CN116291873B - A gas turbine with a secondary combustion detonation combustion chamber - Google Patents
A gas turbine with a secondary combustion detonation combustion chamberInfo
- Publication number
- CN116291873B CN116291873B CN202310192652.9A CN202310192652A CN116291873B CN 116291873 B CN116291873 B CN 116291873B CN 202310192652 A CN202310192652 A CN 202310192652A CN 116291873 B CN116291873 B CN 116291873B
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- detonation
- combustion chamber
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- combustion
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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
- F02C7/16—Cooling of plants characterised by cooling medium
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention provides a gas turbine with post-combustion detonation combustor, comprising: the gas turbine main body comprises a generator, a low-pressure compressor, a high-pressure turbine and a low-pressure turbine which are sequentially and coaxially connected through a main shaft; the air inlet of the slow combustion chamber is connected with the air outlet of the low-pressure air compressor, and the air outlet is connected with the air inlet of the high-pressure turbine; the knocking combustion chamber is characterized in that an air inlet of the knocking combustion chamber is connected with an air outlet of the high-pressure turbine, and the air outlet of the knocking combustion chamber is connected with an air inlet of the low-pressure turbine; the air inlet of the low-pressure compressor is connected with the atmosphere, the compressed atmosphere enters a slow combustion chamber to be mixed and combusted with fuel, generated smoke enters a high-pressure turbine to push the high-pressure turbine to do work, the smoke discharged from the high-pressure turbine enters a detonation combustion chamber to be mixed and detonated with the fuel to be combusted, generated detonation smoke enters a low-pressure turbine to push the low-pressure turbine to do work, and the high-pressure turbine and the low-pressure turbine do work to drive a generator to generate electric energy. The invention can effectively improve the overall cycle efficiency of the gas turbine and reduce the pollutant emission.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a gas turbine with a post-combustion detonation combustor.
Background
A gas turbine is a mechanical device that uses gas energy to generate power. It is generally composed of three parts, a gas engine, an electric generator 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 may provide lubrication to the gas engine, and the exhaust system may 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.
When the conventional gas turbine is applied to a combined cycle system, particularly, the flue gas of the gas turbine needs to be led to the exhaust-heat boiler, and when the gas turbine works under variable working conditions, the exhaust temperature changes along with the working conditions, so that the temperature and the flow rate of the flue gas entering the exhaust-heat boiler cannot be ensured to be always at the optimal efficiency points of the exhaust-heat boiler and the downstream steam turbine.
When the gas turbine is applied to combined cooling heating and power, the problem that the heat value of the flue gas cannot be matched with the requirements of cooling and heating well when the gas turbine meets the requirements of electric power is also existed.
Disclosure of Invention
In view of the above, the embodiment of the application provides a gas turbine with an afterburning detonation combustor, which can be used for adjusting the outlet temperature of a gas turbine in a larger range by adjusting the afterburning detonation combustor in a high-pressure turbine and a low-pressure turbine in a combined gas turbine-steam cycle system, ensuring that a downstream waste heat boiler works in a more efficient working area in the combined gas turbine-steam cycle system, and can be used for adjusting the flue gas heat in a larger range by adjusting the power of the afterburning detonation combustor in the combined gas turbine cooling, heating and cooling.
The embodiment of the application provides a gas turbine with a post-combustion detonation combustor, which comprises the following technical scheme:
The gas turbine main body comprises a generator, a low-pressure compressor, a high-pressure turbine and a low-pressure turbine which are sequentially and coaxially connected through a main shaft;
The air inlet of the slow combustion chamber is connected with the air outlet of the low-pressure air compressor, and the air outlet of the slow combustion chamber is connected with the air inlet of the high-pressure turbine;
The air inlet of the detonation combustion chamber is connected with the air outlet of the high-pressure turbine, and the air outlet of the detonation combustion chamber is connected with the air inlet of the low-pressure turbine;
The air inlet of the low-pressure compressor is connected with the atmosphere and is used for compressing and pressurizing the atmosphere, the compressed atmosphere enters the slow combustion chamber and is mixed with fuel for combustion, the generated flue gas enters the high-pressure turbine to push the high-pressure turbine to do work;
the high-pressure turbine and the low-pressure turbine do work to drive the generator to generate electric energy.
