CN110341981A - Wing cavitation deicer - Google Patents
Wing cavitation deicer Download PDFInfo
- Publication number
- CN110341981A CN110341981A CN201910670657.1A CN201910670657A CN110341981A CN 110341981 A CN110341981 A CN 110341981A CN 201910670657 A CN201910670657 A CN 201910670657A CN 110341981 A CN110341981 A CN 110341981A
- Authority
- CN
- China
- Prior art keywords
- nozzle
- cavitation
- wing
- handle
- cavity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B1/00—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means
- B05B1/34—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B12/00—Arrangements for controlling delivery; Arrangements for controlling the spray area
- B05B12/002—Manually-actuated controlling means, e.g. push buttons, levers or triggers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B9/00—Spraying apparatus for discharge of liquids or other fluent material, without essentially mixing with gas or vapour
- B05B9/03—Spraying apparatus for discharge of liquids or other fluent material, without essentially mixing with gas or vapour characterised by means for supplying liquid or other fluent material
- B05B9/04—Spraying apparatus for discharge of liquids or other fluent material, without essentially mixing with gas or vapour characterised by means for supplying liquid or other fluent material with pressurised or compressible container; with pump
- B05B9/0403—Spraying apparatus for discharge of liquids or other fluent material, without essentially mixing with gas or vapour characterised by means for supplying liquid or other fluent material with pressurised or compressible container; with pump with pumps for liquids or other fluent material
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/20—Ground installations for de-icing aircraft
- B64F5/23—Ground installations for de-icing aircraft by liquid application; Spraying installations therefor, e.g. fitted on vehicles
Abstract
A kind of wing cavitation deicer, including water inlet line, nozzle and handle, water inlet line one end connect water tank, and the other end connects the import of the cavity of handle inner, and nozzle is distributed on handle and is connected to the cavity of handle inner, and water pump is provided on water inlet line.The nozzle, including top nozzle and lower nozzle, top nozzle are connected on lower nozzle, form closed cavity between top nozzle bottom end and lower upper end of nozzle.Water pump is opened by the control switch at handle, water in water tank is pressed into nozzle, pass through fuel factor and mechanical effect brought by the cavitation effect that generates in nozzle, pass through the collision of water flow in the cavity, cavitation effect is generated, and is projected by lower nozzle, achievees the purpose that deicing by fuel factor caused by the crumbling and fall of cavitation bubble and mechanical effect, operator will be directed at the region to freeze in wing, and suitably distance is selected to carry out deicing.Device response is fast, high-efficient, safe and reliable, does not use deicing liquid, Environmental Safety.
Description
Technical field
The present invention relates to a kind of devices for aircraft wing ice-breaking.
Background technique
Aircraft icing refers to the phenomenon that ice sheet is assembled at the certain positions in airframe surface.Aircraft wing can cause after freezing
Resistance increases, drop in lift, and handling is deteriorated；Engine aspirating system icing can cause engine charge flow distortion, into
Gas channel block, engine performance deterioration；The meeting after being sucked by engine if wing or engine aspirating system icing fall off
The blade for damaging engine interior, causes mechanical damage；Aircraft sensors can make aircrew that can not obtain standard once freezing
True flight parameter causes the automatic control system maloperation of aircraft.Aircraft, which awing freezes, can seriously endanger the safety of aircraft
Flight.Therefore deicing must be carried out before taking off.
The most efficient method of aircraft deicing at present is to be removed using the deicing liquid of heat from top is close as closely as possible
The region of ice.So operator station rises to certain altitude in deicing vehicle hanging basket, using spray gun to airplane spray deicing
Liquid, aircraft will take off immediately after general deicing, otherwise will deicing again, such method efficiency is relatively low.
A kind of aircraft wing automatic deicer disclosed in CN107745816A, including the hot deicing of exterior skin, inside panel, gas
Component, electro-thermal deicing component, controller, icing detector and ice thickness detector.The more traditional wing deicing device of the device or
System has made larger change, first is that device increases icing detector on the exterior skin of wing and ice thickness detector, controller can
According to icing information automatic de-icing, thus mitigate the burden of crew, meanwhile, controller can also select to remove according to ice thickness information
Ice mode, starts electro-thermal deicing component operation to ice sheet, uses the hot heating component of gas to thick ice sheet.But the device is still adopted
With electro-thermal deicing, structure is complicated, at high cost." deicing system for aircraft " disclosed in CN102007037A is empty by heating
Gas, by being blown hot gas deicing to ice face, structure is complicated, at high cost.
