CN117738796A - Gas turbine liquid fuel system, control method, medium and equipment - Google Patents
Gas turbine liquid fuel system, control method, medium and equipment Download PDFInfo
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- CN117738796A CN117738796A CN202410041760.0A CN202410041760A CN117738796A CN 117738796 A CN117738796 A CN 117738796A CN 202410041760 A CN202410041760 A CN 202410041760A CN 117738796 A CN117738796 A CN 117738796A
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- 239000000446 fuel Substances 0.000 title claims abstract description 220
- 239000007788 liquid Substances 0.000 title claims abstract description 147
- 238000000034 method Methods 0.000 title claims abstract description 25
- 239000002828 fuel tank Substances 0.000 claims abstract description 34
- 238000002485 combustion reaction Methods 0.000 claims description 17
- 238000004590 computer program Methods 0.000 claims description 5
- 230000004044 response Effects 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 4
- 230000001105 regulatory effect Effects 0.000 claims description 4
- 238000010926 purge Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 10
- 238000000889 atomisation Methods 0.000 abstract description 8
- 238000005507 spraying Methods 0.000 abstract description 3
- 238000002156 mixing Methods 0.000 description 12
- 238000005086 pumping Methods 0.000 description 6
- 230000003287 optical effect Effects 0.000 description 5
- 238000012545 processing Methods 0.000 description 5
- 239000000243 solution Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 239000012535 impurity Substances 0.000 description 4
- 230000006870 function Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
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Abstract
The application discloses a gas turbine liquid fuel system, control method, medium and equipment, the system includes: the fuel tank, the main oil way, the surge oil way, the mixed oil way and the liquid fuel annular main pipe; the inlet of the main oil way is communicated with the fuel tank, and the outlet of the main oil way is communicated with the inlet of the mixed oil way; the inlet of the surge oil way is communicated with the fuel tank, and the outlet of the surge oil way is communicated with the inlet of the mixed oil way; the surge oil way is provided with a booster pump; the outlet of the mixed oil way is communicated with the inlet of the annular main pipe. According to the method, the main oil way and the surge oil way are arranged, the booster pump is arranged on the surge oil way, when the gas turbine is started and the gas fuel is switched to the liquid fuel, the main oil way and the surge oil way are used for supplying oil to the liquid fuel annular main pipe, so that the time that the liquid fuel is filled in the liquid fuel annular main pipe can be shortened, the time difference of spraying the liquid fuel by each nozzle is reduced, the atomization effect of the liquid fuel sprayed by each nozzle is effectively improved, and the starting time is shortened.
Description
Technical Field
The present application relates to the field of gas turbines, and in particular, to a gas turbine liquid fuel system, control method, medium and apparatus.
Background
In the field of gas turbines, gas turbines employing annular combustors are common. For a gas turbine using an annular combustion chamber, the annular combustion chamber is provided with a plurality of fuel nozzles which are connected in an annular manner, and the plurality of fuel nozzles are distributed at different positions in the circumferential direction, so that when the gas turbine is started by using liquid fuel, the fuel nozzles at different positions have different fuel injection timings. For example, among the plurality of annularly connected fuel nozzles, the fuel nozzle located below is closer to the oil path and is filled with fuel first, while the fuel nozzle located above is farther from the oil path and is filled with fuel later than the fuel nozzle located below, so that when the fuel spraying time of each fuel nozzle is larger, the fuel atomization effect is poor and the starting time is long.
In addition, in a gas turbine using a dual-fuel annular combustor, there is also a phenomenon in which the timing of injecting liquid fuel into each fuel nozzle is greatly different in the process of switching gas fuel to liquid fuel, and therefore, the fuel atomization effect is poor and the start-up time is long. Meanwhile, because the gas fuel and the liquid fuel are mixed to be burned during fuel switching, when the time difference of the fuel injection time of each fuel nozzle is larger, the combustion instability in the switching process can be further aggravated.
Disclosure of Invention
The application provides a liquid fuel system, a control method, a medium and equipment of a gas turbine, and aims to solve the problem that the time difference of fuel injection of each fuel nozzle of an annular combustion chamber is large.
