Full-scale gas turbine combustion chamber test system suitable for partial pre-cracking ammonia gas

Abstract

The invention relates to the technical field of ammonia gas combustion tests, in particular to a full-scale gas turbine combustion chamber test system suitable for partially pre-cracked ammonia gas. By constructing a multi-subsystem collaborative cracking ammonia gas combustion test platform, full-parameter simulation and accurate testing of a combustion chamber of a gas turbine in a cracking ammonia gas fuel environment are realized, the system dynamically simulates part of pre-cracking ammonia gas by adopting a hydrogen-nitrogen-ammonia gas mixture, and high-temperature air is generated by combining a heat accumulating type heater; the high-temperature and high-pressure combustion environment of the gas turbine is truly reduced, meanwhile, accurate control over liquid ammonia flow is achieved through a nitrogen extrusion type liquid ammonia supply system, accurate control over the whole process of fuel flow, temperature and ignition is achieved in cooperation with a remote automatic control system, and finally combustion performance and NOx emission data are quantized through a K-type thermocouple and a flue gas analyzer. A test system is provided for exploring the combustion performance of ammonia gas with different cracking degrees in a full-scale gas turbine combustion chamber; the technical problem that in the prior art, a combustion experiment system for exploring the combustion performance of ammonia gas with different pre-cracking degrees in a full-scale gas turbine combustion chamber is lacked is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of ammonia combustion testing, and in particular to a full-scale gas turbine combustion chamber testing system suitable for partially pre-cracking ammonia. Background Art

[0002] Ammonia, as a potential carbon-free clean energy source, has the characteristics of high energy density, easy storage and transportation, and is regarded as one of the key fuels for future gas turbines. However, the combustion characteristics of ammonia are significantly different from those of traditional fuels. For example, it has disadvantages such as slow combustion rate, high ignition temperature, and narrow flammability range. This puts higher requirements on how to organize efficient and stable combustion in the gas turbine combustor. Pre-cracking part of the ammonia and improving the flammability of ammonia through the hydrogen produced by cracking is an ideal way to improve the flammability of ammonia. However, cracking ammonia is an energy-consuming process. Therefore, it is necessary to find a balance between the degree of ammonia cracking and its flammability to improve energy utilization. However, regarding this balance point, it is necessary to explore the combustion performance of ammonia with different pre-cracking degrees in a full-scale gas turbine combustor. However, there is currently no commonly used full-scale gas turbine combustor combustion experimental system based on ammonia pre-cracking for experimentation and verification. Summary of the Invention

[0003] In response to the shortcomings of the existing technology, the present invention provides a full-scale gas turbine combustor test system suitable for partially pre-cracked ammonia, which solves the technical problem in the existing technology of lacking combustion performance experiments of ammonia with different pre-cracked degrees in a full-scale gas turbine combustor.

[0004] To solve the above technical problems, the present invention provides the following technical solution: a full-scale gas turbine combustor test system suitable for partially pre-cracking ammonia, comprising a combustion chamber for gas combustion, a flue gas analyzer for analyzing the combustion exhaust gas in the combustion chamber, an injection disk for injecting gas into the combustion chamber, and an igniter for igniting the gas in the combustion chamber. The system also includes: an ammonia supply system for supplying a predetermined flow of liquid ammonia and vaporizing the liquid ammonia; a hydrogen and combustion nitrogen supply system for supplying a predetermined flow of hydrogen and nitrogen, and including a mixing chamber for mixing the vaporized ammonia with the hydrogen and nitrogen in a predetermined ratio and then feeding the mixed mixture into the injection disk; The air supply and heating system is used to supply air and heat the air before inputting it into the injection disk.

[0005] Preferably, the ammonia supply system includes an extruded nitrogen bottle, and a liquid ammonia storage tank for holding liquid ammonia and a liquid ammonia electromagnetic heater for vaporizing liquid ammonia are sequentially arranged on the pipeline between the extruded nitrogen bottle and the mixing chamber; an extruded nitrogen pressure regulating valve T01 and a solenoid valve D07 are arranged on the pipeline between the extruded nitrogen bottle and the liquid ammonia storage tank, and a solenoid valve D01 and a flow limiting hole L01 are sequentially arranged on the pipeline between the liquid ammonia storage tank and the liquid ammonia electromagnetic heater.

