CN116291872A - All-electric detonation gas turbine system - Google Patents
All-electric detonation gas turbine system Download PDFInfo
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- CN116291872A CN116291872A CN202310183864.0A CN202310183864A CN116291872A CN 116291872 A CN116291872 A CN 116291872A CN 202310183864 A CN202310183864 A CN 202310183864A CN 116291872 A CN116291872 A CN 116291872A
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- 238000005474 detonation Methods 0.000 title claims abstract description 118
- 238000002485 combustion reaction Methods 0.000 claims abstract description 79
- 230000008878 coupling Effects 0.000 claims abstract description 15
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- 238000005859 coupling reaction Methods 0.000 claims abstract description 15
- 239000000779 smoke Substances 0.000 claims abstract description 8
- 239000007789 gas Substances 0.000 claims description 49
- 238000001816 cooling Methods 0.000 claims description 23
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims description 12
- 239000003546 flue gas Substances 0.000 claims description 12
- 238000004146 energy storage Methods 0.000 claims description 10
- 239000000446 fuel Substances 0.000 claims description 10
- 239000003990 capacitor Substances 0.000 claims description 8
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 description 7
- 230000008859 change Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000002457 bidirectional effect Effects 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000003344 environmental pollutant Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- 238000004378 air conditioning Methods 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
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- 230000035939 shock Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
- F02C5/02—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion characterised by the arrangement of the combustion chamber in the chamber in the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
Abstract
The present invention provides an all electric detonation gas turbine system, comprising: the first compressor set comprises a first compressor and a first compressor motor which are connected through a first coupling, the second compressor set comprises a second compressor and a second compressor motor which are connected through a second coupling, and the turbine set comprises a turbine and a turbine motor which are connected through a third coupling; the air inlets of the first air compressor and the second air compressor are respectively communicated with air inlets of the knocking combustion chamber, and the air outlets of the first air compressor are communicated with the air inlets of the knocking combustion chamber; the exhaust port of the second air compressor is communicated with the exhaust port of the detonation combustion chamber and is connected to the turbine together, so that compressed air is mixed with detonation smoke, and the mixed gas pushes the turbine to do work so as to drive the turbine motor to generate electric energy; and the direct current bus is respectively connected with the first compressor motor, the second compressor motor, the turbine motor and the user load. The gas turbine system of the invention can realize the optimal efficiency and stability of the whole system.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to an all-electric detonation gas turbine system.
Background
A gas turbine is a mechanical device that uses gas energy to generate power. It is generally composed of three parts: gas engines, generators and auxiliary equipment. In a gas engine, gas is compressed, mixed with air, and burned at a high temperature. The high temperature gas generated by combustion flows through the piston to enable the piston to move up and down, thereby driving the rotor to rotate. The rotor is provided with a generator, and the generator can rotate when the rotor rotates to generate electric energy. Auxiliary equipment includes cooling systems, oil systems, exhaust systems, etc., which function to assist the gas engine in proper operation. For example, the cooling system may maintain the temperature of the gas engine within a suitable range; the oil circuit system can provide lubricating oil for the gas engine; the exhaust system may then exhaust the exhaust gas produced by the gas engine.
Detonation combustion (detonation combustion) is a combustion technique that achieves combustion by propagation of detonation waves. Detonation waves are shock waves that propagate in a detonation reaction, enabling the reactants and oxygen to react rapidly after contact. Detonation combustion techniques may be used to increase combustion efficiency, reduce pollution, and operate at higher pressures and temperatures. Detonation combustion technology is currently used in the automotive, aerospace and aerospace fields.
The traditional gas turbine mainly improves the overall cycle thermal efficiency of the gas turbine by improving the compressor pressure ratio and the outlet temperature of the combustion chamber, but is limited by the difficulty of material, process and pneumatic design, and the compressor pressure ratio and the outlet temperature of the combustion chamber are difficult to be greatly improved, so that the improvement of the overall power generation efficiency is limited. Meanwhile, the traditional gas turbine also has the problems of high pollutant emission reduction difficulty and the like. Compared with the prior art, the detonation combustion can greatly improve the overall cycle efficiency of the gas turbine and reduce the emission of NOx pollutants. However, knocking combustion is also difficult to start and has a narrow working range.