Cavitation phenomenon is when pressure is brought down below saturated vapor pressure, and the gas dissolved in a fluid can release, together
When fluid vaporization and generate a large amount of bubbles, cavitation bubble during further being flowed with fluid, ambient pressure increase when, volume
It will sharply reduce until crumbling and fall, moment of crumbling and fall can generate high pressure and temperature.There are mainly three types of effect, that is, machines for cavitation phenomenon
Tool effect, fuel factor and chemical effect.The mechanical effect and fuel factor generated using cavitation phenomenon, the energy crumbled and fall using it and
The huge heat generated in vibrating effect and cavitation processes, the purpose of reaching deicing are feasible.
Summary of the invention
The present invention is provided and a kind of responds fast, high-efficient, environmentally friendly wing for deficiency existing for existing wing deicing technology
Cavitation deicer.
Wing cavitation deicer of the invention, using following technical scheme:
The device, including water inlet line, nozzle and handle, handle inner are provided with cavity, and cavity side has inlet,
Water inlet line one end connects water tank, and the other end connects the inlet of handle internal cavity, and nozzle is distributed on handle and and handle
Internal cavity is connected to, and is provided with water pump on water inlet line.
The control switch that control water pump starting or closed is provided on the handle.
Pressure gauge and thermometer are provided on the water inlet line.
The nozzle, including top nozzle and lower nozzle, top nozzle are connected on lower nozzle, on top nozzle bottom end and lower nozzle
Closed cavity is formed between end.By the collision of water flow in the cavity, cavitation effect is generated, and is projected by lower nozzle, is relied on
Fuel factor caused by the crumbling and fall of cavitation bubble and mechanical effect achieve the purpose that deicing.
The top nozzle and lower nozzle junction are equipped with seal washer.
The outer diameter D of the top nozzle and lower nozzle is up to 20mm.The distance L of the top nozzle bottom end and lower upper end of nozzle
(chamber is long) is 10~15mm.
The injection diameter of the lower nozzle is less than the injection diameter of top nozzle.The spray orifice maximum gauge of the top nozzle is
3mm, the spray orifice maximum gauge of lower nozzle are 2mm.
In actual use, water pump is opened by the control switch at handle, the water in water tank is pressed into nozzle, is passed through
Fuel factor brought by the cavitation effect generated in nozzle and mechanical effect, achieve the purpose that deicing, and operator will be directed at machine
The region to freeze in the wing selects suitable distance, carries out deicing.
The present invention carries out wing deicing by the cavitation effect of water, and response is fast, high-efficient, safe and reliable, does not use deicing
Liquid, Environmental Safety.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of wing cavitation deicer of the present invention.
Fig. 2 is the cross-sectional view of nozzle in the present invention.
Fig. 3 is the use state diagram of wing cavitation deicer of the present invention.
In figure: 1. water inlet lines, 2. water tanks, 3. water pumps, 4. control switches, 5. nozzles, 6. top nozzles, 7. seal washers,
8. lower nozzle, 9. self-excitation cavitys, 10. handles, 11. wings.
Specific embodiment
Wing cavitation deicer of the invention, as shown in Figure 1, including water inlet line 1, water pump 3 and nozzle 5.Water inlet pipe
1 one end of road connects water tank 2, and the other end connects handle 10 (referring to Fig. 3), and nozzle 4 is distributed on handle 10.It is provided in handle 10
Cavity, cavity import are connect with water inlet line 1, and each nozzle being distributed on handle 10 is connected to the cavity.Nozzle 5 arranges
One row, totally 4, to increase effective projected area.Water pump 3 is connected on water inlet line 1, between water pump 3 and water tank 1 and water pump 3
Be provided with pressure gauge and thermometer on two-stage water pipeline between nozzle 5, for measure the temperature in operational process and
Pressure.Water pump 3 is opened or closed by the control of control switch 4, and control switch 4 is arranged on handle 10.
