Gas turbine blending combustion system and method

Abstract

The invention 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 fuel gas pipeline, wherein a first combustion area and a second combustion area which are connected in series are arranged in the combustion chamber; the first combustion area is used for combusting by using the received air transmitted by the air pipeline and the received fuel gas transmitted by the fuel gas pipeline, and transmitting the high-temperature fuel gas generated by combustion to the second combustion area; the second combustion area is used for carrying out secondary sufficient combustion by utilizing the received high-temperature fuel gas transmitted by the first combustion area, the air transmitted by the air pipeline and the fuel gas transmitted by the fuel gas pipeline; the composition proportion of the air and the fuel gas transmitted to the second combustion zone is determined based on a fuel gas composition proportion calculation rule of the gas turbine operation mode. When the second combustion area is used for secondary sufficient combustion, air and fuel gas in the first combustion area and the second combustion area are supplied according to a proper proportion, and the purpose of sufficient combustion of the fuel gas is effectively achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine blending system and a gas turbine blending method. Background Art

[0002] Gas turbines are widely used in power generation, pipeline power, ship power and other fields. With the enhancement of global awareness of environmental protection and the promotion of energy conservation and emission reduction policies, gas turbine emission reduction has become an important issue in the current energy field. Axial staged combustion technology has been widely used in the field of gas turbines as an effective means to reduce nitrogen oxide emissions. This axial staged combustion technology adds a secondary combustion zone after the main combustion zone of the combustion chamber, and diverts part of the fuel and air to this secondary combustion zone for combustion, thereby reducing the temperature and flue gas residence time in the main combustion zone, thereby reducing the generation of nitrogen oxides. However, the current axial staged combustion technology has not yet met the demand for blending of different fuels to achieve the appropriate proportion of supply in the main combustion zone and the secondary combustion zone, and has also failed to effectively achieve full combustion of the gas in the blending system.

[0003] Therefore, how to flexibly select the fuel type configuration and introduce it into the combustion zone by setting up the gas and air supply lines of 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 a problem that needs to be solved urgently. Summary of the invention

[0004] The purpose of the embodiments of the present invention is to provide a gas turbine co-firing system and method to at least solve the above-mentioned problem of how to flexibly select the fuel type configuration and introduce it into the combustion zone by setting the gas and air supply lines of 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] In order to achieve the above-mentioned object, the present invention provides a gas turbine co-combustion system in a first aspect, comprising a combustion chamber and a first gas supply pipeline connected to an inlet end of the combustion chamber, wherein a plurality of combustion zones connected in series through a second gas supply pipeline are arranged in the combustion chamber, and each combustion zone is connected in parallel to the first gas supply pipeline; The first combustion zone converts the supply gas of the first gas supply pipeline into high-temperature fuel gas through combustion, and transmits the high-temperature fuel gas to subsequent combustion zones step by step through the second gas supply pipeline for further combustion; Starting from the second 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 fuel gas output from the previous adjacent combustion zone until the combustion of the last combustion zone is completed; wherein, Starting from the second combustion zone, the quantitative rule for each combustion zone to collect quantitative supply gas from the first gas supply pipeline is determined based on a predetermined gas turbine operation mode and a gas composition ratio calculation rule corresponding to the gas turbine operation mode.

[0006] Optionally, there are two combustion zones in the combustion chamber, namely a first combustion zone and a second combustion zone; The first gas supply pipeline includes an air pipeline and a gas pipeline which are independently arranged; Starting from the second combustion zone, each combustion zone collects a quantitative supply of gas from the first gas supply pipeline according to a quantitative rule that is a mixing ratio rule of air and fuel gas.

[0007] Optionally, the 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; The main air line is provided with a first air shut-off valve for cutting off the air transmission passage and an air blower for accelerating the air transmission speed in sequence. The main air line is used to transport 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 blower in sequence.

[0008] Optionally, the first air branch is provided with a second air regulating valve for regulating the air flow of the first air branch and a second air flow meter for monitoring the air flow of the first air branch in sequence, 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, and the second air branch is provided with a second air cut-off valve for cutting off the air transmission passage of the second air branch, a first air regulating valve for regulating the air flow of the second air branch and a first air flow meter for monitoring the air flow of the second air branch in sequence, the second air cut-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.

