Gas turbine co-firing system and method

Abstract

The application provides a gas turbine blending combustion system and method, and belongs to the technical field of gas turbines. The system comprises a combustion chamber, an air pipeline and a gas pipeline, and the combustion chamber is provided with a first combustion zone and a second combustion zone connected in series; the first combustion zone is used for combusting the received air transmitted by the air pipeline and the gas transmitted by the gas pipeline, and transmitting the high-temperature gas generated by combustion to the second combustion zone; the second combustion zone is used for performing secondary full combustion by using the received high-temperature gas transmitted by the first combustion zone, the air transmitted by the air pipeline and the gas transmitted by the gas pipeline; and the composition ratio of the air and the gas transmitted to the second combustion zone is determined based on a gas composition ratio calculation rule of a gas turbine operation mode. While the secondary full combustion is performed by using the second combustion zone, the air and the gas in the first combustion zone and the second combustion zone are also supplied at a proper ratio, so that the purpose of full combustion of the gas is effectively achieved.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and more specifically to a gas turbine co-firing system and a gas turbine co-firing method. Background Technology

[0002] Gas turbines have wide applications in power generation, pipeline propulsion, and ship propulsion. With increasing global awareness of environmental protection and the advancement of energy conservation and emission reduction policies, gas turbine emission reduction has become a crucial issue in the current energy sector. Axial staged combustion technology, as an effective means of reducing nitrogen oxide emissions, has been widely used in the gas turbine field. This technology adds a secondary combustion zone after the main combustion zone in the combustion chamber, diverting a portion of the fuel and air to this secondary combustion zone for combustion. This reduces the temperature and flue gas residence time in the main combustion zone, thereby reducing nitrogen oxide formation. However, current axial staged combustion technology has not yet been able to meet the requirements of blending different fuels to achieve an appropriate supply ratio between the main and secondary combustion zones, thus failing to effectively achieve complete combustion of the gas in the blending system.

[0003] Therefore, how to flexibly select fuel types and supply them to the combustion zones by setting the gas and air supply lines for the two combustion zones and setting different operating modes, so that the blending system can achieve the best operating effect in the corresponding operating mode, is an urgent problem to be solved. Summary of the Invention

[0004] The purpose of this invention is to provide a gas turbine co-firing system and method to at least solve the problem of how to flexibly select fuel types and configure them for the combustion zones by setting the gas and air supply lines in the two combustion zones and setting different operating modes, so that the co-firing system can achieve the best operating effect in the corresponding operating mode.

[0005] To achieve the above objectives, the first aspect of the present invention provides a gas turbine co-firing system, including a combustion chamber and a first gas supply pipeline connected to the inlet end of the combustion chamber. The combustion chamber is provided with a plurality of combustion zones connected in series by a second gas supply pipeline, and each combustion zone is connected in parallel to the first gas supply pipeline.

[0006] The first combustion zone converts the gas supplied by the first gas supply line into high-temperature gas through combustion, and then transmits the high-temperature gas through the second gas supply line to the subsequent combustion zones for further combustion.

[0007] Starting from the second combustion zone, each combustion zone receives a fixed amount of gas from the first gas supply line and performs further combustion based on the supplied gas and the high-temperature fuel gas output from the previous adjacent combustion zone, until combustion in the last combustion zone is completed; among which,

[0008] Starting from the second combustion zone, the quantitative rules for collecting a fixed amount of gas from the first gas supply pipeline in each combustion zone are determined based on the pre-determined gas turbine operating mode and the corresponding gas composition ratio calculation rules for the gas turbine operating mode.

[0009] Optionally, the combustion chamber described above has two combustion zones, namely a first combustion zone and a second combustion zone;

[0010] The first gas supply line includes independently installed air lines and gas lines;

[0011] Starting from the second combustion zone, the quantitative rule for the quantitative gas collection from the first gas supply pipeline in each combustion zone is the mixing ratio rule of air and fuel gas.

[0012] Optionally, the above-mentioned air pipeline includes a main air pipeline and a first air branch and a second air branch respectively connected to the outlet end of the main air pipeline. The outlet end of the first air branch is connected to the inlet end of the first combustion zone, and the outlet end of the second air branch is connected to the inlet end of the second combustion zone.

[0013] The main air supply line is equipped with a first air shut-off valve for cutting off the air transmission path and an air fan for accelerating the air transmission speed. The main air supply line is used to deliver the incoming air to the first air branch and the second air branch respectively after passing through the first air shut-off valve and the air fan.

[0014] Optionally, the first air branch is sequentially provided with a second air regulating valve for adjusting the air flow of the first air branch and a second air flow meter for monitoring the air flow of the first air branch. The second air regulating valve is connected to the outlet end of the main air line, and the second air flow meter is connected to the inlet end of the first combustion zone. The second air branch is sequentially provided with a second air shut-off valve for cutting off the air transmission path of the second air branch, a first air regulating valve for adjusting the air flow of the second air branch, and a first air flow meter for monitoring the air flow of the second air branch. The second air shut-off valve is connected to the outlet end of the main air line, and the first air flow meter is connected to the inlet end of the second combustion zone.