In an embodiment of the present application, a gas turbine liquid fuel system is presented, comprising:
the fuel tank, the main oil way, the surge oil way, the mixed oil way and the liquid fuel annular main pipe;
the fuel tank is used for containing liquid fuel;
the inlet of the main oil way is communicated with the fuel tank, and the outlet of the main oil way is communicated with the inlet of the mixed oil way;
the inlet of the surge oil way is communicated with the fuel tank, and the outlet of the surge oil way is communicated with the inlet of the mixed oil way;
the inlet position of the surge oil way is provided with a booster pump;
the outlet of the mixed oil circuit is communicated with the inlet of the liquid fuel annular main pipe;
the liquid fuel annular main pipe is provided with a plurality of nozzles, the plurality of nozzles are arranged along the circumferential direction of the liquid fuel annular main pipe, and the liquid fuel annular main pipe is used for extending into an annular combustion chamber of the gas turbine so that the plurality of nozzles face each flame tube in the annular combustion chamber respectively.
In this embodiment of the application, from the import of main oil circuit to the export of main oil circuit, main oil circuit is equipped with in proper order: the system comprises a main oil way high-pressure filter, a main oil way first quick-break valve, a regulating valve, a flowmeter and a main oil way second quick-break valve.
In the embodiment of the application, the main oil line is further provided with a main oil line inlet stop valve between the main oil line high-pressure filter and the main oil line first speed stop valve.
In this embodiment of the present application, between the main oil line inlet shutoff valve and the main oil line first speed shutoff valve, the main oil line is further provided with a main oil line gas vent valve.
In this embodiment of the present application, from the booster pump to the outlet of the surge oil path, the surge oil path is further provided with in order: the surge oil way high-pressure filter and the surge oil way inlet stop valve.
In the embodiment of the application, a one-way valve is further arranged between the surge oil way inlet stop valve and the surge oil way outlet.
In this embodiment of the present application, the fuel tank is provided with a first outlet and a second outlet, the inlet of the main oil path is communicated with the first outlet, and the inlet of the surge oil path is communicated with the second outlet.
The application also provides a control method of the gas turbine liquid fuel system, which is applied to the gas turbine liquid fuel system according to any embodiment, and comprises the following steps:
in response to receiving a preset command, opening the main oil path, wherein the preset command comprises one of the following: a start command for the gas turbine, a fuel switching command for switching the gas fuel to the liquid fuel;
after the main oil way is opened for a first preset time, opening the surge oil way; the first preset time is determined based on the lengths, the cross sectional areas and the fuel flow rates of the main oil way and the surge oil way, and the first preset time meets the requirement that the liquid fuel of the main oil way and the liquid fuel of the surge oil way reach the inlet of the mixed oil way at the same time. The present application also proposes a computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, implements a method as described above.
The present application also proposes a computing device comprising a processor for implementing the above-described method when executing a computer program stored in a memory.
In this embodiment of the application, through setting up main oil circuit and surge oil circuit to set up the booster pump on surge oil circuit, when gas turbine starts, and when gas fuel switches to liquid fuel, utilize main oil circuit and surge oil circuit to supply oil to liquid fuel annular main pipe, can shorten the time that liquid fuel is full of liquid fuel annular main pipe, reduce the time difference that each nozzle spouted liquid fuel, thereby effectively improve the atomization effect after each nozzle spouts liquid fuel, shorten the start-up time, and when gas fuel switches to liquid fuel, can also improve the stability of burning.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained from the structures shown in these drawings without inventive effort to a person of ordinary skill in the art.
FIG. 1 is a schematic illustration of a gas turbine liquid fuel system in accordance with an embodiment of the present application;
FIG. 2 is a step diagram of a method of controlling a liquid fuel system of a gas turbine in an embodiment of the present application;
FIG. 3 is a block diagram of a medium in an embodiment of the present application;
FIG. 4 is a block diagram of a computing device in an embodiment of the present application.
Description of the drawings:
100-fuel tank, 110-first outlet, 120-second outlet, 200-main oil line, 210-main oil line high-pressure filter, 220-main oil line inlet stop valve, 230-main oil line blow-out valve, 240-main oil line first speed stop valve, 250-regulating valve, 260-flowmeter, 270-main oil line second speed stop valve, 300-surge oil line, 310-booster pump, 320-surge oil line high-pressure filter, 330-surge oil line inlet stop valve, 340-check valve, 400-mixed oil line, 500-liquid fuel annular manifold, 600-nozzle, 700-annular manifold blow-out valve.