[0006] Preferably, the hydrogen and combustion nitrogen supply system includes a hydrogen cylinder, and the pipeline between the hydrogen cylinder and the mixing chamber is connected in sequence with a pressure regulating valve T02, a pneumatic stop valve D02, a one-way valve J07 and a sonic flowmeter L02. The hydrogen and combustion nitrogen supply system also includes a combustion nitrogen cylinder, and the pipeline between the combustion nitrogen cylinder and the mixing chamber is connected in sequence with a pressure regulating valve T03, a solenoid valve D03, a one-way valve J03 and a sonic flowmeter L03.

[0007] Preferably, the air supply and heating system includes an air cylinder grid, and the pipeline between the air cylinder grid and the injection disk is sequentially connected with a pressure regulating valve T05, a pneumatic stop valve D05, a sonic flowmeter L05 and a thermal storage heater.

[0008] Preferably, the system also includes an oxidant supply system, which includes an oxidant gas cylinder. The pipeline between the oxidant gas cylinder and the injection disk is connected in sequence with a pressure regulating valve T04, a solenoid valve D04, a one-way valve J05 and a sonic flowmeter L04.

[0009] Preferably, the system also includes a nitrogen purge system, which includes a nitrogen purge bottle. A pressure regulating valve T06 and a solenoid valve D06 are provided on the output pipeline of the nitrogen purge bottle. The output end pipe mouth of the solenoid valve D06 is respectively connected to the pipelines in the ammonia supply system, the hydrogen and combustion nitrogen supply system and the combustion aid supply system.

[0010] Preferably, the system also includes an automatic control system, which includes an Ethernet unit, which establishes data communication with an industrial computer used to remotely issue control instructions. The Ethernet unit is provided with a collection module for collecting pressure and temperature data in the pipeline and a control module for controlling each valve and igniter.

[0011] By means of the above technical solution, the present invention provides a full-scale gas turbine combustor test system suitable for partially pre-cracking ammonia, which has at least the following beneficial effects: 1. The present invention realizes full-parameter simulation and precise testing of the gas turbine combustor in a cracked ammonia fuel environment by constructing a multi-subsystem collaborative cracked ammonia combustion test platform. The system uses a hydrogen-nitrogen-ammonia mixture to dynamically simulate part of the pre-cracked ammonia, and combines a regenerative heater to generate high-temperature air, truly recreating the high-temperature and high-pressure combustion environment of the gas turbine. At the same time, a nitrogen extrusion liquid ammonia supply system is used to precisely control the liquid ammonia flow rate, and a remote automatic control system is used to precisely control the entire process of fuel flow rate, temperature, and ignition. Finally, the K-type thermocouple and pressure sensor at the combustion chamber outlet are used to quantify the cracked ammonia combustion performance, and the flue gas analyzer is used to quantify the NOx emission data. This provides a repeatable and high-precision experimental benchmark for exploring the combustion performance of ammonia with different pre-cracked degrees in a full-scale gas turbine combustor, and promotes the design iteration of ammonia-fueled gas turbines.

[0012] 2. To address the problem of large-flow liquid ammonia supply, the present invention adopts nitrogen extrusion drive and electromagnetic heating gasification technology solutions. That is, by squeezing the nitrogen bottle, high-pressure nitrogen is injected into the gas phase space of the liquid ammonia storage tank, and the liquid ammonia is physically squeezed out at a high speed. After the liquid ammonia flows through the flow-limiting hole L01 and stabilizes the flow rate, it enters the liquid ammonia electromagnetic heater for forced gasification, ensuring a stable supply of large-flow ammonia to meet the needs of gas turbine experiments and providing a reliable fuel source for cracking ammonia combustion experiments.

[0013] 3. To simulate the high-temperature conditions at the actual gas turbine inlet, the present invention uses a thermal storage heater to overcome the energy consumption bottleneck of instantaneous heating of large-flow air. The outlet temperature can reach as high as 882K and be maintained for 120 seconds, which saves more than 70% energy compared with traditional resistance instantaneous heating. This design avoids the kilowatt-level power requirement while achieving stable output of high-temperature air with a compact structure. Combined with the closed-loop control of the sonic flowmeter L05 and the pressure regulating valve T05, it ensures an air flow accuracy of ±1.5%, providing the combustion chamber with a high-temperature oxidant that meets the actual operating conditions of the gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings: Figure 1 This is a block diagram of the structure of a full-scale gas turbine combustor test system suitable for partially pre-cracking ammonia according to the present invention; Figure 2 Schematic diagram of a full-scale gas turbine combustor test system suitable for partially pre-cracking ammonia according to the present invention.

