CN115258168B - Hybrid power generation system for unmanned aerial vehicles - Google Patents
Hybrid power generation system for unmanned aerial vehicles Download PDFInfo
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- CN115258168B CN115258168B CN202210997356.1A CN202210997356A CN115258168B CN 115258168 B CN115258168 B CN 115258168B CN 202210997356 A CN202210997356 A CN 202210997356A CN 115258168 B CN115258168 B CN 115258168B
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- 238000010248 power generation Methods 0.000 title claims abstract description 78
- 239000000446 fuel Substances 0.000 claims abstract description 61
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 19
- 238000002485 combustion reaction Methods 0.000 claims description 64
- 239000007789 gas Substances 0.000 claims description 20
- 238000004146 energy storage Methods 0.000 claims description 13
- 230000005284 excitation Effects 0.000 claims description 3
- 230000003313 weakening effect Effects 0.000 claims description 3
- 239000002737 fuel gas Substances 0.000 claims description 2
- 238000012544 monitoring process Methods 0.000 claims 1
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
本发明公开了一种无人飞行器专用混合动力发电系统，其包括微型涡轮发电一体机、发电机控制器、发动机控制器、飞控模块和飞机燃油系统；发电机控制器与微型涡轮发电一体机电性连接，发电机控制器接收发电量的目标指令和微型涡轮发电一体机的反馈信息，并控制微型涡轮发电一体机的输出功率、输出电压和输出电流；发动机控制器控制微型涡轮发电一体机的燃料供给量；飞控模块向发电机控制器和发动机控制器发送操作指令；飞机燃油系统向微型涡轮发电一体机提供燃料。本发明可与飞行器核心控制单元高效协同工作，精准跟随直流电网动态变化，根据飞行器飞控模块需要，随时可以与直流电网进行并网、脱网操作。
The present invention discloses a hybrid power generation system for unmanned aerial vehicles, which includes a micro-turbine generator, a generator controller, an engine controller, a flight control module and an aircraft fuel system; the generator controller is electrically connected to the micro-turbine generator, the generator controller receives the target instruction of the power generation and the feedback information of the micro-turbine generator, and controls the output power, output voltage and output current of the micro-turbine generator; the engine controller controls the fuel supply of the micro-turbine generator; the flight control module sends operation instructions to the generator controller and the engine controller; the aircraft fuel system provides fuel to the micro-turbine generator. The present invention can work efficiently with the aircraft core control unit, accurately follow the dynamic changes of the DC power grid, and can be connected to the DC power grid and disconnected from the grid at any time according to the needs of the aircraft flight control module.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a special hybrid power generation system for an unmanned aerial vehicle.
Background
Electrically driven unmanned aerial vehicles have been rapidly developed in recent years, and have been widely used in a variety of fields and play an important role. However, the propeller of the aircraft needs large working power in the vertical take-off and landing process, so that most of electric energy of batteries on the aircraft is consumed, and the energy mass density of the high-power battery manufactured by the prior art is low, so that the endurance of the aircraft is limited, the air time is short, and larger effective load capacity cannot be provided. In order to increase voyage and emptying time, a simple generator set is added to provide partial energy for the unmanned aerial vehicle, but the engine, the generator and the energy storage unit cannot be fully cooperated, so that the efficiency cannot be exerted to the best. In addition, an alternating current generator is used in the prior art, is converted into direct current through a rectification mode, works in parallel with an energy storage unit and a driving motor, and has the advantages of large current pulsation impact, low power factor, high equipment load and high failure rate of a generator set in the working state of an open loop, incapability of closed loop control, incapability of accurate cooperation with the overall control of an aircraft and incapability of intelligent interaction control.
Disclosure of Invention
The invention provides a special hybrid power generation system for an unmanned aerial vehicle, which can efficiently cooperate with a core control unit of the aerial vehicle to solve the defects in the prior art.
