CN215646182U - Power supply system for hybrid aircraft - Google Patents
Power supply system for hybrid aircraft Download PDFInfo
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- CN215646182U CN215646182U CN202121654547.5U CN202121654547U CN215646182U CN 215646182 U CN215646182 U CN 215646182U CN 202121654547 U CN202121654547 U CN 202121654547U CN 215646182 U CN215646182 U CN 215646182U
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Abstract
The patent discloses a power supply system for hybrid aircraft belongs to aviation electrical system field for solve the problem that hybrid aircraft high voltage electric network and low voltage electric network fuse, realized efficient electric propulsion on the one hand, reduce fuel consumption by a wide margin, on the other hand utilizes energy memory to realize electric propulsion system and start the power generation technology and combine, has improved the integrated level and the multiplexing ability of system. The power supply system of the present invention includes: an energy storage device, a hybrid generator, a starter generator, a prime mover, an electric propulsion system force and an electric energy distribution system.
Description
Technical Field
The utility model relates to the field of aviation electrical systems, in particular to a power supply system for a hybrid aircraft.
Background
At present, along with the change of the electrification technology of the aviation industry, higher requirements on the green, energy-saving, low-carbon and the like of airplanes are provided, and novel energy forms, hybrid power and electric propulsion technologies become research hotspots in the aviation field. Because aviation fuel oil energy density is higher than the battery, electric propulsion efficiency is higher than the traditional gas turbine, and the hybrid power system is a solution provided by combining the advantages of the aviation fuel oil and the traditional gas turbine. The hybrid power system generally adopts a mode of combining turbine power generation with an energy storage device, can realize optimization of an energy structure and improvement of efficiency, and is a breakthrough point for improvement of efficiency and green aviation of a future aircraft propulsion system.
Disclosure of Invention
The overall efficiency of the traditional gas turbine aircraft engine is generally lower than 40%, and the hybrid power technology combines the gas turbine with the electric power technology, so that efficient electric propulsion can be realized, the fuel consumption is greatly reduced, the noise of an airplane is reduced, and the comfort level of taking an aircraft is improved. However, the introduction of the hybrid system on the basis of the conventional aircraft power grid needs to face many technical challenges, and technical difficulties exist in matching, association and the like with the conventional power grid.
The hybrid power system for the aircraft introduces a hybrid architecture on the basis of the current aircraft configuration technology, completes the fusion design with a conventional power grid by combining the starting power generation technology in the current multi-electrical technology, and optimizes the system multiplexing capability to the maximum extent. The hybrid power aircraft adopts a mode of combining turbine power generation with an energy storage device, a system architecture adopts a series connection mode, the turbine power generation and the energy storage device jointly drive a motor, and the hybrid power aircraft is matched with a traditional engine to generate thrust. The hybrid system generally adopts high-voltage direct current of more than 540V, and the conventional power grid generally adopts low-voltage alternating current of 230VAC/115VAC, so that the system integration is difficult, and the system integration level is influenced.
The utility model discloses a power supply system of a hybrid aircraft, which integrates a hybrid power system with a conventional power grid of the aircraft, realizes high-efficiency electric propulsion and greatly reduces fuel consumption on the one hand, and realizes the combination of the electric propulsion system and a starting power generation technology by utilizing an energy storage device on the other hand, thereby improving the integration level and the multiplexing capability of the system.
The system comprises:
an energy storage device;
a hybrid generator for driving the electric propulsion system;
a starter generator having functions of a motor and a generator, wherein at least 1 starter generator is provided for each engine of the hybrid aircraft;
a starting device for starting the starter generator, wherein at least 1 starting device is arranged on each starter generator of the hybrid aircraft;
a prime mover including a turbine engine for driving the hybrid generator and the starter generator; the prime mover drives the hybrid generator to charge the energy storage device;
the electric propulsion system comprises an inverter, a motor and a ducted fan and is used for receiving electric energy generated by the hybrid generator and the energy storage device to generate thrust;
and the electric energy distribution system is used for isolating the high-voltage loop and the low-voltage loop, distributing electric energy, adjusting and controlling voltage.
Preferably, when the aircraft is in a ground sliding stage or a climbing stage, the prime mover drives the hybrid generator and the starter generator to generate electric energy, and the electric energy generated by the hybrid generator and the electric energy output by the energy storage device are used for driving an electric propulsion system;
preferably, when the aircraft is in a cruising stage, the prime mover drives the hybrid generator to generate electric energy, and the electric energy is charged for the energy storage device and/or drives an electric propulsion system through the electric energy distribution unit; the engine drives the starter generator to charge the energy storage device;
preferably, when the aircraft is in a descent phase, the airflow drives a ducted fan in the electric propulsion system to generate electric energy to charge the energy storage device;
preferably, the energy storage device provides electric energy to the starter generator through a low-voltage loop during a starting phase of the aircraft, and the starter generator drives the engine to run before the engine is ignited.
