CN112265641A - Anti-freezing and deicing system for airplane - Google Patents
Anti-freezing and deicing system for airplane Download PDFInfo
- Publication number
- CN112265641A CN112265641A CN202011288856.5A CN202011288856A CN112265641A CN 112265641 A CN112265641 A CN 112265641A CN 202011288856 A CN202011288856 A CN 202011288856A CN 112265641 A CN112265641 A CN 112265641A
- Authority
- CN
- China
- Prior art keywords
- pipe
- silencer
- aluminum pipe
- deicing system
- airplane
- 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
- 238000007710 freezing Methods 0.000 title abstract description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 39
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 39
- 230000003584 silencer Effects 0.000 claims abstract description 27
- 208000001034 Frostbite Diseases 0.000 claims 1
- 238000005265 energy consumption Methods 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 24
- 239000003921 oil Substances 0.000 description 11
- 239000002828 fuel tank Substances 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000002918 waste heat Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- 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
- B64D15/04—Hot gas application
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
- B64D33/06—Silencing exhaust or propulsion jets
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Exhaust Silencers (AREA)
Abstract
The invention discloses an anti-freezing and deicing system for an airplane, and aims to provide an anti-freezing and deicing system for an airplane, which is relatively simple in structure, light in weight and low in energy consumption. The exhaust gas exhaust device comprises an engine cylinder, an exhaust gas discharge pipe, a silencer, an aluminum pipe and an oil tank, wherein one end of the exhaust gas discharge pipe is connected with the engine cylinder, the other end of the exhaust gas discharge pipe is connected with the silencer, one end of the aluminum pipe is connected with a heat exhaust pipe of the silencer, the other end of the aluminum pipe is coiled around the oil tank, a plurality of air outlet holes are formed in the aluminum pipe coiled on the oil tank, and an air outlet is formed in the tail end of the aluminum pipe. The invention is applied to the technical field of aerospace.
Description
Technical Field
The invention relates to an airplane deicing system, in particular to an airplane anti-freezing deicing system.
Background
When an airplane flies, icing phenomenon often occurs at some parts due to the action of the airflow speed, wherein the icing phenomenon is most common at the front edges of fuel oil in a fuel tank arranged in an airplane wing, a tail wing, a windshield engine, an air inlet and the like. Icing not only increases the weight of the airplane, but also destroys the aerodynamic appearance of the surface of the airplane, changes a turbulent flow field, destroys aerodynamic performance, causes the maximum lift force of the airplane to be reduced, the flight resistance to be increased, the operating performance to be reduced and the stability to be reduced, and causes great threat to flight safety, and flight accidents caused by icing are frequent, and severe icing can even lead to the death of the airplane.
The technology of aircraft anti-icing and de-icing has long been an important research topic for aircraft system design. At present, systems such as thermal deicing, mechanical deicing, pneumatic belt deicing and the like are commonly used. Although the systems are mature in development, use and maintenance, the systems are still insufficient in energy consumption, weight and reliability, for example, the common hot gas anti-icing system has a complex structure, high energy consumption and heavy weight; the mechanical deicing system is a deicing device which removes ice on the surface by the action of mechanical force; the pneumatic belt deicing system is characterized in that compressed air is filled into the expansion pipe to expand the expansion pipe, so that a surface ice layer is broken and falls off to achieve the aim of deicing. Therefore, it is desirable to design a deicing system that is relatively simple in construction, light in weight, and consumes little energy.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide an aircraft anti-freezing and deicing system with relatively simple structure, light weight and low energy consumption.
The technical scheme adopted by the invention is as follows: the exhaust gas exhaust device comprises an engine cylinder, an exhaust gas discharge pipe, a silencer, an aluminum pipe and an oil tank, wherein one end of the exhaust gas discharge pipe is connected with the engine cylinder, the other end of the exhaust gas discharge pipe is connected with the silencer, one end of the aluminum pipe is connected with a heat exhaust pipe of the silencer, the other end of the aluminum pipe is coiled around the oil tank, a plurality of air outlet holes are formed in the aluminum pipe coiled on the oil tank, and an air outlet is formed in the tail end of the aluminum pipe.
