CN112158326A - Ventral fin type radiator suitable for aircraft - Google Patents
Ventral fin type radiator suitable for aircraft Download PDFInfo
- Publication number
- CN112158326A CN112158326A CN202010953329.5A CN202010953329A CN112158326A CN 112158326 A CN112158326 A CN 112158326A CN 202010953329 A CN202010953329 A CN 202010953329A CN 112158326 A CN112158326 A CN 112158326A
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- China
- Prior art keywords
- lubricating oil
- inlet
- outlet
- aircraft
- cover plate
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- 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.)
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- 239000010687 lubricating oil Substances 0.000 claims abstract description 127
- 230000017525 heat dissipation Effects 0.000 claims abstract description 26
- 239000003921 oil Substances 0.000 claims description 51
- 230000000694 effects Effects 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 2
- 239000000314 lubricant Substances 0.000 claims 13
- 239000002826 coolant Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 239000010913 used oil Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C7/00—Structures or fairings not otherwise provided for
-
- 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
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The invention belongs to an ventral fin type radiator suitable for an aircraft, and discloses an ventral fin type radiator suitable for an aircraft, which comprises a flow guide body, a mounting bracket and a radiating main body, wherein the front part and the rear part of the radiating main body are connected with the flow guide body, and the whole radiating main body is of an aircraft ventral fin structure and is connected with the aircraft main body through the mounting bracket; the heat dissipation main body comprises an upper cover plate, a lower cover plate, a heat dissipation fin, a lubricating oil inlet, a lubricating oil outlet and a lubricating oil channel, wherein the upper cover plate and the lower cover plate are respectively arranged on the upper side and the lower side of the heat dissipation fin, the lubricating oil inlet and the lubricating oil outlet penetrate through the upper cover plate and extend out of the mounting support, the lubricating oil inlet and the lubricating oil outlet are connected with the inlet and the outlet of the lubricating oil channel, and the lubricating oil channel bypasses inside the heat dissipation fin. The ventral fin type radiator does not occupy the internal space of the body and does not need a separate air inlet and exhaust pipeline, thereby saving the internal space of the body and reducing the structural weight; and the heat exchange power of the radiator is high, and the working reliability of the product is improved by adopting the dual-redundancy design of the main channel and the standby channel.
Description
Technical Field
The invention belongs to the technical field of aviation aircraft design, relates to an aircraft radiator structure, and particularly relates to an ventral fin type radiator suitable for an aircraft.
Background
One of the commonly used oil radiators for aircraft is an air-oil radiator, which uses air as a cooling medium to exchange heat with oil to cool hot oil in an oil system, so that the oil temperature is reduced to meet the requirement of recycling. The existing air-lubricating oil radiator on the aircraft is mostly installed in the fuselage as an independent component, and one or more air flows need to be introduced from the front end or a certain position of the aircraft to radiate the heat of the radiator, and the scheme has the following problems:
1. the size of the appearance structure is limited by the space in the machine;
2. an air inlet and outlet pipeline is separately designed to introduce the air outside the airplane, so that the occupied space is large, and the weight of the airplane is increased;
3. the air flow is limited due to the influence of factors such as airplane aerodynamics and the like.
Disclosure of Invention
In order to solve the problems, the invention provides the ventral fin type radiator suitable for the aircraft, wherein the ventral fin of the aircraft is simultaneously used as a lubricating oil radiator, and the outflow of the aircraft is directly used as a cooling medium to cool hot lubricating oil, so that the ventral fin type radiator suitable for the aircraft is formed.
The technical scheme of the invention is as follows:
the ventral fin type radiator comprises a flow guide body, a mounting bracket and a radiating main body, wherein the front part and the rear part of the radiating main body are connected with the flow guide body, and the whole radiating main body is of an aircraft ventral fin structure and is connected with the aircraft main body through the mounting bracket; the heat dissipation main body comprises an upper cover plate, a lower cover plate, a heat dissipation fin, a lubricating oil inlet, a lubricating oil outlet and a lubricating oil channel, wherein the upper cover plate and the lower cover plate are respectively arranged on the upper side and the lower side of the heat dissipation fin, the lubricating oil inlet and the lubricating oil outlet penetrate through the upper cover plate and extend out of the mounting support, the lubricating oil inlet and the lubricating oil outlet are connected with the inlet and the outlet of the lubricating oil channel, and the lubricating oil channel bypasses inside the heat dissipation fin.
Further, the radiating fin is composed of a plurality of sawtooth type fins. The heat conduction effect of the sawtooth-shaped fins is good.
Furthermore, the plurality of sawtooth-shaped fins are arranged at intervals up and down, and the transverse direction of the plurality of sawtooth-shaped fins is the same as the air inflow direction designed for the ventral fins of the aircraft. This structural design can make this ventral fin formula radiator can satisfy the air rectification demand of ventral fin, can also reduce the windage, improves the radiating efficiency.