[0009] 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 pipeline and a second gas branch pipeline respectively connected to the outlet end of the first gas main pipeline, the outlet end of the first gas branch pipeline is connected to the inlet end of the first combustion zone, and the outlet end of the second gas branch pipeline is connected to the inlet end of the second combustion zone; The first gas main line is provided with a first gas shut-off valve for cutting off the gas transmission path, a first filter for filtering the introduced gas, a first drain valve for draining the gas during shutdown, and a first water bath heater for heating the gas in sequence. The first gas main line is used to transport the introduced gas to the first gas branch line and the second gas branch line respectively after passing through the first gas shut-off valve, the first filter, the first drain valve and the first water bath heater in sequence.

[0010] Optionally, the first gas branch is provided with a first gas regulating valve for regulating the gas flow of the first gas branch, a first gas flowmeter for monitoring the gas flow of the first gas branch and a first check valve for preventing gas backflow of the first gas branch in sequence, 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, and the second gas branch is 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 flowmeter for monitoring the gas flow of the second gas branch and a second check valve for preventing gas backflow of the second gas branch in sequence, 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.

[0011] Optionally, the above-mentioned second gas main line is provided with a third gas shut-off valve for cutting off the gas transmission path, a second filter for filtering the introduced gas, a second drain valve for draining the gas during shutdown, a second water bath heater for heating the gas, a third gas regulating valve for adjusting the gas flow of the second gas main line, a third gas flowmeter for monitoring the gas flow of the second gas main line and a third check valve for preventing the gas backflow of the second gas main line, and the third check valve is connected to the inlet end of the second combustion zone.

[0012] Optionally, the outlet end of the second combustion zone is connected to a turbine, and the turbine is connected to a load; The turbine is used to receive and utilize the high-temperature combustion gas transmitted by the second combustion zone to be driven, so as to drive the load into a working state.

[0013] A second aspect of the present invention provides a gas turbine co-firing method, which is applied to a gas turbine co-firing system. The method comprises: Passing air and the first combined fuel gas into the first combustion zone for combustion, and transmitting the high-temperature fuel gas generated by the combustion in the first combustion zone to the second combustion zone; Based on a predetermined gas turbine operation mode and a gas composition ratio calculation rule corresponding to the gas turbine operation mode, calculating the composition ratio requirement data of air and gas transmitted to the second combustion zone, and determining the required air content and gas content introduced into the second combustion zone based on the calculation result; According to the required air content and gas content introduced into the second combustion zone, air and the second combined gas are introduced into the second combustion zone for secondary full combustion.

[0014] Optionally, the gas turbine operation mode includes an environmental protection mode, an economic mode and a high efficiency mode; The specific contents of the calculation rules for the gas composition ratio corresponding to the gas turbine operation mode include: When the gas turbine is in the environmental protection mode, by comparing the carbon emission of the blended combustion corresponding to the air and gas with different composition ratios, the composition ratio of air and gas corresponding to the lowest carbon emission of the blended combustion under the same output of the gas turbine blended combustion system in the safe operation state is used as the composition ratio demand data of the air and gas transmitted to the second combustion zone; When the gas turbine is in economic mode, by comparing the purchase costs of air and gas with different composition ratios, the composition ratio of air and gas corresponding to the maximum economic benefit of the gas turbine blending system under the same output in a safe operating state is used as the composition ratio demand data of air and gas transmitted to the second combustion zone; When the gas turbine operating mode is the high-efficiency mode, by comparing the combustion efficiencies corresponding to air and gas with different composition ratios, the composition ratio of air and gas corresponding to the shortest blending time when the gas turbine blending system is in a safe operating state with the same output is used as the required data for the composition ratio of air and gas transmitted to the second combustion zone.

[0015] Optionally, the first combination gas is the combination gas introduced into the first gas main line, and the second combination gas is the combination gas introduced into the first gas main line and / or the combination gas introduced into the second gas main line.

[0016] Through the above technical scheme, a gas turbine blending system and method are provided, which transmits supply gas (wherein the supply gas can be a combination of fuel gas and oxygen, a combination of fuel gas and air, a combination of fuel gas, oxygen and nitrogen, etc.) to the first combustion zone through a first gas supply pipeline, so as to perform gas blending in the first combustion zone. The high-temperature fuel gas generated by the combustion in the first combustion zone is transmitted step by step to the subsequent combustion zone through 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 operation mode and the calculation rule of the fuel gas composition ratio corresponding to the gas turbine operation mode. According to the content of the supply gas transmitted to each combustion zone, each combustion zone performs quantitative supply gas collection from the first gas supply pipeline, and performs further combustion based on the supply gas and the high-temperature fuel gas output from the previous adjacent combustion zone until the combustion of the last combustion zone is completed. Therefore, the design of multiple combustion zones arranged in series is conducive to the secondary full combustion of the high-temperature fuel in the first combustion zone in the subsequent combustion zone, thereby reducing the temperature and flue gas residence time of the first combustion zone, and further reducing the generation of nitrogen oxides. The gas turbine co-combustion system and method not only utilizes the subsequent combustion zone for secondary full combustion, but also realizes the supply of appropriate proportions of air and gas in each combustion zone according to different gas turbine operating modes and the co-combustion requirements of different fuels, thereby flexibly selecting the fuel type configuration and introducing it into each combustion zone, so that the gas turbine co-combustion system can achieve the best operating effect in the corresponding gas turbine operating mode, thereby effectively realizing the purpose of full combustion of the gas.