Furthermore, an airplane firewall is further installed at the heat exhaust pipe of the silencer.
Furthermore, an air inlet valve communicated with the heat exhaust pipe of the silencer and an air inlet valve control switch connected with the air inlet valve are mounted on the fireproof wall of the airplane.
Further, an air inlet pipe is arranged on the silencer and communicated with the silencer.
Further, a baffle is arranged at the front end of the outer part of the silencer.
Further, the aluminum pipe is equipped with the lateral conduit, the lateral conduit is installed in driver's cabin and passenger cabin, and the lateral conduit that is located driver's cabin and passenger cabin is equipped with a plurality of gas outlet.
The invention has the beneficial effects that: because the invention comprises an engine cylinder, an exhaust gas discharge pipe, a silencer, an aluminum pipe and an oil tank, wherein one end of the exhaust gas discharge pipe is connected with the engine cylinder, the other end of the exhaust gas discharge pipe is connected with the silencer, one end of the aluminum pipe is connected with a heat exhaust pipe of the silencer, the other end of the aluminum pipe is coiled around the oil tank, a plurality of air outlet holes are arranged on the aluminum pipe coiled on the oil tank, and the tail end of the aluminum pipe is provided with an air outlet, when an airplane is in a starting or flying state, the exhaust gas is discharged from the engine cylinder and enters the silencer through the exhaust gas discharge pipe, the silencer is thermally transmitted to the periphery due to the structure of the silencer, and at the moment, hot gas is conveyed to pass through the air inlet valve control switch and the aluminum pipe under the action of the baffle plate and air blown from the outside through the air inlet pipe, when the aluminum pipe reaches the air outlet holes of the aluminum pipes around the oil tank, a part of hot air flows out of the air outlet holes, a part of hot air continues to flow along the interior of the aluminum pipes, so that the effect that the periphery of the oil tank can be heated is achieved, and finally the hot air flows out of the air outlet holes, so that an open type circulating system is formed and can work continuously. When the oil tank is not required to be heated, the air inlet valve control switch is pulled down, so that hot air can not flow into the aluminum pipe, and the aluminum pipe has the advantages of simple structure, light weight and no power consumption.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Detailed Description
As shown in fig. 1, in the present embodiment, the present invention comprises an engine cylinder, an exhaust gas discharge pipe 1, a muffler 2, an aluminum pipe 3 and a fuel tank 4, wherein one end of the exhaust gas discharge pipe 1 is connected with the engine cylinder, the other end of the exhaust gas discharge pipe 1 is connected with the muffler 2, one end of the aluminum pipe 3 is connected with a heat exhaust pipe 5 of the muffler 2, the other end of the aluminum pipe 3 is coiled around the fuel tank 4, a plurality of air outlet holes 6 are arranged on the aluminum pipe 3 coiled on the fuel tank 4, and an exhaust port 7 is arranged at the tail end of the aluminum pipe 3, in the design, the exhaust gas discharge pipe 1 is used for connecting waste heat from the engine cylinder and conveying the waste heat into the muffler 2; the muffler 2 is for reducing the temperature and pressure of the exhaust gas discharged from the exhaust gas discharge pipe 1 to reduce noise and eliminate flames and sparks in the exhaust gas; the aluminum pipe has the advantages of light weight and good hot gas conveying and exhausting; the fuel tank is an inherent fuel supply system of the aircraft and equipment needing anti-icing.
In this embodiment, an airplane firewall 8 is further installed at the heat exhaust pipe 5 of the muffler 2, and the airplane firewall 8 is used for sound insulation and heat insulation.
In this embodiment, an air inlet valve communicated with the heat exhaust pipe 5 of the muffler 2 and an air inlet valve control switch 9 connected with the air inlet valve are installed on the firewall 8 of the aircraft, and the air inlet valve control switch 9 is used for controlling the inlet or the closing of hot air.
In this embodiment, an air inlet pipe 10 is disposed on the muffler 2, the air inlet pipe 10 is communicated with the muffler 2, and the air inlet pipe 10 is used for receiving external atmosphere to cool heat emitted from the muffler 2.
