CN109441637B - Airplane surplus power integrated system and method for pressurizing oil tank by using nitrogen - Google Patents
Airplane surplus power integrated system and method for pressurizing oil tank by using nitrogen Download PDFInfo
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- CN109441637B CN109441637B CN201811023569.4A CN201811023569A CN109441637B CN 109441637 B CN109441637 B CN 109441637B CN 201811023569 A CN201811023569 A CN 201811023569A CN 109441637 B CN109441637 B CN 109441637B
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- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 title claims abstract description 111
- 229910052757 nitrogen Inorganic materials 0.000 title claims abstract description 53
- 238000000034 method Methods 0.000 title claims description 32
- 239000012528 membrane Substances 0.000 claims abstract description 67
- 239000000295 fuel oil Substances 0.000 claims abstract description 54
- 238000000926 separation method Methods 0.000 claims abstract description 54
- 239000003921 oil Substances 0.000 claims abstract description 52
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 13
- 239000001301 oxygen Substances 0.000 claims abstract description 13
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 13
- 230000005611 electricity Effects 0.000 claims abstract description 7
- 239000007789 gas Substances 0.000 claims description 40
- 239000002828 fuel tank Substances 0.000 claims description 37
- 238000001816 cooling Methods 0.000 claims description 34
- 239000003990 capacitor Substances 0.000 claims description 20
- 238000001514 detection method Methods 0.000 claims description 19
- 230000008569 process Effects 0.000 claims description 15
- 230000001276 controlling effect Effects 0.000 claims description 11
- 229910001873 dinitrogen Inorganic materials 0.000 claims description 5
- 238000000605 extraction Methods 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 238000005057 refrigeration Methods 0.000 abstract description 14
- 238000004146 energy storage Methods 0.000 abstract description 12
- 238000006243 chemical reaction Methods 0.000 abstract description 10
- 238000010248 power generation Methods 0.000 abstract description 10
- 238000010586 diagram Methods 0.000 description 9
- 239000012510 hollow fiber Substances 0.000 description 8
- 230000017525 heat dissipation Effects 0.000 description 4
- 230000000740 bleeding effect Effects 0.000 description 3
- 238000005381 potential energy Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
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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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
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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
- F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
- F02C1/02—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being an unheated pressurised gas
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Separation Using Semi-Permeable Membranes (AREA)
Abstract
The invention relates to an airplane rich electric energy comprehensive utilization system utilizing nitrogen to pressurize an oil tank, which comprises: the system comprises a membrane separation system utilizing surplus power, a pressurized oil tank energy storage system and an energy release system. The membrane separation system utilizing surplus electric power can fully utilize surplus electric energy in an airplane power grid, and the airborne membrane separation system is driven to convert air introduced from the outside of an airplane into high-pressure oxygen and nitrogen. The boosting oil tank energy storage system can fully utilize huge space in the fuel oil tank, and the obtained high-pressure nitrogen is stored in the fuel oil tank. The energy release system can dynamically release high-pressure nitrogen stored in the fuel oil tank for refrigeration and power generation, and meets the refrigeration and short-time high-power electricity utilization requirements of the airplane. The invention fully utilizes the surplus electric energy of the airplane, realizes the transverse conversion, dispatching and storage of the electric energy from the air pressure energy to the cold energy and the electric energy, and ensures the efficient and safe work of the airplane. Has wide application in the aviation field.
Description
Technical Field
The invention belongs to the field of aerospace, and relates to a comprehensive utilization system and method for surplus electric power of an airplane by utilizing a nitrogen pressurized oil tank.
Technical Field
With the continuous development of modern airplanes to more electricity and full electricity, the power demand of airborne equipment is larger and larger, and the power generation capacity of airborne generators is also increased continuously. The rated power generation of the current airborne generator is designed to meet the maximum power requirement under the conventional working condition, however, the power requirement of the airborne equipment is not always in the maximum requirement state, but changes along with the change of the flight phase, so that the generator has surplus power generation capacity in different flight phases, namely the generator is in an underload state. In some extreme cases, such as when high-power devices such as laser weapons and radars work simultaneously, the generator may have short-term insufficient electric energy, and at the same time, the generator may have short-term overload. Both under-load and over-load can adversely affect the operation of the generator. The current main way for aircraft to utilize surplus power is to store surplus electrical energy in storage batteries and super capacitors. Due to the limited capacity of the storage battery and the super capacitor, the onboard surplus power generation capacity is difficult to be utilized and stored on a large scale. Therefore, the dynamic scheduling method which fully and reasonably utilizes the surplus power generation capacity of the airplane power grid and can make up for the required electric energy when the power grid is insufficient has important significance for the electric energy utilization of the airplane and the good operation of the generator, and therefore, the method becomes a problem which needs to be solved urgently.