Furthermore, the lubricating oil channel passes through the zigzag fins which are arranged at intervals up and down through a plurality of back-and-forth passing back and forth paths. This design can increase heat dissipation efficiency.
Furthermore, the lubricating oil inlet comprises a first lubricating oil inlet and a second lubricating oil inlet, the lubricating oil outlet comprises a first lubricating oil outlet and a second lubricating oil outlet, and the lubricating oil channel comprises a common lubricating oil channel and a standby lubricating oil channel.
Further, the first lubricating oil inlet is connected with the inlet end of the common lubricating oil channel, and the first lubricating oil outlet is connected with the outlet end of the common lubricating oil channel; the second lubricating oil inlet is connected with the inlet end of the standby lubricating oil channel, and the second lubricating oil outlet is connected with the outlet end of the standby lubricating oil channel; the common oil passage and the backup oil passage are not communicated with each other. The common oil passage is the main oil passage, but when the engine is stopped in the air, the temperature of the oil may be too low after heat dissipation, so that the oil may freeze, and the standby oil passage is used.
Further, the common oil passage and the spare oil passage are partially positioned close to each other. Therefore, when the standby lubricating oil channel is used, the heat of the standby lubricating oil channel can be transmitted to the common lubricating oil channel to help the lubricating oil of the common lubricating oil channel to be unfrozen, so that the common lubricating oil channel works again.
Further, an oil discharge port is arranged at the bottom of the lubricating oil channel. When the oil drain hole is needed to be detached, the oil drain hole can drain lubricating oil and then detach the oil drain hole.
The invention has the advantages that:
1. the internal space of the machine body is not occupied, and a separate air inlet and exhaust pipeline is not needed, so that the internal space of the machine body is saved, and the structural weight is reduced;
2. the heat radiator is not limited by the space in the heat radiator, and the area of the heat radiating main body part can be increased, so that the heat exchange power of the heat radiator is increased;
3. the air outside the machine is directly used as a cooling medium, the flow is large, the temperature is low, and the heat exchange power of the radiator can be increased;
4. and the dual-redundancy design of the main channel and the standby channel is adopted, so that the working reliability of the product is improved.
Drawings
FIG. 1 is an on-board footprint schematic of an ventral fin radiator of an embodiment of the present invention;
FIG. 2 is a schematic diagram of an embodiment of an ventral fin heat sink;
FIG. 3 is a schematic diagram of the operation of the oil cooling system of the embodiment of the present invention;
wherein: the radiator comprises a flow guide body 1, a mounting support 2, a heat dissipation main body 3, an upper cover plate 3-1, a lower cover plate 3-2, a heat dissipation plate 3-3, a first lubricating oil inlet 4, a second lubricating oil inlet 5, a first lubricating oil outlet 6, a second lubricating oil outlet 7, a common lubricating oil channel 8, a spare lubricating oil channel 9, a temperature control valve 10, a bypass channel 11, a pressure valve 12, a check valve 13 and a ventral fin type radiator 14.
Detailed Description
This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
The radiator is an ventral fin type radiator suitable for an aircraft, and comprises a flow guide body 1, a mounting bracket 2 and a radiating main body 3, wherein the front part and the rear part of the radiating main body 3 are connected with the flow guide body 1, the whole radiator is of an aircraft ventral fin structure and is connected with the aircraft main body through the mounting bracket 2; the heat dissipation main body 3 comprises an upper cover plate 3-1, a lower cover plate 3-2, heat dissipation fins 3-3, a lubricating oil inlet, a lubricating oil outlet and a lubricating oil channel, wherein the upper cover plate 3-1 and the lower cover plate 3-2 are respectively arranged on the upper side and the lower side of the heat dissipation fins 3-3, the lubricating oil inlet and the lubricating oil outlet penetrate through the upper cover plate 3-1 and extend out of the mounting support 2, the lubricating oil inlet and the lubricating oil outlet are connected with the inlet and the outlet of the lubricating oil channel, and the lubricating oil channel penetrates through the heat dissipation fins 3-3.
The heat radiating fins 3-3 are composed of a plurality of zigzag fins. The heat conduction effect of the sawtooth-shaped fins is good. The plurality of sawtooth-shaped fins are arranged at intervals up and down, and the transverse direction of the plurality of sawtooth-shaped fins is the same as the air inflow direction designed by the ventral fins of the aircraft. This structural design can make this ventral fin formula radiator can satisfy the air rectification demand of ventral fin, can also reduce the windage, improves the radiating efficiency. The lubricating oil channel passes through the zigzag fins which are arranged at intervals up and down through a plurality of back-and-forth passing back-and-forth paths. This design can increase heat dissipation efficiency.