The realization, functional characteristics and advantages of the present application will be further described with reference to the embodiments, referring to the attached drawings.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all, of the embodiments of the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It should be noted that, in the embodiment of the present application, directional indications (such as up, down, left, right, front, and rear … …) are referred to, and the directional indications are merely used to explain the relative positional relationship, movement conditions, and the like between the components in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indications are correspondingly changed.
In addition, if there is a description of "first", "second", etc. in the embodiments of the present application, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be regarded as not exist and not within the protection scope of the present application.
As shown in fig. 1, in an embodiment of the present application, the gas turbine liquid fuel system includes: fuel tank 100, main oil passage 200, surge oil passage 300, mixing oil passage 400, and liquid fuel annular manifold 500;
the fuel tank 100 is used for containing liquid fuel;
an inlet of the main oil passage 200 communicates with the fuel tank 100, and an outlet of the main oil passage 200 communicates with an inlet of the mixture oil passage 400;
an inlet of the surge oil path 300 is communicated with the fuel tank 100, and an outlet of the surge oil path 300 is communicated with an inlet of the mixing oil path 400;
the booster pump 310 is arranged at the inlet position of the surge oil path 300;
the outlet of the mixing oil path 400 is communicated with the inlet of the liquid fuel annular main pipe 500;
the liquid fuel annular manifold 500 is provided with a plurality of nozzles 600, the plurality of nozzles 600 being arranged in a circumferential direction of the liquid fuel annular manifold 500, the liquid fuel annular manifold 500 being adapted to extend into an annular combustion chamber of the gas turbine such that the plurality of nozzles 600 are directed towards respective cartridges within the annular combustion chamber.
As shown in fig. 1, in the embodiment of the present application, the fuel tank 100 is a liquid fuel storage device of a gas turbine, and after the liquid fuel is contained in the fuel tank 100, the fuel tank 100 may be used as a fuel source of the main oil path 200 and the surge oil path 300, and the fuel tank 100 may be a high-pressure fuel tank 100, so that the liquid fuel may be smoothly supplied to the main oil path 200 and the surge oil path 300.
With continued reference to FIG. 1, in an embodiment of the present application, the oil circuit of the gas turbine liquid fuel system includes: a main oil passage 200 and a surge oil passage 300. The inlets of the main oil passage 200 and the surge oil passage 300 are both communicated with the fuel tank 100, the outlets of the main oil passage 200 and the surge oil passage 300 are both communicated with the inlet of the mixing oil passage 400, and the outlet of the mixing oil passage 400 is communicated to the liquid fuel annular manifold 500.
With continued reference to fig. 1, in the embodiment of the present application, the two ends of the mixing oil path 400 may be hard metal pipes, and the middle is formed by a metal hose, so that when the liquid fuels in the main oil path 200 and the surge oil path 300 are mixed in the mixing oil path 400, the vibration generated after the fuels in the two oil paths are mixed can be eliminated when passing through the metal hose, and the vibration is prevented from being transmitted to the liquid fuel ring main 500.
With continued reference to FIG. 1, the liquid fuel annular manifold 500 is generally annular in shape with a plurality of nozzles 600 axially disposed, each nozzle 600 in communication with the liquid fuel annular manifold 500. In another embodiment, a ring manifold vent valve 700 is also provided above the liquid fuel ring manifold 500 for venting air within the liquid fuel ring manifold 500.
For the prior art, only a single oil passage is generally provided, and the inlet and outlet of the single oil passage communicate with the fuel tank 100 and the liquid fuel ring main 500, respectively. At the start-up of the gas turbine, or at the time of switching of the gas fuel to the liquid fuel, the liquid fuel passes from the fuel tank 100 through a single oil passage to the liquid fuel annular manifold 500, gradually fills the liquid fuel annular manifold 500, and is injected into each of the nozzles 600 on the liquid fuel annular manifold 500. As shown in fig. 1, each nozzle 600 on the liquid fuel annular manifold 500 is distributed in the annular combustion chamber of the gas turbine in a space approximately according to the vertical position relationship, when the liquid fuel annular manifold 500 is supplied with fuel by using a single oil path under the condition of fixed pumping pressure of the fuel tank 100, the liquid fuel can only gradually fill the liquid fuel annular manifold 500, namely, gradually spray into each nozzle 600, the time for filling the liquid fuel annular manifold 500 is longer, the time for spraying the fuel into each nozzle 600 is longer, thus the fuel atomization effect is poor, the starting time is long, and the combustion instability in the switching process is also aggravated when the gas fuel is switched to the liquid fuel.