Disclosure of Invention
According to one aspect of the invention, the invention provides an aircraft surplus power comprehensive utilization system for pressurizing an oil tank by using nitrogen, which is characterized by comprising:
a motor, a frequency converter, a detection element, a controller, an airborne membrane separation system, an oil tank air pressure sensor, a fuel oil tank, a turbine electronic equipment air cooling system, a generator and a super capacitor,
wherein:
the detection element is used for detecting the current state of the aircraft power grid of the aircraft and, when there is surplus power in the aircraft power grid,
the motor is used for converting part or all of surplus electric power in the power grid into mechanical energy under the control of the controller, so that the extraction of the surplus electric power of the airplane is completed,
the compressor in the onboard membrane separation system is driven by the mechanical energy to do work, the air introduced from the outside of the airplane is compressed into high-pressure gas, the high-pressure gas is then separated into high-pressure oxygen and high-pressure nitrogen by the onboard membrane separation system,
the high-pressure oxygen is delivered to the cabin of the airplane for supplying air, the pressure and the oxygen supply inside the cabin are regulated, a fuel oil tank is fully utilized for storing the high-pressure nitrogen in the space inside the fuel oil tank,
the oil tank air pressure sensor is used for detecting air pressure in the oil tank;
the turbine is pushed by high-pressure nitrogen from a fuel oil tank, the high-pressure nitrogen pushes the turbine to work and then becomes low-temperature and low-pressure nitrogen, the low-temperature and low-pressure nitrogen is used for cooling an electronic equipment air cooling system on the airplane,
the generator is driven by the turbine to generate electricity which is supplied to the super capacitor and/or the aircraft electrical grid.
According to another aspect of the invention, an airplane surplus power comprehensive utilization method based on the airplane surplus power comprehensive utilization system utilizing the nitrogen gas to pressurize the oil tank is provided.
Drawings
Fig. 1 is a general schematic diagram of an aircraft surplus power integrated utilization system using a nitrogen pressurizing fuel tank.
FIG. 2 is a schematic diagram of an airborne membrane separation system.
Fig. 3 is a schematic diagram of the operation of a membrane separation system using surplus power.
Fig. 4 is a schematic diagram of energy conversion.
Fig. 5 is a schematic diagram of the operation of the pressurized oil tank energy storage system.
Fig. 6 is a schematic diagram of the operation of the energy release system.
Fig. 7 is a flow chart of the system.
Description of reference numerals:
motor (101) frequency converter (102) detecting element (103)
Airplane power grid (104) controller (105) onboard membrane separation system (106)
Temperature sensor (1061) of air supply system (107) of aircraft cabin
Compressor (1062)
Electromagnetic valve of membrane separation system (1063) filter (1064)
Hollow fiber type membrane separator (1065) oil tank inflation solenoid valve (201)
Oil tank pressure sensor (202) fuel oil tank (203)
Oil tank air pressure safety valve (204) oil tank air bleed solenoid valve (301)
Turbine (302) electronics air cooling system (303)
Generator (304) super capacitor (305) controllable switch (306)
Detailed Description
In connection with the above-mentioned prior art problems, there is a situation where the onboard cold energy is insufficient while the electrical energy is not utilized properly. Because the power of the airborne equipment of the modern aircraft is increased more and more, on the premise that the efficiency is not obviously improved, the heat productivity of the equipment is increased more and more, the temperature of the equipment is increased sharply, and finally the safe and efficient work of the airborne equipment is greatly influenced. Therefore, timely and reasonable dissipation of heat generated by onboard equipment through the annular system is of great significance to safe and efficient operation of the aircraft. However, as the on-board heat sinks of modern aircraft grow more and more lagging the power increase, they are becoming increasingly unable to meet the heat dissipation requirements of aircraft, and thus the urgent need for current on-board equipment is to generate more cold energy in a reasonably efficient manner.
The aircraft fuel tank is used for storing fuel oil and supplying the aircraft engine to burn and use, and along with the flight of aircraft, the fuel oil in the fuel tank is constantly consumed, can leave huge space. The method not only ensures the isolation of fuel oil in the oil tank from air to prevent fire, but also can improve the high altitude system performance of a fuel oil system. Although the method ensures the reliability of fuel utilization, the method does not fully utilize the huge space in the fuel tank, and has limited help for improving the energy utilization rate of the airplane.
