CN115046227A - High-pressure rotary detonation gas turbine taking ammonia as fuel - Google Patents
High-pressure rotary detonation gas turbine taking ammonia as fuel Download PDFInfo
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- CN115046227A CN115046227A CN202210707732.9A CN202210707732A CN115046227A CN 115046227 A CN115046227 A CN 115046227A CN 202210707732 A CN202210707732 A CN 202210707732A CN 115046227 A CN115046227 A CN 115046227A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R7/00—Intermittent or explosive combustion chambers
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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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
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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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
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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
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Abstract
A high-pressure rotary knocking gas turbine taking ammonia as fuel comprises an air system, an ammonia fuel system, an auxiliary fuel tank, a rotary knocking combustion chamber, a turbine rotor, a transmission shaft, a transmission and a generator set; the air system comprises an air inlet channel, an air compressor, an air storage tank and an air distribution manifold which are connected in sequence; the gas distribution manifold is provided with two gas outlet ports, and the two gas outlet ports of the gas distribution manifold are respectively connected with a primary air inlet and a secondary air inlet of the rotary detonation combustion chamber; the ammonia fuel system comprises an ammonia storage tank and a high-pressure common rail pipeline which are sequentially connected, an auxiliary fuel tank and the high-pressure common rail pipeline are respectively connected with the head of the rotary detonation combustor, the tail of the rotary detonation combustor is connected with a turbine rotor, the turbine rotor is connected with a transmission through a transmission shaft, and the transmission is connected with a generator set. The invention can improve the air inlet pressure, further improve the combustion efficiency, and simultaneously improve the fuel utilization rate and reduce the emission of nitrogen oxides by carrying out secondary combustion on the unburned ammonia gas through secondary air of air.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a high-pressure rotary detonation gas turbine taking ammonia as fuel.
Background
The Gas Turbine (Gas Turbine) is an internal combustion type power machine which takes continuously flowing Gas as a working medium to drive an impeller to rotate at a high speed and converts the energy of fuel into useful work, and is a rotary impeller type heat engine. The simplest working process is that the air compressor sucks air from the external atmospheric environment, compresses the air and sends the air into the combustion chamber to be mixed and combusted with the sprayed fuel to generate high-temperature and high-pressure gas, then the gas enters the turbine to expand and do work to push the turbine to drive the air compressor and the external load rotor to rotate together at high speed, and the purpose that the chemical energy part of the gas or liquid fuel is converted into mechanical work is achieved. Compared with a gasoline engine and a diesel engine, the gas turbine has the advantages of small unit power weight, large unit power, good maneuvering performance, capability of continuously outputting power and the like, so that the gas turbine is widely applied to the fields of aerospace, ships, power generation and the like.
In recent years, gas turbine technology has developed very rapidly and the performance has become increasingly sophisticated. In the aspect of combustion power generation, the power generation power grade of a combined cycle electric field of the gas turbine exceeds that of a steam turbine, the highest power generation efficiency can reach 65%, and particularly, the research and development of advanced combustion technologies such as premixed lean fuel combustion, multistage combustion, catalytic combustion and the like reduce the serious pollution problem of the gas turbine, so that the gas turbine can be further developed. However, conventional gas turbines using natural gas, gasoline, diesel, heavy oil, etc. as fuel have difficulty meeting increasingly stringent environmental standards. Moreover, most of the traditional gas turbines only have a single air inlet channel, and a lot of unburnt fuel cannot be further reacted but is treated along with the exhaust gas, so that the fuel utilization rate is not high; in addition, the high internal temperature of the gas turbine, particularly the ultra-high heat load of the outlet part, causes serious damage to the equipment, low service life and the like.
Disclosure of Invention
The present invention is directed to solve the above problems in the prior art, and an object of the present invention is to provide a high pressure rotary detonation gas turbine using ammonia as fuel, in which a high pressure common rail is added between an ammonia storage tank and a rotary detonation combustor to increase intake pressure and further increase combustion efficiency, and unburned ammonia gas is subjected to secondary combustion by secondary air to increase fuel utilization and reduce nitrogen oxide emission.