[0015] Optionally, the gas pipeline includes a first gas main pipeline, a second gas main pipeline connected to the inlet end of the second combustion zone, and a first gas branch and a second gas branch respectively connected to the outlet end of the first gas main pipeline. The outlet end of the first gas branch is connected to the inlet end of the first combustion zone, and the outlet end of the second gas branch is connected to the inlet end of the second combustion zone.

[0016] The first gas main pipeline is sequentially equipped with a first gas shut-off valve for cutting off the gas transmission path, a first filter for filtering the incoming gas, a first vent valve for venting the gas when the machine is stopped, and a first water bath heater for heating the gas. The first gas main pipeline is used to deliver the incoming gas to the first gas branch and the second gas branch respectively after passing through the first gas shut-off valve, the first filter, the first vent valve and the first water bath heater in sequence.

[0017] Optionally, the first gas branch is sequentially provided with a first gas regulating valve for regulating the gas flow of the first gas branch, a first gas flow meter for monitoring the gas flow of the first gas branch, and a first check valve for preventing gas backflow in the first gas branch. The first gas regulating valve is connected to the outlet end of the first gas main pipeline, and the first check valve is connected to the inlet end of the first combustion zone. The second gas branch is sequentially provided with a second gas shut-off valve for cutting off the gas transmission path of the second gas branch, a second gas regulating valve for regulating the gas flow of the second gas branch, a second gas flow meter for monitoring the gas flow of the second gas branch, and a second check valve for preventing gas backflow in the second gas branch. The second gas shut-off valve is connected to the outlet end of the first gas main pipeline, and the second check valve is connected to the inlet end of the second combustion zone.

[0018] Optionally, the second gas main pipeline is sequentially equipped with a third gas shut-off valve for cutting off the gas transmission path, a second filter for filtering the incoming gas, a second vent valve for venting the gas when the machine is stopped, a second water bath heater for heating the gas, a third gas regulating valve for regulating the gas flow rate of the second gas main pipeline, a third gas flow meter for monitoring the gas flow rate of the second gas main pipeline, and a third check valve for preventing the gas backflow of the second gas main pipeline. The third check valve is connected to the inlet end of the second combustion zone.

[0019] Optionally, a turbine is connected to the outlet end of the second combustion zone, and the turbine is connected to a load;

[0020] The turbine is used to receive and utilize the high-temperature combustion gas transmitted from the second combustion zone to drive the load into operation.

[0021] A second aspect of the present invention provides a gas turbine co-firing method, applied to a gas turbine co-firing system, the method comprising:

[0022] Air and the first combined gas are introduced into the first combustion zone for combustion, and the high-temperature gas generated in the first combustion zone is transferred to the second combustion zone.

[0023] Based on the predetermined gas turbine operating mode and the corresponding gas composition ratio calculation rules for the gas turbine operating mode, the required air and gas composition ratio data transmitted to the second combustion zone are calculated. Based on the calculation results, the required air content and gas content to be introduced into the second combustion zone are determined.

[0024] Based on the required air and fuel gas content for the second combustion zone, air and the second combined fuel gas are introduced into the second combustion zone for secondary and complete combustion.

[0025] Optionally, the above-mentioned gas turbine operating modes include environmental protection mode, economic mode, and high-efficiency mode;

[0026] The specific details of the calculation rules for the gas composition ratio corresponding to the gas turbine operating mode include:

[0027] When the gas turbine is operating in environmental protection mode, by comparing the carbon emission from co-firing of air and gas with different composition ratios, the composition ratio of air and gas corresponding to the lowest carbon emission from co-firing under the same output condition of the gas turbine co-firing system under safe operating conditions is taken as the required composition ratio of air and gas to be transmitted to the second combustion zone.

[0028] When the gas turbine is operating in the economic mode, by comparing the purchase costs corresponding to different proportions of air and gas, the air and gas composition ratio corresponding to the situation that maximizes the economic benefits of the gas turbine co-firing system under the same output under safe operating conditions is used as the air and gas composition ratio demand data to be transmitted to the second combustion zone.

[0029] When the gas turbine is operating in high-efficiency mode, by comparing the combustion efficiency corresponding to different air and gas composition ratios, the air and gas composition ratio corresponding to the shortest co-firing time under the same output condition of the gas turbine co-firing system under safe operating conditions is used as the air and gas composition ratio requirement data to be transmitted to the second combustion zone.

[0030] Optionally, the first combined gas is the combined gas supplied by the first gas main pipeline, and the second combined gas is the combined gas supplied by the first gas main pipeline and / or the combined gas supplied by the second gas main pipeline.