[0017] Other features and advantages of the embodiments of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings are used to provide a further understanding of the embodiments of the present invention and constitute a part of the specification. Together with the following specific embodiments, they are used to explain the embodiments of the present invention, but do not constitute a limitation on the embodiments of the present invention. In the accompanying drawings: Figure 1 It is a structural schematic diagram of a gas turbine blending system provided by one embodiment of the present invention; Figure 2 is a schematic structural diagram of another gas turbine co-firing system provided by one embodiment of the present invention; Figure 3 It is a flow chart of a gas turbine co-firing method provided in one embodiment of the present invention.

[0019] Description of Reference Numerals 1-first combustion zone, 2-second combustion zone, 3-air fan, 4-worm 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 drain valve, 42-second drain 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 DESCRIPTION

[0020] The specific implementation of the embodiment of the present invention is described in detail below in conjunction with the accompanying drawings. It should be understood that the specific implementation described here is only used to illustrate and explain the embodiment of the present invention, and is not used to limit the embodiment of the present invention.

[0021] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0022] In the present invention, unless otherwise specified, directional words such as "up, down, top, bottom" are usually used with reference to the directions shown in the drawings or are used to describe the relative positional relationships of components in the vertical, perpendicular or gravity direction.

[0023] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0024] Figure 1 FIG. 1 is a schematic diagram of a gas turbine co-firing system provided by an embodiment of the present invention. Figure 1As shown, an embodiment of the present invention provides a gas turbine co-firing system, including a combustion chamber, and a first air supply pipeline connected to the inlet end of the combustion chamber, wherein a plurality of combustion zones are arranged in series through a second air supply pipeline, and each combustion zone is connected in parallel to the first air supply pipeline; the first combustion zone 1 converts the supply gas of the first air supply pipeline into high-temperature fuel gas through combustion, and transmits the high-temperature fuel gas step by step to subsequent combustion zones through the second air supply pipeline to perform further combustion; starting from the second combustion zone 2, each combustion zone performs quantitative supply gas collection from the first air supply pipeline, and performs further combustion based on the supply gas and the high-temperature fuel gas output by the previous adjacent combustion zone until the combustion of the last combustion zone is completed; wherein, starting from the second combustion zone 2, the quantitative rule for each combustion zone to perform quantitative supply gas collection from the first air supply pipeline is determined based on a predetermined gas turbine operating mode and a gas composition ratio calculation rule corresponding to the gas turbine operating mode.

[0025] Specifically, the gas turbine blending system transmits supply gas (wherein the supply gas may be a combination of fuel gas and oxygen, a combination of fuel gas and air, a combination of fuel gas, oxygen and nitrogen, etc.) to the first combustion zone 1 through the first gas supply pipeline, so as to perform fuel gas blending in the first combustion zone 1. The high-temperature fuel gas generated by the combustion in the first combustion zone 1 is transmitted step by step to the subsequent combustion zones through the second gas supply pipeline. Starting from the second combustion zone 2, the content of the supply gas transmitted to each combustion zone is determined according to the gas turbine operation mode and the calculation rule of the fuel gas composition ratio corresponding to the gas turbine operation mode. According to the content of the supply gas transmitted to each combustion zone, each combustion zone performs quantitative supply gas collection from the first gas supply pipeline, and performs further combustion based on the supply gas and the high-temperature fuel gas output from the previous adjacent combustion zone until the combustion of the last combustion zone is completed. Therefore, the design of multiple combustion zones arranged in series is conducive to the secondary full combustion of the high-temperature fuel in the first combustion zone 1 in the subsequent combustion zone, thereby reducing the temperature and flue gas residence time of the first combustion zone 1, and further reducing the generation of nitrogen oxides. While utilizing the subsequent combustion zone for secondary full combustion, the gas turbine co-combustion system also realizes the supply of appropriate proportions of air and gas in each combustion zone according to different gas turbine operating modes and the co-combustion requirements of different fuels, thereby flexibly selecting the fuel type configuration and introducing it into each combustion zone, so that the gas turbine co-combustion system can achieve the best operating effect in the corresponding gas turbine operating mode, thereby effectively achieving the purpose of full combustion of the gas.