[0015] In the figure: 1. Liquid ammonia storage tank; 2. Liquid ammonia electromagnetic heater; 3. Squeezed nitrogen cylinder; 5. Air cylinder grid; 6. Blow-off nitrogen cylinder; 7. Hydrogen cylinder; 8. Combustion nitrogen cylinder; 9. Combustion aid cylinder; 10. Mixing chamber; 11. Injection disk; 12. Ignitor; 13. Combustion chamber; 14. Flue gas analyzer; 15. Thermal storage heater; 16. Ethernet unit; 17. Acquisition module; 18. Control module. DETAILED DESCRIPTION

[0016] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0017] In order to explore the combustion performance of ammonia with different pre-cracking degrees in a full-scale gas turbine combustor, it is necessary to conduct component testing on the gas turbine combustor, thereby providing an important reference for the iterative optimization of the design of the combustor components, the ammonia cracker and the gas turbine as a whole, so as to solve the technical problem in the prior art of the lack of a combustion experimental system for exploring the combustion performance of ammonia with different pre-cracking degrees in a full-scale gas turbine combustor. The present application provides a full-scale gas turbine combustor test system suitable for partially pre-cracking ammonia. By constructing a gas turbine combustor component test system using cracked ammonia as fuel, the system can simulate the real environment during gas turbine operation and accurately measure the performance parameters of the combustion of partially pre-cracking ammonia in the combustor components, thereby providing a scientific basis for the design optimization of the ammonia cracker, the combustor and the gas turbine as a whole. The system includes a combustion chamber 13 for gas combustion and a flue gas analyzer 14 for analyzing the combustion exhaust gas of the combustion chamber 13. The flue gas analyzer 14 can measure the NOx content in the combustion exhaust gas. NOx is an atmospheric pollutant, and its emission is an important consideration in the design of the combustor. The system also includes an injection disk 11 that injects mixed gas used to simulate the real gas environment in the gas turbine combustion chamber into the combustion chamber 13, and an igniter 12 that ignites the gas in the combustion chamber 13. The system contains a large amount of combustible gas. Therefore, during the experiment, the system needs to be placed in an open environment, or monitoring must be set up in the environment where the test system is located to monitor the test equipment from all angles to ensure the safety of the test. A blower is installed near the test system to quickly dilute unburned hydrogen and ammonia after ignition failure to ensure the safety of the test system.

[0018] In order to simulate the real gas environment of pre-cracking ammonia combustion during the operation of the gas turbine combustion chamber 13, the test system needs to mix ammonia, hydrogen, nitrogen and air in a certain proportion. Therefore, the test system includes an ammonia supply system for supplying a predetermined flow of liquid ammonia and then gasifying the liquid ammonia into gaseous ammonia. The ammonia supply system includes an extruded nitrogen bottle 3, a liquid ammonia storage tank 1 for containing liquid ammonia and a liquid ammonia electromagnetic heater 2 for gasifying the liquid ammonia are sequentially arranged on the pipeline between the extruded nitrogen bottle 3 and the mixing chamber 10, and a liquid ammonia storage tank 1 for containing liquid ammonia and a liquid ammonia electromagnetic heater 2 for gasifying the liquid ammonia are arranged on the pipeline between the extruded nitrogen bottle 3 and the liquid ammonia storage tank 1. There are extruded nitrogen pressure regulating valve T01 and solenoid valve D07. Solenoid valve D01 and flow limiting hole L01 are sequentially arranged on the pipeline between the liquid ammonia storage tank 1 and the liquid ammonia electromagnetic heater 2. The system supplies liquid ammonia by nitrogen extrusion. The nitrogen pressure regulating valve T01 is used to realize nitrogen extrusion pressure control. The flow rate of liquid ammonia is controlled by the nitrogen pressure regulating valve T01 and the flow limiting hole L01 with a certain cross-sectional diameter. The liquid ammonia is vaporized after passing through the liquid ammonia electromagnetic heater 2 and then enters the mixing chamber 10 for mixing. Pressure sensors and K-type thermocouples can also be set on the pipeline to detect the parameters of the fluid in the pipeline.

