CN111520233A - Aviation oil supply system and oil supply control method - Google Patents
Aviation oil supply system and oil supply control method Download PDFInfo
- Publication number
- CN111520233A CN111520233A CN202010489771.7A CN202010489771A CN111520233A CN 111520233 A CN111520233 A CN 111520233A CN 202010489771 A CN202010489771 A CN 202010489771A CN 111520233 A CN111520233 A CN 111520233A
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- Prior art keywords
- oil tank
- oil
- engine
- cavity
- electromagnetic valve
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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
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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)
- 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 which are used 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 cruise oil tank cavity and a maneuvering oil tank cavity; the cavity of the cruising oil tank is provided with an air inlet which is connected with the engine through a gas transmission pipeline; the cavity of the cruising oil tank and the cavity of the maneuvering oil tank are both provided with oil outlets, the two oil outlets are respectively connected with a three-way electromagnetic valve through oil supply pipelines, 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 engine 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 aircraft are generally divided into hard tanks and soft tanks, which are also pressurized differently. The hard oil tank mode has relatively better pressure resistance, but has high requirements on process sealing, is difficult to maintain after being damaged, needs to design a special consumed oil tank to deal with maneuvering flight, and is relatively complex in whole.
The soft oil tank pressurization mode is divided into an external pressurization mode and an internal pressurization mode. The external pressurization mode needs to seal the oil tank cabin and introduce air to a gap between the cabin and the soft oil tank for pressurization, and the external pressurization mode has the advantages of being suitable for large-maneuvering flight; the process sealing problem similar to a hard oil tank mode exists in the mode, and meanwhile, the opening cover needs to be repeatedly disassembled and sealed during installation and maintenance, so that inconvenience is caused in later-stage use and maintenance. The internal pressurization mode does not need to seal the oil tank cabin, and the oil tank cabin is directly subjected to air-entraining pressurization to the inside of the soft oil tank, so that the shape of the oil tank cabin is required to be regular, and in large-sized maneuvering flight, a consumption oil tank similar to a hard oil tank type also needs to be arranged to prevent the abnormal work of an oil pump or an engine caused by the fact that gas is sucked into an oil circuit.
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 pressurization mode and an external pressurization 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 which are used 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; a diaphragm is arranged in the integrated diaphragm oil tank to divide the oil tank into two cavities, namely a cruise oil tank cavity and a maneuvering oil tank cavity; the cavity of the cruising oil tank is provided with an air inlet which is connected with the engine through a gas transmission pipeline and is used for introducing pressurized gas from the engine; the cruise oil tank cavity and the motor oil tank cavity are respectively provided with an oil outlet, the two oil outlets are respectively connected into a three-way electromagnetic valve through oil supply pipelines, and the three-way electromagnetic valve is connected with an engine through an oil pump; and the flight control system is electrically connected with the three-way electromagnetic valve and is 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 maneuvering oil tank cavity to the engine according to the flight state.
An aircraft is in general climbing and cruising states, when the aircraft is in cruising flight, a flight control system controls a three-way electromagnetic valve to open an oil circuit of a cruising oil tank cavity and an engine, and the cruising oil tank cavity supplies oil to the engine; when the aviation aircraft flies by a motor, the flight control system controls the three-way electromagnetic valve to open the oil circuit between the cavity of the motor-driven oil tank and the engine, and the cavity of the motor-driven oil tank supplies oil to the engine.
Compared with the prior art, the invention has the following remarkable advantages:
the invention adopts an aviation oil supply device which combines the characteristics of a soft oil tank and a hard oil tank and combines the internal pressurization and the external pressurization of the soft oil tank. The oil tank is divided into two parts by the diaphragm, so that internal pressurization and external pressurization are respectively realized, and two different pressurization modes can be freely switched to supply oil to the engine according to the flight state through the control of a flight system. The oil tank is not required to be sealed in the oil tank cabin, has good manufacturability, can meet stable oil supply of the aircraft in different flight states, integrates the advantages of a hard oil tank pressurization mode and two soft oil tank pressurization modes, and is simple and convenient to use and maintain.
Drawings
FIG. 1 is a general schematic view of an aviation fuel supply system
Detailed Description
The invention is further described with reference to the following figures and embodiments.