[0026] In some implementations of the present embodiment, there are two combustion zones in the above-mentioned combustion chamber, namely, a first combustion zone 1 and a second combustion zone 2; the first gas supply pipeline includes independently arranged air pipeline 8 and gas pipeline 9; starting from the second combustion zone 2, each combustion zone carries out quantitative supply gas collection from the first gas supply pipeline, and the quantitative rule is the mixing ratio rule of air and gas.

[0027] Specifically, the gas turbine blending system transmits air to the first combustion zone 1 through the air pipeline 8, and transmits gas to the first combustion zone 1 through the gas pipeline 9, so as to perform gas blending in the first combustion zone 1. The high-temperature gas generated by the combustion in the first combustion zone 1 is transmitted to the second combustion zone 2, and the composition ratio of the air and gas transmitted to the second combustion zone 2 is determined according to the gas turbine operation mode and the gas composition ratio calculation rule corresponding to the gas turbine operation mode. According to the composition ratio of the air and gas transmitted to the second combustion zone 2, the air content transmitted to the second combustion zone 2 by the air pipeline 8 and the gas content transmitted to the second combustion zone 2 by the gas pipeline 9 are controlled, so as to perform secondary blending of gas in the second combustion zone 2, so as to fully burn the gas. The design of the first combustion zone 1 and the second combustion zone 2 arranged in series is conducive to the secondary full combustion of the high-temperature fuel in the first combustion zone 1 in the second combustion zone 2, thereby reducing the temperature and flue gas residence time of the first combustion zone 1, and further reducing the generation of nitrogen oxides. While utilizing the second combustion zone 2 for secondary full combustion, the gas turbine co-combustion system also realizes the supply of appropriate proportions of air and gas in the first combustion zone 1 and the second combustion zone 2 according to different gas turbine operating modes and the co-combustion requirements of different fuels, thereby flexibly selecting the fuel type configuration and introducing it into the first combustion zone 1 and the second combustion zone 2, so that the gas turbine co-combustion system can achieve the best operating effect in the corresponding gas turbine operating mode, thereby effectively realizing the purpose of full combustion of the gas.

[0028] Please refer to Figure 2 , Figure 2 It is a structural schematic diagram of another gas turbine blending system provided by an embodiment of the present invention. In some embodiments of this embodiment, the air pipeline 8 includes an air main pipeline 81 and a first air branch 82 and a second air branch 83 respectively connected to the outlet end of the air main 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; the air main pipeline 81 is provided with a first air shut-off valve 11 for cutting off the air transmission passage and an air blower 3 for accelerating the transmission speed of the air, and the air main pipeline 81 is used to transport 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 blower 3 in sequence.

[0029] In some implementations of the present embodiment, the first air branch 82 is 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 in sequence, the second air regulating valve 32 is connected to the outlet end of the main air line 81, and the second air flow meter 62 is connected to the inlet end of the first combustion zone 1, and the second air branch 83 is provided with a second air cut-off valve 15 for cutting off the air transmission passage 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 in sequence, the second air cut-off valve 15 is connected to the outlet end of the main air line 81, and the first air flow meter 61 is connected to the inlet end of the second combustion zone 2.

[0030] Specifically, air is introduced through the air main line A (i.e., the main air line 81), and is transported through the first air shut-off valve 11 and the air blower 3 in sequence, and is transported to the first air branch 82A1 and the second air branch 83A2 respectively. The first air branch 82A1 is provided 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 provided 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 cut off the air passage, the air blower 3 is used to speed up the transmission speed of the air, the second air regulating valve 32 and the first air regulating valve 31 are used to adjust 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.

[0031] In some implementations of the present embodiment, 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 ends 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 drain valve 41 for draining the gas during shutdown, and a first water bath heater 51 for heating the gas. The first gas main pipeline 91 is used to transport the incoming gas to the first gas branch pipeline 93 and the second gas branch pipeline 94 respectively after passing through the first gas shut-off valve 12, the first filter 21, the first drain valve 41 and the first water bath heater 51 in sequence.

