CN117341958A - Hypersonic aircraft energy supply system oriented to wide speed domain - Google Patents
Hypersonic aircraft energy supply system oriented to wide speed domain Download PDFInfo
- Publication number
- CN117341958A CN117341958A CN202311114579.XA CN202311114579A CN117341958A CN 117341958 A CN117341958 A CN 117341958A CN 202311114579 A CN202311114579 A CN 202311114579A CN 117341958 A CN117341958 A CN 117341958A
- Authority
- CN
- China
- Prior art keywords
- heat
- energy
- recovery device
- heat recovery
- fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000011084 recovery Methods 0.000 claims abstract description 52
- 238000002485 combustion reaction Methods 0.000 claims abstract description 19
- 239000000446 fuel Substances 0.000 claims description 68
- 239000007789 gas Substances 0.000 claims description 48
- 238000002407 reforming Methods 0.000 claims description 46
- 238000010248 power generation Methods 0.000 claims description 32
- 239000000295 fuel oil Substances 0.000 claims description 14
- 239000007787 solid Substances 0.000 claims description 14
- 238000001816 cooling Methods 0.000 claims description 13
- 230000005540 biological transmission Effects 0.000 claims description 7
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- 229910052739 hydrogen Inorganic materials 0.000 claims description 5
- 239000001257 hydrogen Substances 0.000 claims description 5
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims description 3
- 229910002092 carbon dioxide Inorganic materials 0.000 claims description 3
- 239000001569 carbon dioxide Substances 0.000 claims description 3
- 229910002091 carbon monoxide Inorganic materials 0.000 claims description 3
- 125000004435 hydrogen atom Chemical class [H]* 0.000 claims 1
- 239000000203 mixture Substances 0.000 claims 1
- 239000002918 waste heat Substances 0.000 abstract description 2
- 239000007921 spray Substances 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 6
- 238000000605 extraction Methods 0.000 description 4
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 3
- 239000003990 capacitor Substances 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000004146 energy storage Methods 0.000 description 3
- 229910052744 lithium Inorganic materials 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 2
- 102100040255 Tubulin-specific chaperone C Human genes 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 230000003197 catalytic effect Effects 0.000 description 1
- 238000006555 catalytic reaction Methods 0.000 description 1
- 230000019771 cognition Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000006798 recombination Effects 0.000 description 1
- 238000005215 recombination Methods 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 108010093459 tubulin-specific chaperone C Proteins 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention discloses a hypersonic aircraft energy supply system oriented to a wide speed domain, wherein a high-speed aircraft comprises a turbine engine, a ramjet engine, an exhaust tail nozzle and a skin, and the skin is provided with a first heat recovery device; the exhaust tail nozzle is provided with a second heat recovery device, the combustion chamber of the ramjet engine is provided with a third heat recovery device, and the second heat recovery device recovers heat energy to be converted into electric energy in a low-speed stage; during the switching stage, the second heat recovery device recovers heat energy and converts the heat energy into electric energy; in the high-speed stage, the first, second and third heat recovery devices recover heat energy and convert the heat energy into electric energy; and in the unpowered high-speed gliding stage, the first heat recovery device recovers heat energy and converts the heat energy into electric energy. The heat of the skin, the tail spray pipe, the combustion chamber of the ramjet engine and the like is absorbed and waste heat is recovered, so that the high-temperature part is protected, meanwhile, the heat is effectively recovered to generate electric energy, and the electric energy supply is ensured when each speed region of the high-speed aircraft flies under the condition of not adding external power supply equipment.
Description
Technical Field
The invention relates to a hypersonic aircraft, in particular to a hypersonic aircraft energy supply system oriented to a wide-speed domain.
Background
Basic scientific fields such as hypersonic aerodynamics, propulsion, control, materials/structures and the like are broken through in succession, and hypersonic aircrafts (also commonly called high MaMach number aircrafts, cruise speed is more than or equal to 3 Ma) become an important field of development. Wherein the energy consumption requirements of the onboard electromechanical equipment are rapidly increased.
