CN115163309A - Fuel supply system of combustion test bed of gas turbine - Google Patents
Fuel supply system of combustion test bed of gas turbine Download PDFInfo
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- CN115163309A CN115163309A CN202210857636.2A CN202210857636A CN115163309A CN 115163309 A CN115163309 A CN 115163309A CN 202210857636 A CN202210857636 A CN 202210857636A CN 115163309 A CN115163309 A CN 115163309A
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- fuel
- valve
- gas turbine
- combustion test
- turbine combustion
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- 239000000446 fuel Substances 0.000 title claims abstract description 281
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 129
- 238000007664 blowing Methods 0.000 claims abstract description 16
- 230000005540 biological transmission Effects 0.000 claims description 81
- 230000001105 regulatory effect Effects 0.000 claims description 45
- 238000010926 purge Methods 0.000 claims description 33
- 230000001276 controlling effect Effects 0.000 claims description 28
- 238000006073 displacement reaction Methods 0.000 claims description 22
- 230000000740 bleeding effect Effects 0.000 claims description 10
- 238000004140 cleaning Methods 0.000 claims description 8
- 239000010763 heavy fuel oil Substances 0.000 claims description 7
- 238000007599 discharging Methods 0.000 claims description 3
- 238000009792 diffusion process Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 171
- IJGRMHOSHXDMSA-UHFFFAOYSA-N nitrogen Substances N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 28
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 14
- 229910052757 nitrogen Inorganic materials 0.000 description 13
- 239000003345 natural gas Substances 0.000 description 7
- 206010037544 Purging Diseases 0.000 description 5
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 229910001873 dinitrogen Inorganic materials 0.000 description 4
- 230000002093 peripheral effect Effects 0.000 description 4
- QJGQUHMNIGDVPM-UHFFFAOYSA-N nitrogen(.) Chemical compound [N] QJGQUHMNIGDVPM-UHFFFAOYSA-N 0.000 description 3
- 239000001569 carbon dioxide Substances 0.000 description 2
- 229910002092 carbon dioxide Inorganic materials 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 239000002028 Biomass Substances 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- JCXJVPUVTGWSNB-UHFFFAOYSA-N nitrogen dioxide Inorganic materials O=[N]=O JCXJVPUVTGWSNB-UHFFFAOYSA-N 0.000 description 1
- 230000001151 other effect Effects 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
Abstract
The application provides a fuel supply system of gas turbine combustion test platform, wherein, this system includes the fuel main road, the fuel branch road, the replacement gas return circuit, clear the return circuit of blowing, diffuse return circuit and gas turbine combustion test platform, the fuel main road is connected with a plurality of fuel branch roads, a plurality of fuel branch roads are connected respectively in the gas turbine combustion test platform that corresponds separately, the replacement gas return circuit is connected with the fuel main road respectively, a plurality of fuel branch roads and gas turbine combustion test platform, clear the return circuit of blowing is connected with gas turbine combustion test platform, diffuse the return circuit and be connected with fuel main road and a plurality of fuel branch roads respectively, therefore, based on a plurality of functional branch roads in the fuel supply system of gas turbine combustion test platform, realize gas turbine combustion test platform steady operation under the operating mode parameter of different gas turbines, the complexity of gas turbine combustion test platform operation has been reduced, and the security of gas turbine combustion test platform has been improved.
Description
Technical Field
The application relates to the technical field of gas turbines, in particular to a fuel supply system of a combustion test bed of a gas turbine.
Background
At present, adjusting fuel supply is an important means for changing the power of a gas turbine, in order to meet indexes such as combustion stability and pollution emission in a full load range, in the related art, a heavy-duty gas turbine usually adopts multi-path fuel staged supply, different loads correspond to different fuel supply modes, so as to ensure stable operation of the gas turbine, but the fuel staged supply logic is relatively complex, the operation conditions of the gas turbine are numerous, the stability of the operation of the gas turbine under different operation conditions is difficult to ensure, and therefore a more intelligent fuel supply system of a combustion test bed of the gas turbine is urgently needed.
Disclosure of Invention
The application provides a fuel supply system of a combustion test stand of a gas turbine.