Currently, nitrogen filled into a fuel oil tank in an aircraft is mainly generated by an airborne membrane separation system, and mainly comprises a temperature sensor, a compressor, an electromagnetic valve, a filter, a hollow fiber type membrane separator and the like, and a schematic diagram of the nitrogen is shown in fig. 2. The airborne membrane separator has the working principle that air introduced from the outside is compressed into high-pressure air by a compressor, then the high-pressure air is separated into high-pressure nitrogen and high-pressure oxygen by a central control fiber type membrane separator, the separated nitrogen is used for pressurizing the inside of a fuel oil tank, and the oxygen is used for supplying a cabin.
To sum up, the surplus generating capacity of current machine-carried is not by complete reasonable utilization, and the refrigeration ability of aircraft more and more can not satisfy the heat dissipation demand of machine-carried equipment, and simultaneously, the inside huge space of fuel tank also can not by abundant utilization, and the membrane separation system who carries can produce the inside use of nitrogen gas fuel supply tank.
Therefore, the inventor realizes that the surplus electric energy is converted into the air pressure energy, the air pressure energy is converted into the cold energy and the electric energy in a reasonable time by utilizing the huge space in the fuel tank for storage, the great significance is provided for the efficient and reasonable use of the airplane energy, and the feasibility is provided in engineering.
In order to solve the problems that the surplus power of the airplane cannot be reasonably utilized and the heat sink capacity is insufficient in the flying process of the airplane, according to one aspect of the invention, the comprehensive utilization system of the surplus power of the airplane with the nitrogen pressurization oil tank is provided, the surplus power of the airplane can be fully utilized, the surplus power is converted into the pressure potential energy of gas by utilizing a membrane separation system of the surplus power and stored in the oil tank, the problem that the power cannot be fully utilized and stored is solved, meanwhile, the gas storage and gas release processes can be reasonably selected according to the state of an airplane power grid and the cooling requirement of airborne equipment, the refrigerating capacity and the generating capacity of the gas are dynamically adjusted, the heat sink and power requirements of the airborne equipment are dynamically matched, and the trouble that the heat sink capacity is insufficient and the short-time power is insufficient in the flying process of the airplane. Therefore, the invention not only makes full use of the airborne energy, realizes the transverse conversion and dispatching from the electric energy to the cold energy, but also ensures the efficient and safe operation of the airplane.
According to another aspect of the present invention, there is provided an integrated utilization system of surplus electric power of an aircraft using a nitrogen pressurized fuel tank, comprising: a membrane separation system, a pressurized oil tank energy storage system and an energy release system which utilize surplus electric power,
the membrane separation system utilizing surplus power comprises a motor (101), a frequency converter (102), a detection element (103), a controller (105), an airborne membrane separation system (106) and an aircraft cabin air supply system (107);
the pressure boost oil tank energy storage system includes: a tank inflation electromagnetic valve (201), a tank air pressure sensor (202), a fuel tank (203) and a tank air pressure safety valve (204);
the energy release system comprises: the system comprises a fuel tank air bleed solenoid valve (301), a turbine (302), an electronic equipment air cooling system (303), a generator (304), a super capacitor (305) and a controllable switch (306).
Referring to fig. 3, the membrane separation system using surplus power continuously detects the current state of the aircraft power grid (104) by using the detection element (103), and when the aircraft power grid (104) has surplus power generation capacity, the controller (105) converts part or all of the surplus power generation capacity in the power grid into mechanical energy through the motor (101) according to the demand of the system and the state of the aircraft, so that the extraction of the surplus power of the aircraft is completed. The rotary mechanical energy obtained by the motor (101) is used for driving a compressor (1062) in the onboard membrane separator (106) to do work, compressing air introduced from the outside of the airplane into high-pressure gas, and then separating the high-pressure gas into oxygen and nitrogen under the action of the onboard membrane separator (106). Oxygen is supplied to the cabin, nitrogen is conveyed to the pressurized oil tank energy storage system, the conversion from surplus electric energy to air pressure energy is realized, and oxygen supply of the aircraft cabin is ensured. The energy conversion in the onboard membrane separation system is shown as an upper broken line box in fig. 4, and comprises the steps of extracting surplus electric power from an aircraft power grid (104), converting the surplus electric power into rotary mechanical energy through a motor (101), converting the rotary mechanical energy into air pressure energy through a compressor (1062) (fig. 2), and finally converting the air pressure energy into separated nitrogen gas after passing through an onboard membrane separation system (106).
Referring to fig. 5, the pressurized fuel tank energy storage system can fully utilize the space in the fuel tank, and store high-pressure nitrogen obtained by the onboard membrane separation system (106) in the fuel tank (203). The oil tank inflation electromagnetic valve (201) is used for controlling the on-off of an inflation gas path; the oil tank air pressure sensor (202) is used for monitoring the current air pressure in the oil tank in real time; the oil tank air pressure safety valve (204) ensures that the air pressure in the oil tank is kept within a certain range, and when the air pressure exceeds the safety pressure, the air pressure safety valve automatically deflates to release the pressure.