As shown in fig. 1, in the embodiment of the present application, the main oil path 200 and the surge oil path 300 are provided, and when the gas turbine is started, or when the gas fuel is switched to the liquid fuel, the liquid fuel in the fuel tank 100 can be respectively transferred through the main oil path 200 and the surge oil path 300, and under the condition that the pumping pressure of the fuel tank 100 is kept unchanged, one oil path is provided for the two oil paths compared with the prior art, and more liquid fuel is delivered to the liquid fuel annular manifold 500 in unit time, so that the liquid fuel annular manifold 500 can be filled more quickly, and then the time difference of injecting the liquid fuel by each nozzle 600 is relatively reduced. In addition, the surge oil path 300 in the embodiment of the present application is further provided with the booster pump 310, so that after the liquid fuel enters the surge oil path 300, the conveying speed can be further improved, so that the time for filling the liquid fuel into the liquid fuel annular manifold 500 can be further shortened, and the time difference for injecting the liquid fuel into each nozzle 600 can be further shortened.
In this embodiment, through setting up main oil circuit 200 and surge oil circuit 300 to set up booster pump 310 on surge oil circuit 300, when gas turbine starts, and when gas fuel switches to liquid fuel, utilize main oil circuit 200 and surge oil circuit 300 to supply oil to liquid fuel annular main 500, can shorten the time that liquid fuel is full of liquid fuel annular main 500, reduce the time difference that each nozzle 600 spouted liquid fuel, thereby effectively improve the atomization effect after each nozzle 600 spouts liquid fuel, shorten the start-up time, and when gas fuel switches to liquid fuel, can also improve the stability of burning.
As shown in fig. 1, in the embodiment of the present application, from the inlet of the main oil path 200 to the outlet of the main oil path 200, the main oil path 200 is sequentially provided with: a main oil line high pressure filter 210, a main oil line first quick disconnect valve 240, a regulator valve 250, a flow meter 260, and a main oil line second quick disconnect valve 270.
The main oil way high-pressure filter 210 is arranged at the inlet of the main oil way 200, after the liquid fuel enters the main oil way 200 from the fuel tank 100, impurities in the liquid fuel can be effectively removed, the impurities are prevented from entering the subsequent oil way and the combustion chamber, the smoothness of oil supply is ensured, and the stability of combustion is ensured.
By providing the regulating valve 250 in the main oil passage 200, the oil supply speed of the main oil passage 200 can be conveniently regulated, and by providing the flowmeter 260, the oil supply amount of the main oil passage 200 can be conveniently calculated.
A first quick disconnect valve is provided between the main oil line high pressure filter 210 and the regulator valve 250, and a main oil line second quick disconnect valve 270 is provided after the flow meter 260, and when it is necessary to stop the supply of oil to the main oil line 200, the main oil line first quick disconnect valve 240 and the main oil line second quick disconnect valve 270 may be closed, enabling the supply of oil to the main oil line 200 to be quickly stopped. The main oil path second quick-break valve 270 is disposed at the tail end of the main oil path 200, and when the main oil path 200 needs to be closed for supplying oil, the main oil path second quick-break valve 270 is closed, so that the main oil path 200 can be cut off from a position where the main oil path 200 is closer to the liquid fuel annular main pipe 500, thereby achieving the effect of quickly cutting off the main oil path 200 for supplying oil. If only main line second quick disconnect valve 270 is closed, main line 200 may stop supplying fuel to liquid fuel ring main 500, but because main line 200 is long, after main line second quick disconnect valve 270 at the end of main line 200 is closed, liquid fuel in main line 200 may also flow before main line second quick disconnect valve 270, and thus regulator valve 250 and flow meter 260 may misunderstand that main line 200 is still continuing to supply fuel. Therefore, the main oil passage first speed cut-off valve 240 is provided before the regulator valve 250 and the flowmeter 260, and when the main oil passage 200 needs to be closed for supplying oil, the main oil passage first speed cut-off valve 240 is closed, so that erroneous judgment of the regulator valve 250 and the flowmeter 260 can be avoided.