In order to achieve the purpose, the invention adopts the following technical scheme:
a high-pressure rotary detonation gas turbine taking ammonia as fuel comprises an air system, an ammonia fuel system, an auxiliary fuel tank, a rotary detonation combustor, a turbine rotor, a transmission shaft, a transmission and a generator set; the air system comprises an air inlet channel, an air compressor, an air storage tank and an air distribution manifold which are connected in sequence; the gas distribution manifold is provided with two gas outlet ports, the head of the rotary detonation combustion chamber is provided with a primary air inlet, the rear part of the rotary detonation combustion chamber is provided with a secondary air inlet, and the two gas outlet ports of the gas distribution manifold are respectively connected with the primary air inlet and the secondary air inlet; the ammonia fuel system comprises an ammonia storage tank and a high-pressure common rail pipeline which are sequentially connected, the head of the rotary detonation combustor is respectively connected with the auxiliary fuel tank and the high-pressure common rail pipeline, the tail of the rotary detonation combustor is connected with a turbine rotor, the turbine rotor is connected with a transmission through a transmission shaft, and the transmission is connected with a generator set.
The rotary detonation combustion chamber comprises an outer cylinder body, an inner cylinder body, an oil injection ring and an igniter; the inner cylinder body is arranged in the outer cylinder body, and an annular combustion chamber main body is formed between the inner cylinder body and the outer cylinder body; the oil injection ring is arranged at the head of the inner cylinder body, wherein ammonia fuel in the high-pressure common rail pipeline enters the annular combustion chamber main body through the oil injection ring; the igniter is arranged at the head of the outer cylinder body; the head of the outer cylinder is also provided with an auxiliary fuel nozzle and the primary air inlet, and auxiliary fuel enters the annular combustion chamber main body through the auxiliary fuel nozzle; the ammonia fuel, the auxiliary fuel and the high-pressure air are premixed at the head of the annular combustion chamber main body, a local hot spot is formed by ignition of an igniter, the local hot spot induces generation of rotary detonation waves, the rotary detonation waves are transmitted to the downstream along the circumferential direction of the annular combustion chamber main body, high-temperature and high-pressure working media are generated after the rotary detonation waves are expanded and discharged along the circumferential direction to generate thrust, the fuel and the high-pressure air are continuously mixed to form a new premixing area along with continuous supply of the fuel by a fuel injection ring, and therefore the rotary detonation waves can be continuously generated and transmitted in the annular combustion chamber main body.
The rotary detonation combustor also comprises a flame mixer, wherein the flame mixer is arranged at the rear part of the annular combustor main body and is integrally designed with the annular combustor main body; the flame mixer comprises a trapezoidal flame stabilizer, an annular mixer and a contraction and expansion section which are arranged in sequence, and the secondary air inlet is formed in the annular mixer; the trapezoidal flame stabilizer has the advantages that flame at the outlet of the annular combustion chamber main body is stabilized, oscillation frequency of rotary detonation waves is reduced, a stable flow field is generated by forming a backflow area, the annular mixer is used for mixing and combusting high-pressure air, unburned ammonia and auxiliary fuel, the contraction and expansion section is used for expanding and accelerating high-temperature gas, larger thrust is provided for the turbine rotor, and power of the generator is improved.
The oil injection ring comprises an oil inlet pipe, an oil injection needle and an annular gas collecting cavity, the oil inlet pipe is connected with a high-pressure common rail pipeline, ammonia gas is injected into the annular gas collecting cavity through the oil inlet pipe, and then the ammonia gas is injected into the head of the rotary detonation combustion chamber through the transverse oil injection needles which are arranged at equal intervals along the circumference of the annular gas collecting cavity.