In this embodiment, the outside front end of silencer 2 is provided with baffle 11, baffle 11 is used for collecting the steam that gives off from the silencer and blocks the wind and make it form wind pressure and carry steam and cooling.
In the embodiment, the aluminum pipe 3 is provided with branch pipes, the branch pipes are arranged in a cab and a passenger cabin, and the branch pipes in the cab and the passenger cabin are provided with a plurality of air outlets.
In this embodiment, the working process of the present invention is as follows: when the aircraft is in a starting or flying state, exhaust gas is discharged from an engine cylinder through the exhaust gas exhaust pipe 1 into the muffler 2, and then the exhaust gas is discharged from another exhaust gas exhaust pipe 12; because the muffler 2 is structured to transfer heat to the periphery, at this time, under the action of the baffle plate 11 and external air blown in from the air inlet pipe 10, hot air is conveyed to pass through the air inlet valve control switch 9 and the aluminum pipe 3, when the hot air reaches the air outlet holes 6 of the aluminum pipe around the oil tank, a part of the hot air flows out from the air outlet holes 6, a part of the hot air continues to flow along the inside of the aluminum pipe 3, when the air outlet holes 6 exist, a part of the hot air is always discharged, so that the heating effect on the periphery of the oil tank 4 can be achieved, and finally, the residual hot air flows out from the air outlet 7, so that an open type circulating system is formed, the continuous work is realized, and when the air inlet valve control switch 9 is pulled down, the hot air is closed to flow to the aluminum pipe 3.
The invention is applied to the technical field of aerospace.
While the embodiments of the present invention have been described in terms of practical embodiments, they are not to be construed as limiting the meaning of the present invention, and modifications of the embodiments and combinations with other embodiments will be apparent to those skilled in the art in light of the present description.
Claims (6)
1. An aircraft deicing system that prevents frostbite characterized in that: it includes engine cylinder, exhaust emission pipe (1), silencer (2), aluminum pipe (3) and oil tank (4), the one end of exhaust emission pipe (1) with engine cylinder is connected, the other end of exhaust emission pipe (1) with silencer (2) are connected, the one end of aluminum pipe (3) with heat exhaust pipe (5) of silencer (2) are connected, the other end of aluminum pipe (3) is coiled around oil tank (4), and is coiled on oil tank (4) be provided with a plurality of venthole (6) on aluminum pipe (3), just the end of aluminum pipe (3) is provided with gas vent (7).
2. An aircraft deicing system as set forth in claim 1, wherein: and an airplane firewall (8) is also installed at the exhaust gas exhaust (5) of the silencer (2).
3. An aircraft deicing system as set forth in claim 2, wherein: and an air inlet valve communicated with the heat exhaust pipe (5) of the silencer (2) and an air inlet valve control switch (9) connected with the air inlet valve are arranged on the airplane firewall (8).
4. An aircraft deicing system as set forth in claim 1, wherein: an air inlet pipe (10) is arranged on the silencer (2), and the air inlet pipe (10) is communicated with the silencer (2).
5. An aircraft deicing system as set forth in claim 1, wherein: the front end of the exterior of the silencer (2) is provided with a baffle (11).
6. An aircraft deicing system as set forth in claim 1, wherein: the aluminum pipe (3) is provided with branch pipelines, the branch pipelines are installed in the cab and the passenger cabin, and the branch pipelines in the cab and the passenger cabin are provided with a plurality of air outlets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011288856.5A CN112265641A (en) | 2020-11-17 | 2020-11-17 | Anti-freezing and deicing system for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011288856.5A CN112265641A (en) | 2020-11-17 | 2020-11-17 | Anti-freezing and deicing system for airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112265641A true CN112265641A (en) | 2021-01-26 |
Family
ID=74339208
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011288856.5A Pending CN112265641A (en) | 2020-11-17 | 2020-11-17 | Anti-freezing and deicing system for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112265641A (en) |
-
2020
- 2020-11-17 CN CN202011288856.5A patent/CN112265641A/en active Pending
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