CN218431763U - Hybrid power generation system special for unmanned aerial vehicle - Google Patents
Hybrid power generation system special for unmanned aerial vehicle Download PDFInfo
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- CN218431763U CN218431763U CN202222188008.8U CN202222188008U CN218431763U CN 218431763 U CN218431763 U CN 218431763U CN 202222188008 U CN202222188008 U CN 202222188008U CN 218431763 U CN218431763 U CN 218431763U
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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
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- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The utility model discloses a special hybrid power generation system for an unmanned aerial vehicle, which comprises a micro turbine power generation all-in-one machine, a generator controller, an engine controller, a flight control module and an aircraft fuel system; the generator controller is electrically connected with the micro-turbine power generation all-in-one machine, receives a target instruction of generated energy and feedback information of the micro-turbine power generation all-in-one machine, and controls the output power, the output voltage and the output current of the micro-turbine power generation all-in-one machine; the engine controller controls the fuel supply amount of the micro-turbine power generation all-in-one machine; the flight control module sends an operation instruction to the generator controller and the engine controller; the aircraft fuel system provides fuel to the microturbine generator. The utility model discloses can with the high-efficient collaborative work of aircraft core control unit, the accurate direct current electric wire netting dynamic change that follows flies accuse module needs according to the aircraft, can be incorporated into the power networks, off-line operation with direct current electric wire netting at any time.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field, concretely relates to special hybrid power generation system of unmanned vehicles.
Background
The electric drive unmanned aerial vehicle has rapid development in recent years, is widely applied to a plurality of fields and plays an important role. However, in the vertical take-off and landing process, the propeller of the aircraft needs large working power and consumes most of the electric energy of the battery on the aircraft, and the high-power battery manufactured in the prior art has low energy mass density, so that the aircraft has limited endurance, short air-remaining time and further cannot provide large effective load capacity. In order to increase the voyage and the idle time, a simple generator set is added to provide partial energy for the aircraft in the electric drive unmanned aircraft used in some special occasions, but the efficiency cannot be developed to the best due to the insufficient cooperation of the engine, the generator and the energy storage unit. In addition, in the prior art, an alternating current generator is used and is converted into direct current in a rectification mode to be connected with an energy storage unit and a driving motor in parallel for working, the current pulsation impact is large in the working process, the power factor of the generator set is low, the load of equipment is heavy, and the failure rate is high; the generator set is in an open-loop working state, cannot be controlled in a closed-loop mode, cannot be accurately coordinated with the aircraft master control, and cannot be intelligently controlled in an interactive mode.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve prior art not enough, provide one kind can with the high-efficient special hybrid power generation system of unmanned vehicles in coordination of aircraft core control unit.
In order to achieve the above purpose, the utility model provides a following technical scheme:
a hybrid power generation system special for an unmanned aerial vehicle comprises a micro turbine power generation all-in-one machine, a generator controller, an engine controller, a flight control module and an aircraft fuel system. The system comprises a power generator controller, a micro-turbine power generation all-in-one machine, a power generator controller and a power generation control unit, wherein the power generator controller is electrically connected with the micro-turbine power generation all-in-one machine, receives a target instruction of power generation and feedback information of the micro-turbine power generation all-in-one machine, controls output power, output voltage and output current of the micro-turbine power generation all-in-one machine, and converts alternating current generated by the micro-turbine power generation all-in-one machine into direct current; the engine controller controls the fuel supply amount of the micro-turbine power generation all-in-one machine; the flight control module sends an operation instruction to the generator controller and the engine controller; an aircraft fuel system provides fuel to the microturbine generator.
In some embodiments, the hybrid power generation system for the unmanned aerial vehicle further comprises an energy storage unit electrically connected with the generator controller, and at least part of the direct current converted by the generator controller is stored in the energy storage unit.
