CN111520233B - Aviation oil supply system and oil supply control method - Google Patents
Aviation oil supply system and oil supply control method Download PDFInfo
- Publication number
- CN111520233B CN111520233B CN202010489771.7A CN202010489771A CN111520233B CN 111520233 B CN111520233 B CN 111520233B CN 202010489771 A CN202010489771 A CN 202010489771A CN 111520233 B CN111520233 B CN 111520233B
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- Prior art keywords
- oil tank
- oil
- engine
- cavity
- cruising
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Classifications
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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
- F02C7/22—Fuel supply systems
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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
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
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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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
-
- 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)
- General Engineering & Computer Science (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The invention discloses an aviation oil supply system and an oil supply control method, wherein the aviation oil supply system comprises an oil tank cabin, an integrated diaphragm oil tank, a gas transmission pipeline and an oil supply pipeline for connecting the oil tank and an engine, the engine, a flight control system and a three-way electromagnetic valve; the integrated diaphragm oil tank is arranged in the oil tank cabin; the integrated diaphragm oil tank is internally provided with a diaphragm which divides the oil tank into two cavities, namely a cruising oil tank cavity and a motor oil tank cavity; the cruising oil tank cavity is provided with an air inlet, and the air inlet is connected with the engine through a gas transmission pipeline; the cruising oil tank cavity and the motor oil tank cavity are respectively provided with an oil outlet, the two oil outlets are respectively connected with a three-way electromagnetic valve through an oil supply pipeline, and the three-way electromagnetic valve is connected with an engine through an oil pump; the flight control system is electrically connected with the three-way electromagnetic valve and used for controlling the opening and closing of the three-way electromagnetic valve so as to control the oil supply state of the cruising oil tank cavity and the motor oil tank cavity to the engine according to the flight state. The system can meet the requirement of stable oil supply under different flight states.
Description
Technical Field
The invention belongs to the field of aviation power systems, and particularly relates to an aviation oil supply system and an oil supply control method.
Background
The tanks of an aircraft are generally divided into hard and soft tanks, the pressurization of which varies. The hard oil tank mode has relatively better pressure resistance, but has high process sealing requirement, is difficult to maintain after breakage, and needs to design a special consumption oil tank to cope with maneuver flight, so that the whole is relatively complex.
The pressurizing mode of the flexible fuel tank is divided into an external pressurizing mode and an internal pressurizing mode. The external pressurizing mode needs to seal the oil tank cabin and pressurize the air in the gap between the cabin and the soft oil tank, and is beneficial to being suitable for large-motor flight; the process sealing problem similar to the hard oil tank mode exists in the mode, and meanwhile, the maintenance cover needs to be repeatedly detached for sealing, so that the later use and maintenance are inconvenient. The internal pressurization mode does not need to seal an oil tank cabin, and directly leads air to be pressurized into the soft oil tank, the mode requires that the shape of the oil tank cabin is regular, and in the large maneuver, a consumed oil tank similar to a hard oil tank is also required to be arranged, so that the abnormal operation of an oil pump or an engine caused by the suction of air into an oil path is prevented.
Disclosure of Invention
The invention aims to provide an aviation oil supply system and an oil supply control method, which adopt an aviation oil supply device combining soft and hard characteristics and combining an internal pressurizing mode and an external pressurizing mode of a soft oil tank.
The technical solution for realizing the purpose of the invention is as follows:
an aviation oil supply system comprises an oil tank cabin, an integrated diaphragm oil tank, a gas transmission pipeline and an oil supply pipeline for connecting the oil tank and an engine, the engine, a flight control system and a three-way electromagnetic valve;
the integrated diaphragm oil tank is arranged in the oil tank cabin; the integrated diaphragm oil tank is internally provided with a diaphragm which divides the oil tank into two cavities, namely a cruising oil tank cavity and a motor oil tank cavity; the cruising oil tank cavity is provided with an air inlet, and the air inlet is connected with the engine through a gas transmission pipeline and is used for introducing pressurized gas from the engine; the cruising oil tank cavity and the motor oil tank cavity are respectively provided with an oil outlet, the two oil outlets are respectively connected with a three-way electromagnetic valve through an oil supply pipeline, and the three-way electromagnetic valve is connected with an engine through an oil pump; the flight control system is electrically connected with the three-way electromagnetic valve and used for controlling the opening and closing of the three-way electromagnetic valve so as to control the oil supply state of the cruise oil tank cavity and the motor oil tank cavity to the engine according to the flight state.