According to one embodiment of the application, a detonation combustion cooling system is arranged outside the detonation combustion chamber and used for cooling the wall surface of the detonation combustion chamber.
According to one embodiment of the application, the detonation combustion cooling system comprises a cooling channel which surrounds the outer wall of the detonation combustion chamber, an air inlet of the cooling channel is connected with an air outlet of the low-pressure compressor, the air outlet of the cooling channel is connected with the air outlet of the detonation combustion chamber, so that the air compressed by the low-pressure compressor cools the wall surface of the detonation combustion chamber in the cooling channel, and then the air is mixed with high-speed high-pressure flue gas generated by detonation in an exhaust section of the detonation combustion chamber and discharged to the low-pressure turbine.
According to one embodiment of the application, the detonation combustion cooling system comprises a cooling channel which surrounds the outer wall of the detonation combustion chamber, wherein an air inlet of the cooling channel is connected with a fuel input pipeline, and an air outlet of the cooling channel is respectively connected with the slow combustion chamber and 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 slow combustion chamber and the detonation combustion chamber respectively.
According to one embodiment of the application, the detonation combustion cooling system comprises a cooling channel which surrounds the outer wall of the detonation combustion chamber, and circulating cooling liquid is introduced into the cooling channel.
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 application, regulating control valves are respectively arranged on fuel input pipelines connected into the slow combustion chamber and the knocking combustion chamber.
According to one embodiment of the application, the gas turbine is in a motor working mode during starting, and is in a generator working mode during low working conditions and normal working conditions.
According to one embodiment of the application, the detonation combustor is not operated when the power generation and the heat of smoke emission of the slow combustion combustor meet the requirements, and is operated when the power is met and the heat of smoke emission does not meet the system requirements.
The embodiment of the invention adopts a structure that a traditional slow combustion chamber is used for front combustion and a detonation combustion chamber is used for rear afterburning, smoke generated by the combustion of the traditional slow combustion chamber drives a high-pressure turbine rotor to rotate, smoke generated by the detonation combustion of the detonation combustion chamber drives a low-pressure turbine rotor to rotate, the high-pressure turbine and the low-pressure turbine jointly do work, and the power generation efficiency of the whole combustion engine is improved. The traditional slow combustion chamber is mainly used for stable operation of the gas turbine, stable inlet air conditions are provided for the detonation combustion chamber, and partial power generation is realized according to working condition requirements. The post-combustion detonation combustor is mainly used for generating electricity with high efficiency and low pollution, improves the power generation efficiency of the whole combustion engine and reduces the emission of the whole pollutants.
Compared with the prior art, the at least one technical scheme adopted by the embodiment of the specification has the advantages that compared with a traditional slow combustion gas turbine, the after-combustion is carried out by adopting the knocking combustion chamber, the overall circulation efficiency of the gas turbine is effectively improved, the emission of the overall pollutants is reduced, meanwhile, the excessive oxygen after the slow combustion is adopted as the inlet oxygen of the knocking combustion chamber, a stable inlet air condition is provided for the knocking combustion chamber, and the problems that the pure knocking gas turbine is difficult to start, unstable in continuous operation and the like are solved. On the basis, the matching of the flue gas outlet temperature and flow with the waste heat boiler under the condition of combined cycle of the gas turbine and the steam is satisfied in a larger range, the matching of electricity, heat and cold under the condition of combined cooling, heating and power of the gas turbine is satisfied in a larger range, and meanwhile, the energy utilization rate of the system is improved.
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 can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a conventional gas turbine engine;
FIG. 2 is a schematic view of a gas turbine engine according to an embodiment of the present invention.
Detailed Description
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The technical solution of the present application 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 application, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
As shown in FIG. 1, FIG. 1 is a schematic view of a conventional gas turbine engine configuration. The mechanical connection structure is that a generator, a low-pressure air compressor, a high-pressure air compressor and a turbine are connected through a main shaft. When the gas turbine is started, the generator is in a motor working mode, the low-pressure compressor, the high-pressure compressor and the turbine are driven to rotate, and under the power generation working condition, the turbine pushes the low-pressure compressor, the high-pressure compressor and the motor to rotate, and the motor outputs power outwards. The low-pressure compressor sucks air, the air enters the high-pressure compressor after being pressurized, the high-pressure compressor enters the combustion chamber to be mixed with fuel for combustion after being further pressurized, and the generated high-temperature flue gas pushes the turbine to do work so as to drive the low-pressure compressor, the high-pressure compressor and the motor.