The problems of shortage of onboard energy and impulse load impact of hypersonic aircrafts are very prominent, including in particular: (1) a combined engine (as shown in fig. 2) represented by a turbo ramjet combined TBCC engine, relies on the ramjet engine to provide the thrust required by the aircraft in the high speed range. However, the ramjet engine has no rotating part, and cannot supply work or electric energy by adopting a conventional rotating shaft output work mode in the turbine engine; (2) the combined engine adapts to wide-range flying speed change through different types of engine switching, and corresponding mode switching exists in energy extraction and conversion. The traditional design method based on single energy source is difficult to realize the optimization and comprehensive management of the complex supply system with multiple energy sources; (3) the existing power generation device has overlarge time constant and does not have the capability of rapidly responding to pulses, and if the generator is designed according to the peak power of the system, the motor volume and the weight are overlarge. The existing various ground energy storage schemes and technologies are difficult to directly apply to the design of an efficient energy storage and conversion system facing the energy consumption requirement of an airborne pulse load.
Therefore, the supply mode of hypersonic speed aircraft energy generation exceeds the cognition range of the existing research, the existing architecture scheme is difficult to directly adopt, and the existing model cannot be used for accurately describing and predicting the hypersonic speed aircraft energy generation, so that the targeted basic research work is required to be carried out urgently.
Disclosure of Invention
The invention aims to: in view of the above drawbacks, the present invention provides a hypersonic aircraft energy delivery system for addressing energy shortages that is directed to the wide speed domain.
The technical scheme is as follows: in order to solve the problems, the invention adopts a hypersonic speed aircraft energy supply system facing a wide speed range, the hypersonic speed aircraft comprises a combined power engine, an exhaust tail pipe of the combined power engine and a skin, the combined power engine comprises a turbine engine and a ramjet engine, and the skin is provided with a first heat recovery device for recovering heat on the inner surface of the skin; the exhaust tail nozzle is provided with a second heat recovery device for recovering heat of the outer surface of the exhaust tail nozzle, a combustion chamber of the ramjet engine is provided with a third heat recovery device for recovering heat of the wall surface of the combustion chamber of the ramjet engine, the first heat recovery device, the second heat recovery device and the third heat recovery device are used for converting the recovered heat energy into electric energy, and the turbine engine is connected with the first generator through a gear transmission mechanism;
when the hypersonic aircraft is in a low-speed stage, the turbine engine drives the first generator to generate electric energy through the gear transmission mechanism, and the second heat recovery device recovers heat energy to be converted into electric energy;
when the hypersonic aircraft is in a switching stage, the second heat recovery device recovers heat energy and converts the heat energy into electric energy;
when the hypersonic aircraft is in a high-speed stage, the first heat recovery device, the second heat recovery device and the third heat recovery device recover heat energy and convert the heat energy into electric energy;
the hypersonic aircraft is in the unpowered high-speed gliding stage, and the first heat recovery device recovers heat energy to be converted into electric energy.
Further, the speed range of the hypersonic aircraft in the low speed stage is 0-2Ma, the speed range of the hypersonic aircraft in the switching stage is 2-3Ma, and the speed range of the hypersonic aircraft in the high speed stage is greater than 3Ma.
Further, the first heat recovery device comprises a first simulated heat pipe group, a first fuel reforming device and a power generation group, wherein the first simulated heat pipe group, the first fuel reforming device and the power generation group are arranged on the inner surface of the skin, the cold end of the first simulated heat pipe group is fixed on the inner surface of the skin, the hot end of the first simulated heat pipe group is connected with the first fuel reforming device and used for supplying heat to the first fuel reforming device, and the first fuel reforming device supplies fuel to the power generation group to generate electric energy.
Further, the second heat recovery device comprises a second simulated heat pipe group, a first fuel reforming device and a power generation group, wherein the second simulated heat pipe group, the first fuel reforming device and the power generation group are arranged on the outer surface of the exhaust tail pipe, the cold end of the second simulated heat pipe group is fixed on the outer surface of the exhaust tail pipe, and the hot end of the second simulated heat pipe group is connected with the first fuel reforming device and used for supplying heat to the first fuel reforming device.
