stability of the airflow field.
4. The small vertical backflow ice wind tunnel experiment device for ice accretion adhesion measurement according to claim 1, characterized in that:
the height of said fracture of the experimental section (409) is 75mm,
the adjustable range of the rotating speed of the frequency converter (206) is 0-8000 rpm.
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Cited By (9)
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| CN112798214A (en) * | 2021-04-08 | 2021-05-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Testing device and testing method capable of controlling icing area |
| CN113551865A (en) * | 2021-04-26 | 2021-10-26 | 南京航空航天大学 | Spraying system capable of removing residual water in pipeline |
| CN113639988A (en) * | 2021-07-12 | 2021-11-12 | 江铃汽车股份有限公司 | Throttle valve ice breaking verification method |
| CN114739902A (en) * | 2022-03-30 | 2022-07-12 | 成都流体动力创新中心 | Device and method for measuring tensile adhesion strength of dynamic ice layer on surface of material |
| CN115078357A (en) * | 2022-06-14 | 2022-09-20 | 同济大学 | System for inducing and detecting icing of water drops on supercooling surface |
| CN115628876A (en) * | 2022-12-08 | 2023-01-20 | 中国航空工业集团公司沈阳空气动力研究所 | Icing wind tunnel icing and substrate material adhesion force measuring device |
| CN117630089A (en) * | 2023-10-23 | 2024-03-01 | 北京航空航天大学 | Method for determining critical crushing speed of ice crystal vertical impact surface |
| CN117669405A (en) * | 2023-10-23 | 2024-03-08 | 北京航空航天大学 | Multistep prediction method for stable ice shape in high-altitude ice crystal icing process |
| CN118347686A (en) * | 2024-06-18 | 2024-07-16 | 溧阳气动创新研究院有限公司 | Light-weight standard model for wind tunnel flow field calibration |
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| CN112798214A (en) * | 2021-04-08 | 2021-05-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Testing device and testing method capable of controlling icing area |
| CN113551865A (en) * | 2021-04-26 | 2021-10-26 | 南京航空航天大学 | Spraying system capable of removing residual water in pipeline |
| CN113639988A (en) * | 2021-07-12 | 2021-11-12 | 江铃汽车股份有限公司 | Throttle valve ice breaking verification method |
| CN114739902A (en) * | 2022-03-30 | 2022-07-12 | 成都流体动力创新中心 | Device and method for measuring tensile adhesion strength of dynamic ice layer on surface of material |
| CN114739902B (en) * | 2022-03-30 | 2023-08-04 | 成都流体动力创新中心 | Device and method for measuring tensile adhesion strength of dynamic ice layer on material surface |
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| CN115628876A (en) * | 2022-12-08 | 2023-01-20 | 中国航空工业集团公司沈阳空气动力研究所 | Icing wind tunnel icing and substrate material adhesion force measuring device |
| CN115628876B (en) * | 2022-12-08 | 2023-03-14 | 中国航空工业集团公司沈阳空气动力研究所 | Icing wind tunnel icing and substrate material adhesion force measuring device |
| CN117630089A (en) * | 2023-10-23 | 2024-03-01 | 北京航空航天大学 | Method for determining critical crushing speed of ice crystal vertical impact surface |
| CN117669405A (en) * | 2023-10-23 | 2024-03-08 | 北京航空航天大学 | Multistep prediction method for stable ice shape in high-altitude ice crystal icing process |
| CN118347686A (en) * | 2024-06-18 | 2024-07-16 | 溧阳气动创新研究院有限公司 | Light-weight standard model for wind tunnel flow field calibration |
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