In some embodiments, the microturbine integrated power generation machine includes a casing, a main shaft, a compressor wheel, a stator, a rotor, a turbine wheel, a compressor casing, and a fuel combustion device. Both 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; an air inlet is formed in one end of the compressor shell, the compressor shell is arranged on the outer sides of the compressor impeller and the casing, and an air inlet channel communicated with the air inlet is formed 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, the fuel combustion device is used for combusting fuel and generating gas for pushing the turbine impeller to rotate around the axis of the main shaft; the aircraft fuel system is connected with the fuel combustion device and provides fuel for the fuel combustion device; the compressor casing and/or the fuel combustion device are fixedly connected with the casing.
In some embodiments, the fuel combustion apparatus includes a turbine casing, an oil supply nozzle, and a spark plug. One end of the turbine shell is connected with the compressor shell, an exhaust port is formed in one end, far away from the compressor shell, of the turbine shell, a pressurizing chamber and a combustion chamber are arranged inside 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 exhaust port is formed between the turbine shell and the turbine impeller, and one end of the exhaust channel is communicated with the combustion chamber; the fuel supply nozzle and the spark plug are connected with the turbine shell and the engine controller, the fuel supply nozzle is further connected with the aircraft fuel system, and one end of the fuel supply nozzle and one end of the spark plug are located in the combustion chamber.
In some embodiments, the turbine housing includes a plenum housing and a combustor housing interconnected, the combustor housing enclosed within the plenum housing, the air holes disposed on the combustor housing.
In some embodiments, the compressor wheel may rotate 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 base, a flange mounting plate, a cover plate, and a sleeve. The stator is embedded into the base, and one end of the base is open; the flange mounting disc is detachably connected with the open end of the base, and a through hole is formed in the flange mounting disc; the cover plate is connected with the flange mounting plate to plug 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 machine 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.
In some embodiments, the frame is coupled to the compressor casing by fasteners and the flange mounting plate is coupled to the turbine casing by fasteners.
In some embodiments, a bearing is disposed between the bushing and the main shaft.
Compared with the prior art, the utility model can efficiently cooperate with the aircraft core control unit, can accurately control the output voltage and current of the micro turbine power generation all-in-one machine, accurately follows the dynamic change of the direct current power grid, can carry out grid connection and disconnection operations with the direct current power grid at any time according to the requirement of the aircraft flight control module, and is safe and rapid; the micro turbine engine and the generator controller cooperate with the flight control module to work in a closed loop mode, the current pulsation impact is small in the working process, the mechanical energy is converted into a controllable direct current power supply, and direct current grid connection can be accurately carried out on the micro turbine engine and the energy storage unit; furthermore, the utility model discloses can carry out the generated energy according to flying accuse module demand and adjust, realize interconnection, can generate electricity operating mode planning and execution according to the airline strategy.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the description below are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is an embodiment of the present invention.
Fig. 2 is a sectional view of a microturbine power generation all-in-one machine according to an embodiment of the present invention.
Fig. 3 is a sectional view of a casing according to an embodiment of the present invention, which is symmetrical in the top and bottom, and only shows the upper half.
Fig. 4 is a partial enlarged view at a in fig. 2.
