CN110450961B - Wing and flying device for preventing and removing ice by utilizing ultrasonic hydrodynamic cavitation - Google Patents
Wing and flying device for preventing and removing ice by utilizing ultrasonic hydrodynamic cavitation Download PDFInfo
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- CN110450961B CN110450961B CN201910708093.6A CN201910708093A CN110450961B CN 110450961 B CN110450961 B CN 110450961B CN 201910708093 A CN201910708093 A CN 201910708093A CN 110450961 B CN110450961 B CN 110450961B
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- 239000007921 spray Substances 0.000 claims abstract description 11
- 239000007788 liquid Substances 0.000 claims abstract description 9
- 230000001939 inductive effect Effects 0.000 claims abstract description 4
- 239000007789 gas Substances 0.000 claims description 88
- 238000007667 floating Methods 0.000 claims description 16
- 239000000523 sample Substances 0.000 claims description 14
- 239000011261 inert gas Substances 0.000 claims description 12
- 238000000746 purification Methods 0.000 claims description 9
- 230000000694 effects Effects 0.000 description 8
- 238000004887 air purification Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000005265 energy consumption Methods 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physical Or Chemical Processes And Apparatus (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a wing and a flight device for preventing and removing ice by utilizing ultrasonic hydrodynamic cavitation, which comprise a wing body, wherein a wrapping plate is arranged at the front edge position of the wing body, the wrapping plate and an inner lining skin of the wing body form a hydrodynamic cavitation cavity, liquid can be filled in the hydrodynamic cavitation cavity, a plurality of nozzles are respectively arranged on the two side cavity walls of the hydrodynamic cavitation cavity, the nozzles on the two sides are respectively connected with a gas supply mechanism, the gas supply mechanism can spray gas into the hydrodynamic cavitation cavity through the nozzles to form bubbles in the liquid filled in the hydrodynamic cavitation cavity, the hydrodynamic cavitation cavity is connected with an ultrasonic mechanism, and the ultrasonic mechanism is used for inducing the bubbles in the hydrodynamic cavitation cavity to generate cavitation.
Description
Technical Field
The invention relates to the technical field of aviation deicing prevention and removal, in particular to an ultrasonic hydrodynamic cavitation deicing prevention wing and a flight device.
Background
The icing on the surfaces of the wings of the airplane and the rotors of the helicopter seriously affects the flight performance and the flight lift force, the conventional airplane deicing and preventing device mostly adopts electrothermal deicing and hot air deicing and preventing technologies, and the inventor finds that the conventional wing deicing technology has the problems of slow energy release and serious airborne energy consumption.
In recent years, hydrodynamic cavitation is used as a novel high-energy release technology, ultrasonic waves are used for inducing the hydrodynamic cavitation, and the control of the hydrodynamic cavitation process is realized.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide the wing for preventing and removing ice by utilizing ultrasonic hydrodynamic cavitation, the ultrasonic hydrodynamic cavitation ice-preventing and removing technology can be combined with the wing, the energy release is fast, the ice-preventing and removing effect is good, and the onboard energy consumption is low.
In order to achieve the purpose, the invention adopts the following technical scheme:
the wing comprises a wing body, wherein a wrapping plate is arranged at the front edge of the wing body, the wrapping plate and an inner lining skin of the wing body form a hydrodynamic cavitation cavity, liquid can be filled in the hydrodynamic cavitation cavity, a plurality of nozzles are respectively arranged on the two side cavity walls of the hydrodynamic cavitation cavity, the nozzles on the two sides are respectively connected with a gas supply mechanism, the gas supply mechanism can spray gas into the hydrodynamic cavitation cavity through the nozzles to form bubbles in the liquid filled in the hydrodynamic cavitation cavity, the hydrodynamic cavitation cavity is connected with an ultrasonic mechanism, and the ultrasonic mechanism is used for inducing the bubbles in the hydrodynamic cavitation cavity to generate cavitation.
Further, the gas supply mechanism comprises a gas generator, the gas generator is connected with a gas pump through a pipeline, and the gas pump is connected with the nozzle through a pipeline.
Further, the gas generator adopts an inert gas generator.