In order to achieve the above purpose, the present invention provides the following technical solutions:
A special hybrid power generation system for an unmanned aerial vehicle comprises a micro turbine power generation integrated machine, a generator controller, an engine controller, a flight control module and an aircraft fuel system. The power generation system comprises a power generation device, a power generation controller, a power generation system and an aircraft fuel system, wherein the power generation controller is electrically connected with the micro turbine power generation integrated machine, receives a target instruction of power generation amount and feedback information of the micro turbine power generation integrated machine, controls output power, output voltage and output current of the micro turbine power generation integrated machine, converts alternating current generated by the micro turbine power generation integrated machine into direct current, controls fuel supply quantity of the micro turbine power generation integrated machine, and sends operation instructions to the power generation system and the power generation system by the aircraft fuel system.
In some embodiments, the hybrid power generation system dedicated for the unmanned aerial vehicle further comprises an energy storage unit electrically connected with the generator controller, wherein at least part of the direct current converted by the generator controller is stored in the energy storage unit.
In some embodiments, the microturbine power generating machine includes a casing, a main shaft, a compressor wheel, a stator, a rotor, a turbine wheel, a compressor housing, and a fuel combustion device. The two ends of the main shaft penetrate through the casing, the main shaft is rotatably connected with the casing, the air compressor impeller is connected with one end of the main shaft, the stator is connected with the casing, the generator controller is electrically connected with the stator, the rotor is arranged on the air compressor impeller, rotates along with the air compressor impeller and enables the stator to generate current, the turbine impeller is connected with the other end of the main shaft, an air inlet is arranged at one end of the air compressor shell, the air compressor shell is arranged on the outer side of the air compressor impeller and the casing, an air inlet channel communicated with the air inlet is arranged between the air compressor shell and the air compressor impeller, the air inlet channel is connected with the fuel combustion device and used for providing gas for the fuel combustion device, the fuel combustion device is used for combusting fuel and the generated gas drives the turbine impeller to rotate around the axis of the main shaft, the air plane fuel system is connected with the fuel combustion device and provides fuel for the fuel combustion device, and/or the air compressor shell and/or the air compressor combustion device are/is fixedly connected with the air compressor shell and the air compressor combustion device.
In some embodiments, the fuel combustion device includes a turbine housing, an oil supply nozzle, and a spark plug. The turbine engine comprises a turbine shell, a turbine impeller, an oil supply nozzle, an engine controller, an air inlet channel, an air hole, an air plug, an oil supply nozzle and an air plug, wherein one end of the turbine shell is connected with the compressor shell, one end of the turbine shell is provided with an air outlet, one end of the turbine shell is far away from the compressor shell, an air outlet is arranged at one end of the turbine shell, the turbine shell is provided with an air outlet, a pressurizing chamber and a combustion chamber are arranged in the turbine shell, one end of the air inlet channel is communicated with the pressurizing chamber, a plurality of air holes enabling the pressurizing chamber to be communicated with the combustion chamber are further formed in the turbine shell, an exhaust channel communicated with the air outlet is arranged between the turbine shell and the turbine impeller, one end of the exhaust channel is communicated with the combustion chamber, the oil supply nozzle and the spark plug are connected with the turbine shell and the engine controller, the oil supply nozzle is further connected with an aircraft fuel system, and one end of the oil supply nozzle and the spark plug is located in the combustion chamber.
In some embodiments, the turbine casing includes a plenum housing and a combustion housing interconnected, the combustion housing being enclosed within the plenum housing, the air holes being disposed on the combustion housing.
In some embodiments, the compressor wheel may be rotated synchronously with the main shaft, which may drive the turbine wheel to rotate synchronously.
In some embodiments, the rotor is a permanent magnet and the stator is a coil structure.
In some embodiments, the casing includes a housing, a flange mount, a cover plate, and a sleeve. The stator is embedded into the machine base, one end of the machine base is opened, the flange mounting plate is detachably connected with the open end of the machine base, a through hole is formed in the flange mounting plate, the cover plate is connected with the flange mounting plate to block the through hole, one end of the shaft sleeve is connected with the machine base, the other end of the shaft sleeve is connected with the cover plate, the main shaft sequentially penetrates through the machine base and the cover plate, the shaft sleeve is sleeved on the main shaft, and the shaft sleeve is rotatably connected with the main shaft.
In some embodiments, the housing is coupled to the compressor housing by fasteners and the flange mount is coupled to the turbine housing by fasteners.
In some embodiments, a bearing is disposed between the sleeve and the spindle.