The reference numerals are illustrated below:
in the figure: 100. a micro turbine power generation all-in-one machine; 200. a generator controller; 300. an engine controller; 400. a flight control module; 500. an aircraft fuel system; 600. an energy storage unit; 1. a case; 101. a machine base; 102. a flange mounting plate; 103. a cover plate; 104. a shaft sleeve; 2. a main shaft; 3. an air compressor impeller; 4. a stator; 5. a rotor; 6. a turbine wheel; 7. a compressor housing; 8. a fuel combustion device; 801. a turbine casing; 8011. a plenum housing; 8012. a combustion chamber housing; 802. a spark plug; 803. an oil supply nozzle; 9. a fastener; 10. a bearing; 11. an air inlet; 12. an air intake passage; 13. a plenum chamber; 14. an exhaust passage; 15. an exhaust port; 16. a combustion chamber; 17. air holes; 18. and (4) bolts.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be described in detail below. It is to be understood that the disclosed embodiments are merely exemplary of the invention, and are not intended to limit the invention to the precise embodiments disclosed. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Referring to fig. 1 to 4, the present invention provides a hybrid power generation system for an unmanned aerial vehicle, which includes a micro turbine generator 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 all-in-one machine 100, the generator controller 200 receives a target instruction of power generation and feedback information of the micro-turbine power generation all-in-one machine 100 and controls output power, output voltage and output current of the micro-turbine power generation all-in-one machine 100, and the generator controller 200 converts alternating current generated by the micro-turbine power generation all-in-one machine 100 into direct current; the engine controller 300 controls the fuel supply amount of the microturbine generator 100; flight control module 400 sends operating commands to generator controller 200 and engine controller 300; the aircraft fuel system 500 provides fuel to the microturbine generator all-in-one 100.
In some embodiments, the hybrid power generation system dedicated to the unmanned aerial vehicle further includes an energy storage unit 600 electrically connected to the generator controller 200, and at least a portion of the dc power 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 utility model provides a generator control ware 200 mainly comprises computer and power electronics, and the three-phase cable of miniature turbine power generation all-in-one 100 links to each other with machine controller U, V, W end, through computer control power electronics transform back, and alternating current power supply converts adjustable DC power supply into, and the use is incorporated into the power networks with the direct current electric wire netting from the output of direct current end. The computer receives a target instruction of the generated energy and sensor feedback information on the micro turbine power generation all-in-one machine 100, and after operation, the micro turbine power generation all-in-one machine 100 is subjected to excitation or field weakening control through a power electronic device, so that the purposes of adjusting output power, output voltage and output current are achieved, and a power generation system becomes a controllable and editable direct-current power supply.
The generator controller 200 and the engine controller 300 jointly monitor the operation state of the microturbine power generation all-in-one machine 100, and receive the operation instruction of the upper flight control module 400 through a 1553B bus. In order to achieve the target of the operation instruction, the conditions and parameters required by the operation of the all-in-one microturbine power generation machine 100 are calculated, the operating conditions of the all-in-one microturbine power generation machine 100 are met through the execution mechanism, the operating state is monitored by the sensor, and dynamic adjustment is performed after calculation, so that the system can meet the target issued by the flight control module 400 in the optimal operating state.
One or more fuels such as aviation kerosene, natural gas and alcohol are converted into mechanical energy through the micro-turbine engine, the micro-turbine engine 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, the controllable direct current power supply can be accurately connected with the energy storage unit 600 in a direct current grid mode, and electric energy is provided for the 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 all-in-one machine 100, accurately follows the dynamic change of a direct current power grid, can carry out grid connection and disconnection operations with the direct current power grid at any time according to the requirements of the aircraft flight control module 400, and is safe and quick. After grid connection, the generated energy can be adjusted according to the requirements of the flight control module 400, interconnection and intercommunication are realized, cooperative work is realized, and planning and execution of power generation working conditions can be performed according to a route strategy.
The utility model provides a generator control ware 200 accessible computer and power electronics device strengthen excitation or weak magnetism control to the generator, can carry out the regulation of generated energy according to the target value, and power, voltage, electric current are even can carry out the control in magnetic field through a certain magnetic flux angle promptly for the generated energy of miniature turbine power generation all-in-one 100 is controllable. The computer in the generator controller 200 can acquire the generated energy information through a 1553B bus, and can also cooperate with the micro turbine generator integrated machine 100 to create the conditions required by the generating process. When the direct current power grid load of the power utilization end changes, the generator controller 200 can also monitor and feed back the change to the computer in the generator controller 200 through the sensor to carry out operation and adjustment, so that the output quantity can be accurately adjusted along with the dynamic change of the direct current power grid. The utility model discloses possessed the controllable electricity generation subassembly of high accuracy, calculated and to realize fast after receiving the task and be incorporated into the power networks, off-network, functions such as dynamic adjustment.