The high-pressure common rail pipeline comprises an inner pipe, an outer pipe, an Electronic Control Unit (ECU), an electromagnetic valve, a pressure limiter, a rail pressure sensor and an ammonia high-pressure pump; the inner pipe is used for transporting ammonia fuel, and the outer pipe is used for preventing ammonia fuel from leaking; the rail pressure sensor, the electromagnetic valve, the pressure limiter and the ammonia high-pressure pump are all connected with an electronic control unit; the ammonia fuel enters the high-pressure common rail pipeline after being pressurized by the ammonia high-pressure pump, the electronic control unit monitors the rail pressure of the high-pressure common rail pipeline through the rail pressure sensor, the pressure limiter prevents the rail pressure from being too high to protect a pipeline system, after the standard is met, the electronic control unit controls the electromagnetic valve to be opened, and the ammonia fuel in the high-pressure common rail pipeline enters the rotary detonation combustion chamber.
The high-pressure common rail pipeline further comprises an ammonia gas leakage indicator, and the ammonia gas leakage indicator is connected with the electronic control unit and used for monitoring the pipeline in real time to prevent the pipeline leakage.
The high-pressure common rail pipeline further comprises a flow damper, and ammonia fuel in the high-pressure common rail pipeline enters the rotary detonation combustion chamber through the flow damper.
The invention also comprises a filter, wherein the filter is arranged between the ammonia storage tank and the ammonia high-pressure pump; wherein, liquid ammonia in the ammonia storage tank is pressurized by an ammonia high-pressure pump and sent into the high-pressure common rail pipeline after being filtered by a filter.
The auxiliary fuel includes hydrogen, methane, diesel, etc.
According to the invention, clean energy ammonia is used as fuel of the rotary detonation gas turbine, the problems of low ammonia combustion speed, low thermal efficiency and the like are effectively solved by utilizing the high-temperature and high-pressure characteristics of rotary detonation combustion, the high stability of the ammonia is utilized to provide a higher compression ratio for the gas turbine, so that the combustion efficiency of the detonation gas turbine is improved, and compared with the detonation gas turbine of the traditional fuel, the fuel can obviously improve the consumption rate of oxygen in the air and reduce the emission of greenhouse gas.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
1. as ammonia belongs to clean energy, the complete combustion products of ammonia only comprise water and nitrogen, and greenhouse gases are not generated, and compared with the traditional coal and hydrocarbon fuel, the application of ammonia in a gas turbine can greatly reduce the environmental pollution.
2. Compared with the common traditional isobaric combustion, the high-temperature and high-pressure detonation combustion has the advantages of higher heat release rate, higher thermal cycle efficiency, self-pressurization and the like, and is very effective for solving the problems of slow combustion speed, low thermal efficiency and the like of ammonia gas.
3. The ammonia has higher octane number compared with the traditional fuel, the specially designed compression ratio can reach 40:1 to 100:1, which is four times of that of the traditional fuel gas turbine, and the efficiency of the gas turbine can be improved by increasing the compression ratio.
4. The unburned residual ammonia gas and the auxiliary active gas in the combustion chamber are further utilized by introducing secondary combustion, so that the fuel utilization rate and the combustion efficiency are improved, and meanwhile, the normal-temperature air entering from the secondary air flow channel can improve the heat load of the combustion chamber and reduce the emission of reaction pollutants, namely nitrogen oxides.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural diagram of a high-pressure common rail pipe;
fig. 3 is a schematic structural view of a rotary knocking combustor.
Reference numerals: the device comprises an ammonia high-pressure pump 1, a rail pressure sensor 2, an electronic control unit 3, an electromagnetic valve 4, a flow damper 5, a pressure limiter 6, an ammonia leakage indicator 7, a primary air inlet 8, an oil injection ring 9, an auxiliary fuel nozzle 10, an igniter 11, a secondary air inlet 12, a flame mixer 13, a turbine rotor 14, a transmission shaft 15, a transmission 16 and a generator set 17.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects of the present invention clearer and clearer, the present invention is further described in detail below with reference to the accompanying drawings and embodiments.