Compared with the prior art, the invention can efficiently and cooperatively work with an aircraft core control unit, can accurately control the output voltage and current of the micro turbine power generation integrated machine, accurately follows the dynamic change of a direct current power grid, can perform grid connection and grid disconnection operation with the direct current power grid at any time according to the requirements of an aircraft flight control module, is safe and rapid, and the micro turbine power generation integrated machine and a generator controller cooperatively work in a closed loop mode by the flight control module, has small current pulsation impact in the working process, converts mechanical energy into a controllable direct current power supply, can accurately perform direct current grid connection with an energy storage unit, and can adjust the generated energy according to the requirements of the flight control module, realize interconnection and perform power generation working condition planning and execution according to a route strategy.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a micro turbine power generation integrated machine in an embodiment of the invention.
FIG. 2 is a cross-sectional view of a microturbine power generation machine in accordance with an embodiment of the invention.
Fig. 3 is a cross-sectional view of the case of an embodiment of the present invention, illustrating only the upper half, with up-down symmetry.
Fig. 4 is a partially enlarged view at a in fig. 2.
The reference numerals are explained as follows:
In the figure, 100 parts of a micro turbine power generation integrated machine, 200 parts of a generator controller, 300 parts of an engine controller, 400 parts of a flight control module, 500 parts of an aircraft fuel system, 600 parts of an energy storage unit, 1 parts of a casing, 101 parts of a machine base, 102 parts of a flange mounting plate, 103 parts of a cover plate, 104 parts of a shaft sleeve, 2 parts of a main shaft, 3 parts of a gas compressor impeller, 4 parts of a stator, 5 parts of a rotor, 6 parts of a turbine impeller, 7 parts of a gas compressor shell, 8 parts of a fuel combustion device, 801 parts of a turbine shell, 8011 parts of a pressurizing chamber shell, 8012 parts of a combustion chamber shell, 802 parts of a spark plug, 803 parts of an oil supply nozzle, 9 parts of a fastening part, 10 parts of a bearing, 11 parts of a gas inlet, 12 parts of a gas inlet channel, 13 parts of a pressurizing chamber, 14 parts of a gas outlet channel, 15 parts of a gas outlet, 16 parts of a combustion chamber, 17 parts of a gas hole, 18 parts of a bolt.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, based on the examples herein, which are within the scope of the invention as defined by the claims, will be within the scope of the invention as defined by the claims.
Referring to fig. 1-4, the present invention provides a hybrid power generation system dedicated to an unmanned aerial vehicle, which includes a micro turbine power generation integrated machine 100, a generator controller 200, an engine controller 300, a flight control module 400, and an aircraft fuel system 500. The generator controller 200 is electrically connected with the micro turbine power generation integrated machine 100, the generator controller 200 receives a target instruction of power generation and feedback information of the micro turbine power generation integrated machine 100 and controls output power, output voltage and output current of the micro turbine power generation integrated machine 100, the generator controller 200 converts alternating current generated by the micro turbine power generation integrated machine 100 into direct current, the engine controller 300 controls fuel supply quantity of the micro turbine power generation integrated machine 100, the flight control module 400 sends operation instructions to the generator controller 200 and the engine controller 300, and the aircraft fuel system 500 provides fuel for the micro turbine power generation integrated machine 100.
In some embodiments, the hybrid power generation system dedicated for the unmanned aerial vehicle further comprises an energy storage unit 600 electrically connected to the generator controller 200, and at least part of the direct current converted by the generator controller 200 is stored in the energy storage unit 600. In a specific implementation, the energy storage unit 600 may be a lithium battery.
The generator controller 200 in the invention mainly comprises a computer and power electronic devices, a three-phase cable of the micro turbine power generation integrated machine 100 is connected with the end of the motor controller U, V, W, the power electronic devices are controlled by the computer to be transformed, an alternating current power supply is converted into an adjustable direct current power supply, and the adjustable direct current power supply is output from the direct current end and is used in a grid connection with a direct current power grid. The computer receives the target instruction of the generated energy and the feedback information of the sensor on the micro turbine power generation integrated machine 100, and the micro turbine power generation integrated machine 100 is subjected to excitation or field weakening control through the power electronic device after calculation, so that the aim of adjusting output power, output voltage and output current is fulfilled, and the power generation system becomes a controllable and editable direct current power supply.