The generator controller 200 and the engine controller 300 can calculate the work load required by the all-in-one microturbine generator 100 after receiving the instruction of the flight control module 400, optimize the optimal working parameters according to the characteristic table of the all-in-one microturbine generator 100, and issue and execute the parameters, so that the working state of the system is optimal.
Referring to fig. 2 to 4, the microturbine 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. The two ends of the main shaft 2 penetrate through the casing 1, the main shaft 2 is rotatably connected with the casing 1, and the main shaft 2 can rotate around the axis of the main shaft; the compressor impeller 3 is connected with the left end of the main shaft 2, and the main shaft 2 can drive the compressor impeller 3 to rotate when rotating; the stator 4 is fixedly connected with the casing 1, the rotor 5 is arranged on the compressor impeller 3, and the rotor 5 rotates along with the compressor impeller 3 and enables the stator 4 to generate current; the stator 4 is electrically connected with the U, V and W ends of the generator controller 200 through a three-phase cable; in specific implementation, the rotor 5 is a permanent magnet, and the stator 4 is a coil structure; when the compressor impeller 3 rotates, the rotor 5 rotates relative to the stator 4, and the stator 4 cuts magnetic induction lines of the rotor 5 so as to generate current in the stator 4; the turbine impeller 6 is connected with the right end of the main shaft 2, and the main shaft 2 is driven to rotate by the turbine impeller 6 when the turbine impeller 6 rotates; one end of the compressor shell 7 is provided with an air inlet 11 for combustion-supporting gas to enter, the compressor shell 7 is arranged at the outer sides of the compressor impeller 3 and the casing 1, an air inlet channel 12 communicated with the air inlet 11 is arranged between the compressor shell 7 and the compressor impeller 3, blades on the compressor impeller 3 are positioned in the air inlet channel 12, and the compressor impeller 3 sucks air at the air inlet 11 into the air inlet channel 12 when rotating; the intake passage 12 is connected to the fuel combustion device 8 and is configured to supply combustion-supporting gas (e.g., air) to the fuel combustion device 8, the fuel combustion device 8 is configured to combust the fuel and generate gas that urges the turbine impeller 6 to rotate about the axis of the main shaft 2; the aircraft fuel system 500 is connected to the fuel combustion device 8 and supplies fuel to the fuel combustion device 8; the compressor housing 7 and/or the fuel combustion device 8 are fixedly connected to the casing 1.
The utility model discloses well miniature turbine power generation all-in-one 100's principle does: high-pressure gas generated by combustion reaction in the fuel combustion device 8 pushes the turbine impeller 6 to rotate in the discharging process, then the turbine impeller 6 drives the main shaft 2 to rotate, meanwhile, the compressor impeller 3 fixed on the main shaft 2 rotates along with the main shaft 2, air in the air inlet 11 is sucked into the air inlet channel 12 under the action of the upper blades of the compressor impeller 3, and then the air in the air inlet channel 12 enters the fuel combustion device 8 so as to provide combustion-supporting gas for the fuel combustion device 8.
The utility model provides an among the miniature turbine power generation all-in-one 100, compressor impeller 3 and turbine impeller 6 share same shafting, have broken the current situation that engine, generator, compressor need independent design production, collect the function of engine, generator, compressor, it need not assemble the speed reducer, and drive mechanism is more simple, and the whole length of shafting is shorter for this generator all-in-one overall dimension reduces, and weight reduction is favorable to improving the power-to-weight ratio. When the aircraft is applied to the 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, fuel combustion apparatus 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, one end of the turbine housing 801, which is far away from the compressor housing 7, is provided with an exhaust port 15, a pressurizing chamber 13 and a combustion chamber 16 are arranged inside the turbine housing 801, one end of an air inlet channel 12 is communicated with the pressurizing chamber 13, the turbine housing 801 is also provided with a plurality of air holes for communicating the pressurizing chamber 13 with the combustion chamber 16, 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 positioned in the exhaust channel 14, and one end of the exhaust channel 14 is communicated with the combustion chamber 16; both the oil supply nozzle 803 and the spark plug 802 are connected to 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 located in the combustion chamber 16, the other end of the oil supply nozzle 803 is connected to an oil supply line, and the oil supply nozzle 803 is used for injecting atomized fuel into the combustion chamber 16; the fuel supply nozzle 803 is also connected to the aircraft fuel system 500, and fuel is supplied to the fuel supply nozzle 803 by the aircraft fuel system 500. The structural design of the fuel combustion device 8 is simple, the size of the power generation all-in-one machine is further reduced, and the power-weight ratio is further improved.