As shown in fig. 1 to 3, the present embodiment includes, as shown in fig. 1 to 3, a high-pressure rotary knocking gas turbine using ammonia as fuel in the present embodiment, which includes an air system, an ammonia fuel system, an auxiliary fuel tank, a rotary knocking combustor, a turbine rotor 14, a transmission shaft 15, a transmission 16, and a generator set 17;
the air system comprises an air inlet channel, an air compressor, an air storage tank and an air distribution manifold which are connected in sequence; the gas distribution manifold is provided with two gas outlet ports, the head of the rotary detonation combustion chamber is provided with a primary air inlet 8, the rear part of the rotary detonation combustion chamber is provided with a secondary air inlet 12, and the two gas outlet ports of the gas distribution manifold are respectively connected with the primary air inlet 8 and the secondary air inlet 12; the ammonia fuel system comprises an ammonia storage tank and a high-pressure common rail pipeline which are sequentially connected, the auxiliary fuel tank and the high-pressure common rail pipeline are respectively connected with the head of the rotary detonation combustor, the tail of the rotary detonation combustor is connected with a turbine rotor 14, the turbine rotor 14 is connected with a transmission 16 through a transmission shaft 15, and the transmission 16 is connected with a generator set 17.
The rotary detonation combustion chamber comprises an outer cylinder, an inner cylinder, an oil injection ring 9 and an igniter 11; the inner cylinder body is arranged in the outer cylinder body, and an annular combustion chamber main body is formed between the inner cylinder body and the outer cylinder body; the oil injection ring 9 is arranged at the head of the inner cylinder, wherein ammonia fuel in the high-pressure common rail pipeline enters the annular combustion chamber main body through the oil injection ring 9; the igniter 11 is arranged at the head of the outer cylinder body; the head of the outer cylinder body is also provided with an auxiliary fuel nozzle 10 and the primary air inlet 8, and auxiliary fuel enters the annular combustion chamber main body through the auxiliary fuel nozzle 10.
The rotary detonation combustor further comprises a flame mixer 13, wherein the flame mixer 13 is arranged at the rear part of the annular combustor main body and is integrally designed with the annular combustor main body; the flame mixer 13 comprises a trapezoidal flame stabilizer, an annular mixer and a contraction and expansion section which are arranged in sequence, and the secondary air inlet 12 is arranged at the annular mixer; the trapezoidal flame stabilizer has a stabilizing effect on flame at the outlet of the annular combustion chamber main body, reduces oscillation frequency of rotary detonation waves, and generates a stable flow field by forming a backflow area, the annular mixer is used for providing mixed combustion of high-pressure air, unburned ammonia and auxiliary fuel, and the contraction and expansion section is used for expanding and accelerating high-temperature gas, so as to provide greater thrust for the turbine rotor 14 and improve power of the generator.
The oil injection ring 9 comprises an oil inlet pipe, an oil injection needle and an annular gas collecting cavity, the oil inlet pipe is connected with a high-pressure common rail pipeline, ammonia gas is injected into the annular gas collecting cavity through the oil inlet pipe, then the ammonia gas is injected into the head of the rotary detonation combustion chamber through the transverse oil injection needles which are arranged along the circumference of the annular gas collecting cavity at equal intervals, and the oil injection ring 9 continuously injects the ammonia gas into the rotary detonation combustion chamber in the working time. Specifically, the ammonia fuel is gasified by an annular gas collecting cavity in the oil injection ring 9 and then injected into the rotary detonation combustor to be fully premixed with the auxiliary fuel and the high-pressure air flowing in from the primary air inlet 8.