Further, a gas purification device is arranged on a pipeline between the gas pump and the nozzle, and the gas purification device is used for purifying gas in the pipeline.
Furthermore, a flow meter is arranged on a pipeline between the air pump and the nozzle, and the flow meter is used for detecting the air flow in the pipeline.
Furthermore, the ultrasonic mechanism comprises a plurality of ultrasonic probes, the ultrasonic probes are fixed on the outer side surface of the cavity wall of the hydrodynamic cavitation cavity and are positioned inside the wing body, the ultrasonic probes are connected with an ultrasonic generator through an ultrasonic controller, and the ultrasonic generator is connected with a power supply.
Furthermore, the nozzle comprises a first nozzle part and a second nozzle part which are connected in an integrated manner, the first nozzle part and the second nozzle part are both in frustum-shaped structures, the inner spaces are communicated to form a gas flow passage, the end parts with smaller areas of the first nozzle part and the second nozzle part are connected, the end part with larger area of the first nozzle part is provided with a plurality of spray holes for gas to flow into the hydraulic cavitation cavity, the end part with larger area of the second nozzle part is used for connecting a gas supply mechanism, a floating ball is arranged in the first nozzle part and is elastically connected with the first nozzle part and used for controlling the area of the gas flow passage between the first nozzle part and the second nozzle part.
Furthermore, the floating ball is fixedly connected with one end of the spring, the other end of the spring is connected with the inner side face of the end part with the larger area of the first nozzle part, and the floating ball is elastically connected with the first nozzle part through the spring.
Furthermore, one side end of the spring is fixedly connected with a connecting plate, the connecting plate is fixedly connected with one end of an adjusting bolt, and the adjusting bolt is in threaded connection with the end part with the larger area of the first nozzle part.
The invention also discloses a flight device, and the wing using ultrasonic hydrodynamic cavitation to prevent and remove ice is adopted.
The invention has the beneficial effects that:
1. the wing is simple in structure, the front edge of the wing body is provided with the hydrodynamic cavitation cavity, liquid can be filled in the hydrodynamic cavitation cavity, gas can be supplied to the interior by the gas supply mechanism, hydrodynamic cavitation is generated under the action of the ultrasonic mechanism, mechanical energy and heat energy released by hydrodynamic cavitation are used for deicing the wing, the combination of ultrasonic hydrodynamic cavitation deicing and the wing is realized, and the deicing efficiency is high.
2. According to the wing, the initial pressing force of the spring on the floating ball can be adjusted through the adjusting bolt, so that the gas flow passage area through which gas driven by the gas pump can pass is adjusted, the diameter of the bubbles is controlled, bubbles with different diameters can be filled in the two sides of the hydrodynamic cavitation cavity, the position of the hydrodynamic cavitation of the gas bubbles is controlled, and the effect of the hydrodynamic cavitation is comprehensively improved.
3. The wing provided by the invention adopts the inert gas generator, can generate inert gas, can release more energy compared with common hydrodynamic cavitation, and has a better deicing effect.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the application and, together with the description, serve to explain the application and are not intended to limit the application.
FIG. 1 is a schematic view of the overall structure of embodiment 1 of the present invention;
FIG. 2 is a schematic view of a nozzle structure according to example 1 of the present invention;
FIG. 3 is a schematic view of the assembly of the air supply mechanism and the hydrodynamic cavitation chamber in embodiment 1 of the present invention;
fig. 4 is a schematic view of an installation position of an ultrasonic probe in embodiment 1 of the present invention;
the aircraft wing comprises a wing body 1, an inner lining skin 1-1, a wrapping plate 2, a hydrodynamic cavitation cavity 3, a nozzle 4, a first nozzle part 4-1, a second nozzle part 4-2, a spray hole 4-3, a joint 4-4, a floating ball 4-5, a spring 4-6, a connecting plate 4-7, an adjusting bolt 4-8, a first gas generator 5, a second gas generator 6, a first pipeline 7, a first air pump 8, a second pipeline 9, a second air pump 10, a first gas purifying device 11, a first flowmeter 12, a second gas purifying device 13, a second flowmeter 14, an ultrasonic probe 15 and a driving wire 16.