[0032] In some implementations of the present embodiment, the first gas branch 93 is 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 the gas backflow of the first gas branch 93 in sequence, 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, and the second gas branch 94 is 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 the gas backflow of the second gas branch 94 in sequence, 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.

[0033] Specifically, the gas introduced into the first main gas pipeline 91 is gas one, and gas one can be a mixture of multiple gas fuels (for example, natural gas, hydrogen, ammonia, and liquefied petroleum gas, etc.). Gas one is introduced through the first gas main pipeline B (i.e., the first main gas pipeline 91), and is sequentially transported to the first gas branch 93B1 and the second gas branch 94B2 through the first gas shut-off valve 12, the first filter 21, the first drain valve 41, and the first water bath heater 51. The first gas branch 93B1 is provided with a first gas regulating valve 33, a first gas flowmeter 63, and a first check valve 71 and is connected to the first combustion zone 1; the second gas branch 94B2 is provided with a second gas shut-off valve 13, a second gas regulating valve 34, a second gas flowmeter 64, and a second check valve 72 and is connected to the second combustion zone 2.

[0034] In some implementations of the present embodiment, the second gas main line 92 is provided with a third gas shut-off valve 14 for cutting off the gas transmission path, a second filter 22 for filtering the introduced gas, a second drain valve 42 for draining the gas during shutdown, a second water bath heater 52 for heating the gas, a third gas regulating valve 35 for adjusting the gas flow of the second gas main line 92, a third gas flow meter 65 for monitoring the gas flow of the second gas main line 92 and a third check valve 73 for preventing the gas backflow of the second gas main line 92, and the third check valve 73 is connected to the inlet end of the second combustion zone 2.

[0035] Specifically, the gas introduced into the second gas main line 92 is gas 2, which can be a mixture of multiple gas fuels (for example, natural gas, hydrogen, ammonia, and liquefied petroleum gas, etc.). Gas 2 is introduced through the second gas main line C (i.e., the second gas main line 92), and sequentially passes through the third gas shut-off valve 14, the second filter 22, the second drain 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, and is transmitted to the second combustion zone 2. A worm gear 4 is provided at the rear of the second combustion zone 2, and a load 5 is provided at the rear of the worm gear 4.

[0036] In some implementations of this embodiment, 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 combustion gas transmitted by the second combustion zone 2 to drive the load 5 to enter a working state.

[0037] 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 passage of gas; the first filter 21 and the second filter 22 are used to filter the gas to ensure the cleanliness of the fuel; the first drain valve 41 and the second drain valve 42 are used to drain the gaseous fuel when shutting down to ensure the safety of the device; the first water bath heater 51 and the second water bath heater 52 are used to heat the gas to prevent the gas temperature from dropping sharply due to a large pressure drop in the gas, causing the gas temperature to reach the dew point temperature, causing the pipeline and valve to freeze and thus affect 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 adjust the gas flow 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 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 conducted from the second combustion zone 2 drives the worm gear 4 to rotate, and the worm gear 4 drives the load 5 to work.

[0038] Figure 3 FIG. 1 is a flow chart of a gas turbine blending method provided by one embodiment of the present invention. Figure 3 As shown, an embodiment of the present invention provides a gas turbine co-firing method, which is applied to a gas turbine co-firing system. The method comprises: S110: passing air and the first combined fuel gas into the first combustion zone 1 for combustion, and transmitting the high-temperature fuel gas generated by the combustion in the first combustion zone 1 to the second combustion zone 2; S120: based on a predetermined gas turbine operation mode and a gas composition ratio calculation rule corresponding to the gas turbine operation mode, calculating the composition ratio requirement data of air and gas transmitted to the second combustion zone 2, and determining the required air content and gas content introduced into the second combustion zone 2 based on the calculation result; S130: According to the required air content and gas content introduced into the second combustion zone 2, air and the second combined gas are introduced into the second combustion zone 2 for secondary full combustion.