Preferably, after the aircraft is started, the starter generator provides 230V or 115V ac power to other electrical equipment of the aircraft.
Preferably, the hybrid generator generates a high-voltage direct current of more than 540V to provide high-voltage electric energy for the hybrid aircraft.
Preferably, the output voltage of the energy storage device is lower than 540V.
Preferably, the starter generators are redundant and provide 230V or 115V ac power to other electrical equipment of the aircraft.
Preferably, the starting device receives direct current with voltage lower than 540V for starting the starter generator, and a plurality of starting devices are backup to each other.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the description of the embodiments of the present invention will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without inventive labor.
FIG. 1 is a block diagram of a power supply system for a hybrid aircraft in one embodiment provided by the present invention;
FIG. 2 is a schematic illustration of a normal power mode in a power supply system for a hybrid aircraft in one embodiment provided by the present invention;
FIG. 3 is a schematic illustration of a charging mode in a power supply system for a hybrid aircraft in one embodiment provided by the utility model;
FIG. 4 is a schematic illustration of an electric energy feedback mode in a power supply system for a hybrid aircraft in an embodiment provided by the utility model;
FIG. 5 is a schematic illustration of a startup phase in a power supply system for a hybrid aircraft in one embodiment provided by the present invention;
FIG. 6 is a schematic illustration of a ground propulsion phase of a method of powering a hybrid aircraft according to an embodiment of the present disclosure;
in the above figures, the marked S/G1, S/G2, S/G3 are starting engines, and the marked S/G starts are starting devices;
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In an embodiment provided by the utility model, a power supply system of a hybrid aircraft is disclosed, and a specific implementation manner of the power supply system is described below according to functions and connection relations of components in the power supply system.
The power supply system comprises an energy storage device and a battery with the voltage lower than 540V. On one hand, the starter generator can be driven to provide a starting function through a low-voltage loop, and the starter generator can also be used as a power supply backup. On the other hand, the voltage is boosted through the bidirectional DCDC converter, the bidirectional DCDC converter is matched with the hybrid generator to regulate the voltage, and the electric energy stored in the energy storage device and the electric energy generated by the hybrid generator jointly drive the motor and the ducted fan in the takeoff stage of the airplane. And the electric energy of the hybrid generator can be used for charging the energy storage device in the cruising stage of the airplane.
The power supply system further comprises a hybrid generator for driving the electric propulsion system; the hybrid generator receives the kinetic energy provided by the prime mover and converts the kinetic energy into direct current with the voltage of more than 540V. When the aircraft is in a takeoff climbing stage or a ground sliding stage, the electric energy generated by the hybrid generator provides power for the electric propulsion system. When the aircraft is in the cruising stage, the electric energy generated by the hybrid generator is used for charging the energy storage device through the electric energy distribution unit on one hand, and is used for providing power for the electric propulsion system on the other hand.
The power supply system further comprises a starter generator which has the functions of a motor and a generator, and at least 1 starter generator is arranged on each engine of the hybrid aircraft. In one embodiment provided by the present invention, a hybrid aircraft has 3 engines, 2 of which are used to provide thrust and 1 prime mover which is used to provide a source of power for the hybrid generator. Each engine is provided with 1 starter generator, and 3 starter generators are provided in total. Wherein, the first and the second starter generators (S/G1, S/G2 in figure 1) are driven by the first and the second engines; the third starter generator (S/G3 in FIG. 1) is driven by the prime mover.
When the first starter generator, the second starter generator and the third starter generator are used as generators, 230V or 115V alternating current can be provided, and the first starter generator, the second starter generator and the third starter generator are used for supplying power to conventional loads of an airplane together.
The starting devices are 3 in total and used for receiving direct current with the voltage lower than 540V to start the first to third starter generators, and the three starting devices are redundant and backup.
The first starter generator, the second starter generator, the third starter generator and the fourth starter generator are mutually redundant, are used as motors in the starting stage, receive electric energy output by the energy storage device and drive the engine to run before the engine is ignited.
The power supply system further comprises a prime mover which is a megawatt turbine engine for driving the hybrid generator and the starter generator; the prime mover drives the hybrid generator to charge the energy storage device;
the electric propulsion system comprises an inverter, a motor and a ducted fan and is used for receiving electric energy generated by the hybrid generator and the energy storage device to generate thrust;
and the electric energy distribution system is used for isolating the high-voltage loop and the low-voltage loop, distributing electric energy, adjusting and controlling voltage.
The specific operating mode of the power supply system is described below in the sequence of the individual operating modes of the power system in the hybrid aircraft.
A starting stage: as shown in fig. 5, when the aircraft is in the ground starting stage, the energy storage device drives the starting device of the third starter generator to supply power to the third starter generator through the low-voltage loop, and the third starter generator is used as a motor to start the prime mover, and the first starter generator and the second starter generator can be driven to start the aircraft engine in the same way. After the prime mover and the aircraft engine are started, the first to third starter generators enter a normal power supply mode.
And (3) a normal power supply mode: as shown in fig. 2, when the aircraft is in the takeoff and climb phase, the prime mover drives the hybrid generator and the third starter generator, wherein the third starter generator supplies power to the conventional aircraft power grid, and the hybrid generator and the energy storage device drive the electric motor in the electric propulsion system through the electric energy distribution unit to generate thrust. The first to third starter generators together supply the aircraft's conventional electrical grid.
And (3) charging mode: as shown in fig. 3, when the aircraft is in the cruising phase, the prime mover drives the hybrid generator to charge the energy storage device through the electric energy distribution unit, and to drive the electric motor in the electric propulsion system. The conventional power grid supplied by the first to third starter generators can also charge the energy storage device via the electrical energy distribution unit.
Electric energy feedback: as shown in fig. 4, when the aircraft is in the descent stage and the propeller is in the windmill state, i.e. the ducted fan is driven to rotate by the flowing air, the electric motor enters the power generation mode, and the energy storage device is charged and fed back through the electric energy distribution unit and the bidirectional DCDC.
Ground propulsion: as shown in fig. 6, when the aircraft is in the ground taxiing stage, the hybrid generator can be driven by the prime mover to generate thrust for the electric motor and the propeller, the aircraft performs ground taxiing, and the third starter generator supplies power for the onboard system, so that the aircraft engine can be shut down, and the fuel consumption can be reduced.
The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present invention, and are intended to be included within the scope of the present invention.
Claims (10)
1. An electrical power supply system for a hybrid aircraft, the system comprising:
an energy storage device;
a hybrid generator for driving the electric propulsion system;
a starter generator having functions of a motor and a generator, wherein at least 1 starter generator is provided for each engine of the hybrid aircraft;
a starting device for starting the starter generator, wherein at least 1 starting device is arranged on each starter generator of the hybrid aircraft;
a prime mover including a turbine engine for driving the hybrid generator and the starter generator; the prime mover drives the hybrid generator to charge the energy storage device;
the electric propulsion system comprises an inverter, a motor and a ducted fan and is used for receiving electric energy generated by the hybrid generator and the energy storage device to generate thrust;
and the electric energy distribution system is used for isolating the high-voltage loop and the low-voltage loop, distributing electric energy, adjusting and controlling voltage.
2. The power supply system for a hybrid aircraft of claim 1, wherein the prime mover drives the hybrid generator and the starter generator to generate electrical energy when the aircraft is in a ground taxi phase or a climb phase, the electrical energy generated by the hybrid generator and the electrical energy output by the energy storage device being used to drive an electric propulsion system.
3. The power supply system for a hybrid aircraft according to claim 1, characterized in that the prime mover drives the hybrid generator to generate electric energy, via the electric energy distribution unit, for charging the energy storage device and/or for driving an electric propulsion system, when the aircraft is in cruise phase; the engine drives the starter generator to charge the energy storage device.
4. The power supply system for a hybrid aircraft according to claim 1, characterized in that the air flow drives a ducted fan in the electric propulsion system to generate electric energy to charge the energy storage device when the aircraft is in a descent phase.
5. The power supply system for a hybrid aircraft according to claim 1, characterized in that the energy storage device provides electrical energy to the starter generator via a low-voltage circuit during a start-up phase of the aircraft, the starter generator running the engine before the engine ignites.
6. The power supply system for a hybrid aircraft of claim 1, wherein the starter generator provides 230V or 115V ac power to the other aircraft electrical equipment after the aircraft is started.
7. The power supply system for a hybrid aircraft according to one of claims 1 to 6, characterized in that the hybrid generator generates a high voltage direct current above 540V to provide high voltage electrical energy for the hybrid aircraft.
8. The power supply system for a hybrid aircraft according to one of claims 1 to 6, characterized in that the energy storage device output voltage is lower than 540V.
9. The power supply system for a hybrid aircraft according to one of claims 1 to 6, characterized in that the starter generators are redundant of each other and together provide 230V or 115V AC for the other electrical devices of the aircraft.
10. The power supply system for a hybrid aircraft according to claim 1, wherein the starting device receives direct current at a voltage of less than 540V for starting the starter generator, and a plurality of starting devices are backup to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121654547.5U CN215646182U (en) | 2021-07-20 | 2021-07-20 | Power supply system for hybrid aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121654547.5U CN215646182U (en) | 2021-07-20 | 2021-07-20 | Power supply system for hybrid aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN215646182U true CN215646182U (en) | 2022-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121654547.5U Active CN215646182U (en) | 2021-07-20 | 2021-07-20 | Power supply system for hybrid aircraft |
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| CN (1) | CN215646182U (en) |
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2021
- 2021-07-20 CN CN202121654547.5U patent/CN215646182U/en active Active
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