Further, the third heat recovery device comprises a cooling channel arranged on the wall surface of the combustion chamber of the ramjet engine, fuel oil introduced into the cooling channel, a second fuel reforming device and a power generation set, wherein the output end of the cooling channel is connected with the input end of the second fuel reforming device, the fuel oil enters the second fuel reforming device to reform after absorbing the heat of the wall surface of the combustion chamber through the cooling channel, and the second fuel reforming device provides fuel for the power generation set to generate electric energy.
Further, the generating set comprises an air storage tank, a first generating device and a second generating device, wherein the output ends of the first fuel reforming device and the second fuel reforming device are connected with the input end of the air storage tank, the air storage tank is used for storing mixed gas after the fuel oil is reformed by the first fuel reforming device and the second fuel reforming device, and the output end of the air storage tank is connected with the first generating device and the second generating device through valves.
Further, the first power generation device comprises a solid oxide fuel cell, and the mixed gas after reforming the fuel oil is introduced into the solid oxide fuel cell to generate electric energy.
Further, the second power generation device comprises an oil gas turbine, a second generator connected with the oil gas turbine and a solid oxide fuel cell, the mixed gas after the fuel oil is reformed is introduced into the oil gas turbine to generate mechanical energy to drive the second generator to generate electric energy, and the mixed gas after the oil gas turbine does work is introduced into the solid oxide fuel cell to generate electric energy.
Furthermore, the second power generation device comprises an oil-gas turbine, a flywheel, a third power generator and a solid oxide fuel cell, wherein the flywheel is connected with an output shaft of the oil-gas turbine through an electromagnetic clutch, the mixed gas after reforming fuel oil is introduced into the oil-gas turbine to generate mechanical energy to drive the flywheel to rotate so as to store the mechanical energy, and after the flywheel and the oil-gas turbine are disconnected through the electromagnetic clutch, the flywheel drives the third power generator to generate electric energy, and the mixed gas after finishing acting on the oil-gas turbine is introduced into the solid oxide fuel cell to generate electric energy.
The beneficial effects are that: compared with the prior art, the invention has the remarkable advantages that the heat is effectively recovered to generate electric energy while protecting high-temperature components by absorbing the heat of the skin, the tail pipe, the combustion chamber of the ramjet engine and the like and recovering the waste heat, and the electric energy supply is ensured when each speed region of the high-speed aircraft flies under the condition of not adding external power supply equipment.
Drawings
Fig. 1 is a schematic diagram of the principal frame of the energy supply system of the present invention.
FIG. 2 is a schematic view of the low speed stage energy supply of the aircraft of the present invention.
FIG. 3 is a schematic view of the high speed stage energy supply of the aircraft of the present invention.
FIG. 4 is a schematic representation of the energy supply of an aircraft in accordance with the present invention to address the multiple, rapid energy extraction requirements of a pulsed load.
Detailed Description
As shown in fig. 1, in the hypersonic speed aircraft energy supply system facing a wide speed range in the embodiment, a high speed aircraft comprises a combined power engine, an exhaust tail pipe of the combined power engine and a skin, wherein the combined power engine comprises a turbine engine and a ramjet engine, and the skin is provided with a first heat recovery device for recovering heat of the inner surface of the skin; the exhaust tail nozzle is provided with a second heat recovery device for recovering heat of the outer surface of the exhaust tail nozzle, the combustion chamber of the ramjet is provided with a third heat recovery device for recovering heat of the wall surface of the combustion chamber of the ramjet, and the first heat recovery device, the second heat recovery device and the third heat recovery device are used for converting recovered heat energy into electric energy, and the turbine engine is connected with the first generator through a gear transmission mechanism.