Referring to fig. 6, the energy release system can release high-pressure nitrogen stored in a fuel tank (203) through a tank bleed solenoid valve (301), the high-pressure nitrogen flows through a turbine (302) and pushes the turbine (302) to work, then the high-pressure nitrogen becomes low-temperature and low-pressure nitrogen, the nitrogen finally flows into an electronic device (303) for cooling the electronic device, and the work done by the turbine (302) is converted into electric energy through a generator (304) and is provided to a super capacitor (305). The oil tank air discharge electromagnetic valve (301) is used for controlling the on-off of an oil tank air discharge air path and is controlled by the controller (105); according to one embodiment of the invention, the generator (304) is coaxially connected with the turbine (302) and converts the work done by the expansion of the turbine (302) into electric energy; the controllable switch (306) is used for controlling the feedback of the electric energy stored in the super capacitor (305) to the power grid, and makes up for the short-term shortage of electric energy which may occur in the power grid, and is controlled by the controller (105). The energy conversion process in the energy release system is shown as a dotted line box at the lower part of fig. 4, the energy conversion process is that nitrogen gas pressure energy stored in a fuel oil tank (203) is converted into two parts of energy after passing through a turbine (302) and doing work on the turbine, one part of the energy is supplied to an electronic equipment air cooling system (303) in the form of cold energy, the other part of the energy is converted into rotary mechanical energy to drive a generator (304) to do work, and finally, the generator (304) generates electric energy and feeds the electric energy back to an airplane power grid (104).
The controller (105) is used for receiving power grid information output by the detection element (103), pressure information of the oil tank air pressure sensor (202) and information of the air temperature sensor (1061) in the membrane separation system, controlling surplus power input to the motor by the frequency converter (102) according to the current working state and refrigeration requirement of the airplane, performing on/off operation on switches of the membrane separation system electromagnetic valve (1063), the oil tank inflation electromagnetic valve (201) and the oil tank deflation electromagnetic valve (301), and controlling the utilization of electric energy in the current power grid, the gas separation of the membrane separation system, and the inflation energy storage and deflation energy release of the system.
The comprehensive utilization system and method for the surplus electric power of the airplane by utilizing the nitrogen to pressurize the oil tank have the advantages that:
1. the invention fully utilizes the volume of the fuel oil tank, converts the surplus electric energy into the high-pressure potential energy of the gas, and stores the high-pressure potential energy, thereby solving the problem that the surplus electric energy can not be fully utilized and stored, and improving the energy utilization rate of the system.
2. Because the fuel oil tank is filled with high-pressure nitrogen, the fuel oil tank can do work on the fuel oil, and the fuel oil has larger kinetic energy in the process of conveying the fuel oil to the engine, so that the work of the fuel oil conveying pump on the fuel oil is less or even no, and the invention reduces the power consumption of the fuel oil pump and saves energy.
3. The energy storage and refrigeration of the system can be dynamically adjusted, when the refrigeration capacity of the airplane is sufficient, surplus electric energy is converted into high-pressure gas for storage, when the cooling capacity of the airplane is insufficient, the stored high-pressure gas is released for refrigeration, and meanwhile, the surplus working capacity of the turbine is converted into electric energy, so that the heat dissipation requirement of the airplane is matched in time, the dilemma that the existing onboard heat sink cannot meet the heat dissipation requirement more and more is relieved, the transverse conversion of energy is realized, the utilization rate of energy is improved, and the efficient and safe flight of the airplane is ensured.
4. The invention converts all surplus electric power in the airplane power grid into cold energy through reasonable dispatching, and can feed back the generated energy of the super generator to the power grid when the instantaneous electric energy in the power grid is insufficient, so the invention fully utilizes the generating capacity of the main generator and improves the power supply performance of the airplane power grid.
5. The invention fully utilizes the existing airborne equipment, reasonably connects the electrical system with the air compression circulating system, breaks through the energy conversion chain from the electric energy to the cold energy and then to the electric energy, fully utilizes the electric energy, matches the cold energy requirement, reduces the generation and consumption of other energy sources, and has high efficiency and reasonable energy conversion.
Embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
Referring to fig. 1, the comprehensive utilization system of the surplus power of an aircraft for pressurizing a fuel tank with nitrogen according to an embodiment of the present invention includes: a membrane separation system, a pressurized oil tank energy storage system and an energy release system which utilize surplus electric power,
wherein,
the membrane separation system utilizing surplus power comprises a motor (101), a frequency converter (102), a detection element (103), a controller (105), an airborne membrane separation system (106) and an aircraft cabin air supply system (107);
the pressure boost oil tank energy storage system includes: the system comprises a fuel tank inflation electromagnetic valve (201), a fuel tank air pressure sensor (202), a fuel tank (203) and a fuel tank air pressure safety valve (204);
the energy release system mainly comprises a fuel tank air bleed solenoid valve (301), a turbine (302), an electronic equipment air cooling system (303), a generator (304), a super capacitor (305) and a controllable switch (306).
Fig. 3 is a schematic view showing a membrane separation system using surplus power according to an embodiment of the present invention, in which a sensing element (103) is installed on a single-phase line of a generator output for sensing an effective value of a single-phase output current of the generator to determine an operation state of the generator and an operation state of an aircraft power grid (104). The input of the frequency converter (102) is connected with an aircraft power grid (104), the output of the frequency converter is connected with the motor (101), and the electric energy input to the motor (101) from the power grid is controlled by a controller (105). The rated power of the selected motor (101) should not be less than the maximum surplus power generation capacity of the aircraft power grid (104). In this system, a signal of the detection element (103) is an input of the controller (105), and a control signal of the inverter (102) is an output of the controller (105).
Fig. 2 is a schematic view of a membrane separation system using surplus power according to an embodiment of the present invention, in which a compressor (1062) is coaxially connected to a motor (101) and the power requirement of the compressor (1062) is matched to the motor (101). The compressor functions to compress low pressure air introduced in the on-board membrane separation system into high pressure air. The on-board membrane separation system (106) includes a temperature sensor (1061), an air compressor (1062), a membrane separation system solenoid valve (1063), a filter (1064), and a hollow fiber membrane separator (1065) for separating air into oxygen and nitrogen. A temperature sensor (1061) is used for detecting the temperature of the current bleed air from the air, and a detection signal of the temperature sensor is input into the controller (105). According to one embodiment of the invention, the hollow fiber membrane separator (1065) is operated to ensure that the temperature of the bleed air is less than 55 ℃. When the bleed air temperature exceeds 55 ℃, the bleed air solenoid valve (1063) is closed to prevent the high temperature air from damaging the hollow fiber membranes. The hollow fiber membrane separator can work at a high pressure with high efficiency, and according to one embodiment of the invention, the outlet gas pressure of the air compressor (1062) is maintained at 1 MPa.
Fig. 5 is a schematic diagram of a pressurized fuel tank energy storage system according to an embodiment of the invention, wherein a fuel tank charging solenoid valve (201) is used for controlling the on-off of a fuel tank charging air passage, and is controlled by a controller (105); the tank pressure sensor (202) is used for detecting the air pressure in the fuel oil tank (203), and the measuring range of the tank pressure sensor needs to meet the measuring requirement of the tank pressure; the space inside the fuel oil tank (203) except the fuel oil is used for storing high-pressure nitrogen obtained by the onboard membrane separation system (106), so the bearing pressure of the fuel oil tank needs to exceed the maximum storage pressure set in the system. The oil tank air pressure safety valve (204) is used for timely removing air in the oil tank when the air pressure in the oil tank is higher than the safety pressure, and quickly reducing the air pressure in the oil tank to be lower than the safety pressure.
FIG. 6 is a schematic diagram of a bleed air refrigeration system according to an embodiment of the present invention, in which a tank bleed solenoid valve (301) is used to control the on/off of a tank bleed air path, which is controlled by a controller (105); the turbine (302) is used for expanding and refrigerating high-pressure gas stored in a fuel oil tank (203), and the obtained low-temperature nitrogen is led to an electronic equipment cooling system (303) to play a role of cooling electronic equipment. Therefore, at the maximum reserve pressure set by the system, the maximum refrigeration capacity of the selected type of turbine (302) should meet the refrigeration requirements of the system. In order to make reasonable use of and store the mechanical energy generated by the turbine (302), according to one embodiment of the invention, the generator (304) is connected coaxially with the turbine (302), and the output of the generator (304) is connected with the super capacitor (305). In order to control the discharge of the super capacitor (305) and to compensate for possible short-term power shortage in the power grid, the super capacitor (305) is connected to the aircraft power grid (104) by a wire, and a controllable switch (306) is added in the middle. The controllable switch (306) is controlled by the controller (105) to be controllable at any time.