However, the whole power generation efficiency of the traditional gas turbine is difficult to improve, and the pollutant emission reduction difficulty is high. Based on the problems, the invention adopts the structure that the traditional slow combustion chamber burns before and the knocking combustion chamber burns after, so as to solve the problems of the prior knocking combustion engine, difficult starting, unstable continuous operation and the like.
As shown in FIG. 2, an embodiment of the present invention provides a gas turbine with an afterburned detonation combustor, comprising:
The gas turbine main body comprises a generator, a low-pressure compressor, a high-pressure turbine and a low-pressure turbine which are sequentially and coaxially connected through a main shaft;
the combustion device comprises a low-pressure compressor, a low-pressure turbine, a detonation combustion chamber, a low-pressure turbine, a low-pressure combustion chamber and a low-pressure combustion chamber, wherein an air inlet of the low-pressure compressor is connected with an air outlet of the low-pressure compressor, and an air outlet of the low-pressure combustion chamber is connected with an air inlet of the high-pressure turbine;
The low-pressure compressor is characterized in that an air inlet of the low-pressure compressor is connected with the atmosphere and is used for compressing and pressurizing the atmosphere, the compressed atmosphere enters the slow combustion chamber and is mixed with fuel for combustion, generated smoke enters the high-pressure turbine and pushes the high-pressure turbine to do work, smoke discharged from the high-pressure turbine enters the detonation combustion chamber and is mixed with fuel for detonation combustion, generated detonation smoke enters the low-pressure turbine and pushes the low-pressure turbine to do work, and the high-pressure turbine and the low-pressure turbine do work to drive the generator to generate electric energy.
According to the embodiment of the invention, the two-stage turbine structure of the high-pressure turbine and the low-pressure turbine is arranged, the two-stage turbine can achieve higher efficiency, and the flue gas enters the second-stage low-pressure turbine again to do work after the first-stage high-pressure turbine expands to do work. The high-pressure turbine and the low-pressure turbine refer to turbine inlet pressure, the high-pressure turbine is in front, the pressure of the combustion flue gas is reduced after the combustion flue gas expands, and the combustion flue gas enters a second-stage turbine at the back, so the second-stage turbine is called a low-pressure turbine.
The knocking combustion chamber does not work when the power generation power and the smoke emission heat of the slow combustion chamber meet the requirements, and starts to work and perform afterburning when the power generation power and the smoke emission heat of the slow combustion chamber meet the requirements and the smoke emission heat of the slow combustion chamber do not meet the system requirements.
The structure of the embodiment of the invention is arranged and the working principle is that a generator, a low-pressure air compressor, a high-pressure turbine and a low-pressure turbine are connected through a main shaft at a mechanical connecting part and work at the same rotating speed. In the low working condition, the generator is in a generator working mode, the high-pressure turbine and the low-pressure turbine push the low-pressure air compressor and the generator to rotate, and the generator outputs power outwards. The gas turbine is not operated in the process of starting and under low working conditions. The gas turbine is in a normal working state, the generator is in a generator working mode, the high-pressure turbine and the low-pressure turbine push the low-pressure compressor and the generator to rotate, the generator outputs power outwards, and meanwhile, in the normal working state, the detonation combustion chamber for afterburning works, the temperature and the pressure of gas entering the low-pressure turbine are further improved, and the low-pressure turbine is driven to do work.
The air in the atmosphere is pressurized by the low-pressure compressor, enters the slow combustion chamber, is mixed with fuel and combusted, and then the generated flue gas enters the high-pressure turbine to do work.