The generator controller 200 and the engine controller 300 together monitor the operation state of the micro turbine power generation integrated machine 100, and receive the operation instruction of the upper flight control module 400 through the 1553B bus. In order to achieve the above-mentioned purpose of operating command, calculate the condition and parameter that the micro turbine produces the power generation all-in-one 100 to work and need, meet the working condition of the micro turbine produces the power generation all-in-one 100 through the actuating mechanism, and monitor the running state by the sensor, carry on the dynamic regulation after calculating, let the system meet the goal that the flight control module 400 delivers under the best running state.
One or more fuels such as aviation kerosene, natural gas, alcohol and the like are converted into mechanical energy through a micro turbine power generation integrated machine, the micro turbine power generation integrated machine and the generator controller 200 work in a closed loop mode in cooperation with the flight control module 400, the mechanical energy is converted into a controllable direct current power supply, direct current grid connection can be accurately carried out with the energy storage unit 600, and electric energy is provided for an aircraft. The generator controller 200 can adopt a high-speed permanent magnet generator controller 200, can accurately control the output voltage and current of the micro turbine power generation integrated machine 100, accurately follows the dynamic change of the direct current power grid, can perform grid connection and grid disconnection operation with the direct current power grid at any time according to the requirements of the flight control module 400 of the aircraft, and is safe and rapid. After grid connection, the power generation amount can be adjusted according to the requirements of the flight control module 400, interconnection and intercommunication are realized, cooperative work can be realized, and power generation working condition planning and execution can be performed according to the route strategy.
The generator controller 200 in the invention can carry out enhanced excitation or field weakening control on the generator through a computer and a power electronic device, and can regulate the generated energy according to a target value, namely, the uniform power, voltage and current can carry out magnetic field control through a certain magnetic flux angle, so that the generated energy of the micro turbine power generation integrated machine 100 is controllable. The computer in the generator controller 200 can acquire the generating capacity information through a 1553B bus, and can also operate in cooperation with the micro turbine generating integrated machine 100 to create the conditions required by the generating process. When the load of the direct current power grid at the power utilization end changes, the generator controller 200 can also monitor through a sensor and feed back to a computer in the generator controller 200 for operation and adjustment, so that the purpose of accurately adjusting the output quantity along with the dynamic change of the direct current power grid is achieved. The invention has the high-precision controllable power generation assembly, and can quickly realize the functions of grid connection, grid disconnection, dynamic adjustment and the like after calculating and receiving tasks.
The generator controller 200 and the engine controller 300 can calculate the workload required by the micro turbine power generation integrated machine 100 after receiving the instruction of the flight control module 400, optimize the optimal working parameters according to the characteristic table of the micro turbine power generation integrated machine 100, and issue and execute the optimal working parameters so as to optimize the working state of the system.
Referring to fig. 2 to 4, the above-described micro turbine power generation integrated machine 100 includes a casing 1, a main shaft 2, a compressor wheel 3, a stator 4, a rotor 5, a turbine wheel 6, a compressor housing 7, and a fuel combustion device 8. Wherein both ends of the main shaft 2 penetrate through the casing 1, the main shaft 2 is rotatably connected with the casing 1, the main shaft 2 can rotate around the axis of the main shaft 2, the air compressor impeller 3 is connected with the left end of the main shaft 2, the main shaft 2 can drive the air compressor impeller 3 to rotate when rotating, the stator 4 is fixedly connected with the casing 1, the rotor 5 is arranged on the air compressor impeller 3, the rotor 5 rotates along with the air compressor impeller 3 and enables the stator 4 to generate current, the stator 4 is electrically connected with U, V, W ends of the generator controller 200 through a three-phase cable, the rotor 5 is a permanent magnet, the stator 4 is in a coil structure when the air compressor impeller 3 rotates, the rotor 5 rotates relative to the stator 4, the stator 4 cuts a magnetic induction line of the rotor 5 to generate current in the stator 4, the turbine impeller 6 is connected with the right end of the main shaft 2, the turbine impeller 6 drives the main shaft 2 to rotate when rotating, one end of the air compressor shell 7 is provided with an air inlet 11 for entering combustion-supporting gas, the air compressor shell 7 is arranged on the outer side of the air compressor impeller 3 and the casing 1, a channel 12 communicated with the air inlet 11 is arranged between the air compressor shell 7 and the air compressor impeller 3, the air inlet 12 is arranged on the air inlet 3, the blades 3 are arranged on the air inlet channel 12 and the air inlet 12 is arranged in the air inlet channel 8 for combustion-supporting air inlet channel 8 when the combustion-supporting device is connected with the combustion air inlet device (for supplying air to the combustion air inlet device 8 and the combustion air in the air inlet device for air inlet 8 when the combustion air is arranged in the air inlet channel 8 for the combustion device for supplying air for the combustion air inlet device for the combustion air and air inlet device for the combustion air for air inlet 8 in the air inlet device for the combustion device for air intake 12 in the air inlet device, the fuel combustion device 8 is used for combusting fuel and the generated fuel gas drives the turbine wheel 6 to rotate around the axis of the main shaft 2, the aircraft fuel system 500 is connected with the fuel combustion device 8 and supplies fuel to the fuel combustion device 8, and the compressor housing 7 and/or the fuel combustion device 8 are fixedly connected with the casing 1.