[0031] The above technical solution provides a gas turbine co-firing system and method. A first gas supply pipeline transmits a supply gas (which can be a combination of gas and oxygen, gas and air, gas, oxygen, and nitrogen, etc.) to a first combustion zone for gas co-firing. The high-temperature gas generated in the first combustion zone is then transmitted step-by-step to subsequent combustion zones via a second gas supply pipeline. Starting from the second combustion zone, the content of the supply gas transmitted to each combustion zone is determined according to the gas turbine operating mode and the corresponding gas composition ratio calculation rules. Based on the content of the supply gas transmitted to each combustion zone, each combustion zone collects a quantitative amount of supply gas from the first gas supply pipeline and performs further combustion based on the supply gas and the high-temperature gas output from the previous adjacent combustion zone, until combustion in the last combustion zone is completed. This series-connected design of multiple combustion zones facilitates secondary and complete combustion of the high-temperature fuel in the first combustion zone in subsequent combustion zones, thereby reducing the temperature and flue gas residence time in the first combustion zone and thus reducing the formation of nitrogen oxides. This gas turbine co-firing system and method, while utilizing the subsequent combustion zone for secondary and complete combustion, also achieves the appropriate supply of air and gas ratios in each combustion zone according to different gas turbine operating modes and different fuel co-firing requirements. This allows for flexible selection of fuel types and their introduction into each combustion zone, enabling the gas turbine co-firing system to achieve optimal operating performance in the corresponding gas turbine operating mode, thereby effectively achieving the goal of complete gas combustion.

[0032] Other features and advantages of the embodiments of the present invention will be described in detail in the following detailed description section. Attached Figure Description

[0033] The accompanying drawings are provided to further illustrate embodiments of the present invention and form part of the specification. They are used together with the following detailed description to explain the embodiments of the present invention, but do not constitute a limitation thereof. In the drawings:

[0034] Figure 1 This is a schematic diagram of the structure of a gas turbine co-firing system according to one embodiment of the present invention;

[0035] Figure 2 This is a schematic diagram of another gas turbine co-firing system provided in one embodiment of the present invention;

[0036] Figure 3 This is a flowchart of a gas turbine co-firing method provided in one embodiment of the present invention.

[0037] Explanation of reference numerals in the attached figures

[0038] 1-First combustion zone, 2-Second combustion zone, 3-Air fan, 4-Wheel gear, 5-Load, 8-Air pipeline, 81-Main air pipeline, 82-First air branch, 83-Second air branch, 9-Gas pipeline, 91-First gas main pipeline, 92-Second gas main pipeline, 93-First gas branch, 94-Second gas branch, 11-First air shut-off valve, 12-First gas shut-off valve, 13-Second gas shut-off valve, 14-Third gas shut-off valve, 15-Second air shut-off valve, 21-First filter, 22 - Second filter, 31- First air regulating valve, 32- Second air regulating valve, 33- First gas regulating valve, 34- Second gas regulating valve, 35- Third gas regulating valve, 41- First vent valve, 42- Second vent valve, 51- First water bath heater, 52- Second water bath heater, 61- First air flow meter, 62- Second air flow meter, 63- First gas flow meter, 64- Second gas flow meter, 65- Third gas flow meter, 71- First check valve, 72- Second check valve, 73- Third check valve. Detailed Implementation

[0039] The specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit the scope of the present invention.

[0040] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0041] In this invention, unless otherwise stated, directional terms such as "upper," "lower," "top," and "bottom" are generally used to describe the relative positions of components in relation to the directions shown in the accompanying drawings or in relation to the vertical, perpendicular, or gravitational directions.

[0042] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0043] Figure 1 This is a schematic diagram of a gas turbine co-firing system according to one embodiment of the present invention. Figure 1As shown, this invention provides a gas turbine co-firing system, including a combustion chamber and a first gas supply pipeline connected to the inlet of the combustion chamber. The combustion chamber has multiple combustion zones connected in series via a second gas supply pipeline, and each combustion zone is connected in parallel to the first gas supply pipeline. The first combustion zone 1 converts the gas supplied by the first gas supply pipeline into high-temperature gas through combustion, and transmits the high-temperature gas step-by-step to subsequent combustion zones via the second gas supply pipeline for further combustion. Starting from the second combustion zone 2, each combustion zone collects a fixed amount of supplied gas from the first gas supply pipeline and performs further combustion based on the supplied gas and the high-temperature gas output from the preceding adjacent combustion zone, until the combustion of the last combustion zone is completed. The quantitative rule for collecting the fixed amount of supplied gas from the first gas supply pipeline by each combustion zone starting from the second combustion zone 2 is determined based on a pre-determined gas turbine operating mode and a gas composition ratio calculation rule corresponding to the gas turbine operating mode.

[0044] Specifically, the gas turbine co-firing system transmits supply gas (which can be a combination of gas and oxygen, gas and air, gas, oxygen, and nitrogen, etc.) to the first combustion zone 1 via a first gas supply pipeline for gas co-firing in the first combustion zone 1. The high-temperature gas generated in the first combustion zone 1 is then transmitted step-by-step to subsequent combustion zones via a second gas supply pipeline. Starting from the second combustion zone 2, the content of supply gas transmitted to each combustion zone is determined according to the gas turbine operating mode and the corresponding gas composition ratio calculation rules for that mode. Based on the content of supply gas transmitted to each combustion zone, each combustion zone collects a fixed amount of supply gas from the first gas supply pipeline and performs further combustion based on the supply gas and the high-temperature gas output from the adjacent combustion zone until combustion in the last combustion zone is completed. This design of multiple combustion zones arranged in series facilitates secondary and complete combustion of the high-temperature fuel in the first combustion zone 1 in subsequent combustion zones, thereby reducing the temperature and flue gas residence time in the first combustion zone 1, and consequently reducing the generation of nitrogen oxides. This gas turbine co-firing system, while utilizing the subsequent combustion zone for secondary and complete combustion, also achieves the appropriate supply of air and gas ratios in each combustion zone according to different gas turbine operating modes and different fuel co-firing requirements. This allows for flexible selection of fuel types and their introduction into each combustion zone, enabling the gas turbine co-firing system to achieve optimal operating performance in the corresponding gas turbine operating mode, thereby effectively realizing the goal of complete gas combustion.