In the present invention, the controller (105) is part of implementing dynamic scheduling. The controller (105) is configured to:
controlling the output of the frequency converter (102) according to the power grid information output by the detection element (103), the pressure information of the gas pressure sensor (202) of the oil tank and the current working state and the refrigeration demand of the airplane, thereby controlling the utilization of electric energy and the compression of gas in the power grid;
according to the refrigeration requirement of the system and the air pressure of the oil tank, determining whether to turn on or off an oil tank inflation electromagnetic valve (201) and an oil tank deflation electromagnetic valve (301) so as to control the system to be in an inflation or deflation state;
by detecting the state of the aircraft electrical network (104), it is determined whether to open or close the controllable switch (306) and thereby decide whether to feed back the electrical energy in the supercapacitor (305) to the electrical network.
Fig. 7 shows a method for comprehensively utilizing surplus electric power of an aircraft based on the system for comprehensively utilizing surplus electric power of an aircraft using a nitrogen pressurized oil tank according to the present invention, which includes:
A0) after the airplane starts flying, the system starts working, the system is initialized firstly, and each parameter is assigned with an initial value;
A1) detecting the temperature of air introduced into the membrane separator by a temperature sensor (1061), closing a membrane separation system electromagnetic valve (1063) when the temperature exceeds a normal range (55 ℃) acceptable by the hollow fiber type membrane separation system, shutting down a motor (101), keeping the system under no pressure, and keeping an airborne membrane separation system (106) out of work;
A2) when the inlet air temperature of the system is within a normal range, the gas pressure in the fuel tank is detected through a fuel tank pressure sensor (202), the current state of the aircraft power grid (104) is detected through a sensing detection element (103), and the detected signal is input into a controller (105),
A3) the controller (105) judges whether the pressure inside the fuel oil tank (203) exceeds a rated pressure;
A4) if the gas pressure in the fuel oil tank (203) does not exceed the rated pressure, the controller (105) opens the tank charging solenoid valve (201), then judges whether the current aircraft power grid (104) has surplus power or not according to the input signal of the detection element (103),
A5) if the surplus electric power exists, the current surplus electric power Pu is calculated, the input power of the motor (101) is adjusted to force Pu by adjusting the frequency converter (102), and then the motor (101) drives the compressor (1062) to make the N obtained by the onboard membrane separation system2Is compressed into a fuel tank (203),
A6) if the surplus power does not exist, continuously judging whether the aircraft power grid (104) is overloaded currently, if so, jumping to the place before the working process of the air bleeding refrigeration system, opening an oil tank air bleeding electromagnetic valve (301) to start bleeding refrigeration power generation, and enabling the electric energy generated by a generator (304) to supply power to the power grid;
A7) if the aircraft generator is not currently overloaded, processing proceeds to step A8);
A8) the controller (105) judges whether the cooling energy for cooling the electronic equipment air cooling system (303) is insufficient, if the cooling energy is insufficient, the oil tank air bleed solenoid valve (301) is opened to release the gas stored in the fuel oil tank (203), the gas pushes the turbine to do work through the turbine (302) and drives the generator (304) to generate electricity, meanwhile, the gas is changed from high-pressure gas into low-temperature and low-pressure gas which is sent to the electronic equipment air cooling system (303) to cool the electronic equipment, and the generator (304) charges the generated electric energy to the super capacitor (305); if the cold energy is sufficient, the process returns to step A1) and is resumed from A1);
A9) if step A3) judges that the pressure in the fuel oil tank (203) exceeds the rated pressure, a tank air bleed solenoid valve (301) is opened to start air bleed cooling, the gas in the fuel oil tank (203) is released, and the pressure in the fuel oil tank (203) is reduced;
A10) at the end of a work cycle, the process determines whether the current flight of the aircraft is over, and if not, the process returns to step a1) to begin a new cycle; if the flight is over, the process ends.