The temperature of the outlet of the traditional slow combustion chamber is mainly limited by the temperature resistance of the combustion chamber materials and the downstream turbine, so that the temperature of the outlet combustion flue gas generally works between 1000 and 1700K, and when the combustion equivalent ratio is equal to 1, the temperature of the flue gas generated by the complete reaction of the fuel and the oxygen in the air is more than 2200K, so that the combustion equivalent ratio in the traditional slow combustion chamber is less than 1, the flue gas entering the high-pressure turbine contains a large amount of oxygen, the temperature and the pressure of the combusted flue gas are reduced after the high-pressure turbine works, the combusted flue gas enters the detonation combustion chamber for afterburning, and the combusted flue gas is mixed with the fuel again to be combusted, so that the temperature and the pressure of the flue gas are promoted again, and the flue gas enters the low-pressure turbine is pushed to work and then is discharged into the atmosphere. The detonation combustor is adopted for afterburning, so that the overall circulation efficiency of the gas turbine is effectively improved, the emission of overall pollutants is reduced, stable inlet air conditions are provided for the detonation combustor, and the problems of difficult starting, unstable continuous operation and the like of the pure detonation combustor are solved. On the basis, the matching of the flue gas outlet temperature and flow with the waste heat boiler under the condition of combined cycle of the gas turbine and the steam is satisfied in a larger range, the matching of electricity, heat and cold under the condition of combined cooling, heating and power of the gas turbine is satisfied in a larger range, and meanwhile, the energy utilization rate of the system is improved.
Because of the relatively high pressure and temperature operating environment within the detonation combustion chamber, a cooling system is provided 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 air discharged from a low pressure compressor. The detonation combustion cooling system comprises a cooling channel which surrounds the outer wall of the detonation combustion chamber, an air inlet of the cooling channel is connected with an air outlet of the low-pressure air compressor, the air outlet of the cooling channel is connected with the air outlet of the detonation combustion chamber, so that the air compressed by the low-pressure air compressor cools the wall surface of the detonation combustion chamber in the cooling channel, and then the air is mixed with high-speed high-pressure flue gas generated by detonation in an exhaust section of the detonation combustion chamber and discharged to enter a low-pressure turbine to do work.
Because the detonation combustor is arranged at the outlet of the high-pressure turbine, the inlet pressure of the detonation combustor is smaller than the inlet pressure of the high-pressure turbine and the outlet pressure of the low-pressure compressor, and the outlet pressure of the detonation combustor after detonation combustion is still lower than the outlet pressure of the low-pressure compressor although the outlet pressure of the detonation combustor rises to some extent. Therefore, after cooling the detonation combustor, the air at the outlet of the low-pressure compressor can be mixed with the flue gas at the outlet of the detonation combustor, so that the temperature of the flue gas at the outlet of the detonation combustor is reduced, and high-temperature flue gas which is suitable for the low-pressure turbine and acceptable is formed, so that the low-pressure turbine is protected.
In another embodiment, the detonation combustor is cooled using fuel cooling. 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, an air outlet of the cooling channel is connected with the slow combustion chamber and the detonation combustion chamber respectively, so that fuel enters the cooling channel to cool the wall surface of the detonation combustion chamber and then enters the slow combustion chamber and the detonation combustion chamber respectively. Furthermore, the fuel input pipelines connected into the slow combustion chamber and the knocking combustion chamber are respectively provided with an adjusting control valve, so that the operation control is facilitated.
In another embodiment, the detonation combustor may be cooled using an external liquid cooling cycle. The detonation combustion cooling system comprises a cooling channel which is arranged around the outer wall of the detonation combustion chamber, circulating cooling liquid is introduced into the cooling channel, and circulating cooling can be realized through a circulating pump.
In other embodiments, the structure that the air cooling, the fuel cooling, the external liquid cooling circulation and other cooling modes discharged by the low-pressure air compressor are combined can be adopted, the pipeline is independently controlled through the control valve, and the structure can be selected for use 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.
In the embodiment of the invention, a structure that a traditional slow combustion chamber is used for front combustion and a detonation combustion chamber is used for rear afterburning is adopted, wherein the traditional slow combustion chamber is mainly responsible for the stable operation of a gas turbine, provides stable inlet air conditions for the detonation combustion chamber, and simultaneously realizes partial power generation according to working condition requirements. The detonation combustion chamber is mainly responsible for high-efficiency and low-pollution power generation, so that the power generation efficiency of the whole combustion engine is improved, and the emission of whole pollutants is reduced. And solves the problems of difficult starting, unstable continuous operation and the like of the pure detonation combustion engine.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the application is subject to the protection scope of the claims.