[0039] Specifically, the method passes air and a first combination of gas into the first combustion zone 1 for combustion, and transmits the high-temperature gas generated by the combustion in the first combustion zone 1 to the second combustion zone 2. The composition ratio requirement data of the air and gas transmitted to the second combustion zone 2 is determined according to the gas turbine operation mode and the gas composition ratio calculation rule corresponding to the gas turbine operation mode, and the required air content and gas content passed into the second combustion zone 2 are determined according to the composition ratio requirement data of the air and gas transmitted to the second combustion zone 2. According to the required air content and gas content passed into the second combustion zone 2, air and the second combination of gas are passed into the second combustion zone 2 for secondary gas blending to fully burn the gas. The design of the first combustion zone 1 and the second combustion zone 2 arranged in series is conducive to the secondary full combustion of the high-temperature fuel in the first combustion zone 1 in the second combustion zone 2, thereby reducing the temperature and flue gas residence time of the first combustion zone 1, and further reducing the generation of nitrogen oxides. This gas turbine co-combustion method not only utilizes the second combustion zone 2 for secondary full combustion, but also realizes the supply of appropriate proportions of air and gas in the first combustion zone 1 and the second combustion zone 2 according to different gas turbine operating modes and the co-combustion requirements of different fuels, thereby flexibly selecting the fuel type configuration and introducing it into the first combustion zone 1 and the second combustion zone 2, so that the gas turbine co-combustion system can achieve the best operating effect in the corresponding gas turbine operating mode, thereby effectively achieving the purpose of full combustion of the gas.

[0040] In some implementations of the present embodiment, the gas turbine operation modes include an environmental protection mode, an economic mode, and a high-efficiency mode; the specific content of the gas composition ratio calculation rule corresponding to the gas turbine operation mode includes: when the gas turbine operation mode is the environmental protection mode, by comparing the co-combustion carbon emissions corresponding to air and gas with different composition ratios, the composition ratio of air and gas corresponding to the lowest co-combustion carbon emissions of the gas turbine co-combustion system under the same output in a safe operation state is used as the air and gas composition ratio demand data transmitted to the second combustion zone 2; when the gas turbine operation mode is the economic mode, by comparing the air and gas co-combustion carbon emissions corresponding to air and gas with different composition ratios, the air and gas composition ratio corresponding to the lowest co-combustion carbon emissions of the gas turbine co-combustion system under the same output in a safe operation state is used as the air and gas composition ratio demand data transmitted to the second combustion zone 2; The purchase costs corresponding to air and gas with different composition ratios are compared, and the composition ratio of air and gas corresponding to the situation where the economic benefit of the gas turbine blending system is the highest under the condition of safe operation and the same output is used as the demand data of the composition ratio of air and gas transmitted to the second combustion zone 2; when the gas turbine operation mode is the high-efficiency mode, by comparing the combustion efficiencies corresponding to air and gas with different composition ratios, the composition ratio of air and gas corresponding to the situation where the blending time of the gas turbine blending system is the shortest under the condition of safe operation and the same output is used as the demand data of the composition ratio of air and gas transmitted to the second combustion zone 2.

[0041] Specifically, the gas turbine blending system is provided with three blending modes, namely, environmental protection mode, economic mode and high-efficiency mode. According to the selection or proportion of different fuels, the fuel is selected so as to achieve different target effects after staged combustion in the first combustion zone 1 and the second combustion zone 2.

[0042] The specific process of the environmental protection mode is as follows: gas 1 and air are introduced into the first combustion zone 1 for combustion. Gas 1 is a mixture of multiple gas fuels (such as natural gas, hydrogen, ammonia and liquefied petroleum gas, etc.). The high-temperature gas generated in the first combustion zone 1 enters the second combustion zone 2, and then an appropriate amount of air and gas 1 or an appropriate amount of air and gas 2 are introduced according to the fuel required to be fully burned in the second combustion zone 2. By comparing the carbon emissions of the mixed combustion of gases with different proportions, it is calculated that the gas turbine mixed combustion system achieves the lowest carbon emissions under the same output in a safe operating state, which is the environmental protection mode.

[0043] The specific process of the economic mode is as follows: gas 1 and air are introduced into the first combustion zone 1 for combustion. Gas 1 is a mixture of multiple gas fuels (such as natural gas, hydrogen, ammonia and liquefied petroleum gas, etc.). The high-temperature gas generated in the first combustion zone 1 enters the second combustion zone 2, and then an appropriate amount of air and gas 1 or an appropriate amount of air and gas 2 are introduced according to the fuel required for full combustion in the second combustion zone 2. By comparing the purchase costs of gas composed of different proportions, the economic mode is calculated to achieve the maximum economic benefit under the same output of the gas turbine blending system in a safe operating state.