In addition, in the traditional gas turbine, the compressor, the turbine and the starting generator are rigidly connected through the rotor and always work at the same working rotation speed, meanwhile, the compressor, the turbine and the load power are required to be matched, and the performance of the components is difficult to match, so that under the working condition of a non-design point, the condition that each component works at an optimal efficiency point is difficult to meet, the efficiency of the components is reduced under the working condition of the non-design point, and the efficiency of the whole machine components is low.
In addition, when the load suddenly changes, the traditional gas turbine has slower response speed, voltage and frequency change are easy to cause under the isolated network operation condition, and the stability is poor.
Disclosure of Invention
In view of the foregoing, embodiments of the present application provide an all-electric detonation gas turbine system to achieve the goals of optimal efficiency and optimal stability of the system as a whole.
The embodiment of the application provides the following technical scheme: an all electric detonation gas turbine system comprising:
the first air compressor set comprises a first air compressor and a first air compressor motor, and the first air compressor is connected with the first air compressor motor through a first coupling;
the second air compressor set comprises a second air compressor and a second air compressor motor, and the second air compressor is connected with the second air compressor motor through a second coupling;
a turbomachine comprising a turbine and a turbine motor, the turbine and turbine motor being connected by a third coupling;
the air inlets of the first air compressor and the second air compressor are both filled with air for pressurizing air compression, and the air outlet of the first air compressor is communicated with the air inlet of the detonation combustion chamber, so that the compressed air enters the detonation combustion chamber and is mixed with fuel for detonation combustion; the exhaust port of the second air compressor is communicated with the exhaust port of the detonation combustion chamber and is connected to the turbine together, so that compressed air is mixed with detonation smoke generated by the detonation combustion chamber, and the mixed gas enters the turbine to push the turbine to do work so as to drive the turbine motor to generate electric energy;
and the direct current bus is respectively connected with the first compressor motor, the second compressor motor, the turbine motor and the user load.
According to one embodiment of the present application, the first compressor motor, the second compressor motor, the turbine motor and the user load are connected to the direct current bus via a bi-directional AC-DC circuit, respectively.
According to one embodiment of the application, the energy storage device further comprises a super capacitor energy storage and a battery pack, wherein the super capacitor energy storage and the battery pack are connected with the direct current bus.
According to one embodiment of the present application, the first compressor set includes a plurality of first compressors and a plurality of first compressor motors, and the plurality of first compressors and the plurality of first compressor motors are respectively and independently connected through a plurality of first couplers;
the second compressor unit comprises a plurality of second compressors and a plurality of second compressor motors, and the second compressors and the second compressor motors are respectively and independently connected through a plurality of second couplers.
According to one embodiment of the present application, the turbomachine comprises a plurality of turbines and a plurality of turbine motors, the plurality of turbines and the plurality of turbine motors being independently connected by a plurality of third couplings, respectively; the number of the detonation combustion chambers is a plurality, and is consistent with the number of the turbines, and the exhaust ports of the single detonation combustion chambers are connected with the single turbines.
According to one embodiment of the present application, the number of detonation combustors is plural, and exhaust ports of the detonation combustors are all connected with the turbine through a flue gas main pipe; the turbine is a turbine with adjustable guide vanes.
According to one embodiment of the present application, the system further comprises a first compressed air main pipe and a second compressed air main pipe, wherein a plurality of exhaust ports of the first compressors and a plurality of air inlets of the detonation combustors are connected through the first compressed air main pipe, and a plurality of exhaust ports of the second compressors and a plurality of exhaust ports of the detonation combustors are connected through the second compressed air main pipe.
According to one embodiment of the present application, the air inlet and the air outlet of the detonation combustion chamber are respectively provided with a proportional regulating valve.
According to one embodiment of the application, the detonation combustion chamber adopts any supercharging combustion mode including continuous rotation detonation and pulse detonation.
According to one embodiment of the present application, a detonation combustion cooling system is disposed outside the detonation combustion chamber, and is used for cooling the wall surface of the detonation combustion chamber.
Compared with the prior art, the beneficial effects that above-mentioned at least one technical scheme that this description embodiment adopted can reach include at least:
(1) The compressors and the turbines can respectively work at different rotating speeds and loads, so that the overall efficiency of the system can be optimized.
(2) When the external load changes drastically, such as load shedding, the super capacitor energy storage system works, so that the direct current bus can be stabilized, and the stability of the system is ensured.
(3) The battery pack can ensure long-time overload operation.
(4) Meanwhile, when the external load is too small and the overall efficiency of the gas turbine is low, the gas turbine system can be turned off, and the power supply is simply dependent on the battery pack, so that the efficiency maximization of the system under the long-time condition is ensured.