[0045] In some embodiments of this example, the combustion chamber has two combustion zones, namely a first combustion zone 1 and a second combustion zone 2; the first gas supply line includes an independently configured air line 8 and a gas line 9; starting from the second combustion zone 2, the quantitative rule for each combustion zone to collect a quantitative amount of gas from the first gas supply line is a mixing ratio rule for air and gas.

[0046] Specifically, the gas turbine co-firing system transmits air to the first combustion zone 1 via air pipeline 8 and gas to the first combustion zone 1 via gas pipeline 9 for co-firing in the first combustion zone 1. The high-temperature gas generated in the first combustion zone 1 is then transmitted to the second combustion zone 2. The air-to-gas composition ratio transmitted to the second combustion zone 2 is determined according to the gas turbine operating mode and the corresponding gas composition ratio calculation rules. Based on this ratio, the air content transmitted to the second combustion zone 2 via air pipeline 8 and the gas content transmitted via gas pipeline 9 are controlled to achieve secondary co-firing in the second combustion zone 2, ensuring complete combustion of the gas. The series connection of the first and second combustion zones 1 and 2 facilitates secondary and complete combustion of the high-temperature fuel in the first combustion zone 1 within the second combustion zone 2, thereby reducing the temperature and flue gas residence time in the first combustion zone 1 and consequently reducing the formation of nitrogen oxides. This gas turbine co-firing system, while utilizing the second combustion zone 2 for secondary and complete combustion, also achieves the appropriate supply ratio of air and gas in the first combustion zone 1 and the second combustion zone 2 according to different gas turbine operating modes and different fuel co-firing requirements. This allows for flexible selection of fuel types and their introduction into the first and second combustion zones 1 and 2, enabling the gas turbine co-firing system to achieve optimal operating results in the corresponding gas turbine operating mode, thereby effectively achieving the goal of complete gas combustion.

[0047] Please refer to Figure 2 , Figure 2 This is a schematic diagram of another gas turbine co-firing system provided in one embodiment of the present invention. In some embodiments of this embodiment, the air pipeline 8 includes a main air pipeline 81 and a first air branch 82 and a second air branch 83 respectively connected to the outlet end of the main air pipeline 81. The outlet end of the first air branch 82 is connected to the inlet end of the first combustion zone 1, and the outlet end of the second air branch 83 is connected to the inlet end of the second combustion zone 2. A first air shut-off valve 11 for cutting off the air transmission path and an air fan 3 for accelerating the air transmission speed are sequentially arranged on the main air pipeline 81. The main air pipeline 81 is used to deliver the incoming air to the first air branch 82 and the second air branch 83 respectively after passing through the first air shut-off valve 11 and the air fan 3.

[0048] In some embodiments of this example, the first air branch 82 is sequentially provided with a second air regulating valve 32 for regulating the air flow of the first air branch 82 and a second air flow meter 62 for monitoring the air flow of the first air branch 82. The second air regulating valve 32 is connected to the outlet end of the main air branch 81, and the second air flow meter 62 is connected to the inlet end of the first combustion zone 1. The second air branch 83 is sequentially provided with a second air shut-off valve 15 for cutting off the air transmission path of the second air branch 83, a first air regulating valve 31 for regulating the air flow of the second air branch 83, and a first air flow meter 61 for monitoring the air flow of the second air branch 83. The second air shut-off valve 15 is connected to the outlet end of the main air branch 81, and the first air flow meter 61 is connected to the inlet end of the second combustion zone 2.

[0049] Specifically, air enters through air main A (i.e., main air line 81), passes sequentially through the first air shut-off valve 11 and the air fan 3, and is delivered to the first air branch 82A1 and the second air branch 83A2 respectively. The first air branch 82A1 is equipped with a second air regulating valve 32 and a second air flow meter 62 and is connected to the first combustion zone 1; the second air branch 83A2 is equipped with a second air shut-off valve 15, a first air regulating valve 31 and a first air flow meter 61 and is connected to the second combustion zone 2. The first air shut-off valve 11 and the second air shut-off valve 15 are used to shut off the air passage, the air fan 3 is used to accelerate the air transmission speed, the second air regulating valve 32 and the first air regulating valve 31 are used to regulate the air flow of different branches, and the second air flow meter 62 and the first air flow meter 61 are used to monitor the air flow of different branches.