[0044] The specific process of the high-efficiency mode is as follows: gas 1 and air are introduced into the first combustion zone 1 for combustion. Gas 1 is a mixture of multiple gas fuels (such as natural gas, hydrogen, ammonia, and liquefied petroleum gas, etc.). The high-temperature gas generated in the first combustion zone 1 enters the second combustion zone 2, and then an appropriate amount of air and gas 1 or an appropriate amount of air and gas 2 are introduced according to the fuel required to be fully burned in the second combustion zone 2. By comparing the combustion efficiency of gases composed of different proportions, it is calculated that the gas turbine blending system achieves the shortest blending time under the same output in a safe operating state, which is the high-efficiency mode.

[0045] In some implementations of this embodiment, the method for selecting different blending modes includes the following steps: S1. Adopt environmentally friendly mode in response to the call for energy conservation and emission reduction; S2. When carbon emission meets the standard and cost saving is required, the economic model is adopted; S3. When carbon emissions meet targets and work efficiency needs to be improved, adopt high-efficiency mode.

[0046] Specifically, air and gas 1 enter the first combustion zone 1 through the first air branch 82A1 and the first gas branch 93B1 respectively for mixed combustion, and the high-temperature flue gas generated by the combustion in the first combustion zone 1 enters the second combustion zone 2. Then, according to the need for fully combusted fuel in the second combustion zone 2, appropriate amounts of air and gas 1 or air and gas 2 are introduced to fully combust in the second combustion zone 2. Then, according to the different needs of environmental protection benefits, economic benefits and work efficiency, an appropriate working mode is selected to control the gas turbine mixed combustion system to achieve the best operating effect.

[0047] In some implementations of this embodiment, the first combination gas is the combination gas introduced into the first gas main line 91 , and the second combination gas is the combination gas introduced into the first gas main line 91 and / or the combination gas introduced into the second gas main line 92 .

[0048] During the above-mentioned implementation process, the system and method realize appropriate proportion supply in the first combustion zone 1 and the second combustion zone 2 by providing a shut-off valve and a regulating valve for controlling the introduction of air and gas, thereby realizing full combustion of the gas in the blending system, reducing nitrogen oxide emissions, and achieving environmental benefits; by setting an environmental protection mode, an economic mode, and a high-efficiency mode, and by calculating the gas ratio, the system and method realize the effects of lowest carbon emissions, maximum economic benefits, and shortest blending time under the same output conditions in a safe operating state, and make selections according to different needs to control the gas turbine blending system to achieve the best operating effect.

[0049] The optional implementation modes of the embodiments of the present invention are described in detail above in conjunction with the accompanying drawings. However, the embodiments of the present invention are not limited to the specific details in the above implementation modes. Within the technical concept of the embodiments of the present invention, various simple modifications can be made to the technical scheme of the embodiments of the present invention, and these simple modifications all belong to the protection scope of the embodiments of the present invention.

[0050] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, the embodiments of the present invention will not further describe various possible combinations.

[0051] Those skilled in the art can understand that all or part of the steps in the above-mentioned embodiment method can be completed by instructing the relevant hardware through a program, and the program is stored in a storage medium, including a number of instructions to enable a single-chip microcomputer, a chip or a processor to execute all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk and other media that can store program codes.

[0052] In addition, various implementations of the embodiments of the present invention may be arbitrarily combined, and as long as they do not violate the concept of the embodiments of the present invention, they should also be regarded as the contents disclosed in the embodiments of the present invention.

Claims

1. A gas turbine co-firing system, characterized in that: It comprises a combustion chamber and a first air supply pipeline connected to the inlet end of the combustion chamber, wherein a plurality of combustion zones connected in series through a second air supply pipeline are arranged in the combustion chamber, and each combustion zone is connected in parallel to the first air supply pipeline; The first combustion zone converts the supply gas of the first gas supply pipeline into high-temperature fuel gas through combustion, and transmits the high-temperature fuel gas to subsequent combustion zones step by step through the second gas supply pipeline for further combustion; Starting from the second 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 fuel gas output from the previous adjacent combustion zone until the combustion of the last combustion zone is completed; wherein, Starting from the second combustion zone, the quantitative rule for each combustion zone to collect quantitative supply gas from the first gas supply pipeline is determined based on a predetermined gas turbine operation mode and a gas composition ratio calculation rule corresponding to the gas turbine operation mode.

2. The gas turbine co-firing system according to claim 1, characterized in that: There are two combustion zones in the combustion chamber, namely a first combustion zone and a second combustion zone; The first gas supply pipeline includes an air pipeline and a gas pipeline that are independently arranged; The quantitative rule for collecting quantitative supply gas from the first gas supply pipeline in each combustion zone starting from the second combustion zone is the mixing ratio rule of air and fuel gas.