Detailed Description
It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the disclosure. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
For convenience of description, the words "up" and "down" in the present application, if any, are used merely to indicate correspondence with the directions of the upper and lower portions of the drawings, and are not intended to limit the structure, but merely to facilitate the description of the present invention and to simplify the description, and do not indicate or imply that the apparatus or components so referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be considered as limiting the present invention.
As introduced in the background art, the conventional wing deicing mostly adopts electrothermal deicing and hot air deicing, the energy release is slow, the airborne energy consumption is serious, and the application provides the wing for preventing the deicing by utilizing ultrasonic hydrodynamic cavitation.
In example 1 of an exemplary embodiment of the present application, as shown in fig. 1 to 4, an airfoil for preventing and removing ice by using ultrasonic hydrodynamic cavitation includes an airfoil body 1, where the airfoil body includes a frame and an inner lining skin 1-1 wrapped on an outer side surface of the frame, and the airfoil body may adopt an existing airfoil structure, and its specific structure is not described in detail herein.
The wing is characterized in that a wrapping plate 2 is installed at the front edge of the wing body, the wrapping plate is made of a thin iron plate, the wrapping plate and an inner lining skin at the front edge of the wing body form a hydrodynamic cavitation cavity 3, and the inner space of the hydrodynamic cavitation cavity is used for containing liquid water.
All install a plurality of nozzles 4 on the both sides chamber wall of hydrodynamic cavitation cavity, a plurality of nozzles are along the chord of wing to setting up, the nozzle is connected with air feed mechanism, and air feed mechanism can inject gas through the nozzle to the space in the hydrodynamic cavitation cavity.
The nozzle comprises a first nozzle part 4-1 and a second nozzle part 4-2 which are in frustum structures, the end parts of the first nozzle part and the second nozzle part with smaller areas are integrally connected, cavities communicated with each other are arranged inside the first nozzle part and the second nozzle part to form a gas flow passage, a plurality of spray holes 4-3 are formed in the nozzle wall of the end part with the larger area of the first nozzle part, gas can flow into the space in the hydrodynamic cavitation cavity through the spray holes, and a joint 4-4 is arranged on the nozzle wall of the end part with the larger area of the second nozzle part and is used for being connected with a gas supply mechanism.
The inner part of the first nozzle part is provided with a floating ball 4-5 which is elastically connected with the first nozzle part, the floating ball is arranged at the connecting position of the first nozzle part and the second nozzle part, and the floating ball can move along the axial direction of the nozzle, so that the size of the cross section area of a gas flow passage in the first nozzle part and the second nozzle part is controlled, and the pressure of gas flowing out of the spray holes is controlled.
The floating ball is fixedly connected with one end of a spring 4-6, the other end of the spring is fixedly connected with a connecting plate 4-7, the connecting plate is fixedly connected with an adjusting bolt 4-8, and the adjusting bolt is in threaded connection with the nozzle wall at the end part with the larger area of the first nozzle part.
When the gas supply mechanism supplies gas to the nozzle at the set gas pressure, the initial pressure applied to the floating ball by the spring can be adjusted through the adjusting bolt, so that the moving distance of the floating ball when the stress is balanced is adjusted, the sectional area of a gas flow passage through which the gas can pass is adjusted, and the adjustment of the pressure of the gas flowing out of the spray hole is realized.
The gas supply mechanism comprises a first gas generator 5 and a second gas generator 6, the first gas generator is connected with a first gas pump 8 through a first pipeline 7, the first gas pump is connected with a nozzle on one side of the hydrodynamic cavitation cavity through a first pipeline, the second gas generator is connected with a second gas pump 10 through a second pipeline 9, the second gas pump is connected with a nozzle on the other side of the hydrodynamic cavitation cavity through a second pipeline, the first gas generator and the second gas generator both adopt inert gas generators which can generate inert gas, and the inert gas is sprayed into the hydrodynamic cavitation cavity through the nozzles on the first pipeline, the second pipeline and the two sides under the action of the first gas pump and the second gas pump respectively.