According to another aspect of the present invention, there is provided an aircraft surplus power integrated utilization method based on an aircraft surplus power integrated utilization system that pressurizes a fuel tank using nitrogen, the aircraft surplus power integrated utilization system including:
a motor (101), a frequency converter (102), a detection element (103), a controller (105), an onboard membrane separation system (106), a fuel tank air pressure sensor (202), a fuel oil tank (203), a turbine (302), a generator (304) and a super capacitor (305),
it is characterized by comprising:
A1) detecting the temperature of the air introduced into the membrane separator, and when the temperature exceeds the acceptable normal range (55 ℃) of the hollow fiber type membrane separation system (1065), shutting down the motor (101) to enable the airborne membrane separation system (106) to be in a non-working state;
A2) when the inlet air temperature of the system is within a normal range, the air pressure inside the oil tank (203) is detected, the current state of the aircraft power grid (104) of the aircraft is detected by using the detection element (103), and the detected signal is input to the controller (105),
A4) when the gas pressure in the fuel oil tank (203) does not exceed the rated pressure, the charging gas path from the airborne membrane separation system (106) to the fuel oil tank (203) is opened, then whether the current aircraft power grid (104) has surplus power or not is judged according to the input signal of the detection element (103),
A5) when the airplane power grid (104) has surplus power, determining the current surplus power Pu, adjusting the frequency converter (102) to enable the input power of the motor (101) to be Pu, driving a compressor (1062) in the airborne membrane separation system (106) by the motor (101) to compress nitrogen produced by the airborne membrane separation system into a fuel oil tank (203),
A6) when the aircraft power grid (104) has no surplus power, judging whether the aircraft power grid (104) is overloaded currently, if the aircraft power grid (104) is overloaded, driving a turbine (302) to drive a generator (304) to generate power by using compressed nitrogen in a fuel oil tank (203), and supplying the power to the aircraft power grid (104) by using the power generated by the generator (304),
A7) if the aircraft electrical grid (104) is not currently overloaded, processing proceeds to step A8);
A8) the controller (105) judges whether the cooling energy for cooling the electronic equipment air cooling system (303) is insufficient, if the cooling energy is insufficient, the turbine (302) is driven by the compressed nitrogen in the fuel oil tank (203) to drive the generator (304) to generate electricity, meanwhile, the compressed nitrogen is changed into low-temperature and low-pressure gas from high-pressure gas, and the low-temperature and low-pressure gas is sent to the electronic equipment air cooling system (303) of the airplane to cool the electronic equipment, and the super capacitor (305) is charged by the electric energy generated by the generator (304); if the cold energy is sufficient, the process returns to step A1) and is resumed from A1).
Claims (9)
1. The utility model provides an utilize surplus electric power of aircraft of nitrogen gas pressure boost oil tank to synthesize utilizes system which characterized in that includes:
a motor (101), a frequency converter (102), a detection element (103), a controller (105), an onboard membrane separation system (106), a fuel tank air pressure sensor (202), a fuel oil tank (203), a turbine (302), a generator (304) and a super capacitor (305),
wherein:
the detection element (103) is used to detect the current state of the aircraft electrical network (104) of the aircraft and, when there is surplus electrical power in the aircraft electrical network (104),
the electric motor (101) is used for converting part or all of surplus electric power in the power grid into mechanical energy under the control of the controller (105), so that the extraction of the surplus electric power of the airplane is completed,
the compressor (1062) in the on-board membrane separation system (106) is driven by said mechanical energy to perform work, compressing the air introduced from outside the aircraft into a high-pressure gas, which is subsequently separated by the on-board membrane separation system (106) into high-pressure oxygen and high-pressure nitrogen,
said high pressure oxygen is delivered to the cabin of the aircraft for supply (107), regulating the pressure and oxygen supply inside the cabin,
the fuel tank (203) is fully utilized for storing the high-pressure nitrogen in the space therein,
the tank air pressure sensor (202) is used for detecting air pressure in a fuel oil tank (203);
the turbine (302) is used for being pushed by high-pressure nitrogen from a fuel oil tank (203), the high-pressure nitrogen pushes the turbine (302) to work and then turns into low-temperature and low-pressure nitrogen, and the low-temperature and low-pressure nitrogen is used for cooling electronic equipment on the airplane by an electronic equipment air cooling system (303),
the generator (304) generates electrical power, driven by the turbine (302), which is supplied to the super capacitor (305) and/or the aircraft electrical grid (104).
2. The comprehensive utilization system of surplus electric power of an aircraft according to claim 1, further comprising:
the oil tank air bleed solenoid valve (301) is used for controlling the on-off of an oil tank air bleed air path and is controlled by the controller (105);
and the controllable switch (306) is used for controlling the connection and disconnection of the super capacitor (305) to the power line of the aircraft power grid (104) and is controlled by the controller (105).
3. The comprehensive utilization system of surplus electric power of an aircraft according to claim 1 or 2, characterized by further comprising:
and the oil tank inflation electromagnetic valve (201) is used for controlling the on-off of an inflation gas path from the airborne membrane separation system (106) to the fuel oil tank (203).
4. The comprehensive utilization system of surplus electric power of an aircraft according to claim 1 or 2, characterized by further comprising:
and the tank air pressure safety valve (204) is used for automatically deflating and releasing pressure when the air pressure of the fuel tank (203) exceeds the safety pressure.