An embodiment of an aspect of the present application provides a fuel supply system of a gas turbine combustion test bed, the fuel supply system of the gas turbine combustion test bed includes a main fuel path, a fuel branch path, a replacement gas loop, a purge loop, a bleed loop and a gas turbine combustion test bed, wherein: the fuel main path is connected with a plurality of fuel branches and is used for supplying fuel to the plurality of fuel branches; the fuel branches are respectively connected with the gas turbine combustion test beds corresponding to the fuel branches and used for conveying fuel to the gas turbine combustion test beds; the replacement gas loop is respectively connected with the main fuel path, the fuel branches and the gas turbine combustion test bed and is used for replacing the fuel in the main fuel path and the corresponding transmission pipeline of each fuel branch and the residual fuel of the gas turbine combustion test bed; the cleaning and blowing loop is connected with the gas turbine combustion test bed and is used for cleaning and blowing a fuel nozzle in the gas turbine combustion test bed according to cleaning and blowing gas in the cleaning and blowing loop; the diffusion loop is respectively connected with the main fuel path and the plurality of fuel branches and is used for discharging the fuel in the corresponding delivery pipelines of the main fuel path and the plurality of fuel branches.
In one embodiment of the present application, a pressure regulating module, a first shut-off valve, an emergency shut-off valve and a heater are installed on a transmission pipeline of the main fuel pipeline, wherein: the output of the pressure regulating module is connected with the input of the first shutoff valve through a transmission pipeline and is used for controlling the pressure of the fuel in the transmission pipeline of the fuel main pipeline; the output of the first shut-off valve is connected with the input of the emergency shut-off valve through a transmission pipeline and is used for controlling the start and stop of the transmission of the fuel to the transmission pipeline of the main fuel pipeline; the output of the emergency cut-off valve is connected with the input of the heater through a transmission pipeline and is used for emergently stopping the transmission of the fuel in the fuel main pipeline in the transmission pipeline; the output of the heater is connected with a plurality of fuel branches through a transmission pipeline and is used for preheating the fuel in the transmission pipeline of the main fuel pipeline.
In one embodiment of the present application, the transfer pipe of the fuel branch is mounted with a regulating valve and a second shut-off valve, wherein: the input of the regulating valve is connected with the output of the heater, and the output of the regulating valve is connected with the second shutoff valve and used for regulating the flow of the fuel in the transmission pipeline of the fuel branch; and the output of the second shut-off valve is connected with the gas turbine combustion test bed through a transmission pipeline and is used for controlling the start and stop of the transmission of the fuel to the gas turbine combustion test bed.
In one embodiment of the present application, the displacement gas circuit comprises a first displacement gas circuit and a second displacement gas circuit, wherein: the output of the first replacement gas circuit is connected with the output of the first shutoff valve and is used for replacing the fuel in the transmission pipelines of the main fuel pipeline and the fuel branch pipeline based on low-pressure gas; and the output of the second replacement gas loop is respectively connected with the output of the regulating valve and the gas turbine combustion test bed and used for replacing the fuel in the transmission pipeline of the fuel branch and the residual fuel of the gas turbine combustion test bed based on high-pressure gas.
In one embodiment of the application, a third shut-off valve is mounted on the transport pipe of the first replacement gas circuit, wherein: the output of the third shut-off valve is connected with the output of the first shut-off valve through a transmission pipeline and is used for controlling the start and stop of the transmission of the low-pressure gas to the transmission pipelines of the fuel main pipeline and the fuel branch pipeline.
In one embodiment of the present application, a fourth shutoff valve and a fifth shutoff valve are installed on the transfer pipe of the second displacement gas circuit, wherein: the output of the fourth shutoff valve is connected with the input of the fifth shutoff valve through a transmission pipeline and is used for controlling the start and stop of the transmission of the high-pressure gas to the second replacement gas loop; and the output of the fifth shutoff valve is connected with the gas turbine combustion test bed through a transmission pipeline and is used for controlling the start and stop of the transmission of the high-pressure gas to the gas turbine combustion test bed.
In one embodiment of the present application, a check valve is further mounted on the transfer pipe of the second displacement gas circuit, wherein: the check valve is installed between the output of the shut-off valve and the combustion test bed of the gas turbine and used for preventing the backflow of the high-pressure gas.
In one embodiment of the present application, a sixth shut-off valve is further installed on the transmission pipeline of the second replacement gas loop, wherein: and the input of the sixth shutoff valve is connected with the output of the fourth shutoff valve through a transmission pipeline, and the output of the sixth shutoff valve is connected with the output of the regulating valve through a transmission pipeline and is used for controlling the start and stop of the transmission of the high-pressure gas to the transmission pipeline of the fuel branch.