A first pipeline between the first air pump and the nozzle is provided with a first air purification device 11 and a first flowmeter 12, the first air purification device is used for purifying inert gas in the first pipeline, the first flowmeter is used for detecting the gas flow in the first pipeline, a second pipeline between the second air pump and the nozzle is provided with a second air purification device 13 and a second flowmeter 14, the second air purification device is used for purifying the inert gas in the second pipeline, and the second flowmeter is used for detecting the gas flow in the second pipeline.
The first gas purification device and the second gas purification device are conventional gas purification devices, and the specific structure thereof will not be described in detail.
In this embodiment, the first pipeline and the second pipeline are uniformly arranged in the inner space of the wing body, and the first gas generator, the second gas generator, the first air pump, the second air pump, the first gas purification device and the second gas purification device can be arranged in a flight device body used in cooperation with the wing, for example, in an airplane body.
The hydrodynamic cavitation cavity is also connected with an ultrasonic mechanism, the ultrasonic mechanism comprises a plurality of ultrasonic probes 15 which are fixed on the outer side surface of the cavity wall of the hydrodynamic cavitation cavity and are positioned in the wing body, in the embodiment, the ultrasonic probes are fixed on the inner side surface of the lining skin of the wing body, the plurality of ultrasonic probes are distributed along the span direction of the wing, the ultrasonic probes are connected with an ultrasonic controller through a driving wire 16, the ultrasonic controller is connected with an ultrasonic generator, the ultrasonic generator is connected with a power supply, the power supply is used for supplying power to the ultrasonic probes, the ultrasonic controller adopts the existing ultrasonic control equipment for controlling the power of ultrasonic waves, the existing equipment is adopted, the detailed description is omitted, the existing equipment is adopted as the ultrasonic generator, the detailed description is omitted here, the driving wire is arranged in the wing body, the power supply, the ultrasonic controller and the ultrasonic generator can be arranged inside the flying device body matched with the wing for use, and can be set by a person skilled in the art according to actual needs, which is not described in detail herein.
Example 2:
the embodiment discloses a flying device, which is provided with the wing which utilizes ultrasonic hydrodynamic cavitation to prevent and remove ice in the embodiment 1.
In the working process of the wing, the first gas generator and the second gas generator can generate inert gas, the generated inert gas is sprayed into the hydraulic cavitation cavity through the nozzles on two sides under the action of the first air pump and the second air pump, bubbles are generated in liquid water in the hydraulic cavitation cavity, the ultrasonic probe works, the generated bubbles are induced to generate a cavitation effect, energy is released, impact vibration is generated, and an anti-icing effect is achieved on the wing.
The adjusting bolt is rotated to adjust the initial pressure applied by the spring to the floating ball, so that the moving distance of the floating ball when the force balance is achieved is adjusted, the sectional area of a gas flow passage through which gas can pass is adjusted, the adjustment of the pressure of the gas flowing out of the spray hole is realized, the adjustment of the diameter of bubbles sprayed by the nozzle is realized, the occurrence position of cavitation can be adjusted, the filling content of the gas is adjusted, the gas hydrodynamic cavitation is controlled, the hydrodynamic cavitation effect of the gas is comprehensively improved, and the effect of controlling the wings to prevent and remove ice is achieved.
In the embodiment, the first gas generator and the second gas generator both adopt inert gas generators, so that more energy can be released compared with common hydrodynamic cavitation, and the deicing effect is better.
Although the embodiments of the present invention have been described with reference to the accompanying drawings, it is not intended to limit the scope of the present invention, and it should be understood by those skilled in the art that various modifications and variations can be made without inventive efforts by those skilled in the art based on the technical solution of the present invention.