As shown in fig. 2, when the hypersonic aircraft is in a low-speed stage (mach number 0-2), the ramjet engine does not work in the stage, the turbine engine can directly output mechanical energy through the gear transmission mechanism, and the turbine engine drives the first generator through the gear transmission mechanism to convert the mechanical energy into electric energy, and the second heat recovery device recovers heat energy to convert the electric energy into the electric energy on the basis of providing the electric energy (energy flow path (1)) by the starter generator; the first heat recovery device comprises a first simulated heat pipe group, a first fuel reforming device and a power generation group, wherein the first simulated heat pipe group, the first fuel reforming device and the power generation group are arranged on the inner surface of a skin, the cold end of the first simulated heat pipe group is fixed on the inner surface of the skin, the hot end of the first simulated heat pipe group is connected with the first fuel reforming device, the wall surface of an exhaust tail nozzle is cooled by the first simulated heat pipe group and the heat on the exhaust tail nozzle is conveyed to the first fuel reforming device, the first fuel reforming device is a mixed gas which takes hydrogen as a main component and contains trace methane, carbon monoxide and carbon dioxide after being subjected to catalytic reaction, the mixed gas enters a gas storage tank for storage, one part of the mixed gas is directly introduced into a Solid Oxide Fuel Cell (SOFC) (energy flow path (2)), and the other part of the mixed gas is introduced into an oil-gas turbine for outputting mechanical energy (energy flow path (3)), and the hydrogen after work can be conveyed to the solid oxide fuel cell for power generation or introduced into a combustion chamber for combustion.
When the hypersonic aircraft is in a mode switching stage (Mach number 2-3), the turbofan engine is stopped gradually, the ramjet engine starts to start, the energy flow path (1) is closed, and the second heat recovery device recovers heat energy to be converted into electric energy; the second heat recovery device comprises a second simulated heat pipe group, a first fuel reforming device and a power generation group, wherein the second simulated heat pipe group, the first fuel reforming device and the power generation group are arranged on the outer surface of the exhaust tail pipe, the cold end of the second simulated heat pipe is fixed on the outer surface of the exhaust tail pipe, the hot end of the second simulated heat pipe is connected with the first fuel reforming device, and the heat on the wall surface of the exhaust pipe is absorbed for heat supply of the first fuel reforming device, so that electric energy and mechanical energy are provided through energy flow paths (2) and (3).
As shown in fig. 3, when the hypersonic aircraft is in a high speed stage (mach number 3 to 5, or even higher), the turbofan engine is not operated at this stage, and only the ramjet engine is operated, and the first heat recovery device, the second heat recovery device, and the third heat recovery device recover heat energy to convert it into electric energy; the third heat recovery device comprises a cooling channel arranged on the wall surface of a combustion chamber of the ramjet engine, fuel oil introduced into the cooling channel, a second fuel reforming device and a power generation set, wherein the output end of the cooling channel is connected with the input end of the second fuel reforming device to construct a fuel oil cooling/catalyst integrated multi-layer annular second fuel reforming device, on one hand, a heat sink is obviously promoted through catalytic recombination reaction, the cooling effect of the high-temperature wall surface of the combustion chamber is effectively ensured, on the other hand, more mixed gas mainly comprising hydrogen, trace methane, carbon monoxide and carbon dioxide can be generated, the mixed gas firstly enters a gas storage tank for storage, and part of the mixed gas is directly introduced into a fuel cell for power generation (energy source flow path)
(2) And the other part of the mixed gas is introduced into an oil-gas turbine to output mechanical energy (an energy flow path (3)), and the hydrogen after acting can be transported to a fuel cell for power generation or introduced into a combustion chamber for combustion. .
When the hypersonic aircraft is in an unpowered high-speed gliding stage (part of a flight mission), the turbofan engine and the ramjet engine are stopped at the stage, the heat energy recovered by the first heat recovery device is converted into electric energy, the high-speed aerodynamic heat on the windward surface of the aircraft body is recovered to the first fuel reforming device by the first simulated heat pipe group, and the electric energy is provided through the energy flow path (2).
In order to cope with the multiple and rapid energy extraction requirements of pulse load and the load impact problem caused by the pulse load, a hybrid energy storage mode of oil gas turbine/flywheel/motor/super capacitor/lithium battery fusion is adopted. Under the conventional working condition of the hypersonic aircraft, the redundant energy of the fuel cell and the oil gas turbine is stored by improving the rotation speed of the flywheel, charging the super capacitor and the lithium battery; when the pulse load starts to work, the flywheel and the turbine are disconnected through the electric clutch, and meanwhile, the generator connected with the flywheel runs under load, and the instantaneous high-power extraction is satisfied by comprehensively utilizing the reduction of the rotating speed of the flywheel and the discharge of the super capacitor and the lithium battery through the energy flow path (4).