[0050] In some embodiments of this example, the gas pipeline 9 includes a first gas main pipeline 91, a second gas main pipeline 92 connected to the inlet end of the second combustion zone 2, and a first gas branch pipeline 93 and a second gas branch pipeline 94 respectively connected to the outlet end of the first gas main pipeline 91. The outlet end of the first gas branch pipeline 93 is connected to the inlet end of the first combustion zone 1, and the outlet end of the second gas branch pipeline 94 is connected to the inlet end of the second combustion zone 2. The first gas main pipeline 91 is sequentially provided with a first gas shut-off valve 12 for cutting off the gas transmission path, a first filter 21 for filtering the incoming gas, a first vent valve 41 for venting the gas when the machine is stopped, and a first water bath heater 51 for heating the gas. The first gas main pipeline 91 is used to sequentially transport the incoming gas through the first gas shut-off valve 12, the first filter 21, the first vent valve 41, and the first water bath heater 51 to the first gas branch pipeline 93 and the second gas branch pipeline 94 respectively.

[0051] In some embodiments of this example, the first gas branch 93 is sequentially provided with a first gas regulating valve 33 for regulating the gas flow of the first gas branch 93, a first gas flow meter 63 for monitoring the gas flow of the first gas branch 93, and a first check valve 71 for preventing gas backflow in the first gas branch 93. The first gas regulating valve 33 is connected to the outlet end of the first gas main line 91, and the first check valve 71 is connected to the inlet end of the first combustion zone 1. The second gas branch 94 is sequentially provided with a second gas shut-off valve 13 for cutting off the gas transmission path of the second gas branch 94, a second gas regulating valve 34 for regulating the gas flow of the second gas branch 94, a second gas flow meter 64 for monitoring the gas flow of the second gas branch 94, and a second check valve 72 for preventing gas backflow in the second gas branch 94. The second gas shut-off valve 13 is connected to the outlet end of the first gas main line 91, and the second check valve 72 is connected to the inlet end of the second combustion zone 2.

[0052] Specifically, the gas introduced into the first gas main pipeline 91 is gas one, which can be a mixture of various gaseous fuels (e.g., natural gas, hydrogen, ammonia, and liquefied petroleum gas). Gas one is introduced through the first gas main pipeline B (i.e., the first gas main pipeline 91), and sequentially passes through the first gas shut-off valve 12, the first filter 21, the first vent valve 41, and the first water bath heater 51 to be delivered to the first gas branch pipeline 93B1 and the second gas branch pipeline 94B2. The first gas branch pipeline 93B1 is equipped with a first gas regulating valve 33, a first gas flow meter 63, and a first check valve 71 and is connected to the first combustion zone 1; the second gas branch pipeline 94B2 is equipped with a second gas shut-off valve 13, a second gas regulating valve 34, a second gas flow meter 64, and a second check valve 72 and is connected to the second combustion zone 2.

[0053] In some embodiments of this example, the second gas main pipeline 92 is sequentially provided with a third gas shut-off valve 14 for cutting off the gas transmission path, a second filter 22 for filtering the incoming gas, a second vent valve 42 for venting the gas when the machine is stopped, a second water bath heater 52 for heating the gas, a third gas regulating valve 35 for regulating the gas flow of the second gas main pipeline 92, a third gas flow meter 65 for monitoring the gas flow of the second gas main pipeline 92, and a third check valve 73 for preventing the gas backflow of the second gas main pipeline 92. The third check valve 73 is connected to the inlet end of the second combustion zone 2.

[0054] Specifically, the gas introduced into the second gas main pipeline 92 is gas 2, which can be a mixture of various gaseous fuels (e.g., natural gas, hydrogen, ammonia, and liquefied petroleum gas). Gas 2 is introduced through the second gas main pipeline C (i.e., the second gas main pipeline 92), and sequentially passes through the third gas shut-off valve 14, the second filter 22, the second vent valve 42, the second water bath heater 52, the third gas regulating valve 35, the third gas flow meter 65, and the third check valve 73, before being transmitted to the second combustion zone 2. A worm gear 4 is installed behind the second combustion zone 2, and a load 5 is installed behind the worm gear 4.

[0055] In some embodiments of this example, the outlet end of the second combustion zone 2 is connected to a turbine, which is connected to the load 5. The turbine is used to receive and utilize the high-temperature gas transmitted by the second combustion zone 2 to drive the load 5 into the working state.

[0056] In the above implementation process, the first gas shut-off valve 12, the second gas shut-off valve 13, and the third gas shut-off valve 14 are used to cut off the gas passage; the first filter 21 and the second filter 22 are used to filter the gas to ensure fuel cleanliness; the first vent valve 41 and the second vent valve 42 are used to vent gaseous fuel during shutdown to ensure device safety; the first water bath heater 51 and the second water bath heater 52 are used to heat the gas to prevent a sudden drop in gas temperature due to a significant pressure drop, which could lead to the gas reaching the dew point temperature and causing icing in pipelines and valves, thus affecting the stable operation of the fuel system; the first gas regulating valve 33, the second gas regulating valve 34, and the third gas regulating valve 35 are used to regulate the gas flow rate of different branches; the first gas flow meter 63, the second gas flow meter 64, and the third gas flow meter 65 are used to monitor the gas flow rate of different branches; the first check valve 71, the second check valve 72, and the third check valve 73 are used to prevent gas backflow. The high-temperature gas transmitted from the second combustion zone 2 drives the worm gear 4 to rotate, and the worm gear 4 drives the load 5 to work.