(5) Aiming at the narrow working range of the detonation combustion chamber, the invention adopts two groups of independent air compressors, and simultaneously the two groups of air compressors can independently adjust the load, the outlet pressure and the temperature, so that the stable working of the detonation combustion chamber under each working condition can be satisfied through the matching of the two groups of air compressors.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, 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 structural view of a first embodiment of an all electric detonation gas turbine system of the present invention;
FIG. 2 is a schematic structural view of a second embodiment of the fully electric detonation gas turbine system of the present invention;
FIG. 3 is a schematic structural view of a third embodiment of the fully electric detonation gas turbine system of the present invention.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The technical solution of the present invention will be clearly and completely described below in detail with reference to the accompanying drawings in combination with the embodiments, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in FIG. 1, an embodiment of the present invention provides an all electric detonation gas turbine system including:
the first air compressor set comprises a first air compressor and a first air compressor motor, and the first air compressor is connected with the first air compressor motor through a first coupling; the second air compressor set comprises a second air compressor and a second air compressor motor, and the second air compressor is connected with the second air compressor motor through a second coupling; a turbomachine comprising a turbine and a turbine motor, the turbine and turbine motor being connected by a third coupling;
the air inlets of the first air compressor and the second air compressor are both filled with air for pressurizing air compression, and the air outlet of the first air compressor is communicated with the air inlet of the detonation combustion chamber, so that the compressed air enters the detonation combustion chamber and is mixed with fuel for detonation combustion; the exhaust port of the second air compressor is communicated with the exhaust port of the detonation combustion chamber and is connected to the turbine together, so that compressed air is mixed with detonation smoke generated by the detonation combustion chamber, and the mixed gas enters the turbine to push the turbine to do work so as to drive the turbine motor to generate electric energy;
and the direct current bus is respectively connected with the first compressor motor, the second compressor motor, the turbine motor and the user load.
According to the mechanical connecting part, the first air compressor set, the second air compressor set and the turbine set are respectively connected by adopting independent couplers, and the three sets can respectively work at different rotating speeds and loads, so that the problem of difficult matching of component performances is avoided, and the overall efficiency of the system can be optimized.
In one embodiment, the first compressor motor, the second compressor motor and the turbine motor are respectively connected with the direct current bus through a bidirectional AC-DC circuit, in addition, the direct current bus is also connected with a user load through the bidirectional AC-DC circuit, and a load end can output three-phase electricity.
The working principle of the embodiment is as follows: after being compressed by the first air compressor, the air enters a detonation combustion chamber and is mixed with fuel to generate detonation combustion, so that high-temperature flue gas is generated. After the air is compressed by the second compressor, the air is mixed with high-temperature flue gas at the outlet of the knocking combustion chamber, the flue gas is cooled and then enters the turbine to apply work, the turbine drives the motor to apply work, and the power is output to the outside, so that electric energy is provided for the compressor motor and the user load through the direct current bus. The compressed air and the detonation gas are mixed to form high-temperature flue gas which is suitable for the turbine, so that the problems that the detonation gas is too high in temperature and the turbine cannot work are solved, the service life and reliability of the turbine are improved, and the cost is reduced.
In one embodiment, the system further comprises a super capacitor energy storage and a battery pack, wherein the super capacitor energy storage and the battery pack are connected with the direct current bus. When the external load changes drastically, such as load shedding, the super capacitor energy storage system works, so that the direct current bus can be stabilized, and the stability of the system is ensured. The battery pack can ensure long-time overload operation. Meanwhile, when the external load is too small and the overall efficiency of the gas turbine is low, the gas turbine system can be turned off, and the power supply is simply dependent on the battery pack, so that the efficiency maximization of the system under the long-time condition is ensured. According to the embodiment, the super capacitor energy storage and the battery pack energy storage are added on the direct current bus, so that power impact can be well absorbed, power balance can be maintained, and the stability of the whole system is improved.
In another embodiment of the present invention, as shown in fig. 2, the first compressor set includes a plurality of first compressors and a plurality of first compressor motors, where the plurality of first compressors and the plurality of first compressor motors are respectively and independently connected through a plurality of first couplers; the second compressor unit comprises a plurality of second compressors and a plurality of second compressor motors, and the second compressors and the second compressor motors are respectively and independently connected through a plurality of second couplers.
