CN112610296B - Lubricating oil cooling system - Google Patents
Lubricating oil cooling system Download PDFInfo
- Publication number
- CN112610296B CN112610296B CN202011496453.XA CN202011496453A CN112610296B CN 112610296 B CN112610296 B CN 112610296B CN 202011496453 A CN202011496453 A CN 202011496453A CN 112610296 B CN112610296 B CN 112610296B
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- Prior art keywords
- lubricating oil
- heat dissipation
- oil
- flow
- radiator
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
- F01M5/00—Heating, cooling, or controlling temperature of lubricant; Lubrication means facilitating engine starting
- F01M5/002—Cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
- F01M5/00—Heating, cooling, or controlling temperature of lubricant; Lubrication means facilitating engine starting
- F01M5/005—Controlling temperature of lubricant
- F01M5/007—Thermostatic control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
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- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The invention belongs to the technical field of lubricating oil cooling and heat dissipation, and discloses a lubricating oil heat dissipation system.A lubricating oil flow channel is divided into two parts by fins between an upper cover plate and a lower cover plate, and then a heat radiator is divided into six lubricating oil heat dissipation cavities by two partition plates, so that the whole heat dissipation main body is finally formed together and is simultaneously used as an airplane ventral fin structure, and the occupied space and the weight of the heat radiator are reduced under the same heat dissipation power; the six lubricating oil radiating cavities are internally provided with the sawtooth fins, so that common lubricating oil cavities of four flow lubricating oil channels and standby lubricating oil cavities of two flow lubricating oil channels are formed respectively, and the dual-redundancy design greatly improves the working reliability of a product; the lubricating oil heat dissipation cavity and the S-shaped lubricating oil flow channel in the process are designed, so that the structural weight is reduced, and meanwhile, the air outside the machine is fully utilized as a cooling medium, and the heat dissipation power of the radiator is improved.
Description
Technical Field
The invention belongs to the technical field of cooling and heat dissipation of lubricating oil, and particularly relates to a lubricating oil heat dissipation system.
Background
The air-lubricating oil radiator on the aircraft utilizes air as a cooling medium to exchange heat with lubricating oil so as to cool hot lubricating oil in a lubricating oil system, and the temperature of the lubricating oil is reduced so as to meet the requirement of recycling. The existing lubricating oil transmission design method of the air-lubricating oil radiator is mostly designed with a single lubricating oil radiating cavity and has no redundancy design, so that 1) the appearance structure size occupies large space, but cooling media are not fully utilized, and the radiating efficiency is poor; 2) when the engine works, residues can appear in lubricating oil, or the oil inlet of the lubricating oil heat dissipation cavity of the aircraft in a low-temperature environment is frozen, and the phenomena often cause the radiator to work normally.
Disclosure of Invention
The invention provides a multi-flow lubricating oil heat dissipation cavity and an S-shaped lubricating oil flow channel design, and the multi-flow lubricating oil heat dissipation cavity and the S-shaped lubricating oil flow channel are divided into a common lubricating oil cavity with four flow lubricating oil flow channels and a standby lubricating oil cavity with two flow lubricating oil flow channels, so that a high-safety lubricating oil transmission method suitable for an aircraft is formed, and the multi-flow lubricating oil heat dissipation cavity and the S-shaped lubricating oil flow channel design have great innovation significance and engineering practical value.
The technical scheme of the invention is as follows:
an oil heat dissipation system, comprising: a first heat dissipation channel and a second heat dissipation channel;
the first heat dissipation channel is provided with a first oil inlet and a first oil outlet; the first oil inlet is connected with an engine lubricating oil outlet through a pipeline; the first oil outlet is connected with an oil inlet of a lubricating oil tank through a pipeline;
the second heat dissipation channel is provided with a second oil inlet and a second oil outlet, and the second oil outlet is communicated with the first oil outlet; the second oil inlet is communicated with the first oil inlet.
Further, the system further comprises: a one-way valve;
the one-way valve is arranged at the second oil outlet; the check valve is used for preventing the lubricating oil from the first oil outlet from flowing back to the second heat dissipation channel.