[0057] Figure 3 This is a flowchart of a gas turbine co-firing method provided in one embodiment of the present invention. Figure 3 As shown, this invention provides a gas turbine co-firing method, applied to a gas turbine co-firing system, the method comprising:

[0058] S110: Air and the first combined gas are introduced into the first combustion zone 1 for combustion, and the high-temperature gas generated by combustion in the first combustion zone 1 is transferred to the second combustion zone 2;

[0059] S120: Based on the predetermined gas turbine operating mode and the corresponding gas composition ratio calculation rules for the gas turbine operating mode, calculate the required air and gas composition ratio data transmitted to the second combustion zone 2, and determine the required air content and gas content to be introduced into the second combustion zone 2 based on the calculation results.

[0060] S130: Based on the required air content and fuel content of the second combustion zone 2, air and the second combined fuel are introduced into the second combustion zone 2 for secondary and complete combustion.

[0061] Specifically, this method introduces air and a first combined gas fuel into a first combustion zone 1 for combustion, and then transfers the high-temperature gas produced in the first combustion zone 1 to a second combustion zone 2. Based on the gas turbine operating mode and the corresponding gas composition ratio calculation rules, the required air and gas composition ratios for the second combustion zone 2 are determined. Based on these requirements, the required air and gas content for the second combustion zone 2 are determined. Then, based on these required air and gas content, the air and the second combined gas fuel are introduced into the second combustion zone 2 for secondary co-combustion to ensure complete combustion. The series connection of the first and second combustion zones 1 and 2 facilitates secondary and complete combustion of the high-temperature fuel in the first combustion zone 1 within the second combustion zone 2, thereby reducing the temperature and flue gas residence time in the first combustion zone 1 and consequently reducing nitrogen oxide formation. This gas turbine co-firing method, while utilizing the second combustion zone 2 for secondary and complete combustion, also achieves the appropriate supply ratio of air and gas in the first combustion zone 1 and the second combustion zone 2 according to different gas turbine operating modes and different fuel co-firing requirements. This allows for flexible selection of fuel types and their introduction into the first and second combustion zones 1 and 2, enabling the gas turbine co-firing system to achieve optimal operating performance in the corresponding gas turbine operating mode, thereby effectively achieving the goal of complete gas combustion.

[0062] In some embodiments of this example, the gas turbine operating modes include an environmental protection mode, an economic mode, and a high-efficiency mode. The specific content of the gas composition ratio calculation rules corresponding to the gas turbine operating modes includes: when the gas turbine operating mode is environmental protection mode, by comparing the carbon emissions corresponding to different air and gas co-firing ratios, the air and gas composition ratio corresponding to the lowest carbon emissions under the same output condition of the gas turbine co-firing system in safe operation is used as the air and gas composition ratio requirement data transmitted to the second combustion zone 2; when the gas turbine operating mode is economic mode, by... By comparing the purchase costs corresponding to different proportions of air and gas, the air and gas composition ratio corresponding to the condition that maximizes the economic benefits of the gas turbine co-firing system under the same output state of safe operation is used as the required air and gas composition ratio data for transmission to the second combustion zone 2. When the gas turbine is operating in high-efficiency mode, by comparing the combustion efficiencies corresponding to different proportions of air and gas, the air and gas composition ratio corresponding to the condition that minimizes the co-firing time of the gas turbine co-firing system under the same output state of safe operation is used as the required air and gas composition ratio data for transmission to the second combustion zone 2.

[0063] Specifically, the gas turbine co-firing system is equipped with three co-firing modes: environmental protection mode, economic mode, and high-efficiency mode. The mode is selected according to the choice or ratio of different fuels, so that the fuel achieves different target effects after staged combustion in the first combustion zone 1 and the second combustion zone 2.

[0064] The specific process of the environmental protection mode is as follows: Combustion is carried out in the first combustion zone 1 by introducing gas 1 and air. Gas 1 is a mixture of various gaseous fuels (such as natural gas, hydrogen, ammonia, and liquefied petroleum gas). The high-temperature gas generated in the first combustion zone 1 enters the second combustion zone 2. Then, depending on the fuel required for complete combustion in the second combustion zone 2, an appropriate amount of air and gas 1 or an appropriate amount of air and gas 2 is introduced. By comparing the carbon emissions from co-firing different proportions of gas, the environmental protection mode is determined by calculating the lowest carbon emissions achieved by the gas turbine co-firing system under the same output and safe operating conditions.

[0065] The specific process of the economic model is as follows: Combustion is achieved by introducing gas 1 and air into the first combustion zone 1. Gas 1 is a mixture of various gaseous fuels (such as natural gas, hydrogen, ammonia, and liquefied petroleum gas). The high-temperature gas generated in the first combustion zone 1 enters the second combustion zone 2. Then, based on the fuel required for complete combustion in the second combustion zone 2, an appropriate amount of air and gas 1 or an appropriate amount of air and gas 2 is introduced. By comparing the purchase costs of different gas composition ratios, the economic model is calculated to achieve the maximum economic benefit under the same output conditions during safe operation.