The distributed arrangement of the multiple compressors can work under different loads and rotating speeds, so that the problem that when the multiple gas turbine networking is required to operate in large-scale application, the power characteristic of a single gas turbine is limited, and the optimal efficiency of the system is difficult to realize is solved, and the system can provide better and more stable inlet conditions for the detonation combustion chamber and ensure the stable operation of the detonation combustion chamber.
In a preferred aspect of the present embodiment, the turbo-machine group includes a plurality of turbines and a plurality of turbine motors, and the plurality of turbines and the plurality of turbine motors are independently connected through a plurality of third couplings, respectively; the number of the detonation combustion chambers is a plurality, and is consistent with the number of the turbines, and the exhaust ports of the single detonation combustion chambers are connected with the single turbines. In the scheme, each compressor, each turbine and each detonation combustion chamber can be independently opened and closed, and the load of each compressor, each detonation combustion chamber and each turbine can be independently regulated.
In another preferable scheme of the embodiment, as shown in fig. 3, the number of the detonation combustion chambers is multiple, and exhaust ports of the detonation combustion chambers are all connected with the turbine through a flue gas main pipe; the turbine is a turbine with adjustable guide vanes. In the scheme, smoke generated by a plurality of detonation combustors enters a smoke main pipe, and all smoke in the smoke main pipe enters a turbine with an adjustable guide vane to do work so as to drive a generator to generate electricity. The outlet of the flue gas main pipe is connected with a turbine with adjustable guide vanes, and when the working quantity of the detonation combustion chamber changes to change the flue gas flow, the working inlet condition of the turbine is ensured by adjusting the angle of the adjustable turbine guide vanes. Moreover, the turbine inlet can ensure the working efficiency in a large flow change range through the adjustable guide vane structure.
In this embodiment, the air conditioning system further includes a first compressed air manifold and a second compressed air manifold, wherein the exhaust ports of the first compressors are connected to the air inlets of the detonation combustors through the first compressed air manifold, and the exhaust ports of the second compressors are connected to the exhaust ports of the detonation combustors through the second compressed air manifold.
The compressed air main pipe is arranged, so that a part of compressor outlets are connected into the first compressed air main pipe, and a part of compressor outlets are connected into the second compressed air main pipe. The pressure of the first compressed air manifold and the second compressed air manifold may be different or the same. The separation of the first compressed air main and the second compressed air main is beneficial to improving the system efficiency, but all the compressor outlets can be converged into one main pipe.
In this embodiment, the air inlet and the air outlet of the detonation combustion chamber are respectively provided with a proportional regulating valve. Each detonation combustion chamber is connected with a first compressed air main pipe through a proportional control valve, the air-entraining quantity of the single detonation combustion chamber can be adjusted through the proportional control valve, and compressed air of the first compressed air main pipe enters the detonation combustion chamber and is mixed with fuel for detonation combustion, so that high-temperature flue gas is generated. The high-temperature flue gas at the outlet of the detonation combustion chamber is mixed with compressed air from a second compressed air main pipe, the temperature is reduced, the mixed flue gas enters a turbine to do work, and the flow of the mixed cooling gas can be regulated through a proportional regulating valve. Aiming at the problem of narrow working range of the detonation combustion chamber, air and mixed gas are extracted from a compressed air main pipe through a proportional regulating valve, so that the single detonation combustion chamber can always work at an optimal design point.
Because of the relatively high pressure and temperature operating environment within detonation combustors, a cooling system is required to maintain the temperature of the gas engine within a suitable range. Therefore, in the embodiment of the invention, the detonation combustion chamber is provided with the detonation combustion cooling system for cooling the wall surface of the detonation combustion chamber.
In one embodiment, the detonation combustor is cooled using fuel cooling. The concrete structure is as follows: the detonation combustion cooling system comprises a cooling channel which is arranged on the outer wall of the detonation combustion chamber in a surrounding mode, an air inlet of the cooling channel is connected with a fuel input pipeline, and an air outlet of the cooling channel is connected with the detonation combustion chamber, so that fuel enters the cooling channel to cool the wall surface of the detonation combustion chamber and then enters the detonation combustion chamber. Furthermore, a regulating control valve is arranged on a fuel input pipeline connected into the detonation combustion chamber, so that operation control is facilitated.
In another embodiment, the detonation combustor may be cooled using an external liquid cooling cycle. The concrete structure is as follows: the detonation combustion cooling system comprises a cooling channel which is arranged on the outer wall of the detonation combustion chamber in a surrounding mode, circulating cooling liquid is introduced into the cooling channel, and particularly, circulating cooling can be achieved through a circulating pump.