With reference to fig. 1, the aviation oil supply system of the present invention comprises an oil tank cabin 1, an integrated diaphragm oil tank 2, an air transmission pipeline and an oil supply pipeline for connecting the oil tank and an engine, an engine 4, a flight control system 7 and a three-way solenoid 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, a diaphragm 21 is arranged in the integrated diaphragm oil tank 2 to divide the oil tank into two cavities, namely a cruise oil tank cavity 22 and a maneuvering oil tank cavity 23; the cavity 22 of the cruising oil tank is provided with an air inlet which is connected with the engine through a gas pipeline and is used for introducing pressurized gas from the engine; the cruise oil tank cavity 22 and the motor oil tank cavity 23 are both provided with oil outlets, the two oil outlets are respectively connected to a three-way electromagnetic valve 6 through oil supply pipelines, 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 cruise oil tank cavity 22 and the maneuvering oil tank cavity 23 to the engine 4 according to the flight state.
Further, a pressure release valve 3 is further arranged on the gas transmission pipeline, the pressure input by the engine 4 is large, the pressure input into the cruise oil tank cavity 22 can be controlled through the pressure release valve 3, and when the pressure in the cruise oil tank cavity 22 is balanced, the continuous inflation is stopped.
Furthermore, liquid level sensors are arranged in the cruise oil tank cavity 22 and the motor-driven oil tank cavity 23 respectively 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 fuel oil in the cruise oil tank cavity 22 is consumed by the aircraft in the ordinary climbing and cruising states, the fuel oil in the maneuvering oil tank cavity 23 is consumed by the aviation aircraft in maneuvering flight, and when the maneuvering flight is switched from cruising to maneuvering flight or maneuvering to cruising flight, the flight control lower system 7 reaches an electric signal to control the two-position three-way electromagnetic valve 6, and the two-part oil tank cavity for supplying the fuel oil to the engine 4 is switched. When the aircraft flies in a maneuvering mode, due to the existence of the flexible diaphragm 21, the air-entraining supercharging pressure in the cruising oil tank space can be conducted to the maneuvering oil tank cavity 23, so that the supercharging oil supply effect of the maneuvering oil tank cavity 23 is realized, gas is prevented from mixing into an oil circuit, and the normal work of an engine of the aircraft in the maneuvering flight state is ensured.
The invention adopts an aviation oil supply device which combines the characteristics of a soft oil tank and a hard oil tank and combines the internal pressurization and the external pressurization of the soft oil tank. The oil tank is divided into two parts by the diaphragm, so that internal pressurization and external pressurization are respectively realized, and two different pressurization modes can be freely switched to supply oil to the engine through control of a flight system. The oil tank is not required to be sealed in the oil tank cabin, has good manufacturability, can meet stable oil supply of the aircraft in different flight states, integrates the advantages of a hard oil tank pressurization mode and two soft oil tank pressurization modes, and is simple and convenient to use and maintain.
Claims (6)
1. An 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 cruise oil tank cavity (22) and a power-driven oil tank cavity (23); the cruise oil tank cavity (22) is provided with an air inlet, and the air inlet is connected with the engine through an air pipeline and is used for introducing pressurized air from the engine; the cruise oil tank cavity (22) and the motor oil tank cavity (23) are respectively provided with oil outlets, the two oil outlets are respectively connected to a three-way electromagnetic valve (6) through oil supply pipelines, and the three-way electromagnetic valve (6) is connected with an 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 three-way electromagnetic valve (6) to be opened and closed so as to control the oil supply state of the cruise oil tank cavity (22) and the maneuvering oil tank cavity (23) to the engine (4) according to the flight state.
2. Airborne oil supply system according to claim 1, characterised in that a pressure control device is also provided between the cruise tank cavity (22) and the engine (4).
3. The airborne oil supply system of claim 2 wherein said pressure control device is a pressure relief valve, said pressure relief valve being disposed on an air delivery conduit.
4. -airborne oil supply system according to claim 1, characterised in that level sensors are provided both in the cruise tank cavity (22) and in the mobile tank cavity (23) for detecting the level of oil.
5. -the aircraft oil supply system according to claim 1, characterized in that said three-way solenoid valve (6) is a two-position three-way solenoid valve.
6. The method for controlling the fuel supply of the aviation fuel supply system according to any one of claims 1 to 5, wherein when the aircraft is in a normal climbing and cruising state, and the aviation aircraft is in cruising flight, the flight control system controls the three-way solenoid valve to open the oil circuit between the cruising oil tank cavity and the engine, and the cruising oil tank cavity supplies fuel to the engine; when the aviation aircraft flies by a motor, the flight control system controls the three-way electromagnetic valve to open the oil circuit between the cavity of the motor-driven oil tank and the engine, and the cavity of the motor-driven oil tank supplies oil to the engine.
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 |
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| Publication Number | Publication Date |
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| CN111520233A true CN111520233A (en) | 2020-08-11 |
| CN111520233B CN111520233B (en) | 2023-08-22 |
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| CN111520233B (en) | 2023-08-22 |
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