The fuel supply control method of the aviation fuel supply system comprises the steps that when the aviation aircraft is in a general climbing and cruising state, the three-way electromagnetic valve is controlled by the aviation control system to open a cruising fuel tank cavity and a fuel path of an engine when the aviation aircraft is in cruising flight, and the cruising fuel tank cavity supplies fuel to the engine; when the aviation aircraft is in motor flight, the flight control system controls the three-way electromagnetic valve to open the cavity of the motor oil tank and the oil way of the engine, and the cavity of the motor oil tank supplies oil to the engine.
Compared with the prior art, the invention has the remarkable advantages that:
the invention adopts an aviation oil supply device combining the characteristics of a soft oil tank and a hard oil tank and combining the internal pressurization mode and the external pressurization mode of the soft oil tank. The oil tank is divided into two parts by the diaphragm, so that internal pressurization and external pressurization can be realized respectively, and two different pressurization modes can be freely switched to supply oil to the engine according to the flight state through flight system control. The oil tank is free from sealing of an oil tank cabin, good in manufacturability, capable of meeting stable oil supply of the aircraft under different flight states, and simple and convenient to use and maintain, and integrates the advantages of a hard oil tank pressurizing mode and two soft oil tank pressurizing modes.
Drawings
FIG. 1 is a schematic overview of an aircraft fuel supply system
Detailed Description
The invention is further described with reference to the drawings and specific embodiments.
Referring to fig. 1, the aviation fuel supply system of the invention comprises a fuel tank cabin 1, an integrated diaphragm fuel tank 2, a gas pipeline and a fuel supply pipeline for connecting the fuel tank and an engine, an engine 4, a flight control system 7 and a three-way electromagnetic valve 6;
the integrated diaphragm oil tank 2 is arranged in the oil tank cabin 1; the integrated diaphragm oil tank 2 is made of flexible materials, and a diaphragm 21 is arranged in the integrated diaphragm oil tank 2 to divide the oil tank into two cavities, namely a cruising oil tank cavity 22 and a motor oil tank cavity 23; the cruising oil tank cavity 22 is provided with an air inlet, and the air inlet is connected with the engine through a gas transmission pipeline and is used for introducing pressurized gas from the engine; the cruising oil tank cavity 22 and the motor oil tank cavity 23 are respectively provided with an oil outlet, the two oil outlets are respectively connected with a three-way electromagnetic valve 6 through an oil supply pipeline, and the three-way electromagnetic valve 6 is connected with the engine 4 through the oil supply pipeline and the oil pump 5; the flight control system 7 is electrically connected with the three-way electromagnetic valve 6 and is used for controlling the opening and closing of the three-way electromagnetic valve 6 so as to control the oil supply state of the cruising oil tank cavity 22 and the motor oil tank cavity 23 to the engine 4 according to the flight state.
Furthermore, the gas transmission pipeline is also provided with a pressure relief valve 3, the pressure input by the engine 4 is larger, the pressure input into the cruising oil tank cavity 22 can be controlled through the pressure relief valve 3, and when the pressure in the cruising oil tank cavity 22 reaches equilibrium, the continuous inflation is stopped.
Further, liquid level sensors are arranged in the cruising oil tank cavity 22 and the motor oil tank cavity 23, and are used for detecting the liquid level of oil.