In other embodiments, the above-mentioned structure that multiple cooling modes such as fuel cooling and external liquid cooling circulation are combined can also be adopted, and the control valves are respectively used for independent control on the pipelines, so that the structure can be selectively used according to the high temperature resistance of the detonation combustion chamber.
In embodiments of the present invention, the detonation combustor may be a continuous rotation detonation, pulse detonation, or other form of booster combustion technology.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. An all electric detonation gas turbine system, comprising:
the first air compressor set comprises a first air compressor and a first air compressor motor, and the first air compressor is connected with the first air compressor motor through a first coupling;
the second air compressor set comprises a second air compressor and a second air compressor motor, and the second air compressor is connected with the second air compressor motor through a second coupling;
a turbomachine comprising a turbine and a turbine motor, the turbine and turbine motor being connected by a third coupling;
the air inlets of the first air compressor and the second air compressor are both filled with air for pressurizing air compression, and the air outlet of the first air compressor is communicated with the air inlet of the detonation combustion chamber, so that the compressed air enters the detonation combustion chamber and is mixed with fuel for detonation combustion; the exhaust port of the second air compressor is communicated with the exhaust port of the detonation combustion chamber and is connected to the turbine together, so that compressed air is mixed with detonation smoke generated by the detonation combustion chamber, and the mixed gas enters the turbine to push the turbine to do work so as to drive the turbine motor to generate electric energy;
and the direct current bus is respectively connected with the first compressor motor, the second compressor motor, the turbine motor and the user load.
2. The all electric detonation gas turbine system of claim 1, wherein the first compressor motor, the second compressor motor, the turbine motor, and a user load are each connected to the direct current bus by a bi-directional AC-DC circuit.
3. The all electric detonation gas turbine system of claim 1, further comprising a super capacitor energy storage and a battery, both connected to the dc bus.
4. The all electric detonation gas turbine system of claim 1, wherein the first compressor assembly includes a plurality of first compressors and a plurality of first compressor motors, the plurality of first compressors and the plurality of first compressor motors being independently connected by a plurality of first couplers, respectively;
the second compressor unit comprises a plurality of second compressors and a plurality of second compressor motors, and the second compressors and the second compressor motors are respectively and independently connected through a plurality of second couplers.
5. The all electric detonation gas turbine system of claim 4, wherein the turbomachine includes a plurality of turbines and a plurality of turbine motors, the plurality of turbines and the plurality of turbine motors being independently connected by a plurality of third couplings, respectively; the number of the detonation combustion chambers is a plurality, and is consistent with the number of the turbines, and the exhaust ports of the single detonation combustion chambers are connected with the single turbines.
6. The all electric detonation gas turbine system of claim 4, wherein the number of detonation combustors is a plurality, and wherein the exhaust ports of the plurality of detonation combustors are each connected to the turbine by a flue gas header; the turbine is a turbine with adjustable guide vanes.
7. The all electric detonation gas turbine system of claim 5 or 6, further comprising a first compressed air manifold through which the exhaust ports of the plurality of first compressors and the intake ports of the plurality of detonation combustors are connected and a second compressed air manifold through which the exhaust ports of the plurality of second compressors and the exhaust ports of the plurality of detonation combustors are connected.
8. The all electric detonation gas turbine system of claim 7, wherein the detonation combustor inlet and outlet are each provided with a proportional control valve.
9. The all electric detonation gas turbine system of claim 1, wherein any of a booster combustion regime including continuous rotary detonation, pulse detonation is employed in the detonation combustor.
10. The all-electric detonation gas turbine system of claim 9, wherein a detonation combustion cooling system is disposed outside the detonation combustion chamber for cooling a wall surface of the detonation combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310183864.0A CN116291872A (en) | 2023-02-24 | 2023-02-24 | All-electric detonation gas turbine system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310183864.0A CN116291872A (en) | 2023-02-24 | 2023-02-24 | All-electric detonation gas turbine system |
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| CN116291872A true CN116291872A (en) | 2023-06-23 |
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|---|---|---|---|
| CN202310183864.0A Pending CN116291872A (en) | 2023-02-24 | 2023-02-24 | All-electric detonation gas turbine system |
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| CN (1) | CN116291872A (en) |
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- 2023-02-24 CN CN202310183864.0A patent/CN116291872A/en active Pending
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