[0019] The test system also includes a hydrogen and combustion nitrogen supply system for supplying a predetermined flow of hydrogen and nitrogen. The combustion nitrogen supply system includes a mixing chamber 10 for mixing the vaporized ammonia with hydrogen and nitrogen in a predetermined proportion and then inputting the mixture into the injection disk 11, thereby completing the mixing of ammonia, hydrogen and air so that the proportion of the three is similar to the actual environment during combustion in the gas turbine combustion chamber 13. The hydrogen and combustion nitrogen supply system includes a hydrogen cylinder 7 for storing hydrogen. The pipeline between the hydrogen cylinder 7 and the mixing chamber 10 is connected in sequence with a pressure regulating valve T02, a pneumatic stop valve D02, a one-way valve J07 and a sonic flowmeter L02 to achieve flow control. Since hydrogen is a flammable gas, in order to prevent the gas from burning in the pipeline, electrical separation is achieved here by providing a pneumatic stop valve D02 instead of a solenoid valve. The gas required to supply the pneumatic stop valve D02 can be Figure 2 As shown in the figure, the gas in the control nitrogen cylinder 4 is preferably an inert gas. For price considerations, relatively cheap nitrogen is selected here. The hydrogen and combustion nitrogen supply system also includes a combustion nitrogen cylinder 8 for storing nitrogen injected into the combustion chamber. The hydrogen cylinder 7 and the combustion nitrogen cylinder 8 are both high-pressure gas cylinders. The pipeline between the combustion nitrogen cylinder 8 and the mixing chamber 10 is connected in sequence with a pressure regulating valve T03, a solenoid valve D03, a one-way valve J03 and a sonic flowmeter L03, so as to realize the control of the nitrogen flow injected into the combustion chamber. Of course, a pressure sensor and a K-type thermocouple can also be set on the system to monitor the fluid parameters in the pipeline.

[0020] The test system also includes an air supply and heating system for supplying air and heating the air before inputting it into the injection disk 11. The air supply and heating system includes an air cylinder grid 5. The pipeline between the air cylinder grid 5 and the injection disk 11 is connected in sequence with a pressure regulating valve T05, a stop valve D05, a sonic flowmeter L05 and a thermal storage heater 15. In order to simulate the combustion engine environment, the air injected into the mixing chamber 10 needs to be heated first. Due to the large amount of air, the power required for instantaneous heating is too large. Therefore, a self-designed thermal storage heater 15 is used to heat the air. The thermal storage heater 15 can be cylindrical in shape, 1m long and 130mm in diameter. It is made of GH625 material and weighs 100kg. Six heating pipes can be arranged in the middle to and 54 air flow channels with a diameter of 2 mm. Before the test, the thermal storage heater 15 is heated to a certain temperature so that it has a certain heat sink. When the air flows through the heater flow channel, the air is heated by convection heat transfer. For example, the thermal storage heater 15 can be first heated to 943K. After the air with a flow rate of 222g / s flows through, the air temperature can reach 882K and the duration can reach 120s. Therefore, for the combustion chamber using cracked ammonia as fuel, the present application provides a gas turbine combustion chamber component test system that uses a hydrogen-nitrogen-ammonia mixture to simulate cracked ammonia, and by controlling the proportion of various gases and measuring the NOx content in the combustion exhaust gas, the combustion performance of ammonia with different pre-cracking degrees in a full-scale gas turbine combustion chamber is explored.

[0021] In order to further ensure the stability of this test system, an oxidant supply system is further designed to supply the oxidant, including an oxidant gas cylinder 9 for storing the oxidant. The oxidant gas cylinder 9 is a high-pressure gas cylinder. The oxidant can be oxygen and nitrous oxide, etc., to increase the flammability of ammonia. The pipeline between the oxidant gas cylinder 9 and the injection disk 11 is connected in sequence with a pressure regulating valve T04, a solenoid valve D04, a one-way valve J05 and a sonic flowmeter L04 to control the flow of the oxidant.

[0022] After the test, in order to prevent unburned ammonia and hydrogen from accumulating in the pipeline and the combustion chamber 13, nitrogen is used to purge the hydrogen, ammonia and combustion-supporting agent pipelines and the combustion chamber 13. Therefore, a nitrogen purge system is designed. The system includes a purge nitrogen cylinder 6 which is a high-pressure gas cylinder. The purge nitrogen cylinder 6 is provided with an inert gas, nitrogen being selected here. A pressure regulating valve T06 and a solenoid valve D06 are provided on the output pipeline of the purge nitrogen cylinder 6. The output end pipe mouth of the solenoid valve D06 is respectively connected to the pipelines in the ammonia supply system, the hydrogen and combustion nitrogen supply system and the combustion-supporting agent supply system. Figure 2 An optimal pipe connection point is shown in FIG.