The oil supply control method based on the aviation oil supply system comprises the following steps:
the pressurized gas from the engine 4 is introduced into the cruise oil tank cavity 2, the aircraft consumes the fuel oil of the cruise oil tank cavity 22 in the general climbing and cruising state, the aircraft consumes the fuel oil of the motor oil tank cavity 23 in the motor-driven flight, and the two-position three-way electromagnetic valve 6 is controlled by the flight control system 7 to switch the two-part oil tank cavity for supplying the fuel oil of the engine 4 when the motor-driven flight is shifted from cruising to motor-driven flight or from motor-driven to cruising flight. When the aircraft is in maneuvering flight, due to the existence of the flexible diaphragm 21, the air-entraining pressurizing pressure in the cruising oil tank space can be conducted to the maneuvering oil tank cavity 23, so that the pressurizing oil supply effect of the maneuvering oil tank cavity 23 is realized, gas is prevented from mixing into an oil way, and the normal operation of an engine of the aircraft in a maneuvering flight state is ensured.
The invention adopts an aviation oil supply device combining the characteristics of a soft oil tank and a hard oil tank and combining the internal pressurization mode and the external pressurization mode of the soft oil tank. The oil tank is divided into two parts by the diaphragm, so that internal pressurization and external pressurization can be realized respectively, and two different pressurization modes can be freely switched to supply oil to the engine through control of the flight system. The oil tank is free from sealing of an oil tank cabin, good in manufacturability, capable of meeting stable oil supply of the aircraft under different flight states, and simple and convenient to use and maintain, and integrates the advantages of a hard oil tank pressurizing mode and two soft oil tank pressurizing modes.
Claims (5)
1. The aviation oil supply system is characterized by comprising an oil tank cabin (1), an integrated diaphragm oil tank (2), a gas transmission pipeline and an oil supply pipeline for connecting the oil tank and an engine, the engine (4), a flight control system (7) and a three-way electromagnetic valve (6);
the integrated diaphragm oil tank (2) is arranged in the oil tank cabin (1); a diaphragm (21) is arranged in the integrated diaphragm oil tank (2) to divide the oil tank into two cavities, namely a cruising oil tank cavity (22) and a motor oil tank cavity (23); the cruising oil tank cavity (22) is provided with an air inlet, and the air inlet is connected with the engine through a gas transmission pipeline and is used for introducing pressurized gas from the engine; the cruising oil tank cavity (22) and the motor oil tank cavity (23) are respectively provided with an oil outlet, the two oil outlets are respectively connected with a three-way electromagnetic valve (6) through an oil supply pipeline, and the three-way electromagnetic valve (6) is connected with the engine (4) through an oil pump (5); the flight control system (7) is electrically connected with the three-way electromagnetic valve (6) and is used for controlling the opening and closing of the three-way electromagnetic valve (6) so as to control the oil supply state of the cruising oil tank cavity (22) and the motor oil tank cavity (23) to the engine (4) according to the flight state;
when the aircraft is in a general climbing and cruising state, the flight control system controls the three-way electromagnetic valve to open the cruising oil tank cavity and the oil way of the engine when the aircraft is in cruising flight, and the cruising oil tank cavity supplies oil to the engine; when the aviation aircraft is in motor flight, the flight control system controls the three-way electromagnetic valve to open the cavity of the motor oil tank and the oil way of the engine, and the cavity of the motor oil tank supplies oil to the engine.
2. Aviation fuel supply system according to claim 1, characterized in that a pressure control device is also provided between the cruise tank cavity (22) and the engine (4).
3. The aviation fuel supply system of claim 2, wherein the pressure control device is a pressure relief valve, the pressure relief valve being disposed on a gas delivery line.
4. Aviation fuel supply system according to claim 1, characterized in that the cruise tank cavity (22) and the motor tank cavity (23) are provided with level sensors for detecting the level of the oil.
5. Aviation fuel supply system according to claim 1, characterized in that the three-way solenoid valve (6) is a two-position three-way solenoid valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010489771.7A CN111520233B (en) | 2020-06-02 | 2020-06-02 | Aviation oil supply system and oil supply control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010489771.7A CN111520233B (en) | 2020-06-02 | 2020-06-02 | Aviation oil supply system and oil supply control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111520233A CN111520233A (en) | 2020-08-11 |
| CN111520233B true CN111520233B (en) | 2023-08-22 |
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| CN202010489771.7A Active CN111520233B (en) | 2020-06-02 | 2020-06-02 | Aviation oil supply system and oil supply control method |
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Citations (14)
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| CN111520233A (en) | 2020-08-11 |
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