As shown in fig. 1, in the embodiment of the present application, the main oil line 200 is further provided with a main oil line inlet shutoff valve 220 between the main oil line high pressure filter 210 and the main oil line first shutoff valve 240. By providing the main oil passage inlet shutoff valve 220 between the main oil passage high-pressure filter 210 and the main oil passage first speed shutoff valve 240, the supply of oil to the main oil passage 200 can be shut off at a position where the main oil passage 200 is closer to the fuel tank 100, that is, the main oil passage inlet shutoff valve 220 can exert an overall control shut-off effect on the main oil passage 200.
As shown in fig. 1, in the embodiment of the present application, the main oil line 200 is further provided with a main oil line 200 gas vent valve between the main oil line inlet shutoff valve 220 and the main oil line first speed shutoff valve 240. A main oil line 200 gas release valve is provided between the main oil line inlet shutoff valve 220 and the main oil line first speed shutoff valve 240, and can function as a main oil line 200 gas release valve.
As shown in fig. 1, in the embodiment of the present application, from the booster pump 310 to the outlet of the surge oil path 300, the surge oil path 300 further includes, in order: surge oil path high pressure filter 320 and surge oil path inlet shutoff valve 330.
Wherein, the inlet of the pumping oil path 300 is provided with a booster pump 310, the liquid fuel can be boosted by the booster pump after entering the pumping oil path 300 from the fuel tank 100, the flow speed is improved, the booster pump 310 is provided with a pumping oil path high-pressure filter 320, the liquid fuel enters the pumping oil path high-pressure filter 320 after passing through the booster pump 310, the impurities in the liquid fuel can be effectively removed, the impurities are prevented from entering the subsequent oil path and combustion chamber, the smoothness of oil supply is ensured, and the stability of combustion is ensured.
In addition, the surge oil path 300 is opened and closed by providing the surge oil path inlet shutoff valve 330 after the surge oil path 300 filter.
As shown in fig. 1, in the embodiment of the present application, a check valve 340 is further disposed between the surge oil path inlet shutoff valve 330 and the surge oil path 300 outlet. The flow direction of the check valve 340 is from the surge oil path 300 to the mixing oil path 400, that is, the check valve 340 only allows the liquid fuel to flow from the surge oil path 300 to the mixing oil path 400, but does not allow the liquid fuel in the mixing oil path 400 to flow back to the surge oil path 300, so that the backflow can be avoided. In addition, when the surge oil passage 300 is not opened, the high-pressure high-speed liquid fuel in the main oil passage 200 can be prevented from flowing to the surge oil passage 300 only when the main oil passage 200 is opened.
As shown in fig. 1, in the embodiment of the present application, the fuel tank 100 is provided with a first outlet 110 and a second outlet 120, the inlet of the main oil passage 200 communicates with the first outlet 110, and the inlet of the surge oil passage 300 communicates with the second outlet 120. Two fuel outlets are provided in the fuel tank 100 and are respectively communicated with the main oil passage 200 and the surge oil passage 300, and the two oil passages of the main oil passage 200 and the surge oil passage 300 are respectively supplied with fuel through two different fuel outlets, so that the supply is more stable.
In this embodiment, through setting up main oil circuit 200 and surge oil circuit 300 to set up booster pump 310 on surge oil circuit 300, when gas turbine starts, and when gas fuel switches to liquid fuel, utilize main oil circuit 200 and surge oil circuit 300 to supply oil to liquid fuel annular main 500, can shorten the time that liquid fuel is full of liquid fuel annular main 500, reduce the time difference that each nozzle 600 spouted liquid fuel, thereby effectively improve the atomization effect after each nozzle 600 spouts liquid fuel, shorten the start-up time, and when gas fuel switches to liquid fuel, can also improve the stability of burning.
Exemplary method
Having described the apparatus of an exemplary embodiment of the present application, a description will now be made of an exemplary gas turbine liquid fuel system control method, as shown in FIG. 2, for use with a gas turbine liquid fuel system as described in any of the foregoing, and in an example of the present application, the method includes the steps of:
step S100: in response to receiving a preset command, opening a main oil circuit, wherein the preset command comprises one of the following: a start command for the gas turbine, and a fuel switching command for switching the gas fuel to the liquid fuel.