[0023] This test system also designs an automatic control system to achieve remote control. The automatic control system can use a 4-slot cDAQ-9185 as the Ethernet unit 16. The Ethernet unit 16 establishes data communication with the industrial computer used to remotely issue control instructions, thereby remotely operating the test. The Ethernet unit 16 is provided with an acquisition module 17 for collecting pressure and temperature data in the pipeline and a control module 18 for controlling each valve and igniter 12. The acquisition module 17 and the control module 18 can be NI9205 and NI9472 respectively. The acquisition module 17 collects the 0-10V voltage signal input by the pressure sensor and the temperature sensor. Each NI9205 module has 32 acquisition channels. The control module 18 outputs a 24V voltage signal to control the opening and closing of the solenoid valve and the power switch of the igniter 12, thereby achieving remote control and data acquisition.

[0024] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements that are inherent to such process, method, article or apparatus.

[0025] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A full-scale gas turbine combustion chamber test system suitable for partially pre-cracking ammonia, comprising a combustion chamber (13) for gas combustion, a flue gas analysis instrument (14) for analyzing combustion exhaust gas from the combustion chamber (13), an injection disk (11) for injecting gas into the combustion chamber (13), and an igniter (12) for igniting the gas in the combustion chamber (13), characterized in that: The system also includes: an ammonia supply system, the ammonia supply system being used to supply liquid ammonia at a predetermined flow rate and to gasify the liquid ammonia; A hydrogen and combustion nitrogen supply system, the hydrogen and combustion nitrogen supply system is used to supply predetermined flow rates of hydrogen and nitrogen, and includes a mixing chamber (10) for mixing vaporized ammonia with hydrogen and nitrogen in a predetermined ratio and then inputting the mixed mixture into the injection disk (11); An air supply and heating system is used to supply air and heat the air before inputting it into the injection disk (11).

2. The combustion chamber test system according to claim 1, characterized in that: The ammonia supply system comprises an extruded nitrogen bottle (3), a liquid ammonia storage tank (1) for storing liquid ammonia, and a liquid ammonia electromagnetic heater (2) for gasifying the liquid ammonia, which are sequentially arranged on the pipeline between the extruded nitrogen bottle (3) and the liquid ammonia storage tank (1), an extruded nitrogen pressure regulating valve T01 and an electromagnetic valve D07 are arranged on the pipeline between the extruded nitrogen bottle (3) and the liquid ammonia storage tank (1), and a electromagnetic valve D01 and a flow limiting hole L01 are sequentially arranged on the pipeline between the liquid ammonia storage tank (1) and the liquid ammonia electromagnetic heater (2).

3. The combustion chamber test system according to claim 1, characterized in that: The hydrogen and combustion nitrogen supply system comprises a hydrogen cylinder (7), a pressure regulating valve T02, a pneumatic stop valve D02, a one-way valve J07 and a sonic flowmeter L02 being sequentially connected to the pipeline between the hydrogen cylinder (7) and the mixing chamber (10), and the hydrogen and combustion nitrogen supply system further comprises a combustion nitrogen cylinder (8), a pressure regulating valve T03, a solenoid valve D03, a one-way valve J03 and a sonic flowmeter L03 being sequentially connected to the pipeline between the combustion nitrogen cylinder (8) and the mixing chamber (10).

4. The combustion chamber test system according to claim 1, characterized in that: The air supply and heating system comprises an air cylinder grid (5), and a pressure regulating valve T05, a stop valve D05, a sonic flow meter L05 and a thermal storage heater (15) are sequentially connected to the pipeline between the air cylinder grid (5) and the injection plate (11).

5. The combustion chamber test system according to claim 1, characterized in that: The system also includes an oxidant supply system, which includes an oxidant gas cylinder (9), and a pressure regulating valve T04, a solenoid valve D04, a one-way valve J05 and a sonic flowmeter L04 are sequentially connected to the pipeline between the oxidant gas cylinder (9) and the injection disk (11).

6. The combustion chamber test system according to claim 5, characterized in that: The system also includes a nitrogen purge system, which includes a purge nitrogen bottle (6). A pressure regulating valve T06 and a solenoid valve D06 are provided on the output pipeline of the purge nitrogen bottle (6). The output end pipe of the solenoid valve D06 is respectively connected to the pipelines in the ammonia supply system, the hydrogen and combustion nitrogen supply system, and the combustion-supporting agent supply system.

7. The combustion chamber test system according to claim 1, characterized in that: The system further includes an automatic control system, which includes an Ethernet unit (16), wherein the Ethernet unit (16) establishes data communication with an industrial computer for remotely issuing control instructions, and the Ethernet unit (16) is provided with a collection module (17) for collecting pressure and temperature data in the pipeline and a control module (18) for controlling each valve and the igniter (12).

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