3. The gas turbine co-firing system according to claim 2, characterized in that: The air pipeline includes an air main line and a first air branch and a second air branch respectively connected to the outlet end of the air main line, 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 line is provided with a first air shut-off valve for cutting off the air transmission passage and an air blower for accelerating the air transmission speed in sequence. The main air line is used to transport 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 blower in sequence.

4. The gas turbine co-firing system according to claim 3, characterized in that: The first air branch is 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 in sequence, 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, and the second air branch is provided with a second air cut-off valve for cutting off the air transmission passage 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 in sequence, the second air cut-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.

5. The gas turbine co-firing system according to claim 2, characterized in that: The gas pipeline includes a first gas main line, a second gas main line connected to the inlet end of the second combustion zone, and a first gas branch line and a second gas branch line respectively connected to the outlet ends of the first gas main line, the outlet end of the first gas branch line is connected to the inlet end of the first combustion zone, and the outlet end of the second gas branch line is connected to the inlet end of the second combustion zone; The first gas main line is provided with a first gas shut-off valve for cutting off the gas transmission path, a first filter for filtering the introduced gas, a first drain valve for draining the gas during shutdown, and a first water bath heater for heating the gas in sequence. The first gas main line is used to transport the introduced gas to the first gas branch line and the second gas branch line respectively after passing through the first gas shut-off valve, the first filter, the first drain valve and the first water bath heater in sequence.

6. The gas turbine co-firing system according to claim 5, characterized in that: The first gas branch is provided with a first gas regulating valve for regulating the gas flow of the first gas branch, a first gas flowmeter for monitoring the gas flow of the first gas branch and a first check valve for preventing gas backflow of the first gas branch in sequence, 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, and the second gas branch is 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 flowmeter for monitoring the gas flow of the second gas branch and a second check valve for preventing gas backflow of the second gas branch in sequence, 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.

7. The gas turbine co-firing system according to claim 5, characterized in that: The second gas main line is provided with a third gas shut-off valve for cutting off the gas transmission path, a second filter for filtering the introduced gas, a second drain valve for draining the gas during shutdown, a second water bath heater for heating the gas, a third gas regulating valve for adjusting the gas flow of the second gas main line, a third gas flow meter for monitoring the gas flow of the second gas main line and a third check valve for preventing the gas backflow of the second gas main line, and the third check valve is connected to the inlet end of the second combustion zone.

8. The gas turbine co-firing system according to claim 2, characterized in that: The outlet end of the second combustion zone is connected to a turbine, and the turbine is connected to a load; The turbine is used to receive and utilize the high-temperature combustion gas transmitted by the second combustion zone to be driven, so as to drive the load into a working state.

9. A gas turbine co-firing method, characterized in that: Applied to the gas turbine blending system according to any one of claims 1 to 8, the method comprises: Passing air and the first combined fuel gas into the first combustion zone for combustion, and transmitting the high-temperature fuel gas generated by the combustion in the first combustion zone to the second combustion zone; Based on a predetermined gas turbine operation mode and a gas composition ratio calculation rule corresponding to the gas turbine operation mode, calculating the composition ratio requirement data of air and gas transmitted to the second combustion zone, and determining the required air content and gas content passed into the second combustion zone based on the calculation result; According to the required air content and gas content introduced into the second combustion zone, air and the second combined gas are introduced into the second combustion zone for secondary full combustion.

10. The gas turbine co-firing method according to claim 9, characterized in that: The gas turbine operation modes include an environmental protection mode, an economic mode and a high efficiency mode; The specific contents of the gas composition ratio calculation rule corresponding to the gas turbine operation mode include: When the gas turbine is in an environmentally friendly mode, by comparing the carbon emission of air and gas with different composition ratios, the composition ratio of air and gas corresponding to the lowest carbon emission of the gas turbine blending system under the same output in a safe operating state is used as the composition ratio demand data of air and gas transmitted to the second combustion zone; When the gas turbine operation mode is the economic mode, by comparing the purchase costs of air and gas with different composition ratios, the composition ratio of air and gas corresponding to the maximum economic benefit of the gas turbine blending system under the same output in a safe operation state is used as the composition ratio demand data of air and gas transmitted to the second combustion zone; When the gas turbine operating mode is the high-efficiency mode, by comparing the combustion efficiencies corresponding to air and gas with different composition ratios, the composition ratio of air and gas corresponding to the shortest blending time of the gas turbine blending system under the same output in a safe operating state is used as the air and gas composition ratio requirement data transmitted to the second combustion zone.

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