Further, the system further comprises: a pressure valve;
the pressure valve is arranged at the second oil inlet; the pressure valve is used for opening when the first heat dissipation channel is blocked, so that lubricating oil from the engine lubricating oil outlet can enter the second heat dissipation channel for heat dissipation.
Further, the system further comprises: a temperature control valve; the temperature control valve is respectively connected with an engine lubricating oil outlet and a lubricating oil tank oil inlet through pipelines; the temperature control valve is used for being opened when the temperature of the fuel is lower than a set temperature value, so that the lubricating oil from the lubricating oil outlet of the engine directly flows back to the lubricating oil tank.
Further, the system further comprises: the first heat dissipation channel and the second heat dissipation channel are integrated in the radiator;
the radiator is equally divided into a left part and a right part by fins; the left half part of the radiator is divided into the following parts from top to bottom: a first constant flow, a second constant flow and a third constant flow which are communicated in sequence; the right half part of the radiator is divided into the following parts from top to bottom in equal parts: a first standby flow, a second standby flow and a fourth normal flow;
the first standby flow is communicated with the second standby flow, and the fourth constant flow is communicated with the third constant flow;
the first common flow path is communicated with the first oil inlet, and the fourth common flow path is communicated with the first oil outlet;
the first standby flow is communicated with a second oil inlet; and the second standby flow is communicated with the second oil outlet.
Further, the system further comprises: each flow is internally provided with zigzag fins which are oppositely inserted; the lubricating oil flows in an S shape in the gaps between the opposite inserted zigzag fins to increase the heat dissipation area. The fins are made of aluminum materials with high heat-conducting performance.
Further, the radiator is arranged on the belly of the fuselage and forms a whole with the belly fin of the fuselage; ram air flows across the left and right surfaces of the radiator to cool oil within the radiator.
Further, all be provided with in first heat dissipation channel and the second heat dissipation channel and put the glib talker, put the glib talker and be used for discharging the lubricating oil in the heat dissipation channel when maintaining.
Compared with the prior art, the lubricating oil transmission scheme with high safety mainly has the beneficial effects in the following aspects:
a) the lubricating oil flow channel is divided into two parts by the fins between the upper cover plate and the lower cover plate, and then the radiator is divided into six lubricating oil radiating cavities by the two partition plates, so that the whole radiating main body is finally formed together and is simultaneously used as an airplane ventral fin structure, and the occupied space and the weight of the radiator are reduced under the same radiating power;
b) the six lubricating oil radiating cavities are internally provided with the sawtooth fins, so that common lubricating oil cavities of four flow lubricating oil channels and standby lubricating oil cavities of two flow lubricating oil channels are formed respectively, and the dual-redundancy design greatly improves the working reliability of a product;
c) the design of the multi-flow lubricating oil heat dissipation cavity and the S-shaped lubricating oil flow channel not only reduces the structural weight, but also fully utilizes the air outside the machine as a cooling medium to improve the heat dissipation power of the radiator.
Drawings
FIG. 1 is a schematic block diagram of a lubricant cooling system;
fig. 2 is a schematic view of a heat sink.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings, and all other embodiments obtained by those skilled in the art without any creative work belong to the protection scope of the present invention.
As shown in fig. 1, the lubricating oil heat dissipation system is composed of a radiator body, a temperature control valve, a pressure valve, a check valve and the like, which are connected with each other through a lubricating oil pipeline and used as a lubricating oil heat dissipation and circulation device between an engine and a lubricating oil tank.
As shown in fig. 2, the heat dissipating body is composed of upper and lower cover plates, a partition plate and a zigzag fin. The radiator takes outside ram air as a cooling medium to cool engine lubricating oil, and the temperature of the engine lubricating oil is ensured to be within a normal working range. The temperature control valve controls whether the radiator body needs to be in a working mode or not by sensing the incoming flow temperature of the lubricating oil; the pressure valve senses the pressure change of an oil inlet of the common lubricating oil cavity and controls the working mode of the standby lubricating oil cavity, so that the safety and the reliability of the transmission and the heat dissipation of the lubricating oil are improved.