[0066] The specific process of the high-efficiency mode is as follows: Combustion is achieved by introducing gas 1 and air into the first combustion zone 1. Gas 1 is a mixture of various gaseous fuels (such as natural gas, hydrogen, ammonia, and liquefied petroleum gas). The high-temperature gas generated in the first combustion zone 1 enters the second combustion zone 2. Then, depending on the fuel required for complete combustion in the second combustion zone 2, an appropriate amount of air and gas 1 or an appropriate amount of air and gas 2 is introduced. By comparing the combustion efficiency of different gas composition ratios, the high-efficiency mode is determined by calculating the shortest co-firing time under the same output conditions during safe operation of the gas turbine co-firing system.

[0067] In some embodiments of this example, the method for selecting different co-firing modes includes the following steps:

[0068] S1. In response to the call for energy conservation and emission reduction, adopt an environmentally friendly approach;

[0069] S2. When carbon emissions meet the standards and cost savings are required, adopt an economic model.

[0070] S3. When carbon emissions meet the standards and work efficiency needs to be improved, adopt the high-efficiency mode.

[0071] Specifically, air and fuel gas 1 enter the first combustion zone 1 for co-combustion via the first air branch 82A1 and the first fuel gas branch 93B1, respectively. The high-temperature flue gas generated in the first combustion zone 1 enters the second combustion zone 2. Then, based on the fuel requirements for complete combustion in the second combustion zone 2, an appropriate amount of air and fuel gas 1 or an appropriate amount of air and fuel gas 2 is introduced to ensure complete co-combustion within the second combustion zone 2. Furthermore, by considering different needs for environmental benefits, economic benefits, and operational efficiency, an appropriate operating mode is selected to control the gas turbine co-combustion system and achieve optimal operating results.

[0072] In some embodiments of this example, the first combined gas is the combined gas supplied through the first gas main line 91, and the second combined gas is the combined gas supplied through the first gas main line 91 and / or the combined gas supplied through the second gas main line 92.

[0073] In the above-mentioned process, the system and method are equipped with shut-off valves and regulating valves to control the supply of air and gas, thereby achieving an appropriate ratio of supply to the first combustion zone 1 and the second combustion zone 2. This ensures complete combustion of the gas in the co-firing system, reduces nitrogen oxide emissions, and achieves environmental benefits. By setting environmental protection mode, economic mode, and high-efficiency mode, and by calculating the gas ratio, the system achieves the lowest carbon emissions, the highest economic benefits, and the shortest co-firing time under the same output conditions in safe operation. The system can be selected according to different needs to control the gas turbine co-firing system to achieve the best operating effect.

[0074] The optional embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the embodiments of the present invention are not limited to the specific details in the above embodiments. Within the scope of the technical concept of the embodiments of the present invention, various simple modifications can be made to the technical solutions of the embodiments of the present invention, and these simple modifications all fall within the protection scope of the embodiments of the present invention.

[0075] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, the embodiments of the present invention will not describe the various possible combinations separately.

[0076] Those skilled in the art will understand that all or part of the steps in the methods of the above embodiments can be implemented by a program instructing related hardware. This program is stored in a storage medium and includes several instructions to cause a microcontroller, chip, or processor to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as a USB flash drive, a portable hard drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk.

[0077] Furthermore, various different implementations of the present invention can be combined arbitrarily, as long as they do not violate the spirit of the present invention, they should also be regarded as the content disclosed in the present invention.

Claims

1. A gas turbine co-firing system, characterized in that, It includes a combustion chamber and a first air supply pipeline connected to the inlet end of the combustion chamber. The combustion chamber is provided with multiple combustion zones connected in series by a second air supply pipeline. Each combustion zone is connected in parallel to the first air supply pipeline. There are two combustion zones in the combustion chamber, namely a first combustion zone and a second combustion zone. The first combustion zone converts the gas supplied by the first gas supply line into high-temperature gas through combustion, and then transmits the high-temperature gas through the second gas supply line to the subsequent combustion zones for further combustion. Starting from the second combustion zone, each combustion zone receives a fixed amount of gas from the first gas supply line and performs further combustion based on the supplied gas and the high-temperature fuel gas output from the previous adjacent combustion zone, until combustion in the last combustion zone is completed; among which, Starting from the second combustion zone, the quantitative rules for collecting a fixed amount of gas from the first gas supply pipeline in each combustion zone are determined based on the pre-determined gas turbine operating mode and the corresponding gas composition ratio calculation rules for the gas turbine operating mode. The first gas supply line includes independently installed air lines and gas lines; The quantitative rule for collecting a fixed amount of gas from the first gas supply pipeline for each combustion zone, starting from the second combustion zone, is the mixing ratio rule for air and fuel gas. The air pipeline includes a main air pipeline and a first air branch and a second air branch, which are respectively connected to the outlet end of the main air pipeline. The outlet end of the first air branch is connected to the inlet end of the first combustion zone, and the outlet end of the second air branch is connected to the inlet end of the second combustion zone. The main air pipe is sequentially equipped with a first air shut-off valve for cutting off the air transmission path and an air fan for accelerating the air transmission speed. The main air pipe is used to deliver the incoming air to the first air branch and the second air branch respectively after passing through the first air shut-off valve and the air fan. The first air branch is sequentially provided with a second air regulating valve for adjusting the air flow of the first air branch and a second air flow meter for monitoring the air flow of the first air branch. The second air regulating valve is connected to the outlet end of the main air line, and the second air flow meter is connected to the inlet end of the first combustion zone. The second air branch is sequentially provided with a second air shut-off valve for cutting off the air transmission path of the second air branch, a first air regulating valve for adjusting the air flow of the second air branch, and a first air flow meter for monitoring the air flow of the second air branch. The second air shut-off valve is connected to the outlet end of the main air line, and the first air flow meter is connected to the inlet end of the second combustion zone.