In the embodiment of the application, when a start instruction of the gas turbine or a fuel switching instruction for switching the gas fuel to the liquid fuel is received, the main oil passage is first opened. Taking the gas turbine liquid fuel system shown in fig. 1 as an example, when the main oil path 200 is opened, the main oil path inlet shutoff valve 220, the main oil path first quick disconnect valve 240, and the main oil path second quick disconnect valve 270 may be simultaneously opened.
In another embodiment, when the main oil path 200 is opened, the main oil path vent valve 230 on the main oil path 200 and the annular manifold vent valve 700 on the liquid fuel annular manifold 500 can be opened to vent the main oil path 200 and the liquid fuel annular manifold 500.
Step S200: after the main oil way is opened for a first preset time, opening the surge oil way; the first preset time is determined based on the lengths, the cross sectional areas and the fuel flow rates of the main oil way and the surge oil way, and the first preset time meets the requirement that the liquid fuel of the main oil way and the liquid fuel of the surge oil way reach the inlet of the mixed oil way at the same time.
In the embodiment of the present application, assuming that the first preset time is t1, after the main oil path 200 is opened for t1 time, the surge oil path 300 is opened, where, taking the gas turbine liquid fuel system shown in fig. 1 as an example, when the surge oil path 300 is opened, the surge oil path inlet shutoff valve 330 may be opened.
In addition, in the embodiment of the present application, t1 needs to be satisfied, when the main oil path 200 is opened for t1 time, and then the surge oil path 300 is opened, the fuel in the main oil path 200 and the fuel in the surge oil path 300 may reach the inlet of the mixing oil path 400 at the same time.
In the embodiment of the present application, the first preset time t1 may be calculated as follows:
assume that the length and cross-sectional integral of main oil passage 200 is L B 、A B The liquid fuel supply flow rate in the main oil path 200 is M B Then the time T1 required for the liquid fuel to enter from the main oil passage 200 to exit from the main oil passage 200 is:
assume that the length and cross-sectional integral of surge oil circuit 300 is L C 、A C The liquid fuel supply flow rate in the surge oil path 300 is M C Then the time T2 required for the liquid fuel to flow from the inlet of the surge oil path 300 to the outlet of the surge oil path 300 is:
in order to make the liquid fuels in the main oil path 200 and the surge oil path 300 reach the mixed oil path 400 at the same time, the main oil path 200 needs to be opened in advance for a period of time, namely a first preset time T1, wherein t1=t1-T2, the magnitude of the first preset time T1 can be calculated according to the above formula (1) and formula (2), after the first preset time is calculated, the main oil path 200 is opened first, after the main oil path 200 is opened for the first preset time, the surge oil path 300 is opened again, so that the fuels in the main oil path 200 and the surge oil path 300 can reach the mixed oil path 400 at the same time.
In this embodiment, when a start instruction of the gas turbine is received, or a fuel switching instruction for switching the gas fuel to the liquid fuel is received, the main oil path 200 is opened first, and the surge oil path 300 is opened after a first preset time, where the first preset time satisfies: so that the fuel in main oil passage 200 and surge oil passage 300 reach mixing oil passage 400 at the same time. The fuel pressure in the main oil path 200 is smaller, the flow speed is slower, and the fuel pressure in the surge oil path 300 is larger and the flow speed is faster, so that when the fuel in the main oil path 200 and the fuel in the surge oil path 300 are mixed in the mixed oil path 400, the fuel in the main oil path 200 can be driven by the high-pressure and high-flow-speed fuel in the surge oil path 300 to quickly fill the liquid fuel ring manifold 500, thereby reducing the time difference of the liquid fuel injected by each nozzle 600, effectively improving the atomization effect after the liquid fuel is injected by each nozzle 600, shortening the starting time, and improving the combustion stability when the gas fuel is switched to the liquid fuel.
Exemplary Medium
Having described the methods and apparatus of exemplary embodiments of the present invention, a computer-readable storage medium of exemplary embodiments of the present invention is described next with reference to FIG. 3.
Referring to fig. 3, a computer readable storage medium is shown as an optical disc 70, on which a computer program (i.e., a program product) is stored, which when executed by a processor, implements the steps described in the above method embodiments, for example: in response to receiving a preset command, opening the main oil path, wherein the preset command comprises one of the following: a start command for the gas turbine, a fuel switching command for switching the gas fuel to the liquid fuel; and opening the surge oil way after the main oil way is opened for a first preset time, wherein the first preset time is determined based on the length, the cross section area and the fuel flow of the main oil way and the surge oil way, and the first preset time meets the requirement that the liquid fuel of the main oil way and the liquid fuel of the surge oil way reach the inlet of the mixed oil way at the same time. The specific implementation of each step is not repeated here.