The high-pressure common rail pipeline is a closed-loop oil supply pipeline system, can completely separate the generation of injection pressure and the injection process from each other, and can monitor the oil pressure in the common rail oil pipe and accurately control the oil injection quantity through the electronic control unit 3. Specifically, the high-pressure common rail pipeline comprises an inner pipe, an outer pipe, an electronic control unit 3, an electromagnetic valve 4, a pressure limiter 6, a rail pressure sensor 2, an ammonia high-pressure pump 1, an ammonia leakage indicator 7 and a flow damper 5; the inner pipe is used for transporting ammonia fuel, and the outer pipe is used for preventing ammonia fuel from leaking; and the rail pressure sensor 2, the electromagnetic valve 4, the pressure limiter 6, the ammonia gas leakage indicator 7 and the ammonia gas high-pressure pump 1 are all connected with the electronic control unit 3.
The embodiment also comprises a filter, wherein the filter is arranged between the ammonia storage tank and the ammonia high-pressure pump 1; wherein, liquid ammonia in the ammonia storage tank is pressurized and sent into the high-pressure common rail pipeline by the ammonia high-pressure pump 1 after being filtered by the filter.
The auxiliary fuel is mainly high-activity fuel, such as hydrogen, methane, diesel oil and the like, and can obviously increase the laminar flame speed of ammonia gas and reduce ignition delay time after being mixed with the ammonia gas, so that the ammonia gas can generate rotary detonation waves under a high-pressure condition.
The working principle and the method of the invention are as follows:
1. when the rotary detonation high-pressure gas turbine works, pressurized air enters from the head of a rotary detonation combustor, ammonia fuel enters a high-pressure common rail pipeline after being pressurized by an ammonia high-pressure pump 1, then an electronic control unit 3 monitors the rail pressure of the high-pressure common rail pipeline through a rail pressure sensor 2, a pressure limiter 6 can prevent the rail pressure from being overhigh to protect a pipeline system, after the standard is met, the electronic control unit 3 controls an electromagnetic valve 4 to be opened, the ammonia fuel in the high-pressure common rail pipeline enters an oil injection ring 9 through a flow damper 5, and an ammonia leakage indicator 7 monitors the pipeline in real time to prevent pipeline leakage;
2. ammonia gas entering the rotary detonation combustor through the oil injection ring 9, auxiliary fuel entering the rotary detonation combustor through the auxiliary fuel nozzle 10 and high-pressure air entering the primary air inlet 8 are fully premixed at the head of the annular combustor main body to form a premixing area, then an igniter 11 ignites at the head of the premixing area to induce a local hot spot to be generated in the rotary detonation combustor and generate rotary detonation waves, the rotary detonation waves are transmitted along the circumferential direction of the annular combustor main body and are transmitted to the downstream, high-temperature and high-pressure working media are generated after the rotary detonation waves are expanded and discharged along the circumferential direction to generate thrust, and the fuel and the high-pressure air are continuously mixed to form a new premixing area along with the continuous supply of fuel to the oil injection ring 9, so that the rotary detonation waves can be continuously generated and transmitted in the annular combustor main body;
3. the rotary detonation wave at the outlet of the annular combustion chamber main body firstly passes through the trapezoid flame stabilizer at the head of the flame mixer 13, the high-temperature gas obtains a relatively uniform and stable flow field after passing through the trapezoid flame stabilizer, the stabilized high-temperature gas enters the annular mixer, the annular mixer is connected with the secondary air inlet 12, the high-pressure normal-temperature air injected from the secondary air inlet 12 is mixed with the high-temperature high-pressure ammonia gas which is not combusted and the auxiliary fuel and then is combusted again, the combusted high-temperature gas forms a backflow area along the wall surface of the annular mixer to obtain a relatively stable and uniform temperature field and speed field, the flame upwards spreads along the wall surface of the annular mixer and enters the contraction and expansion section, the high-temperature gas further expands and accelerates through the contraction and expansion section to provide higher thrust for the turbine rotor 14 behind the high-speed rotating turbine rotor 14, and the transmission shaft 15 drives the transmission 16 to operate, thereby driving the generator set 17 to operate and generate electricity.