The inside of the lubricating oil heat dissipation cavity is respectively provided with a common lubricating oil cavity with four flow lubricating oil flow passages and a standby lubricating oil cavity with two flow lubricating oil flow passages by sawtooth fins. In the flow of the common lubricating oil cavity 1-3, the lubricating oil and the air form a reverse cross flow mode, and in the flow of 4, the lubricating oil and the air form a single-flow cross flow mode. In the flow of the standby lubricating oil cavity 1-2, the lubricating oil and air form a reverse cross flow mode (the same as the flow of the common lubricating oil cavity 1-2).
When the oil cooling device is normally used, a common oil cavity works, high-temperature lubricating oil flows in fins, low-temperature air flows between fins of an upper cover plate and fins of a lower cover plate, the lubricating oil transfers heat to cold air flowing through the fins of the upper cover plate through the upper cover plate in 1-3 processes, and the lubricating oil transfers heat to the cold air flowing through the fins of the lower cover plate through the lower cover plate in 4 processes. When the standby lubricating oil cavity works, high-temperature lubricating oil flows in the fins, low-temperature air flows on the surface of the lower cover plate, and the lubricating oil transfers heat to cold air flowing through the fins of the lower cover plate through the lower cover plate.
Due to the space distribution relation, the standby lubricating oil cavity has lower heat dissipation power than the common lubricating oil cavity, but the standby lubricating oil cavity enables the lubricating oil transmission to be changed into a dual-redundancy transmission heat dissipation design, and the safety of the lubricating oil transmission is greatly improved. For example, when the temperature of the aircraft lubricating oil system is lower than a set value, the temperature control valve can control the lubricating oil from the engine to directly flow to the lubricating oil tank without passing through a radiator, when the engine is in a normal working state, the temperature of the engine lubricating oil rises, the temperature control valve starts to be closed, the temperature control valve is completely closed until a certain set temperature value is reached, the common lubricating oil cavity works, and the spare lubricating oil cavity does not work. However, under high altitude and low temperature environment outside the engine, the residual lubricating oil in the main channel of the radiator may be frozen, or when the oil inlet of the common lubricating oil cavity is blocked due to the residue in the lubricating oil, the engine lubricating oil can flow to the standby lubricating oil cavity through the pressure valve, and at the moment, the standby channel continues to play the role of the radiator, so that the temperature of the lubricating oil from the engine end can be temporarily reduced in the emergency situation.
Claims (7)
1. A lubricating oil cooling system is characterized in that: the system comprises: a first heat dissipation channel and a second heat dissipation channel;
the first heat dissipation channel is provided with a first oil inlet and a first oil outlet; the first oil inlet is connected with an engine lubricating oil outlet through a pipeline; the first oil outlet is connected with an oil inlet of a lubricating oil tank through a pipeline;
the second heat dissipation channel is provided with a second oil inlet and a second oil outlet, and the second oil outlet is communicated with the first oil outlet; the second oil inlet is communicated with the first oil inlet;
the first heat dissipation channel and the second heat dissipation channel are integrated in the radiator;
the radiator is divided into a left part and a right part by fins; the left half part of the radiator is divided into the following parts from top to bottom: a first constant flow, a second constant flow and a third constant flow which are communicated in sequence; the right half part of the radiator is divided into the following parts from top to bottom: a first standby flow, a second standby flow and a fourth normal flow;
the first standby flow is communicated with the second standby flow, and the fourth constant flow is communicated with the third constant flow;
the first common flow path is communicated with the first oil inlet, and the fourth common flow path is communicated with the first oil outlet;
the first standby flow is communicated with a second oil inlet; and the second standby flow is communicated with the second oil outlet.
2. The oil heat dissipation system of claim 1, wherein: the system further comprises: a one-way valve;
the one-way valve is arranged at the second oil outlet; the check valve is used for preventing the lubricating oil from the first oil outlet from flowing back to the second heat dissipation channel.
3. The oil heat dissipation system of claim 1, wherein: the system further comprises: a pressure valve;
the pressure valve is arranged at the second oil inlet; the pressure valve is used for opening when the first heat dissipation channel is blocked, so that lubricating oil from the engine lubricating oil outlet can enter the second heat dissipation channel for heat dissipation.