In one embodiment of the present application, a pressure regulating valve and a seventh shut-off valve are installed on the purge loop, wherein: the output of the pressure regulating valve is connected with the input of the seventh shutoff valve and is used for controlling the start and stop of the transmission of the purge gas to the purge loop; and the seventh shut-off valve is connected with the gas turbine combustion test bed through a transmission pipeline and is used for controlling the start and stop of the transmission of the blowing gas to the gas turbine combustion test bed.
In one embodiment of the present application, a first bleed valve and a second bleed valve are mounted on a transport pipe of the bleed circuit, wherein: the output of the first side emission valve is connected with the input of the emergency cut-off valve and is used for diffusing the fuel in the transmission pipeline of the main fuel pipeline; and the output of the second relief valve is connected with the input of the second shutoff valve and is used for relieving the fuel in the transmission pipeline of the fuel branch.
The application provides a fuel supply system of gas turbine combustion test platform, wherein, this system includes the fuel main road, the fuel branch road, the replacement gas return circuit, clear the return circuit of blowing, diffuse return circuit and gas turbine combustion test platform, the fuel main road is connected with a plurality of fuel branch roads, a plurality of fuel branch roads are connected respectively in the gas turbine combustion test platform that corresponds separately, the replacement gas return circuit is connected with the fuel main road respectively, a plurality of fuel branch roads and gas turbine combustion test platform, clear the return circuit of blowing is connected with gas turbine combustion test platform, diffuse the return circuit and be connected with fuel main road and a plurality of fuel branch roads respectively, therefore, based on a plurality of functional branch roads in the fuel supply system of gas turbine combustion test platform, realize gas turbine combustion test platform steady operation under the operating mode parameter of different gas turbines, the complexity of gas turbine combustion test platform operation has been reduced, and the security of gas turbine combustion test platform has been improved.
Other effects of the above-described alternative will be described below with reference to specific embodiments.
Drawings
FIG. 1 is a schematic diagram of a fuel supply system of a gas turbine combustion test stand according to an embodiment of the present application;
FIG. 2 is a logical block diagram of a fuel supply system of a gas turbine combustion test stand of an embodiment of the present application;
FIG. 3 is a nitrogen and natural gas displacement compliance logic diagram of one embodiment of the present application.
Detailed Description
Reference will now be made in detail to the embodiments of the present application, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application.
The fuel supply system of the gas turbine combustion test stand of the embodiment of the present application is described below with reference to the drawings.
FIG. 1 is a schematic illustration of a fuel supply system of a gas turbine combustion test stand according to an embodiment of the present application.
As shown in fig. 1, the fuel supply system of the gas turbine combustion test stand includes a main fuel path 101, a branch fuel path 102, a replacement gas path 103, a purge loop 104, a bleed loop 105, and a gas turbine combustion test stand (not shown), wherein:
in some embodiments, the gas turbine combustion test stand may be, but is not limited to, a heavy duty gas turbine combustion test stand.
In other embodiments, the fuel supply system of the gas turbine combustion test stand may supply fuel for single-stage and multi-stage combustors, single gas fuel gas turbines, and dual-fuel gas turbines, but is not limited thereto, and the embodiment is not particularly limited thereto.
In some embodiments, as shown in FIG. 1, the main fuel path 101 is connected to a plurality of fuel branches 102 for providing fuel to the plurality of fuel branches 102.
In some embodiments, the fuel may be natural gas, rich/pure hydrogen, biomass gas, but is not limited thereto, and the embodiment is not particularly limited thereto.
In some embodiments, the fuel main circuit 101 and the fuel branch circuit 102 may be composed of a plurality of transfer pipes that transfer fuel.
In some embodiments, as shown in FIG. 1, a plurality of fuel branches 102 are connected to each respective gas turbine combustion test stand for delivering fuel to each gas turbine combustion test stand.
In some embodiments, in a case that a preset gas turbine combustion test bed needs to be switched, a preset valve of a fuel branch 102 corresponding to the gas turbine combustion test bed is opened, so as to implement intelligent control of the gas turbine combustion test bed corresponding to each of the plurality of fuel branches 102.
In some embodiments, as shown in fig. 1, the displacement gas circuit 103 is connected to the main fuel path 101, the plurality of fuel branches 102, and the gas turbine combustion test rig, respectively, for displacing the fuel in the main fuel path 101 and each fuel branch 102 corresponding to the transport duct, and the residual fuel of the gas turbine combustion test rig.
In some embodiments, the gas transported in the replacement gas loop 103 may be an inert gas, such as nitrogen or carbon dioxide, but is not limited thereto, and the embodiment is not limited thereto.