The invention can effectively utilize clean energy ammonia as the main fuel of the high-pressure rotary detonation gas turbine, thereby reducing greenhouse gas pollution caused by traditional energy, improving the combustion characteristic of the ammonia by the high-temperature and high-pressure combustion environment caused by rotary detonation, and providing higher compression ratio to improve the combustion efficiency of the gas turbine due to the high stability of the ammonia. In addition, compared with the primary combustion, the secondary combustion is introduced, so that the fuel utilization rate can be effectively improved, the heat load of the rotary detonation combustion chamber is reduced, and a certain inhibiting effect on the generation of reaction pollutant nitrogen oxides is achieved.
Claims (9)
1. An ammonia-fueled, high pressure, rotary detonation gas turbine, characterized by: the system comprises an air system, an ammonia fuel system, an auxiliary fuel tank, a rotary detonation combustor, a turbine rotor, a transmission shaft, a transmission and a generator set; the air system comprises an air inlet channel, an air compressor, an air storage tank and an air distribution manifold which are connected in sequence; the gas distribution manifold is provided with two gas outlet ports, the head of the rotary detonation combustion chamber is provided with a primary air inlet, the rear part of the rotary detonation combustion chamber is provided with a secondary air inlet, and the two gas outlet ports of the gas distribution manifold are respectively connected with the primary air inlet and the secondary air inlet; the ammonia fuel system comprises an ammonia storage tank and a high-pressure common rail pipeline which are sequentially connected, the head of the rotary detonation combustor is respectively connected with the auxiliary fuel tank and the high-pressure common rail pipeline, the tail of the rotary detonation combustor is connected with a turbine rotor, the turbine rotor is connected with a transmission through a transmission shaft, and the transmission is connected with a generator set.
2. An ammonia-fueled, high pressure, rotary detonation gas turbine as claimed in claim 1, wherein: the rotary detonation combustion chamber comprises an outer cylinder, an inner cylinder, an oil injection ring and an igniter; the inner cylinder body is arranged in the outer cylinder body, and an annular combustion chamber main body is formed between the inner cylinder body and the outer cylinder body; the oil injection ring is arranged at the head of the inner cylinder body, wherein ammonia fuel in the high-pressure common rail pipeline enters the annular combustion chamber main body through the oil injection ring; the igniter is arranged at the head of the outer cylinder body; the head of the outer cylinder is also provided with an auxiliary fuel nozzle and the primary air inlet, and auxiliary fuel enters the annular combustion chamber main body through the auxiliary fuel nozzle; the ammonia fuel, the auxiliary fuel and the high-pressure air are premixed at the head of the annular combustion chamber main body, a local hot spot is formed by ignition of an igniter, the local hot spot induces generation of rotary detonation waves, the rotary detonation waves are transmitted to the downstream along the circumferential direction of the annular combustion chamber main body, high-temperature and high-pressure working media are generated after the rotary detonation waves are expanded and discharged along the circumferential direction to generate thrust, the fuel and the high-pressure air are continuously mixed to form a new premixing area along with continuous supply of the fuel by a fuel injection ring, and therefore the rotary detonation waves can be continuously generated and transmitted in the annular combustion chamber main body.
3. An ammonia-fueled, high pressure, rotary detonation gas turbine as claimed in claim 2, wherein: the rotary detonation combustor also comprises a flame mixer, wherein the flame mixer is arranged at the rear part of the annular combustor main body and is integrally designed with the annular combustor main body; the flame mixer comprises a trapezoidal flame stabilizer, an annular mixer and a contraction and expansion section which are arranged in sequence, and the secondary air inlet is formed in the annular mixer; the trapezoidal flame stabilizer has the advantages that flame at the outlet of the annular combustion chamber main body is stabilized, oscillation frequency of rotary detonation waves is reduced, a stable flow field is generated by forming a backflow area, the annular mixer is used for mixing and combusting high-pressure air, unburned ammonia and auxiliary fuel, the contraction and expansion section is used for expanding and accelerating high-temperature gas, larger thrust is provided for the turbine rotor, and power of the generator is improved.