It should be noted that examples of the computer readable storage medium may also include, but are not limited to, a phase change memory (PRAM), a Static Random Access Memory (SRAM), a Dynamic Random Access Memory (DRAM), other types of Random Access Memory (RAM), a Read Only Memory (ROM), an Electrically Erasable Programmable Read Only Memory (EEPROM), a flash memory, or other optical or magnetic storage medium, which will not be described in detail herein.
Exemplary computing device
Having described the method, apparatus, and medium of the exemplary embodiments of the present invention, a computing device 80 of the exemplary embodiments of the present invention is next described with reference to FIG. 4.
FIG. 4 illustrates a block diagram of an exemplary computing device 80 suitable for use in implementing embodiments of the invention, the computing device 80 may be a computer system or a server. The computing device 80 shown in fig. 4 is merely an example and should not be taken as limiting the functionality and scope of use of embodiments of the present invention.
As shown in fig. 4, components of computing device 80 may include, but are not limited to: one or more processors or processing units 801, a system memory 802, and a bus 803 that connects the various system components (including the system memory 802 and processing units 801).
Computing device 80 typically includes a variety of computer system readable media. Such media can be any available media that is accessible by computing device 80 and includes both volatile and nonvolatile media, removable and non-removable media.
The system memory 802 may include computer system readable media in the form of volatile memory, such as Random Access Memory (RAM) 8021 and/or cache memory 8022. Computing device 70 may further include other removable/non-removable, volatile/nonvolatile computer system storage media. By way of example only, ROM8023 may be used to read from and write to non-removable, nonvolatile magnetic media (not shown in FIG. 4, commonly referred to as a "hard disk drive"). Although not shown in fig. 4, a magnetic disk drive for reading from and writing to a removable non-volatile magnetic disk (e.g., a "floppy disk"), and an optical disk drive for reading from or writing to a removable non-volatile optical disk (e.g., a CD-ROM, DVD-ROM, or other optical media), may be provided. In such cases, each drive may be coupled to bus 803 via one or more data medium interfaces. The system memory 802 may include at least one program product having a set (e.g., at least one) of program modules configured to carry out the functions of the embodiments of the invention.
A program/utility 8025 having a set (at least one) of program modules 8024 may be stored, for example, in system memory 802, and such program modules 8024 include, but are not limited to: an operating system, one or more application programs, other program modules, and program data, each or some combination of which may include an implementation of a network environment. Program modules 8024 generally perform the functions and/or methods in the embodiments described herein.
The computing device 80 may also communicate with one or more external devices 804 (e.g., keyboard, pointing device, display, etc.). Such communication may be through an input/output (I/O) interface. Moreover, computing device 80 may also communicate with one or more networks such as a Local Area Network (LAN), a Wide Area Network (WAN) and/or a public network, such as the Internet, through network adapter 806. As shown in fig. 4, network adapter 806 communicates with other modules of computing device 80 (e.g., processing unit 801, etc.) over bus 803. It should be appreciated that although not shown in fig. 4, other hardware and/or software modules may be used in connection with computing device 80.
The processing unit 801 executes various functional applications and data processing by running programs stored in the system memory 802, for example, opens the main oil passage in response to receiving a preset instruction including one of: a start command for the gas turbine, a fuel switching command for switching the gas fuel to the liquid fuel; after the main oil way is opened for a first preset time, opening the surge oil way; the first preset time is determined based on the lengths, the cross sectional areas and the fuel flow rates of the main oil way and the surge oil way, and the first preset time meets the requirement that the liquid fuel of the main oil way and the liquid fuel of the surge oil way reach the inlet of the mixed oil way at the same time. The specific implementation of each step is not repeated here.
Furthermore, although the operations of the methods of the present invention are depicted in the drawings in a particular order, this is not required to either imply that the operations must be performed in that particular order or that all of the illustrated operations be performed to achieve desirable results. Additionally or alternatively, certain steps may be omitted, multiple steps combined into one step to perform, and/or one step decomposed into multiple steps to perform.