The principle of the micro turbine power generation integrated machine 100 in the invention is that high-pressure gas generated by combustion reaction in the fuel combustion device 8 pushes the turbine impeller 6 to rotate in the process of discharging, then the turbine impeller 6 drives the main shaft 2 to rotate, meanwhile, the air compressor impeller 3 fixed on the main shaft 2 rotates along with the main shaft 2, air of the air inlet 11 is sucked into the air inlet channel 12 under the action of blades on the air compressor impeller 3, and the air in the air inlet channel 12 then enters the fuel combustion device 8 so as to provide combustion-supporting gas for the fuel combustion device 8.
In the micro turbine power generation integrated machine 100 provided by the invention, the compressor impeller 3 and the turbine impeller 6 share the same shaft system, so that the current situation that an engine, a generator and a compressor need to be independently designed and produced is broken, functions of the engine, the generator and the compressor are integrated, a speed reducer is not required to be assembled, a transmission mechanism is simpler, the whole length of the shaft system is shorter, the whole size of the generator integrated machine is reduced, the weight is reduced, and the power-weight ratio is improved. When the device is applied to an aircraft, the endurance mileage and the load capacity of the aircraft can be effectively improved, and the overall performance of the aircraft is greatly improved.
In some embodiments, the fuel combustion device 8 includes a turbine casing 801, an oil supply nozzle 803, and a spark plug 802. The left end of the turbine housing 801 is connected with the compressor housing 7, an exhaust port 15 is arranged at one end of the turbine housing 801 far away from the compressor housing 7, a pressurizing chamber 13 and a combustion chamber 16 are arranged in the turbine housing 801, one end of an air inlet channel 12 is communicated with the pressurizing chamber 13, a plurality of air holes enabling the pressurizing chamber 13 to be communicated with the combustion chamber 16 are further formed in the turbine housing 801, an exhaust channel 14 communicated with the exhaust port 15 is arranged between the turbine housing 801 and the turbine impeller 6, blades on the turbine impeller 6 are arranged in the exhaust channel 14, one end of the exhaust channel 14 is communicated with the combustion chamber 16, an oil supply nozzle 803 and a spark plug 802 are connected with the turbine housing 801 and the engine controller 300, one end of the oil supply nozzle 803 and one end of the spark plug 802 are arranged in the combustion chamber 16, the other end of the oil supply nozzle 803 is connected with an oil supply pipeline, the oil supply nozzle 803 is used for injecting atomized fuel into the combustion chamber 16, and the oil supply nozzle 803 is further connected with the aircraft fuel system 500, and the aircraft fuel system 500 supplies fuel to the oil supply nozzle 803. The fuel combustion device 8 is simple in structural design, and is beneficial to further reducing the size of the power generation integrated machine, so that the power ratio is improved.