In some embodiments, by replacing the fuel in the main fuel path 101, the plurality of fuel branches 102 and the gas turbine combustion test bed through the replacement gas loop 103, the residual air in the main fuel path 101, the plurality of fuel branches 102 and the gas turbine combustion test bed can be exhausted, so that the danger caused by mixing of air and fuel during operation is avoided, and the safety of a fuel supply system of the gas turbine combustion test bed is ensured.
In some embodiments, as shown in FIG. 1, the purge circuit 104 is coupled to a gas turbine combustion test stand for purging fuel nozzles in the gas turbine combustion test stand based on purge gas in the purge circuit 104.
In some embodiments, the purge gas in the purge loop 104 may be air or carbon dioxide, but is not limited thereto.
In some embodiments, as shown in fig. 1, the bleeding circuit 105 is connected to the main fuel circuit 101 and the plurality of fuel branches 102, respectively, for discharging the fuel in the corresponding transport ducts of the main fuel circuit 101 and the plurality of fuel branches 102.
In some embodiments, as shown in fig. 1, a pressure regulating module 1011, a first shut-off valve 1012, an emergency shut-off valve 1013, and a heater 1014 are installed on the transmission pipeline of the fuel main path 101, wherein:
the output of the pressure regulating module 1011 is connected via a transfer line to the input of the first shut-off valve 1012 for controlling the pressure of the fuel in the transfer line of the main fuel circuit 101.
As shown in fig. 1, the pressure regulating module 1011 may include a plurality of pressure regulating valves, for example, three pressure regulating valves, i.e., a pressure regulating valve a, a pressure regulating valve B, and a pressure regulating valve C, so as to cooperatively control the pressure of the fuel in the transmission pipeline of the main fuel path 101 through the plurality of pressure regulating valves.
The output of the first shut-off valve 1012 is connected via a transfer line to the input of the emergency shut-off valve 1013 for controlling the start and stop of the transfer of fuel to the transfer line of the main fuel circuit 101.
In some embodiments, when the first shut-off valve 1012 is in the open state, the fuel is controlled to start transferring to the transfer pipe of the main fuel circuit 101, and when the first shut-off valve 1012 is in the closed state, the fuel is controlled to stop transferring to the transfer pipe of the main fuel circuit 101.
The output of the emergency shut-off valve 1013 is connected via a transfer line to the input of the heater 1014 for emergency stopping of the transfer of fuel in the fuel main circuit 101 within the transfer line.
The output of the heater 1014 is connected to the plurality of fuel branches 102 via transfer lines for preheating the fuel in the transfer line of the main fuel path 101.
In some embodiments, to improve the combustion efficiency of the gas turbine combustion test stand, the fuel in the transportation pipeline of the main fuel pipeline 101 may be preheated to be heated to a preset temperature, and the fuel at the preset temperature is transported to the gas turbine combustion test stand to improve the ignition efficiency of the gas turbine combustion test stand.
In some embodiments, as shown in fig. 1, the delivery line of the fuel branch 102 is equipped with a regulating valve 1021 and a second shut-off valve 1022, wherein:
an input of the regulating valve 1021 is connected to an output of the heater 1014, and an output of the regulating valve 1021 is connected to a second shutoff valve 1022 for regulating the flow rate of the fuel in the transport line of the fuel branch 102.
In some embodiments, the flow rate of the fuel in the transport pipeline of the fuel branch 102 can be dynamically adjusted by adjusting the valve opening of the adjusting valve 1021, which can be remotely controlled by a network or manually controlled, to control the flow rate value of the fuel to meet a target fuel flow rate value required in the gas turbine combustion stage.
The output of the second shut-off valve 1022 is connected to the gas turbine combustion test stand via a transmission line for controlling the start and stop of the transmission of fuel to the gas turbine combustion test stand.
In some embodiments, when second shutoff valve 1022 is in an open state, control fuel begins to be delivered to the gas turbine combustion stage, and when first shutoff valve 1012 is in a closed state, control fuel stops being delivered to the gas turbine combustion stage.
In some embodiments, as shown in fig. 1, the displacement gas circuit 103 comprises a first displacement gas circuit 1031 and a second displacement gas circuit 1032, wherein:
the output of the first replacement gas circuit 1031 is connected to the output of the first shut-off valve 1012 for replacing fuel in the delivery conduits of the main fuel circuit 101 and the fuel branch 102 based on low pressure gas.
In this embodiment, low-pressure nitrogen gas may be used as the low-pressure gas for replacing the fuel in the transfer pipes of the main fuel path 101 and the fuel branch path 102 with the low-pressure nitrogen gas, but the present invention is not limited thereto.