The lubricating oil inlet comprises a first lubricating oil inlet 4 and a second lubricating oil inlet 5, the lubricating oil outlet comprises a first lubricating oil outlet 6 and a second lubricating oil outlet 7, and the lubricating oil channel comprises a common lubricating oil channel 8 and a standby lubricating oil channel 9.
The first lubricating oil inlet is connected with the inlet end of the common lubricating oil channel, and the first lubricating oil outlet is connected with the outlet end of the common lubricating oil channel; the second lubricating oil inlet is connected with the inlet end of the standby lubricating oil channel, and the second lubricating oil outlet is connected with the outlet end of the standby lubricating oil channel; the common oil passage and the backup oil passage are not communicated with each other. The common oil passage is the main oil passage, but when the engine is stopped in the air, the temperature of the oil may be too low after heat dissipation, so that the oil may freeze, and the standby oil passage is used.
The common oil passage and the spare oil passage are partially positioned close to each other. Therefore, when the standby lubricating oil channel is used, the heat of the standby lubricating oil channel can be transmitted to the common lubricating oil channel to help the lubricating oil of the common lubricating oil channel to be unfrozen, so that the common lubricating oil channel works again.
An oil discharge port is arranged at the bottom of the lubricating oil channel. When the oil drain hole is needed to be detached, the oil drain hole can drain lubricating oil and then detach the oil drain hole.
Another embodiment of the present invention is described below with reference to the drawings.
The technical scheme of the ventral fin type radiator is that an airplane ventral fin is simultaneously used as a lubricating oil radiator, and the structure function of the airplane ventral fin is combined with the lubricating oil radiating function. Fig. 1 is a schematic view of a mounting position of a ventral fin radiator on an aircraft, and fig. 2 is a schematic view of a structure of the ventral fin radiator.
The ventral fin radiator mainly comprises a radiating main body 3, a flow guide body 1 and a mounting bracket 2. The radiator uses the outflow of the aircraft at a lower temperature to cool the higher temperature oil. The lubricating oil flows into the hot side channel from the hot side inlet of the radiator, meanwhile, the cold air flows over the radiator, and the fluid media of the cold side and the hot side transfer heat through the fins in the radiating main body, thereby carrying out heat exchange.
The whole ventral fin type radiator is used as an airplane ventral fin, wherein the radiating main body 3 is a main radiating component of the ventral fin radiator and mainly comprises an upper cover plate 3-1, a lower cover plate 3-2 and sawtooth fins. The inside of the heat dissipation main body 3 is respectively provided with 4 process lubricating oil channels (namely, channels which are wound for four times back and forth, because the space of the ventral fin is limited, the heat dissipation efficiency is increased for more processes of a common channel as much as possible) and a standby lubricating oil cavity of 2 process lubricating oil channels, and the outside is provided with sawtooth type fins.
When the heat radiator is normally used, the main channel of the heat radiator works, low-temperature air flows between the upper cover plate and the lower cover plate, hot lubricating oil flows in the common lubricating oil channel 8, and heat is transferred to cold air flowing through the sawtooth-shaped fins; when the common oil passage 8 is blocked, the passage switching is performed by the parts such as the pressure valve 12 and the like installed on the airplane, the standby oil passage 9 is put into operation, and hot oil flows in the standby oil passage 9 to exchange heat with cold air. The heat exchange power of the standby lubricating oil channel 9 is lower than that of the common lubricating oil channel 8, and the functions of increasing the working redundancy of the radiator and improving the reliability are achieved: for example, when the aircraft is parked in the air, the temperature of the oil system is reduced, and the oil can be controlled by the on-board temperature control valve 10 and other parts to directly return to the oil tank without passing through the radiator. However, in a high-altitude and low-temperature environment outside the machine, the residual lubricating oil in the common lubricating oil channel 8 of the radiator may be frozen, so that the common lubricating oil channel 8 is blocked and loses working capacity. Once the engine is restarted successfully in the air, the spare oil passage 9 is enabled to continue to function as a radiator before the normal working capacity of the common oil passage 8 of the radiator is restored.
The schematic diagram of the radiator is shown in fig. 3, when the radiator normally works, the lubricating oil enters the common lubricating oil channel 8 through the temperature control valve 10 for heat radiation, and after the engine stops in the air, the temperature control valve 10 detects that the temperature of the lubricating oil is lower than a certain threshold value, the bypass channel 11 is communicated to directly convey the lubricating oil to the lubricating oil cavity. At this time, because the external air temperature is too low, the residual lubricating oil in the common lubricating oil channel 8 may be frozen to cause blocking, after the engine is restarted, the temperature control valve 10 is closed again, at this time, the common lubricating oil channel 8 is not communicated, the pressure valve 12 is opened after detecting the lubricating oil pressure with a certain threshold value, and the lubricating oil radiates heat through the spare lubricating oil channel 9.