In some embodiments, as shown in FIG. 2, the turbine casing 801 includes a plenum housing 8011 and a combustion housing 8012 that are connected to each other, the combustion housing 8012 being enclosed within the plenum housing 8011 such that the combustion chamber 16 will be inside the plenum 13 with air holes evenly disposed on the combustion housing 8012. The combustion-supporting gas in the air inlet channel 12 enters the plenum chamber 13 under the action of the compressor impeller 3, the flow speed of the combustion-supporting gas is reduced after the combustion-supporting gas enters the plenum chamber 13, the pressure of the combustion-supporting gas in the plenum chamber 13 is increased, and the combustion-supporting gas enters the combustion chamber 16 through the air holes and is fully mixed with fuel. By arranging the combustion chamber 16 inside the pressurizing chamber 13 and uniformly on the combustion chamber housing 8012, combustion-supporting gas can enter the combustion chamber 16 from different directions, which is beneficial to fully and uniformly mixing the combustion-supporting gas and fuel, and further, the full combustion of the fuel can be realized.
In some embodiments, the compressor wheel 3 and the turbine wheel 6 are fixedly connected to the main shaft 2, the compressor wheel 3 can rotate synchronously with the main shaft 2, the main shaft 2 can drive the turbine wheel 6 to rotate synchronously, and the compressor wheel 3 and the turbine wheel 6 have the same rotation speed.
In some embodiments, the casing 1 includes a housing 101, a flange mount 102, a cover plate 103, and a sleeve 104. The stator 4 is embedded into the left end face of the machine base 101, the right end of the machine base 101 is of an open structure, the flange mounting plate 102 is connected with the open end of the machine base 101 through bolts, through holes are formed in the flange mounting plate 102, the cover plate 103 is connected with the flange mounting plate 102 to seal the through holes in the flange mounting plate 102, the machine base 101, the flange mounting plate 102 and the cover plate 103 jointly form a closed cavity, one end of the shaft sleeve 104 is fixedly connected with the machine base 101 through bolts 18, the other end of the shaft sleeve 104 is fixedly connected with the cover plate 103 through bolts 18, the main shaft 2 sequentially penetrates through the machine base 101 and the cover plate 103, the shaft sleeve 104 is sleeved on the main shaft 2, and the shaft sleeve 104 is rotatably connected with the main shaft 2. In some embodiments, in order to achieve a rotatable connection between the sleeve 104 and the spindle 2, two bearings 10 may be provided between said sleeve 104 and the spindle 2.
In some embodiments, the housing 101 is coupled to the compressor case 7 by fasteners 9 and the flange mount 102 is coupled to the turbine case 801 by fasteners 9. The connecting mode has the advantages of simplicity and rapidness, and is beneficial to improving the assembly efficiency.
The foregoing is merely illustrative of the present invention, and the present invention is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A hybrid power generation system dedicated for an unmanned aerial vehicle, comprising:
the micro turbine power generation integrated machine comprises a sensor, wherein the sensor is used for monitoring the running state of the micro turbine power generation integrated machine;
the energy storage unit is electrically connected with the generator controller, and at least part of direct current converted by the generator controller is stored in the energy storage unit;
the power generator controller is electrically connected with the micro turbine power generation integrated machine and comprises a power electronic device and a computer, the power generator controller converts alternating current generated by the micro turbine power generation integrated machine into direct current and is connected with the energy storage unit in a direct current grid mode, and the power generator controller controls the micro turbine power generation integrated machine to be connected with or disconnected from the direct current grid according to the requirement of the flight control module;
When the micro turbine power generation integrated machine is in the grid-connected state, the computer receives a target instruction of the power generation amount and feedback information of the sensor, and adjusts the output power, the output voltage and the output current of the micro turbine power generation integrated machine through a power electronic device based on excitation control or field weakening control;
An engine controller that controls a fuel supply amount of the micro turbine power generation integrated machine;
A flight control module that sends operation instructions to the generator controller and the engine controller;
An aircraft fuel system that provides fuel to the microturbine power generation all-in-one;
and after receiving the operation instruction sent by the flight control module, the generator controller and the engine controller calculate the workload required by the micro turbine power generation integrated machine, and optimize the working parameters according to the characteristic table of the micro turbine power generation integrated machine.