The output of the second replacement gas circuit 1032 is connected to the output of the regulator valve 1021 and to the gas turbine combustion test stand, respectively, for replacing the fuel in the transport duct of the fuel branch 102, and the residual fuel of the gas turbine combustion test stand, based on the high pressure gas.
In this embodiment, the high-pressure nitrogen gas may be used as the high-pressure gas to replace the fuel in the transmission pipeline of the fuel branch 102 and the residual fuel of the combustion test stand of the gas turbine with the high-pressure nitrogen gas, but the present invention is not limited thereto.
In some embodiments, as shown in fig. 1, a third shut-off valve 10311 is mounted on the transport pipe of the first replacement gas circuit 1031, wherein:
the output of the third shut-off valve 10311 is connected to the output of the first shut-off valve 1012 via a delivery line for controlling the start and stop of the delivery of low-pressure gas to the delivery lines of the main fuel circuit 101 and the fuel branch 102.
In some embodiments, when the third shut-off valve 10311 is in the open state, the low-pressure gas is controlled to start being transferred to the transfer pipes of the fuel main circuit 101 and the fuel branch 102, and when the third shut-off valve 10311 is in the closed state, the low-pressure gas is controlled to stop being transferred to the transfer pipes of the fuel main circuit 101 and the fuel branch 102.
In some embodiments, as shown in fig. 1, a fourth shutoff valve 10321 and a fifth shutoff valve 10322 are installed on the transport conduit of the second displacement gas circuit 1032, wherein:
the output of fourth shutoff valve 10321 is connected via a transfer line to the input of fifth shutoff valve 10322 for controlling the start and stop of the transfer of high pressure gas to second displacement gas circuit 1032.
In some embodiments, when fourth shutoff valve 10321 is in an open state, high pressure gas is controlled to begin delivery to the delivery conduit of second replacement gas circuit 1032, and when fourth shutoff valve 10321 is in a closed state, high pressure gas is controlled to cease delivery to the delivery conduit of second replacement gas circuit 1032.
The output of the fifth shut-off valve 10322 is connected to the gas turbine combustion test stand through a transmission line for controlling the start and stop of the transmission of the high-pressure gas to the gas turbine combustion test stand.
In some embodiments, when fifth shutoff valve 10322 is in an open state, high pressure gas is controlled to begin delivery to the gas turbine combustion test stand, and when fifth shutoff valve 10322 is in a closed state, high pressure gas is controlled to cease delivery to the gas turbine combustion test stand.
In some embodiments, as shown in fig. 1, the transfer line of the second displacement gas circuit 1032 also has a check valve 10323 mounted thereon, wherein:
a check valve 10323 is installed between the output of the shutoff valve and the gas turbine combustion test stand for preventing backflow of high pressure gas and improving the safety of the second replacement gas circuit.
In some embodiments, as shown in fig. 1, a sixth shutoff valve 10324 is further installed on the transmission line of the second displacement gas circuit 1032, wherein:
the input of sixth shutoff valve 10324 is connected to the output of fourth shutoff valve 10321 via a transfer line, and the output of sixth shutoff valve 10324 is connected to the output of regulating valve 1021 via a transfer line for controlling the start and stop of the transfer of high-pressure gas to the transfer line of fuel branch 102.
In some embodiments, when the sixth shutoff valve 10324 is in the open state, the high pressure gas is controlled to begin delivery to the delivery line of the fuel branch 102, and when the sixth shutoff valve 10324 is in the closed state, the high pressure gas is controlled to stop delivery to the delivery line of the fuel branch 102.
In some embodiments, as shown in fig. 1, the purge circuit 104 is installed with a pressure regulating valve 1041 and a seventh shut-off valve 1042, wherein:
the output of the pressure regulating valve 1041 is connected to the input of the seventh shut-off valve 1042 for controlling the start and stop of the transmission of the purge gas to the purge loop 104.
The seventh shut-off valve 1042 is connected to the gas turbine combustion test stand through a transmission line, and is configured to control the start and stop of the transmission of the purge gas to the gas turbine combustion test stand.
In some embodiments, when the seventh shut-off valve 1042 is in the open state, the purge gas is controlled to start being delivered to the gas turbine combustion test stand, and when the seventh shut-off valve 1042 is in the closed state, the purge gas is controlled to stop being delivered to the gas turbine combustion test stand.