While the spirit and principles of the present invention have been described with reference to several particular embodiments, it is to be understood that the invention is not limited to the disclosed embodiments nor does it imply that features of the various aspects are not useful in combination, nor are they useful in any combination, such as for convenience of description. The invention is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
The foregoing description is only of the optional embodiments of the present application, and is not intended to limit the scope of the patent application, and all equivalent structural changes made by the specification and drawings of the present application or direct/indirect application in other related technical fields are included in the scope of the patent protection of the present application.
Claims (10)
1. A gas turbine liquid fuel system, comprising: the fuel tank, the main oil way, the surge oil way, the mixed oil way and the liquid fuel annular main pipe;
the fuel tank is used for containing liquid fuel;
the inlet of the main oil way is communicated with the fuel tank, and the outlet of the main oil way is communicated with the inlet of the mixed oil way;
the inlet of the surge oil way is communicated with the fuel tank, and the outlet of the surge oil way is communicated with the inlet of the mixed oil way;
the inlet position of the surge oil way is provided with a booster pump;
the outlet of the mixed oil circuit is communicated with the inlet of the liquid fuel annular main pipe;
the liquid fuel annular main pipe is provided with a plurality of nozzles, the plurality of nozzles are arranged along the circumferential direction of the liquid fuel annular main pipe, and the liquid fuel annular main pipe is used for extending into an annular combustion chamber of the gas turbine so that the plurality of nozzles face each flame tube in the annular combustion chamber respectively.
2. The gas turbine liquid fuel system according to claim 1, wherein from an inlet of the main oil passage to an outlet of the main oil passage, the main oil passage is provided with, in order: the system comprises a main oil way high-pressure filter, a main oil way first quick-break valve, a regulating valve, a flowmeter and a main oil way second quick-break valve.
3. The gas turbine liquid fuel system of claim 2, wherein said main circuit is further provided with a main circuit inlet shutoff valve between said main circuit high pressure filter and said main circuit first shutoff valve.
4. The gas turbine liquid fuel system of claim 3, wherein said main circuit is further provided with a main circuit gas purge valve between said main circuit inlet shutoff valve and said main circuit first shutoff valve.
5. The gas turbine liquid fuel system according to claim 1, wherein from the booster pump to an outlet of the surge oil passage, the surge oil passage is further provided with, in order: the surge oil way high-pressure filter and the surge oil way inlet stop valve.
6. The gas turbine liquid fuel system of claim 5, wherein a check valve is further disposed between the surge oil path inlet shutoff valve and the surge oil path outlet.
7. The gas turbine liquid fuel system of claim 1, wherein the fuel tank is provided with a first outlet and a second outlet, an inlet of the main oil passage being in communication with the first outlet, an inlet of the surge oil passage being in communication with the second outlet.
8. A gas turbine liquid fuel system control method for use in a gas turbine liquid fuel system according to any one of claims 1-7, said method comprising:
in response to receiving a preset command, opening the main oil path, wherein the preset command comprises one of the following: a start command for the gas turbine, a fuel switching command for switching the gas fuel to the liquid fuel;
after the main oil way is opened for a first preset time, opening the surge oil way; the first preset time is determined based on the lengths, the cross sectional areas and the fuel flow rates of the main oil way and the surge oil way, and the first preset time meets the requirement that the liquid fuel of the main oil way and the liquid fuel of the surge oil way reach the inlet of the mixed oil way at the same time.
9. A computer readable storage medium having stored thereon a computer program which, when executed by a processor, implements the method of claim 8.
10. A computing device comprising a processor for implementing the method of claim 8 when executing a computer program stored in memory.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410041760.0A CN117738796A (en) | 2024-01-10 | 2024-01-10 | Gas turbine liquid fuel system, control method, medium and equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410041760.0A CN117738796A (en) | 2024-01-10 | 2024-01-10 | Gas turbine liquid fuel system, control method, medium and equipment |
Publications (1)
| Publication Number | Publication Date |
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| CN117738796A true CN117738796A (en) | 2024-03-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202410041760.0A Pending CN117738796A (en) | 2024-01-10 | 2024-01-10 | Gas turbine liquid fuel system, control method, medium and equipment |
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| Country | Link |
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| CN (1) | CN117738796A (en) |
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- 2024-01-10 CN CN202410041760.0A patent/CN117738796A/en active Pending
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