In some embodiments, as shown in fig. 2, the turbine housing 801 includes a plenum housing 8011 and a combustion housing 8012 interconnected, the combustion housing 8012 being enclosed within the plenum housing 8011 such that the combustion chamber 16 will be inside the plenum 13 with the orifices evenly disposed on the combustion housing 8012. The combustion-supporting gas in the air inlet channel 12 enters the pressurizing chamber 13 under the action of the compressor impeller 3, the flow rate of the combustion-supporting gas is reduced after the combustion-supporting gas enters the pressurizing chamber 13, the pressure of the combustion-supporting gas in the pressurizing chamber 13 is increased, and the combustion-supporting gas enters the combustion chamber 16 through the air holes and is fully mixed with the fuel. By having the combustion chamber 16 inside the plenum 13 and being uniformly disposed on the combustion chamber housing 8012, it is possible to achieve that the combustion supporting gas enters the combustion chamber 16 from different directions, which is beneficial to achieve sufficient and uniform mixing of the combustion supporting gas and the fuel, and thus sufficient combustion of the fuel.
In some embodiments, the compressor wheel 3 and the turbine wheel 6 are both 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 rotating speed.
In some embodiments, the casing 1 includes a base 101, a flange mounting plate 102, a cover plate 103, and a sleeve 104. The stator 4 is embedded into the left end face of the base 101, and the right end of the base 101 is of an open structure; the flange mounting disc 102 is connected with the open end of the base 101 through a bolt, a through hole is formed in the flange mounting disc 102, the cover plate 103 is connected with the flange mounting disc 102 to plug the through hole in the flange mounting disc 102, and the base 101, the flange mounting disc 102 and the cover plate 103 jointly form a closed cavity; one end of the shaft sleeve 104 is fixedly connected with the base 101 through a bolt 18, and the other end of the shaft sleeve 104 is fixedly connected with the cover plate 103 through the bolt 18; the main shaft 2 sequentially penetrates through the 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 main shaft 2, two bearings 10 may be provided between said sleeve 104 and the main shaft 2.
In some embodiments, the frame 101 is coupled to the compressor case 7 by fasteners 9 and the flange mounting plate 102 is coupled to the turbine case 801 by fasteners 9. The connecting mode has the advantages of simplicity and quickness, and is beneficial to improving the assembly efficiency.
The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of the changes or substitutions within the technical scope of the present invention, and all should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (12)
1. A hybrid power generation system dedicated to an unmanned aerial vehicle, comprising:
a micro turbine power generation all-in-one machine;
the generator controller is electrically connected with the micro-turbine power generation all-in-one machine, receives a target instruction of generated energy and feedback information of the micro-turbine power generation all-in-one machine, controls output power, output voltage and output current of the micro-turbine power generation all-in-one machine, and converts alternating current generated by the micro-turbine power generation all-in-one machine into direct current;
an engine controller that controls a fuel supply amount of the microturbine-generator integrated machine;
a flight control module that sends operating instructions to the generator controller and the engine controller;
an aircraft fuel system that provides fuel to the microturbine generator all-in-one.
2. The unmanned aerial vehicle-specific hybrid power generation system of claim 1, wherein: 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.