Claims (7)
1. A gas turbine with post-combustion detonation combustor, comprising:
The gas turbine main body comprises a generator, a low-pressure compressor, a high-pressure turbine and a low-pressure turbine which are sequentially and coaxially connected through a main shaft;
The air inlet of the slow combustion chamber is connected with the air outlet of the low-pressure air compressor, and the air outlet of the slow combustion chamber is connected with the air inlet of the high-pressure turbine;
The air inlet of the detonation combustion chamber is connected with the air outlet of the high-pressure turbine, and the air outlet of the detonation combustion chamber is connected with the air inlet of the low-pressure turbine;
The air inlet of the low-pressure compressor is connected with the atmosphere and is used for compressing and pressurizing the atmosphere, the compressed atmosphere enters the slow combustion chamber and is mixed with fuel for combustion, the generated flue gas enters the high-pressure turbine to push the high-pressure turbine to do work;
The high-pressure turbine and the low-pressure turbine do work to drive the generator to generate electric energy;
The detonation combustion chamber is provided with a detonation combustion cooling system outside for cooling the wall surface of the detonation combustion chamber;
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 an air outlet of the low-pressure air compressor, the air outlet of the cooling channel is connected with the air outlet of the detonation combustion chamber, so that the air compressed by the low-pressure air compressor cools the wall surface of the detonation combustion chamber in the cooling channel, and then the air outlet section of the detonation combustion chamber is mixed with high-speed high-pressure flue gas generated by detonation and discharged to the low-pressure turbine.
2. The gas turbine with post-combustion detonation combustor of claim 1, wherein the detonation combustion cooling system comprises a cooling channel surrounding an outer wall of the detonation combustor, an air inlet of the cooling channel is connected with a fuel input pipeline, an air outlet of the cooling channel is respectively connected with the slow combustion combustor and the detonation combustor, and fuel enters the cooling channel to cool a wall surface of the detonation combustor and then enters the slow combustion combustor and the detonation combustor respectively.
3. The gas turbine with post-combustion detonation combustor of claim 1, wherein the detonation combustion cooling system includes a cooling channel disposed about an outer wall of the detonation combustor, the cooling channel being vented with a circulating coolant.
4. The gas turbine with post combustion detonation combustor of claim 1, wherein any of a booster combustion regime including continuous rotary detonation, pulse detonation is employed in the detonation combustor.
5. The gas turbine with post-combustion detonation combustor of claim 1, wherein regulating control valves are provided on fuel input lines to the slow combustion combustor and the detonation combustor, respectively.
6. The gas turbine with post-combustion detonation combustor of claim 1, wherein the generator is in a motoring mode during start-up and the generator is in a generator mode during low and normal operating conditions.
7. The gas turbine with post combustion detonation combustor of claim 1, wherein the detonation combustor is inactive when both the power generated by the slow combustion combustor and the heat of flue gas emissions meet demand, and the detonation combustor is active when the power meets demand and the heat of flue gas emissions does not meet system demand.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310192652.9A CN116291873B (en) | 2023-02-24 | 2023-02-24 | A gas turbine with a secondary combustion detonation combustion chamber |
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| CN202310192652.9A CN116291873B (en) | 2023-02-24 | 2023-02-24 | A gas turbine with a secondary combustion detonation combustion chamber |
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| CN110715323A (en) * | 2019-10-14 | 2020-01-21 | 哈尔滨工程大学 | Rotary detonation combustor for liquid fuel |
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| US7721523B2 (en) * | 2008-04-01 | 2010-05-25 | General Electric Company | Ground based pulse detonation combustor for power generation |
| WO2014120115A1 (en) * | 2013-01-29 | 2014-08-07 | United Technologies Corporation | Reverse-flow core gas turbine engine with a pulse detonation system |
| RU2674172C1 (en) * | 2017-07-11 | 2018-12-05 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Turbo engine and method for operation thereof |
| US20190017437A1 (en) * | 2017-07-13 | 2019-01-17 | General Electric Company | Continuous detonation gas turbine engine |
| CN115342380A (en) * | 2022-07-13 | 2022-11-15 | 清航空天(北京)科技有限公司 | Nonlinear detonation combustion chamber |
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| CN105221263A (en) * | 2015-09-18 | 2016-01-06 | 中国航空工业集团公司沈阳发动机设计研究所 | Cold Gas Turbine Combined-cycle system between one |
| CN110715323A (en) * | 2019-10-14 | 2020-01-21 | 哈尔滨工程大学 | Rotary detonation combustor for liquid fuel |
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