4. The oil heat dissipation system of claim 1, wherein: the system further comprises: a temperature control valve; the temperature control valve is respectively connected with an engine lubricating oil outlet and a lubricating oil tank oil inlet through pipelines; the temperature control valve is used for being opened when the temperature of the fuel is lower than a set temperature value, so that the lubricating oil from the lubricating oil outlet of the engine directly flows back to the lubricating oil tank.
5. The oil heat dissipation system of claim 1, wherein: the system further comprises: each flow is internally provided with zigzag fins which are oppositely inserted; the lubricating oil flows in an S shape in the gaps between the opposite inserted zigzag fins to increase the heat dissipation area.
6. The oil heat dissipation system of claim 1, wherein: the radiator is arranged at the belly of the fuselage and forms a whole with the belly fin of the fuselage; ram air flows across the left and right surfaces of the radiator to cool the oil within the radiator.
7. The oil heat dissipation system of claim 1, wherein: and oil discharging nozzles are arranged in the first heat dissipation channel and the second heat dissipation channel and used for discharging lubricating oil in the heat dissipation channels during maintenance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011496453.XA CN112610296B (en) | 2020-12-17 | 2020-12-17 | Lubricating oil cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011496453.XA CN112610296B (en) | 2020-12-17 | 2020-12-17 | Lubricating oil cooling system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112610296A CN112610296A (en) | 2021-04-06 |
| CN112610296B true CN112610296B (en) | 2022-07-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011496453.XA Active CN112610296B (en) | 2020-12-17 | 2020-12-17 | Lubricating oil cooling system |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2044916A (en) * | 1979-03-08 | 1980-10-22 | Daimler Benz Ag | A heat exchange device for vehicles |
| DE3714230A1 (en) * | 1987-04-29 | 1988-11-10 | Kloeckner Humboldt Deutz Ag | Oil cooler for an internal combustion engine |
| CN203349672U (en) * | 2013-05-29 | 2013-12-18 | 天津捷强动力装备有限公司 | Multi-oil-way air cooling cooler |
| CN106762150A (en) * | 2016-11-24 | 2017-05-31 | 新乡航空工业(集团)有限公司 | A kind of aircraft engine fires lubricating oil integrated heat exchange device |
| CN207229184U (en) * | 2017-08-10 | 2018-04-13 | 陕西北方动力有限责任公司 | A kind of diesel engine transmission case machine oil radiating subassembly |
| CN210686081U (en) * | 2019-06-26 | 2020-06-05 | 中天飞龙(西安)智能科技有限责任公司 | Aviation piston engine lubricating oil temperature regulation and control device |
| CN112158326A (en) * | 2020-09-11 | 2021-01-01 | 中国航空工业集团公司成都飞机设计研究所 | Ventral fin type radiator suitable for aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9765660B2 (en) * | 2015-05-29 | 2017-09-19 | Honeywell International Inc. | Internal bypass to improve decongealing of surface type air to oil coolers |
-
2020
- 2020-12-17 CN CN202011496453.XA patent/CN112610296B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2044916A (en) * | 1979-03-08 | 1980-10-22 | Daimler Benz Ag | A heat exchange device for vehicles |
| DE3714230A1 (en) * | 1987-04-29 | 1988-11-10 | Kloeckner Humboldt Deutz Ag | Oil cooler for an internal combustion engine |
| CN203349672U (en) * | 2013-05-29 | 2013-12-18 | 天津捷强动力装备有限公司 | Multi-oil-way air cooling cooler |
| CN106762150A (en) * | 2016-11-24 | 2017-05-31 | 新乡航空工业(集团)有限公司 | A kind of aircraft engine fires lubricating oil integrated heat exchange device |
| CN207229184U (en) * | 2017-08-10 | 2018-04-13 | 陕西北方动力有限责任公司 | A kind of diesel engine transmission case machine oil radiating subassembly |
| CN210686081U (en) * | 2019-06-26 | 2020-06-05 | 中天飞龙(西安)智能科技有限责任公司 | Aviation piston engine lubricating oil temperature regulation and control device |
| CN112158326A (en) * | 2020-09-11 | 2021-01-01 | 中国航空工业集团公司成都飞机设计研究所 | Ventral fin type radiator suitable for aircraft |
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| CN112610296A (en) | 2021-04-06 |
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