2. The gas turbine co-firing system according to claim 1, characterized in that, The gas pipeline includes a first main gas pipeline, a second main gas pipeline connected to the inlet end of the second combustion zone, and a first branch gas pipeline and a second branch gas pipeline respectively connected to the outlet end of the first main gas pipeline. The outlet end of the first branch gas pipeline is connected to the inlet end of the first combustion zone, and the outlet end of the second branch gas pipeline is connected to the inlet end of the second combustion zone. The first gas main pipeline is sequentially equipped with a first gas shut-off valve for cutting off the gas transmission path, a first filter for filtering the incoming gas, a first vent valve for venting the gas when the machine is stopped, and a first water bath heater for heating the gas. The first gas main pipeline is used to deliver the incoming gas to the first gas branch and the second gas branch respectively after passing through the first gas shut-off valve, the first filter, the first vent valve and the first water bath heater in sequence.

3. The gas turbine co-firing system according to claim 2, characterized in that, The first gas branch is sequentially equipped with a first gas regulating valve for adjusting the gas flow of the first gas branch, a first gas flow meter for monitoring the gas flow of the first gas branch, and a first check valve for preventing gas backflow in the first gas branch. The first gas regulating valve is connected to the outlet end of the first gas main line, and the first check valve is connected to the inlet end of the first combustion zone. The second gas branch is sequentially equipped with a second gas shut-off valve for cutting off the gas transmission path of the second gas branch, a second gas regulating valve for adjusting the gas flow of the second gas branch, a second gas flow meter for monitoring the gas flow of the second gas branch, and a second check valve for preventing gas backflow in the second gas branch. The second gas shut-off valve is connected to the outlet end of the first gas main line, and the second check valve is connected to the inlet end of the second combustion zone.

4. The gas turbine co-firing system according to claim 2, characterized in that, The second gas main pipeline is sequentially equipped with a third gas shut-off valve for cutting off the gas transmission path, a second filter for filtering the incoming gas, a second vent valve for venting the gas when the machine is stopped, a second water bath heater for heating the gas, a third gas regulating valve for regulating the gas flow rate of the second gas main pipeline, a third gas flow meter for monitoring the gas flow rate of the second gas main pipeline, and a third check valve for preventing the gas backflow of the second gas main pipeline. The third check valve is connected to the inlet end of the second combustion zone.

5. The gas turbine co-firing system according to claim 1, characterized in that, The outlet end of the second combustion zone is connected to a turbine, which is connected to a load; The turbine is used to receive and utilize the high-temperature gas transmitted from the second combustion zone for driving, so as to drive the load into the working state.

6. A method for co-firing in a gas turbine, characterized in that, The method, applied to a gas turbine co-firing system as described in any one of claims 1 to 5, comprises: Air and the first combined gas are introduced into the first combustion zone for combustion, and the high-temperature gas generated in the first combustion zone is transferred to the second combustion zone. Based on the predetermined gas turbine operating mode and the corresponding gas composition ratio calculation rules for the gas turbine operating mode, the required air and gas composition ratio data transmitted to the second combustion zone are calculated. Based on the calculation results, the required air content and gas content to be introduced into the second combustion zone are determined. Based on the required air and fuel gas content for the second combustion zone, air and the second combined fuel gas are introduced into the second combustion zone for secondary and complete combustion.

7. The gas turbine co-firing method according to claim 6, characterized in that, The gas turbine operating modes include environmental protection mode, economic mode, and high-efficiency mode; The specific details of the calculation rules for the gas composition ratio of the corresponding gas turbine operating mode include: When the gas turbine is operating in environmental protection mode, by comparing the carbon emission from co-firing of air and gas with different composition ratios, the composition ratio of air and gas corresponding to the lowest carbon emission from co-firing under the same output condition of the gas turbine co-firing system under safe operating conditions is taken as the required composition ratio of air and gas to be transmitted to the second combustion zone. When the gas turbine is operating in the economic mode, by comparing the purchase costs corresponding to different proportions of air and gas, the air and gas composition ratio corresponding to the situation that maximizes the economic benefits of the gas turbine co-firing system under the same output under safe operating conditions is used as the air and gas composition ratio demand data to be transmitted to the second combustion zone. When the gas turbine is operating in high-efficiency mode, by comparing the combustion efficiency corresponding to different air and gas composition ratios, the air and gas composition ratio corresponding to the shortest co-firing time under the same output condition of the gas turbine co-firing system under safe operating conditions is used as the air and gas composition ratio requirement data to be transmitted to the second combustion zone.

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