3. The unmanned aerial vehicle-specific hybrid power generation system of claim 1, wherein the microturbine-generator all-in-one comprises:
a case;
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 comprises a compressor shell, wherein one end of the compressor shell is provided with an air inlet, the compressor shell is arranged on the outer sides of a compressor impeller and a casing, and an air inlet channel communicated with the air inlet is arranged between the compressor shell and the compressor impeller;
a fuel combustion device, wherein the air inlet channel is connected with the fuel combustion device and is used for providing combustion-supporting gas for the fuel combustion device, the fuel combustion device is used for combusting fuel and generating gas to drive the turbine impeller to rotate around the axis of the main shaft; the aircraft fuel system is connected with the fuel combustion device and provides fuel for the fuel combustion device;
the compressor casing and/or the fuel combustion device are fixedly connected with the casing.
4. The unmanned aerial vehicle-specific hybrid power generation system of claim 3, wherein the fuel combustion device comprises:
the turbine shell is connected with the compressor shell, an exhaust port is formed in one end, away from the compressor shell, of the turbine shell, a pressurizing chamber and a combustion chamber are arranged inside 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 exhaust port is formed between the turbine shell and the turbine impeller, and one end of the exhaust channel is communicated with the combustion chamber;
the fuel supply nozzle and the spark plug are connected with the turbine shell and the engine controller, the fuel supply nozzle is further connected with the aircraft fuel system, and one end of the fuel supply nozzle and one end of the spark plug are located in the combustion chamber.
5. The unmanned aerial vehicle-specific hybrid power generation system of claim 4, wherein: the turbine casing includes interconnect's plenum housing and combustion chamber shell, the combustion chamber shell is enclosed in the plenum housing, the gas pocket sets up on the combustion chamber shell.
6. The unmanned aerial vehicle-specific hybrid power generation system of claim 3, wherein: the compressor impeller can synchronously rotate along with the main shaft, and the main shaft can drive the turbine impeller to synchronously rotate.
7. The unmanned aerial vehicle-specific hybrid power generation system of claim 3, wherein: the rotor is a permanent magnet, and the stator is of a coil structure.
8. The unmanned aerial vehicle-specific hybrid power generation system of claim 4 or 5, wherein the casing comprises:
the stator is embedded into the base, and one end of the base is open;
the flange mounting disc is detachably connected with the open end of the base, and a through hole is formed in the flange mounting disc;
the cover plate is connected with the flange mounting plate to plug 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 machine 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.
9. The unmanned aerial vehicle-specific hybrid power generation system of claim 8, wherein: the base is connected with the compressor casing through a fastener, and the flange mounting plate is connected with the turbine casing through a fastener.
10. The unmanned aerial vehicle-specific hybrid power generation system of claim 8, wherein: and a bearing is arranged between the shaft sleeve and the main shaft.
11. The unmanned aerial vehicle-specific hybrid power generation system of any one of claims 3, 6, and 7, wherein the casing comprises:
the stator is embedded into the base, and one end of the base is open;
the flange mounting disc is detachably connected with the open end of the base, and a through hole is formed in the flange mounting disc;
the cover plate is connected with the flange mounting plate to plug 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 machine 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.
12. The unmanned aerial vehicle-specific hybrid power generation system of claim 11, wherein: and a bearing is arranged between the shaft sleeve and the main shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202222188008.8U CN218431763U (en) | 2022-08-19 | 2022-08-19 | Hybrid power generation system special for unmanned aerial vehicle |
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| CN202222188008.8U CN218431763U (en) | 2022-08-19 | 2022-08-19 | Hybrid power generation system special for unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115258168A (en) * | 2022-08-19 | 2022-11-01 | 上海翠日航空科技有限公司 | Special hybrid power generation system for unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115258168A (en) * | 2022-08-19 | 2022-11-01 | 上海翠日航空科技有限公司 | Special hybrid power generation system for unmanned aerial vehicle |
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