Claims (4)
1. The wing is characterized by comprising a wing body, wherein a wrapping plate is arranged at the front edge of the wing body, the wrapping plate and an inner lining skin of the wing body form a hydrodynamic cavitation cavity, the hydrodynamic cavitation cavity can be filled with liquid, a plurality of nozzles are respectively arranged on the cavity walls on two sides of the hydrodynamic cavitation cavity, the nozzles on two sides are respectively connected with a gas supply mechanism, the gas supply mechanism can spray gas into the hydrodynamic cavitation cavity through the nozzles to form bubbles in the liquid filled in the hydrodynamic cavitation cavity, the hydrodynamic cavitation cavity is connected with an ultrasonic mechanism, and the ultrasonic mechanism is used for inducing the bubbles in the hydrodynamic cavitation cavity to generate cavitation;
the nozzle comprises a first nozzle part and a second nozzle part which are connected in an integrated manner, the first nozzle part and the second nozzle part are both of frustum-shaped structures, the inner spaces of the first nozzle part and the second nozzle part are communicated to form a gas flow passage, the end part with the smaller area of the first nozzle part is connected with the end part with the larger area of the second nozzle part, the end part with the larger area of the first nozzle part is provided with a plurality of spray holes for gas to flow into the hydraulic cavitation cavity, the end part with the larger area of the second nozzle part is connected with a gas supply mechanism, a floating ball is arranged in the first nozzle part and is elastically connected with the first nozzle part and used for controlling the area of the gas flow passage between the first nozzle; the floating ball is fixedly connected with one end of the spring, the other end of the spring is connected with the inner side surface of the end part with the larger area of the first nozzle part, and the floating ball is elastically connected with the first nozzle part through the spring; the end part of one side of the spring is fixedly connected with a connecting plate, the connecting plate is fixedly connected with one end of an adjusting bolt, and the adjusting bolt is in threaded connection with the end part with the larger area of the first nozzle part;
the gas supply mechanism comprises a gas generator, and the gas generator adopts an inert gas generator;
the gas generator is connected with the gas pump through a pipeline, and the gas pump is connected with the nozzle through a pipeline; a flow meter is arranged on a pipeline between the air pump and the nozzle and used for detecting the flow of the air in the pipeline;
the ultrasonic mechanism comprises a plurality of ultrasonic probes, and the ultrasonic probes are fixed on the outer side surface of the cavity wall of the hydrodynamic cavitation cavity and are positioned inside the wing body.
2. The wing for preventing and removing ice by utilizing ultrasonic hydrodynamic cavitation as claimed in claim 1, wherein a gas purification device is arranged on the pipeline between the gas pump and the nozzle, and the gas purification device is used for purifying the gas in the pipeline.
3. The wing for preventing and removing ice by utilizing ultrasonic hydrodynamic cavitation as claimed in claim 1, wherein the ultrasonic probe is connected with an ultrasonic generator through an ultrasonic controller, and the ultrasonic generator is connected with a power supply.
4. A flying device, characterized in that the wing using ultrasonic hydrodynamic cavitation to prevent ice according to any of claims 1 to 3 is used.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910708093.6A CN110450961B (en) | 2019-08-01 | 2019-08-01 | Wing and flying device for preventing and removing ice by utilizing ultrasonic hydrodynamic cavitation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910708093.6A CN110450961B (en) | 2019-08-01 | 2019-08-01 | Wing and flying device for preventing and removing ice by utilizing ultrasonic hydrodynamic cavitation |
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| CN110450961A CN110450961A (en) | 2019-11-15 |
| CN110450961B true CN110450961B (en) | 2021-01-22 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113931811B (en) * | 2021-10-28 | 2024-02-09 | 浙江大学包头工业技术研究院 | Device for deicing wind driven generator blade |
| CN116395140B (en) * | 2023-04-27 | 2023-12-12 | 成都流体动力创新中心 | Ice prevention and removal method based on ultrasonic cavitation principle |
| CN116176843B (en) * | 2023-04-27 | 2023-06-23 | 成都流体动力创新中心 | Aircraft deicing system based on ultrasonic cavitation |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4434045C2 (en) * | 1994-09-23 | 1996-08-29 | Daimler Benz Aerospace Ag | Device for de-icing aircraft wing leading edges |
| CN202449211U (en) * | 2011-12-27 | 2012-09-26 | 东南大学 | Novel anti-icing and de-icing device for airplane airfoil |
| CN203937843U (en) * | 2014-06-25 | 2014-11-12 | 哈尔滨对俄高端技术转移孵化中心 | hydrodynamic cavitation generator nozzle |
| CN104857904A (en) * | 2015-05-19 | 2015-08-26 | 金海能国际机电设备(北京)有限公司 | Cavitation reactor |
| CN106348502A (en) * | 2016-09-21 | 2017-01-25 | 江苏科技大学 | Water hammer impact wave pulsation system applied to ship ballast water treatment |
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