In other embodiments, in the case that there are three nozzles in the gas turbine combustion test bed and ignition is required, where the three nozzles may be the center nozzle, the peripheral nozzles 1 and the peripheral nozzles 2, the second shut-OFF valve 1022 ON the transport pipeline of the fuel branch 102 corresponding to the three nozzles may be adjusted to a closed (OFF) state, the regulating valve 1021 may be opened to adjust the fuel flow value to a preset target fuel flow value, the second shut-OFF valve 1022 may be adjusted to an Open (ON) state, and the igniter may be activated to ignite the fuel at the center nozzle, the peripheral nozzles 1 and the peripheral nozzles 2, if ignition is successful, the fuel flow value may be dynamically adjusted according to the combustion state, and if ignition is unsuccessful, the second shut-OFF valve 1022 and the regulating valve 1021 may be closed urgently to reduce the loss of the fuel.
In addition, when any nozzle of the combustion table needs to be purged, the adjusting valve 1021 on the transmission pipeline of the fuel branch 102 corresponding to the nozzle may be closed first, the second shut-off valve 1022 is also closed, and then the purge loop 104 is controlled to be opened to purge air to the nozzle of the downstream gas turbine combustion table, so as to achieve rapid cooling of the nozzle, provide thermal protection for the nozzle, and prolong the service life of the nozzle.
In some embodiments, as shown in fig. 1, the transfer line of the bleed circuit 105 has a first bleed valve 1051 and a second bleed valve 1052 mounted thereon, wherein:
the output of the first side launch valve is connected to the input of the emergency shutdown valve 1013 for bleeding fuel from the delivery pipe of the main fuel path 101.
In some embodiments, in the case of nitrogen substitution of the fuel in the transfer pipe of the main fuel circuit 101, the nitrogen in the transfer pipe of the main fuel circuit 101 may also be discharged through a bleed valve.
The output of the second bleed valve 1052 is connected to the input of the second shut-off valve 1022 for bleeding fuel from the delivery line of the fuel branch 102.
In some embodiments, the nitrogen in the transport line of the fuel branch 102 may also be vented through a bleed valve in the event that the fuel in the transport line of the fuel branch 102 is nitrogen purged.
To sum up, for better understanding of the present application, the present application provides a logic block diagram of a fuel supply system of a gas turbine combustion test bed, taking natural gas as fuel, nitrogen as displacement gas, and air as purge gas, as shown in fig. 2, the control flow of the fuel can be that, in case that it is determined that nitrogen displacement is required, the gas in the transmission pipelines of the main nitrogen displacement fuel pipeline 101 and the fuel branch pipeline 102 is firstly turned ON, then the gas in the transmission pipelines of the main natural gas displacement fuel pipeline 101 and the fuel branch pipeline 102 is turned ON, and according to the input command of the fuel, the second shut-OFF valve 1022 of the fuel branch pipeline 102 is adjusted to be closed (OFF), and simultaneously the fuel flow value of the fuel branch pipeline 102 is adjusted to reach the preset fuel flow value, then the ignition command of the gas turbine combustion test bed is obtained, and the igniter is turned ON, the second shut-OFF valve 1022 of the fuel branch pipeline 102 is synchronously adjusted to be Opened (ON), if the ignition fails, the second shutoff valve 1022 is closed, and if the ignition succeeds, the supply of the fuel is adjusted according to the test working condition of the gas turbine, wherein the supply of the fuel can be controlled by automatically controlling the valve opening degree of the regulating valve 1021 of the fuel branch 102 and manually controlling the valve opening degree of the regulating valve 1021 of the fuel branch 102, under the condition that the fuel branch 102 is changed, the switching instruction of the fuel branch 102 can be obtained, the second shutoff valve 1022 of the preset fuel branch 102 is adjusted to be opened or closed, if the regulating valve 1021 of the preset fuel branch 102 controls the fuel at the set flow value, the air purging instruction is opened, the fuel branch 102 before switching is subjected to purging treatment, the second shutoff valve 1022 and the regulating valve 1021 of the preset fuel branch 102 are adjusted to be closed, and then the purging loop is opened or closed to perform the purging treatment ON the preset fuel branch 102, and closing the second shutoff valve 1022, the purge loop 104 and the regulating valve 1021 in sequence until a test ending instruction is obtained so as to close a fuel supply system of the combustion test bed of the gas turbine.