Claims (8)
1. The ventral fin type radiator is characterized by comprising a flow guide body (1), a mounting bracket (2) and a heat dissipation main body (3), wherein the flow guide body (1) is connected with the heat dissipation main body (3) in front and at the back, the whole radiator is of an aircraft ventral fin structure and is connected with the aircraft main body through the mounting bracket (2); the heat dissipation main body (3) comprises an upper cover plate (3-1), a lower cover plate (3-2), heat dissipation fins (3-3), a lubricating oil inlet, a lubricating oil outlet and a lubricating oil channel, wherein the upper cover plate (3-1) and the lower cover plate (3-2) are respectively arranged on the upper side and the lower side of the heat dissipation fins (3-3), the lubricating oil inlet and the lubricating oil outlet penetrate through the upper cover plate (3-1) and extend out of the mounting support (2), the lubricating oil inlet and the lubricating oil outlet are connected with the inlet and the outlet of the lubricating oil channel, and the lubricating oil channel bypasses inside the heat dissipation fins (3-3).
2. Ventral fin radiator according to claim 1, characterised in that the cooling fins (3-3) consist of a plurality of zigzag-shaped fins. The heat conduction effect of the sawtooth-shaped fins is good.
3. The ventral fin type radiator for an aircraft according to claim 2, wherein the plurality of zigzag fins are arranged at intervals up and down, and the transverse direction of the plurality of zigzag fins is the same as the air inflow direction designed for ventral fins of the aircraft.
4. The ventral fin radiator according to claim 3, wherein the oil passage passes through a plurality of back and forth pass-and-forth return paths through the zigzag fins arranged at intervals up and down.
5. The ventral fin radiator according to claim 1, wherein the lubricant inlet comprises a first lubricant inlet (4) and a second lubricant inlet (5), the lubricant outlet comprises a first lubricant outlet (6) and a second lubricant outlet (7), and the lubricant passage comprises a common lubricant passage (8) and a spare lubricant passage (9).
6. The ventral fin radiator for an aircraft according to claim 5, wherein the first lubricant inlet is connected to an inlet end of the common lubricant passage, and the first lubricant outlet is connected to an outlet end of the common lubricant passage; the second lubricating oil inlet is connected with the inlet end of the standby lubricating oil channel, and the second lubricating oil outlet is connected with the outlet end of the standby lubricating oil channel; the common oil passage and the backup oil passage are not communicated with each other.
7. The ventral fin radiator of claim 6, wherein the common oil gallery and the spare oil gallery are partially located in close proximity.
8. The ventral fin radiator for an aircraft according to claim 1, wherein an oil drain is formed at the bottom of the lubricating oil channel. When the oil drain hole is needed to be detached, the oil drain hole can drain lubricating oil and then detach the oil drain hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010953329.5A CN112158326B (en) | 2020-09-11 | 2020-09-11 | Ventral fin type radiator suitable for aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010953329.5A CN112158326B (en) | 2020-09-11 | 2020-09-11 | Ventral fin type radiator suitable for aircraft |
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| Publication Number | Publication Date |
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| CN112158326A true CN112158326A (en) | 2021-01-01 |
| CN112158326B CN112158326B (en) | 2023-03-14 |
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| CN202010953329.5A Active CN112158326B (en) | 2020-09-11 | 2020-09-11 | Ventral fin type radiator suitable for aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610296A (en) * | 2020-12-17 | 2021-04-06 | 中国航空工业集团公司成都飞机设计研究所 | Lubricating oil cooling system |
| CN113382608A (en) * | 2021-06-09 | 2021-09-10 | 北京机电工程研究所 | Aircraft equipment cabin heat dissipation system and heat dissipation method thereof |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112610296A (en) * | 2020-12-17 | 2021-04-06 | 中国航空工业集团公司成都飞机设计研究所 | Lubricating oil cooling system |
| CN112610296B (en) * | 2020-12-17 | 2022-07-12 | 中国航空工业集团公司成都飞机设计研究所 | Lubricating oil cooling system |
| CN113382608A (en) * | 2021-06-09 | 2021-09-10 | 北京机电工程研究所 | Aircraft equipment cabin heat dissipation system and heat dissipation method thereof |
| CN113382608B (en) * | 2021-06-09 | 2022-11-08 | 北京机电工程研究所 | Aircraft equipment cabin heat dissipation system and heat dissipation method thereof |
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| Publication number | Publication date |
|---|---|
| CN112158326B (en) | 2023-03-14 |
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