4. An ammonia-fueled, high pressure, rotary detonation gas turbine as claimed in claim 2, wherein: the oil injection ring comprises an oil inlet pipe, an oil injection needle and an annular gas collecting cavity, the oil inlet pipe is connected with a high-pressure common rail pipeline, ammonia gas is injected into the annular gas collecting cavity through the oil inlet pipe, and then the ammonia gas is injected into the head of the rotary detonation combustion chamber through the transverse oil injection needles which are arranged at equal intervals along the circumference of the annular gas collecting cavity.
5. An ammonia-fueled, high pressure, rotary detonation gas turbine as claimed in claim 1, wherein: the high-pressure common rail pipeline comprises an inner pipe, an outer pipe, an electronic control unit, an electromagnetic valve, a pressure limiter, a rail pressure sensor and an ammonia high-pressure pump; the inner pipe is used for transporting ammonia fuel, and the outer pipe is used for preventing ammonia fuel from leaking; the rail pressure sensor, the electromagnetic valve, the pressure limiter and the ammonia high-pressure pump are all connected with an electronic control unit; the ammonia fuel enters the high-pressure common rail pipeline after being pressurized by the ammonia high-pressure pump, the electronic control unit monitors the rail pressure of the high-pressure common rail pipeline through the rail pressure sensor, the pressure limiter prevents the rail pressure from being too high to protect a pipeline system, after the standard is met, the electronic control unit controls the electromagnetic valve to be opened, and the ammonia fuel in the high-pressure common rail pipeline enters the rotary detonation combustion chamber.
6. An ammonia-fueled, high pressure, rotary detonation gas turbine as claimed in claim 5, wherein: the high-pressure common rail pipeline further comprises an ammonia gas leakage indicator, and the ammonia gas leakage indicator is connected with the electronic control unit and used for monitoring the pipeline in real time to prevent the pipeline leakage.
7. An ammonia-fueled, high pressure, rotary detonation gas turbine as claimed in claim 5, wherein: the high-pressure common rail pipeline further comprises a flow damper, and ammonia fuel in the high-pressure common rail pipeline enters the rotary detonation combustion chamber through the flow damper.
8. An ammonia-fueled, high pressure, rotary detonation gas turbine as claimed in claim 5, wherein: the filter is arranged between the ammonia storage tank and the ammonia high-pressure pump; wherein, liquid ammonia in the ammonia storage tank is pressurized by an ammonia high-pressure pump and sent into the high-pressure common rail pipeline after being filtered by a filter.
9. An ammonia-fueled, high pressure, rotary detonation gas turbine as claimed in claim 1, wherein: the auxiliary fuel comprises hydrogen, methane and diesel oil.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115614778A (en) * | 2022-11-04 | 2023-01-17 | 北京理工大学 | Ammonia-hydrogen mixed combustion chamber and ammonia-hydrogen mixed combustion method |
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| CN104153884A (en) * | 2014-08-06 | 2014-11-19 | 西安热工研究院有限公司 | Rotary knocking gas turbine |
| CN105864824A (en) * | 2015-02-06 | 2016-08-17 | 三菱日立电力系统株式会社 | Gas Turbine Combustor and Steam Injected Gas Turbine |
| CN107882638A (en) * | 2017-06-09 | 2018-04-06 | 厦门大学 | Actuating unit |
| CN112628030A (en) * | 2020-12-11 | 2021-04-09 | 哈尔滨工程大学 | Ammonia fuel supply system for marine diesel engine |
| CN113551264A (en) * | 2021-07-29 | 2021-10-26 | 厦门大学 | Interstage rotary detonation combustion chamber for ground combustion engine combined cycle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115614778A (en) * | 2022-11-04 | 2023-01-17 | 北京理工大学 | Ammonia-hydrogen mixed combustion chamber and ammonia-hydrogen mixed combustion method |
| CN115614778B (en) * | 2022-11-04 | 2023-08-15 | 北京理工大学 | Ammonia-hydrogen mixed combustion chamber and ammonia-hydrogen mixed combustion method |
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