In addition, the present application further proposes a nitrogen and natural gas replacement sequential control logic, as shown in fig. 3, wherein, on one hand, the sequential control logic of the fuel supply system of the nitrogen replacement gas turbine combustion test bed may be to complete nitrogen replacement for the main fuel path 101 by closing the first shut-off valve 1012 and the second shut-off valve 1022, opening the emergency shut-off valve 1013, the first bleeding valve 1051, the regulating valve 1021, and the second bleeding valve 1052, and opening the third shut-off valve 10311, wherein the preset delay time may be 10 seconds after the preset delay time elapses, complete nitrogen replacement for the fuel branch path 102 by closing the third shut-off valve 10311, closing the emergency shut-off valve 1013, the first bleeding valve 1051, the second bleeding valve 1052, and the regulating valve 1021, opening the fourth shut-off valve 10321 and the sixth shut-off valve 10324, and complete nitrogen replacement for the fuel supply system of the combustion test bed of the gas turbine combustion test bed 10322 by closing the fourth shut-off valve 10321 and the fifth shut-off valve 1022.
On the other hand, the sequential control logic of the fuel supply system of the natural gas replacement gas turbine combustion test stand may be such that the replacement of the natural gas in the main fuel path 101 is completed by closing the second shutoff valve 1022, opening the emergency shutoff valve 1013, the first purge valve 1051, the adjustment valve 1021, and the second purge valve 1052, and opening the first shutoff valve 1012, and after a preset delay time elapses, closing the first shutoff valve 1012, and closing the first purge valve 1051, the adjustment valve 1021, and the second purge valve 1052.
The application provides a fuel supply system of gas turbine combustion test platform, wherein, this system includes the fuel main road, the fuel branch road, the replacement gas return circuit, clear the return circuit of blowing, diffuse return circuit and gas turbine combustion test platform, the fuel main road is connected with a plurality of fuel branch roads, a plurality of fuel branch roads are connected respectively in the gas turbine combustion test platform that corresponds separately, the replacement gas return circuit is connected with the fuel main road respectively, a plurality of fuel branch roads and gas turbine combustion test platform, clear the return circuit of blowing is connected with gas turbine combustion test platform, diffuse the return circuit and be connected with fuel main road and a plurality of fuel branch roads respectively, therefore, based on a plurality of functional branch roads in the fuel supply system of gas turbine combustion test platform, realize gas turbine combustion test platform steady operation under the operating mode parameter of different gas turbines, the complexity of gas turbine combustion test platform operation has been reduced, and the security of gas turbine combustion test platform has been improved.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless explicitly specified otherwise.
In the description herein, reference to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present application, and that variations, modifications, substitutions and alterations may be made to the above embodiments by those of ordinary skill in the art within the scope of the present application.
Claims (10)
1. A fuel supply system of a gas turbine combustion test stand, comprising a main fuel circuit, a branch fuel circuit, a displacement gas circuit, a purge circuit, a blow-down circuit, and a blow-off circuit, wherein:
the fuel main path is connected with a plurality of fuel branches and is used for supplying fuel to the plurality of fuel branches;
the fuel branches are respectively connected with the corresponding gas turbine combustion test beds and used for conveying fuel to the gas turbine combustion test beds;
the replacement gas loop is respectively connected with the main fuel path, the fuel branches and the gas turbine combustion test bed and is used for replacing the fuel in the main fuel path and the corresponding transmission pipeline of each fuel branch and the residual fuel of the gas turbine combustion test bed;
the cleaning and blowing loop is connected with the gas turbine combustion test bed and is used for cleaning and blowing a fuel nozzle in the gas turbine combustion test bed according to cleaning and blowing gas in the cleaning and blowing loop;
the diffusion loop is respectively connected with the main fuel path and the plurality of fuel branches and is used for discharging the fuel in the corresponding delivery pipelines of the main fuel path and the plurality of fuel branches.
2. The fuel supply system of a gas turbine combustion test stand according to claim 1, wherein a pressure regulating module, a first shut-off valve, an emergency shut-off valve and a heater are installed on a transmission pipeline of the main fuel path, wherein:
the output of the pressure regulating module is connected with the input of the first shutoff valve through a transmission pipeline and is used for controlling the pressure of the fuel in the transmission pipeline of the fuel main pipeline;
the output of the first shut-off valve is connected with the input of the emergency shut-off valve through a transmission pipeline and is used for controlling the start and stop of the transmission of the fuel to the transmission pipeline of the fuel main pipeline;
the output of the emergency shut-off valve is connected with the input of the heater through a transmission pipeline and is used for emergently stopping the transmission of the fuel in the fuel main pipeline in the transmission pipeline;
the output of the heater is connected with a plurality of fuel branches through a transmission pipeline and is used for preheating the fuel in the transmission pipeline of the main fuel pipeline.