5. The comprehensive utilization method of the surplus electric power of the airplane based on the comprehensive utilization system of the surplus electric power of the airplane utilizing the nitrogen to pressurize the oil tank comprises the following steps:
a motor (101), a frequency converter (102), a detection element (103), a controller (105), an onboard membrane separation system (106), a fuel tank air pressure sensor (202), a fuel oil tank (203), a turbine (302), a generator (304) and a super capacitor (305),
it is characterized by comprising:
A1) detecting the temperature of the air introduced into the membrane separator, and when the temperature is equal to or higher than 55 ℃, shutting down the motor (101) to enable the onboard membrane separation system (106) to be in an idle state;
A2) when the inlet air temperature of the system is lower than 55 ℃, the air pressure in the oil tank is detected, the current state of an aircraft power grid (104) of the aircraft is detected by a detection element (103), and the detected signal is input to a controller (105),
A3) the controller (105) determines whether the pressure inside the fuel tank (203) exceeds a rated pressure,
A4) when the gas pressure in the fuel oil tank (203) does not exceed the rated pressure, the charging gas path from the airborne membrane separation system (106) to the fuel oil tank (203) is opened, then whether the current aircraft power grid (104) has surplus power or not is judged according to the input signal of the detection element (103),
A5) when the airplane power grid (104) has surplus power, determining the current surplus power Pu, adjusting the frequency converter (102) to enable the input power of the motor (101) to be Pu, driving a compressor (1062) in the airborne membrane separation system (106) by the motor (101) to compress nitrogen produced by the airborne membrane separation system into a fuel oil tank (203),
A6) when the aircraft power grid (104) has no surplus power, judging whether the aircraft power grid (104) is overloaded currently, if the aircraft power grid (104) is overloaded, driving a turbine (302) to drive a generator (304) to generate power by using compressed nitrogen in a fuel oil tank (203), and supplying the power to the aircraft power grid (104) by using the power generated by the generator (304),
A7) if the aircraft electrical grid (104) is not currently overloaded, processing proceeds to step A8);
A8) the controller (105) judges whether the cooling energy for cooling the electronic equipment air cooling system (303) is insufficient, if the cooling energy is insufficient, the turbine (302) is driven by the compressed nitrogen in the fuel oil tank (203) to drive the generator (304) to generate electricity, meanwhile, the compressed nitrogen is changed into low-temperature and low-pressure gas from high-pressure gas, and the low-temperature and low-pressure gas is sent to the electronic equipment air cooling system (303) of the airplane to cool the electronic equipment, and the super capacitor (305) is charged by the electric energy generated by the generator (304); if the cold energy is sufficient, the process returns to step A1) and is resumed from A1).
6. The method for comprehensively utilizing surplus electric power of an aircraft according to claim 5, characterized by further comprising:
judging whether the pressure inside the fuel oil tank (203) exceeds the rated pressure by using the controller (105);
when the pressure in the fuel oil tank (203) is judged to exceed the rated pressure, a tank air bleed solenoid valve (301) is opened to start air bleed cooling, and/or air bleed pressure relief is carried out by using an air pressure safety valve (204) of the fuel oil tank (203).
7. The method for comprehensively utilizing surplus power of an aircraft according to claim 5 or 6, characterized by further comprising:
after step A8) is performed, it is determined whether the current flight of the aircraft is finished, and if not, the process returns to step a1) to start a new cycle; if the flight is over, the process ends.
8. The method for comprehensively utilizing surplus electric power of an aircraft according to claim 5 or 6, characterized by comprising the following steps:
the step A1) comprises the following steps: the temperature of the air introduced into the membrane separator is detected by an intake air temperature sensor (1061), and when the temperature is equal to or higher than 55 deg.c, a membrane separation system solenoid valve (1063) is closed,
the step A2) comprises the following steps: the gas pressure inside the fuel tank is detected by a fuel tank pressure sensor (202),
the step A4) comprises the following steps: and opening a tank inflation solenoid valve (201) from the onboard membrane separation system (106) to an inflation gas path of a fuel tank (203).
9. The method for comprehensively utilizing surplus electric power of an aircraft according to claim 5 or 6, characterized by comprising the following steps:
when it is judged in the step A8 that the cooling energy for cooling the electronic equipment air cooling system (303) is insufficient, the compressed nitrogen in the fuel tank (203) drives the turbine (302) to drive the generator (304) to generate power by opening the tank bleed solenoid valve (301) on the gas path from the fuel tank (203) to the turbine (302).
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| CN109373626B (en) * | 2018-09-04 | 2021-01-08 | 北京航空航天大学 | Air expansion refrigerating system with high adaptability based on compressed air energy storage |
| CN112855343B (en) * | 2019-11-28 | 2022-05-06 | 中国航发商用航空发动机有限责任公司 | Aviation power system, liquid nitrogen expansion assembly, aircraft and driving method thereof |
| FR3105298B1 (en) * | 2019-12-20 | 2021-12-03 | Safran Helicopter Engines | AIRCRAFT TURBOGENERATOR, INCLUDING AN IMPROVED OIL SYSTEM |
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