2. The unmanned aerial vehicle-specific hybrid power generation system of claim 1, wherein the micro turbine power generation all-in-one machine comprises:
A casing;
the two ends of the main shaft penetrate through the casing, and the main shaft is rotatably connected with the casing;
The compressor impeller is connected with one end of the main shaft;
the stator is connected with the casing, and the generator controller is electrically connected with the stator;
the rotor is arranged on the compressor impeller, rotates along with the compressor impeller and enables the stator to generate current;
The turbine impeller is connected with the other end of the main shaft;
The compressor shell is arranged at the outer sides of the compressor impeller and the casing, and an air inlet channel communicated with the air inlet is arranged between the compressor shell and the compressor impeller;
The air inlet channel is connected with the fuel combustion device and is used for providing combustion-supporting gas for the fuel combustion device, and the fuel combustion device is used for combusting fuel and the generated fuel gas drives the turbine impeller to rotate around the axis of the main shaft;
The compressor housing and/or the fuel combustion device are/is fixedly connected with the casing.
3. The unmanned aerial vehicle-specific hybrid power generation system of claim 2, wherein the fuel combustion device comprises:
The turbine shell is provided with a plurality of air holes which enable the pressurizing chamber to be communicated with the combustion chamber, an exhaust channel communicated with the exhaust port is arranged between the turbine shell and the turbine impeller, and one end of the exhaust channel is communicated with the combustion chamber;
The fuel supply device comprises a fuel supply nozzle and a spark plug, wherein the fuel supply nozzle and the spark plug are both connected with the turbine shell and the engine controller, the fuel supply nozzle is also connected with the aircraft fuel system, and one ends of the fuel supply nozzle and the spark plug are positioned in the combustion chamber.
4. The hybrid power system as set forth in claim 3, wherein said turbine housing includes a plenum housing and a combustion housing connected to each other, said combustion housing being enclosed within said plenum housing, said air holes being provided in said combustion housing.
5. The hybrid power generation system special for unmanned aerial vehicle of claim 4, wherein the compressor wheel rotates synchronously with the main shaft, and the main shaft drives the turbine wheel to rotate synchronously.
6. The hybrid power generation system special for unmanned aerial vehicle of claim 5, wherein the rotor is a permanent magnet and the stator is a coil structure.
7. The hybrid power generation system dedicated for an unmanned aerial vehicle according to any one of claims 2 to 6, wherein the casing comprises:
the stator is embedded into the stand, and one end of the stand is open;
the flange mounting plate is detachably connected with the open end of the base, and a through hole is formed in the flange mounting plate;
The cover plate is connected with the flange mounting plate to block the through hole;
one end of the shaft sleeve is connected with the base, and the other end of the shaft sleeve is connected with the cover plate;
The main shaft penetrates through the base and the cover plate in sequence, the shaft sleeve is sleeved on the main shaft, and the shaft sleeve is rotatably connected with the main shaft.
8. The hybrid power system as set forth in claim 7 wherein said housing is connected to said compressor housing by fasteners and said flange mounting plate is connected to said turbine housing by fasteners.
9. The hybrid power generation system special for unmanned aerial vehicle of claim 7, wherein a bearing is provided between the shaft sleeve and the main shaft.
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| CN101592081B (en) * | 2009-06-05 | 2011-06-15 | 中国航空动力机械研究所 | Gas turbine generating engine |
| US9467021B2 (en) * | 2010-02-16 | 2016-10-11 | Sine Waves, Inc. | Engine and induction generator |
| CN102900533A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Micro gas turbine generating device |
| CN105952539A (en) * | 2016-04-22 | 2016-09-21 | 山东元动力科技有限公司 | Micro turbojet engine |
| GB2558228B (en) * | 2016-12-22 | 2020-05-20 | Rolls Royce Plc | Aircraft electrically-assisted propulsion control system |
| CN111216901A (en) * | 2018-11-26 | 2020-06-02 | 本田技研工业株式会社 | Power supply device and flying object |
| CN110985215B (en) * | 2019-12-27 | 2024-05-24 | 西安觉天动力科技有限责任公司 | Integrated system for starting of micro turbojet engine |
| US11820526B2 (en) * | 2020-02-26 | 2023-11-21 | Honda Motor Co., Ltd. | Power supply apparatus for a flying body including a combustion gas and intake air heat exchanger |
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