3. The fuel supply system of a gas turbine combustion test stand according to claim 2, wherein a regulating valve and a second shut-off valve are installed on a delivery pipe of the fuel branch, wherein:
the input of the regulating valve is connected with the output of the heater, and the output of the regulating valve is connected with the second shutoff valve and used for regulating the flow of the fuel in the transmission pipeline of the fuel branch;
and the output of the second shutoff valve is connected with the gas turbine combustion test bed through a transmission pipeline and is used for controlling the start and stop of the transmission of the fuel to the gas turbine combustion test bed.
4. The gas turbine combustion test stand fuel supply system of claim 3, wherein said displacement gas circuit comprises a first displacement gas circuit and a second displacement gas circuit, wherein:
the output of the first replacement gas circuit is connected with the output of the first shutoff valve and is used for replacing the fuel in the transmission pipelines of the main fuel pipeline and the fuel branch pipeline based on low-pressure gas;
and the output of the second replacement gas loop is respectively connected with the output of the regulating valve and the gas turbine combustion test bed and used for replacing the fuel in the transmission pipeline of the fuel branch based on high-pressure gas and the residual fuel of the gas turbine combustion test bed.
5. The gas turbine combustion test stand fuel supply system of claim 4, wherein a third shut-off valve is installed on the transfer duct of the first replacement gas circuit, wherein:
and the output of the third shut-off valve is connected with the output of the first shut-off valve through a transmission pipeline and is used for controlling the start and stop of the transmission of the low-pressure gas to the transmission pipelines of the main fuel pipeline and the fuel branch pipeline.
6. The fuel supply system for a gas turbine combustion test stand of claim 4, wherein a fourth shutoff valve and a fifth shutoff valve are installed on a transfer pipe of the second replacement gas circuit, wherein:
the output of the fourth shutoff valve is connected with the input of the fifth shutoff valve through a transmission pipeline and is used for controlling the start and stop of the transmission of the high-pressure gas to the second replacement gas loop;
and the output of the fifth shutoff valve is connected with the gas turbine combustion test bed through a transmission pipeline and is used for controlling the start and stop of the transmission of the high-pressure gas to the gas turbine combustion test bed.
7. The fuel supply system for a gas turbine combustion test stand of claim 6, wherein a check valve is further installed on the transfer pipe of the second replacement gas circuit, wherein:
the check valve is installed between the output of the shut-off valve and the combustion test bed of the gas turbine and used for preventing the backflow of the high-pressure gas.
8. The fuel supply system for a gas turbine combustion test stand of claim 6, wherein a sixth shut-off valve is further installed on the transfer pipe of the second replacement gas circuit, wherein:
and the input of the sixth shutoff valve is connected with the output of the fourth shutoff valve through a transmission pipeline, and the output of the sixth shutoff valve is connected with the output of the regulating valve through a transmission pipeline and used for controlling the start and stop of the transmission of the high-pressure gas to the transmission pipeline of the fuel branch.
9. The fuel supply system for a gas turbine combustion test stand according to claim 6, wherein a pressure regulating valve and a seventh shut-off valve are installed on the purge circuit, wherein:
the output of the pressure regulating valve is connected with the input of the seventh shutoff valve and is used for controlling the start and stop of the transmission of the purge gas to the purge loop;
and the seventh shutoff valve is connected with the gas turbine combustion test bed through a transmission pipeline and is used for controlling the start and stop of the transmission of the clean blowing gas to the gas turbine combustion test bed.
10. The fuel supply system for a gas turbine combustion test stand according to claim 4, wherein a first bleeding valve and a second bleeding valve are mounted on a transfer pipe of the bleeding circuit, wherein:
the output of the first side launching valve is connected with the input of the emergency shut-off valve and is used for diffusing the fuel in the transmission pipeline of the main fuel pipeline;
and the output of the second relief valve is connected with the input of the second shutoff valve and is used for relieving the fuel in the transmission pipeline of the fuel branch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210857636.2A CN115163309A (en) | 2022-07-20 | 2022-07-20 | Fuel supply system of combustion test bed of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210857636.2A CN115163309A (en) | 2022-07-20 | 2022-07-20 | Fuel supply system of combustion test bed of gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN115163309A true CN115163309A (en) | 2022-10-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210857636.2A Pending CN115163309A (en) | 2022-07-20 | 2022-07-20 | Fuel supply system of combustion test bed of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115163309A (en) |
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2022
- 2022-07-20 CN CN202210857636.2A patent/CN115163309A/en active Pending
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