Nozzle 4 uses self-excited nozzle, and structure is as shown in Fig. 2, include top nozzle 6 and lower nozzle 8, top nozzle 6 and lower spray
Mouth 8 is connected through a screw thread, and junction is equipped with seal washer 7, formed between 6 bottom end of top nozzle and lower 8 upper end of nozzle it is closed from
Swashing cavity 9, the spray orifice of nozzle and the cross section of cavity 9 are circle, by collision of the water flow in cavity 9, cavitation effect is generated,
Water temperature increases, and pressure increases, and is projected by lower nozzle 8, reaches by fuel factor caused by the crumbling and fall of cavitation bubble and mechanical effect
To the purpose of deicing.By many experiments, to reach optimum efficiency, the outer diameter D of top nozzle 6 and lower nozzle 8 is up to 20mm, on
The distance L (chamber is long) of 6 bottom end of nozzle and lower 8 upper end of nozzle is 10~15mm.The spray orifice a maximum gauge of top nozzle 6 is 3mm, under
The spray orifice b maximum gauge of nozzle 8 is 2mm.
In actual use, as shown in figure 3, water pump 3 is opened by the control switch 4 at handle 10, by the hydraulic pressure in water tank 2
Enter into nozzle 5, by fuel factor and mechanical effect brought by the cavitation effect that generates in nozzle 5, achieve the purpose that deicing,
Operator will be directed at the region to freeze in wing, select suitable distance, carry out deicing, be detected by pressure gauge and thermometer
The temperature and pressure of water should be stopped using when displays temperature and too high or too low pressure in measurement operational process, to equipment into
Row maintenance.After the completion of deicing, aircraft should take off at once, prevent from freezing again.
Claims (10)
1. a kind of wing cavitation deicer, it is characterized in that: including water inlet line, nozzle and handle, handle inner setting is free
Chamber, cavity side have inlet, and water inlet line one end connects water tank, and the other end connects the inlet of handle internal cavity, spray
Mouth is distributed on handle and is connected to the cavity of handle inner, and water pump is provided on water inlet line.
2. wing cavitation deicer according to claim 1 opens it is characterized in that: being provided with control water pump on the handle
Control switch that is dynamic or closing.
3. wing cavitation deicer according to claim 1, it is characterized in that: being provided with pressure gauge on the water inlet line
And thermometer.
4. wing cavitation deicer according to claim 1, it is characterized in that: the nozzle, including top nozzle and lower spray
Mouth, top nozzle are connected on lower nozzle, form closed cavity between top nozzle bottom end and lower upper end of nozzle.
5. wing cavitation deicer according to claim 4, it is characterized in that: the top nozzle is set with lower nozzle junction
There is seal washer.
6. wing cavitation deicer according to claim 4, it is characterized in that: the outer diameter D of the top nozzle and lower nozzle
It is up to 20mm.
7. wing cavitation deicer according to claim 4, it is characterized in that: the top nozzle bottom end and lower upper end of nozzle
Distance L be 10~15mm.
8. wing cavitation deicer according to claim 4, it is characterized in that: the injection diameter of the lower nozzle is less than upper
The injection diameter of nozzle.
9. according to the described in any item wing cavitation deicers of claim 4-8, it is characterized in that: the inner hole of the top nozzle is most
Major diameter is 3mm.
10. according to the described in any item wing cavitation deicers of claim 4-8, it is characterized in that: the inner hole of the lower nozzle
Maximum gauge is 2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910670657.1A CN110341981A (en) | 2019-07-24 | 2019-07-24 | Wing cavitation deicer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910670657.1A CN110341981A (en) | 2019-07-24 | 2019-07-24 | Wing cavitation deicer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110341981A true CN110341981A (en) | 2019-10-18 |
Family
ID=68180147
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910670657.1A Pending CN110341981A (en) | 2019-07-24 | 2019-07-24 | Wing cavitation deicer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110341981A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4434045A1 (en) * | 1994-09-23 | 1996-03-28 | Daimler Benz Aerospace Ag | Deicing arrangement for leading edges of aircraft wings |
| 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 |
| CN104153274A (en) * | 2014-08-25 | 2014-11-19 | 云南省交通规划设计研究院 | Ultrasonic anti-icing and ice-removing complete device used for highway pavement |
| 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 |
-
2019
- 2019-07-24 CN CN201910670657.1A patent/CN110341981A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4434045A1 (en) * | 1994-09-23 | 1996-03-28 | Daimler Benz Aerospace Ag | Deicing arrangement for leading edges of aircraft wings |
| 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 |
| CN104153274A (en) * | 2014-08-25 | 2014-11-19 | 云南省交通规划设计研究院 | Ultrasonic anti-icing and ice-removing complete device used for highway pavement |
| 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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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20191018 |
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| WD01 | Invention patent application deemed withdrawn after publication |