Claims (10)
1. The hypersonic speed aircraft energy supply system facing the wide speed range comprises a combined power engine, an exhaust tail pipe of the combined power engine and a skin, wherein the combined power engine comprises a turbine engine and a ramjet engine, and the hypersonic speed aircraft energy supply system is characterized in that the skin is provided with a first heat recovery device for recovering heat on the inner surface of the skin; the exhaust tail nozzle is provided with a second heat recovery device for recovering heat of the outer surface of the exhaust tail nozzle, a combustion chamber of the ramjet engine is provided with a third heat recovery device for recovering heat of the wall surface of the combustion chamber of the ramjet engine, the first heat recovery device, the second heat recovery device and the third heat recovery device are used for converting the recovered heat energy into electric energy, and the turbine engine is connected with the first generator through a gear transmission mechanism;
when the hypersonic aircraft is in a low-speed stage, the turbine engine drives the first generator to generate electric energy through the gear transmission mechanism, and the second heat recovery device recovers heat energy to be converted into electric energy;
when the hypersonic aircraft is in a switching stage, the second heat recovery device recovers heat energy and converts the heat energy into electric energy;
when the hypersonic aircraft is in a high-speed stage, the first heat recovery device, the second heat recovery device and the third heat recovery device recover heat energy and convert the heat energy into electric energy;
when the hypersonic aircraft is in an unpowered high-speed gliding stage, the first heat recovery device recovers heat energy and converts the heat energy into electric energy.
2. The hypersonic aircraft energy delivery system of claim 1 wherein the hypersonic aircraft low speed stage has a speed range of 0-2Ma, the hypersonic aircraft switching stage has a speed range of 2-3Ma, and the hypersonic aircraft high speed stage has a speed range of greater than 3Ma.
3. The hypersonic aircraft energy supply system of claim 1 wherein the first heat recovery device comprises a first simulated heat pipe group, a first fuel reforming device and a power generation group, wherein the first simulated heat pipe group is arranged on the inner surface of the skin, the cold end of the first simulated heat pipe group is fixed on the inner surface of the skin, the hot end of the first simulated heat pipe group is connected with the first fuel reforming device for heat supply of the first fuel reforming device, and the first fuel reforming device supplies fuel to the power generation group to generate electric energy.
4. The hypersonic aircraft energy supply system of claim 3 wherein the second heat recovery device comprises a second simulated heat pipe assembly, a first fuel reformer, and a power generation assembly disposed on an outer surface of the exhaust nozzle, a cold end of the second simulated heat pipe assembly being secured to the outer surface of the exhaust nozzle, a hot end of the second simulated heat pipe assembly being connected to the first fuel reformer for heat supply to the first fuel reformer.
5. The hypersonic aircraft energy supply system of claim 4 wherein the third heat recovery device comprises a cooling channel arranged on the wall surface of the combustion chamber of the ramjet engine, fuel oil introduced into the cooling channel, a second fuel reforming device and a power generation group, wherein the output end of the cooling channel is connected with the input end of the second fuel reforming device, the fuel oil absorbs the heat of the wall surface of the combustion chamber through the cooling channel and enters the second fuel reforming device to reform, and the second fuel reforming device supplies fuel to the power generation group to generate electric energy.
6. The hypersonic aircraft energy supply system of claim 5 wherein the power generation unit comprises a gas tank, a first power generation device and a second power generation device, the output ends of the first fuel reforming device and the second fuel reforming device are connected with the input end of the gas tank, the gas tank is used for storing mixed gas after the fuel oil is reformed by the first fuel reforming device and the second fuel reforming device, and the output end of the gas tank is connected with the first power generation device and the second power generation device through valves.
7. The hypersonic aircraft energy delivery system of claim 6 wherein the first power generation device comprises a solid oxide fuel cell and the reformed fuel mixture is fed to the solid oxide fuel cell to generate electrical power.
8. The hypersonic aircraft energy supply system of claim 6 wherein the second power generation device comprises an oil-gas turbine, a second generator connected to the oil-gas turbine, and a solid oxide fuel cell, wherein the mixed gas after reforming the fuel oil is fed into the oil-gas turbine to generate mechanical energy to drive the second generator to generate electric energy, and the mixed gas after finishing the work of the oil-gas turbine is fed into the solid oxide fuel cell to generate electric energy.
9. The hypersonic aircraft energy supply system of claim 6 wherein the second power generation device comprises an oil-gas turbine, a flywheel, a third generator and a solid oxide fuel cell, wherein the flywheel and an output shaft of the oil-gas turbine are connected through an electromagnetic clutch, the mixed gas after reforming fuel oil is introduced into the oil-gas turbine to generate mechanical energy to drive the flywheel to rotate and store mechanical energy, and the flywheel drives the third generator to generate electric energy after disengaging the flywheel and the oil-gas turbine through the electromagnetic clutch, and the mixed gas after finishing working of the oil-gas turbine is introduced into the solid oxide fuel cell to generate electric energy.
10. Hypersonic aircraft energy supply system in accordance with any one of claims 3 to 9 wherein the first and second fuel reformers catalytically reform fuel oil and the reformed mixed gas comprises hydrogen, methane, carbon monoxide and carbon dioxide.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311114579.XA CN117341958A (en) | 2023-08-31 | 2023-08-31 | Hypersonic aircraft energy supply system oriented to wide speed domain |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311114579.XA CN117341958A (en) | 2023-08-31 | 2023-08-31 | Hypersonic aircraft energy supply system oriented to wide speed domain |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117341958A true CN117341958A (en) | 2024-01-05 |
Family
ID=89356397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311114579.XA Pending CN117341958A (en) | 2023-08-31 | 2023-08-31 | Hypersonic aircraft energy supply system oriented to wide speed domain |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117341958A (en) |
-
2023
- 2023-08-31 CN CN202311114579.XA patent/CN117341958A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Sehra et al. | Propulsion and power for 21st century aviation | |
| US8950703B2 (en) | Independent power generation in aircraft | |
| Nøland | Hydrogen Electric Airplanes: A disruptive technological path to clean up the aviation sector | |
| US20120301814A1 (en) | Electrically driven aircraft | |
| Bennabi et al. | Hybrid propulsion systems for small ships: Context and challenges | |
| US20180363564A1 (en) | Hybrid power or thrust generator and vehicle including such a generator | |
| CN112623233B (en) | Self-adaptive power and heat management system for airplane | |
| JP2011520707A (en) | Aircraft powered by a hybrid power source | |
| CN104595032B (en) | A kind of multi-fan super large bypass ratio turbine push system | |
| CN108252807B (en) | Turbo-electric engine propulsion system | |
| Ansell | Hydrogen-Electric Aircraft Technologies and Integration: Enabling an environmentally sustainable aviation future | |
| Seitz et al. | Pre-concept performance investigation of electrically powered aero-propulsion systems | |
| US20220307423A1 (en) | Electric Heating Systems and Methods for Gas Turbine Engines and Jet Engines | |
| CN116526590B (en) | Electric heating integrated system of on-board high-power equipment and management method | |
| CN113446094B (en) | Tail gas power generation system and method for turboshaft turboprop engine | |
| Madavan et al. | Hybrid-electric and distributed propulsion technologies for large commercial transports: a NASA perspective | |
| US20180237130A1 (en) | Aircraft using energy recovery systems | |
| CN117341958A (en) | Hypersonic aircraft energy supply system oriented to wide speed domain | |
| US6846208B1 (en) | Wave rotor based power and propulsion generation for a marine vessel | |
| CN108757218B (en) | Novel thermoelectric cycle combined engine | |
| CN114264199B (en) | General core-level-based combined body recovery rocket overall configuration | |
| CN109178325A (en) | Hydrogen electric stack Electric aircraft | |
| CN110963052A (en) | Distributed propulsion system, aircraft and propulsion method | |
| CN109878687B (en) | Double-engine three-propeller type ship hybrid power system with composite energy storage function | |
| Volchenko et al. | Hybrid and electric propulsion system of aircrafts |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |