JPH11166424A - Gas turbine system for gasified fuel - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine system for gasified fuel, which is capable of reducing systematic piping around a gas turbine, improving maintenance, simplifying control, increasing reliability and shortening starting time or the like. SOLUTION: A gas turbine system is provided for gasifying a combustible component included in high calorie liquid fuel or solid fuel by a gasifying furnace 11 by using highly concentrated oxygen separated from air and supplying the obtained gas as gasified fuel to the combustor 4 of a gas turbine 18 to perform main combustion. In the system for supplying surplus nitrogen 21 generated at the time of air separation to the combustor 4 during main combustion so as to reduce thermal Nox, the surplus nitrogen 21 is supplied to the combustor 4 as the decreasing injection fluid of a nitrogen oxide generated in a local high temperature area during the combustion of gas turbine ignition starting fuel 30.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine system using a gasified fuel obtained by gasifying a high-calorie fuel with oxygen, and more particularly to a method for removing excess nitrogen generated when oxygen is separated from air during combustion of the gasified fuel. The present invention relates to a gas turbine system for gasification fuel used for purposes other than cooling.

[0002]

2. Description of the Related Art As a method for efficiently and cleanly extracting energy from high-calorie, high-impurity fuels such as coal and heavy oil, these fuels are partially oxidized in a gasification furnace to mono-oxidize combustibles. 2. Description of the Related Art A gas turbine system has been put to practical use in which a combustible gas such as carbon or hydrogen is converted, and the obtained combustible gas is removed from a contaminant contained in the combustible gas and supplied to a combustor of a gas turbine for combustion. In this system, as oxygen for partial oxidation in the gasifier,
There are a type that uses air as it is and a type that separates oxygen from air and uses the oxygen.

In the latter case, excess nitrogen is generated when oxygen is obtained by separating air. This nitrogen is usually supplied to the combustor at a high pressure, and is used to reduce nitrogen oxides (NOx) generated when the gasified fuel is burned. That is, NO
Since x is generated by the combination of nitrogen and oxygen contained in the combustion air in a local high temperature region of the combustion field, by injecting nitrogen, which is an inert gas, into the combustion field. The temperature of this high temperature region is lowered to suppress the oxidation reaction of nitrogen.

An example of this system will be described with reference to FIG. Gas turbine suction air 1 is supplied to gas turbine compressor 2
And a part is introduced into the combustor 4 as the combustion air 3, and another part is sent to the heat exchanger 6 as the bleed air 5 where it is cooled and cooled to a low temperature to the air separator 7 (ASU). be introduced. The air supplied to the air separator 7 is separated into oxygen and nitrogen, and the oxygen 8 is pressurized by a booster 9 and
Will be introduced.

The gasification furnace 11 is supplied with a high-calorie fuel 10 containing impurities such as coal and heavy oil, which is difficult to directly burn with a gas turbine. It is partially oxidized using oxygen 8 that is insufficient for complete combustion, and is exhausted as a product gas 12 mainly containing carbon monoxide and hydrogen. The generated gas 12 contains impurities such as dust and sulfur dioxide.
Is passed through a gas purification device 13 to remove impurities, from which purified gas is discharged as a gasified fuel 14.

When the gasified fuel 14 is used in a gas turbine, the gasified fuel 14 is sent to the combustor 4 together with the combustion air 3 via the gasified fuel system 16 and burned. 17 occurs. The high-temperature and high-pressure combustion gas 17 is supplied as a working fluid to a turbine 18 to drive it, and then becomes an exhaust 19. Part of the power from the turbine 18 drives the compressor 2 and the remaining power is used for rotating the load of the generator 20 and the like. When the gasified fuel 14 is not used in the gas turbine, it is led to the flare stack system 15.

On the other hand, surplus nitrogen 21 separated from the air by the air separator 7 is sent to the heat exchanger 6, where it is subjected to heat exchange for cooling the bleed air 5, and then sent to the booster 23. After the pressure is increased, the pressure is introduced into the combustor 4 through the combustor nitrogen system 24. The nitrogen introduced into the combustor 4 is
As described above, it is used for suppressing thermal NOx generated by the combustion of the gasification gas 16. In addition, surplus nitrogen 2
1 is discharged from the heat exchanger 6 when not used,
The air is blown from the blowing system 22.

In such a gasification plant, since it takes time to start up the gasification furnace 11, the gasification fuel 14 is not used at the time of starting the gas turbine ignition, and a high calorie gas turbine ignition starting fuel 30 is used. Is used.
When the gas turbine ignition start-up fuel 30 is a liquid fuel such as light oil, a part of the combustion air 3 is extracted as spray air 31, and is boosted by a booster 32 before being supplied to the fuel nozzle of the combustor 4. And spray it for spraying liquid fuel.

Conventionally, pure water 33 is injected into the combustor as a means for reducing NOx generated by combustion of the gas turbine ignition start-up fuel 30. That is, NOx in this case is also generated by the combination of nitrogen and oxygen in the air in a local high-temperature region of the combustion field, but is locally generated by the latent heat and sensible heat of the pure water 33 injected. The temperature in the high temperature range is reduced, and NOx is reduced.

[0010] In addition, during the single combustion of the gas turbine ignition start-up fuel 30, if nothing is supplied to the gasification fuel system 16 corresponding to the combustor whose operation is suspended in the multi-can combustor, the combustion during the combustion operation is performed. Due to the slight differential pressure between the burner and the burner 4, high-temperature combustion gas in the combustor 4 during operation may circulate through a fuel manifold (not shown), and pipes that are not hot parts may be burned. Therefore, in the related art, a part of the air extracted from the combustion air 3 flows as the purge air 40 into the casked fuel system 16. When the operation of the gas turbine ignition start-up fuel 30 is switched to the main combustion operation of the gasified fuel 14, the pressure is increased so that the purge air 40 in the pipe and the gasified fuel 14 are mixed and do not ignite in the pipe. Machine 4
The excess nitrogen 21 pressurized in 6 is supplied to the piping via a nitrogen supply system 41, thereby performing a nitrogen purge.

[0011] Further, conventionally, when the gasified fuel is exclusively fired,
A part of the bleed air of the combustion air 3 is supplied to the booster 32 of the supply system of the spray air 31 so that the gas turbine ignition start fuel ejection portion of the fuel nozzle is not burned by being exposed to the high temperature combustion gas in the combustor 4. Is always supplied to the fuel injection portion for starting gas turbine ignition of the fuel nozzle to cool the fuel nozzle. In FIG. 8, reference numeral 43 denotes a separate system air intake, and reference numeral 44 denotes a booster thereof.

FIG. 9 schematically shows the switching state of each system when the gas turbine around the combustor 4 is started as described above on the same graph. Since the ranges of the flow rates of the gasified fuel 41, the purge air 40, and the gas turbine ignition start-up fuel 30 are different, in FIG. 9, these must be shown on the same graph. Indicated by value. As shown in FIG. 9, conventionally, there are many types of switching.

[0013]

In the above-mentioned conventional system, the combustor 4 has a pipe for supplying the gasified fuel 14, a pipe for supplying the surplus nitrogen 21, and a pipe for supplying the fuel 30 for starting the gas turbine ignition. And a supply pipe for the spray air 31 and a supply pipe for the pure water 33. Further, the calorific value of the gasified fuel 14 is one fifth of that of natural gas or the like.
Therefore, the gas supply fuel supply pipe must be large in diameter, and similarly, the excess nitrogen supply pipe has the same large diameter. When the type of the gas turbine is a multi-can type, for example, two large manifolds are required around the gas turbine. In such a conventional system, the configuration of the piping around the gas turbine is complicated due to the large thickness of the piping and the large number of systems, so that there is a problem that the operations such as disassembly and assembly are troublesome, and the maintainability is reduced.

Further, since there is a control system for purging each fuel pipe in addition to the pipe configuration, there is also a problem that the control aspect is very complicated and reliability is reduced. Further, there is a problem that running cost is increased due to consumption of the pure water 33.

Furthermore, since the gasified fuel contains a large amount of water, when the gasified fuel is first introduced into the gas turbine, if the pipe is cooled, the water inside the combustor 4 is drained. And may cause combustion instability. Therefore, conventionally, until drain runs out,
It is necessary to heat the piping while maintaining a co-firing state of the gas turbine ignition start-up fuel and the gasified fuel for a certain period of time, which is one of the causes of prolonging the start-up time.

The present invention has been made in view of such circumstances, and has as its object to reduce the number of system piping around a gas turbine, improve maintainability, simplify control, and improve reliability. It is an object of the present invention to provide a gas turbine system for gasified fuel, which can improve the fuel consumption and shorten the start-up time.

[0017]

SUMMARY OF THE INVENTION The present inventor has abolished the injection of pure water, which has been applied as a measure to reduce NOx generated from liquid fuel or the like burned at the time of startup in a conventional system, and has replaced it. The focus was on using an excess nitrogen extraction system provided for reducing NOx during combustion of gasified fuel. That is, the air separator is already operated before the combustion of the gas turbine ignition start-up fuel, and the conventional system blows off excess nitrogen initially generated in the air separator. If this surplus nitrogen is injected into the combustor, the temperature of the local high-temperature portion of the flame during the start-up operation can be lowered by the same function as the extraction of pure water, and NOx can be reduced.

Therefore, in the invention of claim 1, high-concentration oxygen separated from air is used to gasify combustible components of high-calorie liquid fuel or solid fuel in a gasification furnace, and the obtained gas is gasified. A gas turbine system for supplying fuel to a combustor of a gas turbine to perform main combustion, wherein excess nitrogen generated during air separation is supplied to the combustor during main combustion to reduce thermal NOx. Supplying the surplus nitrogen to the combustor as an injection fluid for reducing nitrogen oxides generated in a local high-temperature region when the gas turbine ignition start-up fuel is burned. I do.

Note that nitrogen has a specific heat of about half that of water and has no effect of latent heat, so that its NOx reduction function is generally small. However, conventionally, pure water is supplied by an air separator in consideration of the fact that a predetermined NOx reduction effect is improved by making a supply amount of pure water approximately equal to that of liquid fuel as fuel for starting ignition of a gas turbine. The amount of surplus nitrogen is several times that of liquid fuel, and by injecting this large amount of surplus nitrogen, a NOx reduction effect equal to or higher than that of pure water can be obtained.

Therefore, according to the first aspect of the present invention, a predetermined NOx reduction effect can be achieved by using the excess nitrogen that has been blown off in the past, and a pure water system is not required, which is omitted. Therefore, the number of systems around the gas turbine can be reduced.

Further, it is possible to replace the spray air which has been conventionally used as a spray assist of the liquid fuel for starting the ignition of the gas turbine with excess nitrogen. Since excess nitrogen is generated in larger quantities than the normally required atomizing air,
Even if the pressure difference between the supply pressure and the combustion gas pressure in the combustor is small, sufficient spray can be obtained.

According to the second aspect of the present invention, high-concentration oxygen separated from air is used to gasify combustible components of high-calorie liquid fuel or solid fuel in a gasification furnace, and the obtained gas is gasified. A gas turbine system for supplying fuel as a fuel to a combustor of a gas turbine to perform main combustion, wherein a system in which excess nitrogen generated during air separation is supplied to the combustor during main combustion to reduce thermal NOx. A gas turbine system for gasified fuel, wherein the surplus nitrogen is supplied as a fuel spraying fluid when the gas turbine ignition starting fuel is burned.

When the liquid fuel is pressure-sprayed from the fuel nozzle, the spraying state deteriorates when the flow rate is small. However, in the fuel nozzle of the gas turbine combustor, the fuel flow rate is the smallest in the vicinity of the ignition condition.At this time, the pressure in the combustor is close to the atmospheric pressure, so the supply pressure of the excess nitrogen is sufficiently higher than this. The conditions suitable for spraying can be easily obtained.

Therefore, according to the second aspect of the present invention, the nebulizing air booster and the nebulizing air system therewith become unnecessary, and the number of systems around the gas turbine can be reduced.

Next, in the third aspect of the present invention, high-concentration oxygen separated from air is used to gasify combustible components of high-calorie liquid fuel or solid fuel in a gasifier, and the obtained gas is converted into gas. A gas turbine system that supplies main gas as a fuel to a combustor of the gas turbine to perform main combustion,
In a system for reducing thermal NOx by supplying surplus nitrogen generated during air separation to a combustor at the time of main combustion, when the combustor is a multi-can type, part of the surplus nitrogen is converted to a gasified fuel system. The present invention provides a gas turbine system for gasified fuel, characterized by being injected into a gas turbine.

According to the third aspect of the present invention, when the gasified fuel is not flowing into the gasified fuel system, a part of the surplus nitrogen is injected so that a part of the surplus nitrogen is removed from the gasified fuel system. Through the fuel nozzle into the combustor. As a result, a pressure difference is generated in the fuel nozzle, and this pressure difference exceeds a small pressure difference between the cans in the multi-can combustor, thereby preventing a situation in which high-temperature combustion gas circulates through the fuel manifold. Reliability can be improved.

In general, when using gasified fuel, the pressure of the nitrogen booster is reduced to a minimum in order to reduce the power of auxiliary equipment. For this reason, the pressure of the surplus nitrogen is generally lower than the pressure of the gasified fuel, and the pressure of the surplus nitrogen is reduced.
In the invention of the present invention, for example, a stop valve is provided in a pipe connecting a supply pipe for excess nitrogen and a supply pipe for gasified fuel. Means such as closing the stop valve to prevent the gasified fuel from flowing back into the nitrogen pipe during the burning of the fuel is required, but providing the stop valve or the like leads to a complicated structure.

Therefore, according to the invention of claim 4, in the gas turbine system for gasified fuel according to claim 3, a flow only from the surplus nitrogen side is provided between the gasified fuel system and the system for injecting surplus nitrogen. Provided is a gas turbine system for gasified fuel, which is provided with an allowable check valve.

According to such a configuration, the control can be simplified by performing the opening / closing function of the pipe by the check valve, and the reliability of the system can be improved.

According to a fifth aspect of the present invention, in the gas turbine system for a gasified fuel according to the third or fourth aspect, the fuel nozzle of the combustor has a fuel injection path for starting ignition at the center of the nozzle, and has a fuel injection path therearound. A gasification fuel ejection path and an excess nitrogen ejection path are arranged adjacent to each other via a partition wall, and the gasification fuel ejection path and the excess nitrogen ejection path communicate with each other by a communication hole formed in the partition plate. A gas turbine system for gasified fuel.

According to such a configuration, during the firing of liquid fuel or the like, the pressure of the gasified fuel ejection path through which no fuel is flowing becomes the same as the internal pressure of the combustor communicating through the ejection port, while the excess Since the pressure in the nitrogen ejection path is higher than the internal pressure of the combustor, a part of the surplus nitrogen flows to the fuel ejection port side of the gasification fuel ejection path through the communication hole, and the backflow of the high-temperature combustion gas is prevented. Conversely, when the gasified fuel is exclusively fired, the fuel pressure in the gasified fuel ejection path is higher than the excess nitrogen pressure, so the gasified fuel partially flows to the excess nitrogen side through the communication hole. However, since the communication hole is located close to the inside of the combustor, it does not flow backward toward the upstream side of the excess nitrogen ejection path,
A part of the gasified fuel and excess nitrogen are discharged into the combustor while being mixed. This gaseous mixture of nitrogen and fuel has a low calorific value and is usually difficult to burn, but when injected into the combustion gas of gasified fuel in the combustor, it burns in a state close to complete combustion. Therefore, the fuel control can be simplified according to the invention of claim 5, and the reliability of the system can be improved.

According to the sixth aspect of the present invention, high-concentration oxygen separated from air is used to gasify combustible components of high-calorie liquid fuel or solid fuel in a gasification furnace, and the obtained gas is used as gasification fuel. A gas turbine system for supplying main gas to a combustor of a gas turbine to perform main combustion, wherein excess nitrogen generated during air separation is supplied to the combustor during main combustion to reduce thermal NOx. A gas turbine system for gasified fuel, characterized in that a system for heating surplus nitrogen with a heat exchanger and injecting the gas into a gasified fuel system at the time of combustion of fuel for starting turbine ignition is provided.

According to the present invention, since only excess nitrogen is used in place of the air conventionally used for purging the gasified fuel system, a purge air system is not required, and the piping layout and control system are simplified. Thus, maintainability and reliability can be improved.

When the excess nitrogen is directly introduced from the air separator, the temperature of the excess nitrogen is low, the gasified fuel pipe is cooled, and the moisture in the gasified fuel may be drained when the gasified fuel is introduced. . Therefore, in the present invention, the excess nitrogen is heated by the heat exchanger and then introduced into the gasification fuel system, so that the time required for starting can be greatly reduced.

According to the seventh aspect of the present invention, high-concentration oxygen separated from air is used to gasify combustible components of high-calorie liquid fuel or solid fuel in a gasification furnace, and the obtained gas is used as gasification fuel. A gas turbine system for supplying main gas to a combustor of a gas turbine to perform main combustion, wherein excess nitrogen generated during air separation is supplied to the combustor during main combustion to reduce thermal NOx. A gas turbine system for gasified fuel, characterized in that the excess nitrogen is supplied to a gas turbine ignition start-up fuel ejection portion of a fuel nozzle of the combustor at the time of combustion of gasified fuel.

According to the present invention, instead of the compressor discharge air which has been used to prevent burnout of the fuel nozzle for starting gas turbine ignition of the fuel nozzle at the time of gasification fuel combustion, surplus nitrogen having a lower temperature than this is used. The use of the nozzle and the elimination of oxygen for oxidizing metal, which is a constituent material of the nozzle, make it possible to effectively perform the nozzle cooling action, thereby dramatically extending the nozzle life.

In the eighth aspect of the present invention, high-concentration oxygen separated from air is used to gasify a combustible component of a high-calorie liquid or solid fuel in a gasification furnace, and the obtained gas is used as a gasified fuel. A gas turbine system for supplying main gas to a combustor of a gas turbine to perform main combustion, wherein excess nitrogen generated during air separation is supplied to the combustor during main combustion to reduce thermal NOx. Excess nitrogen is supplied to the fuel nozzle of the combustor as a fuel spray fluid when the gas turbine ignition start fuel is burned, and is supplied to the gas turbine ignition start fuel ejection portion of the fuel nozzle when the gasified fuel is burned. Provided is a gas turbine system for gasified fuel characterized by supplying.

According to the present invention, by combining the configurations of the second and seventh aspects of the invention, the configuration and control of the piping around the combustor can be simplified, and the reliability of the system can be improved. Become like

[0039]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of a gas turbine system for gasified fuel according to the present invention will be described below with reference to FIGS.
This will be described with reference to FIG. Note that, for ease of explanation, the same reference numerals as in FIG. 8 are used in FIGS.

First Embodiment (FIGS. 1 and 2) FIG. 1 is a system diagram showing a system configuration of this embodiment.
FIG. 2 is a graph for explaining the operation.

In the present embodiment, the gas turbine suction air 1 is pressurized by the gas turbine compressor 2, a part is introduced into the combustor 4 as combustion air 3, and the other part is extracted 5 as a heat exchanger 6. And cooled to a low temperature and introduced into the air separator 7 (ASU). The air supplied to the air separator 7 is separated into oxygen 8 and nitrogen 21, and the oxygen 8 is pressurized by a booster 9 and introduced into a gasification furnace 11.

The gasification furnace 11 is supplied with a high-calorie fuel 10 containing impurities such as coal and heavy oil, which is difficult to burn directly with a gas turbine. It is partially oxidized using oxygen 8 that is insufficient for complete combustion, and is exhausted as a product gas 12 mainly containing carbon monoxide and hydrogen. The generated gas 12 contains impurities such as dust and sulfur dioxide.
Is passed through a gas purification device 13 to remove impurities, from which purified gas is discharged as a gasified fuel 14.

When used in a gas turbine, the gasified fuel 14 is sent to the combustor 4 along with the combustion air 3 via the gasified fuel system 16 and burned. 17 occurs. The high-temperature and high-pressure combustion gas 17 is supplied to the turbine 18 as a working fluid, drives the turbine 18, and becomes the exhaust 19. This turbine 18
Is used to drive the compressor 2 and the remaining power is used for rotating the load of the generator 20 and the like. When the gasified fuel 14 is not used in the gas turbine, it is led to the flare stack system 15.

On the other hand, surplus nitrogen 21 separated from the air by the air separator 7 is sent to the heat exchanger 6, where it is subjected to heat exchange for cooling the bleed air 5, and then sent to the booster 23. After the pressure is increased, the pressure is introduced into the combustor 4 through the combustor injection nitrogen system 24. As described above, the nitrogen introduced into the combustor 4 is used for suppressing thermal NOx generated by the combustion of the gasification gas 16. When the surplus nitrogen 21 is not used, it is discharged from the heat exchanger 6 and then discharged from the discharge system 22.

In such a gasification plant, since it takes time to start up the gasification furnace 11, the gasification fuel 14 is not used at the time of starting the gas turbine ignition, and the high calorie gas turbine ignition starting fuel 30 is not used. Is used.

In this case, when the ignition start-up fuel 30 is a liquid fuel such as light oil, a gas for assisting spraying is required, but in this embodiment, the combustor injection nitrogen system 24 is used.
Sprayed nitrogen 34 from the combustor 4
And the excess nitrogen 21 is used for assisting the spraying of the gas turbine ignition start-up fuel 30. Further, in order to reduce NOx generated from the gas turbine ignition start-up fuel 30 at the time of start-up, surplus nitrogen 21 is also used as a gas to be injected into the combustor 4, and is injected into the combustor 4 at the start-up. I have.

Further, in this embodiment, when the gas turbine ignition start-up fuel 30 is independently burned, the high temperature combustion gas in the combustor 4 passes through a fuel manifold (not shown) due to a slight pressure difference between the cans of the multi-can combustor. A part of the surplus nitrogen 21 is also used as a purge gas for preventing the pipes that circulate and are not hot parts from being burned out, and are supplied to the gasification fuel system 16 as purge nitrogen 45.

Similarly, during firing of the gasified fuel, the ignition start-up fuel nozzle (not shown) is always flowed during firing of the gasified fuel with the sprayed nitrogen 34 so as not to be burned by being exposed to the high-temperature combustion gas in the combustor 4. The starting fuel nozzle is cooled.

FIG. 2 is a graph for explaining the control operation of the present embodiment, and the horizontal axis represents the time from startup to switching. It should be noted that the time on the horizontal axis indicates movement, so that the length of the axis does not always match the actual time. The vertical axis represents the flow rate of each system. In this horizontal axis, the gasified fuel and the liquid fuel having different flow rate ranges are shown on the same axis. Therefore, only the change in the flow rate does not always coincide with the actual flow rate.

In the present embodiment, the surplus nitrogen 21 is introduced before the start-up, and a part of the nitrogen is branched via a valve to be purged nitrogen 45 of the gasified fuel system. Although FIG. 2 does not show the sprayed nitrogen, a part of the excess nitrogen 21 is diverted without control in the present embodiment, and the excess nitrogen 21
This is because it is under the same control as. However, in the present invention, the spray nitrogen may be controlled.

At the start of ignition of the gas turbine, for example, liquid fuel is introduced, and a part of surplus nitrogen 21 is supplied as spray nitrogen to atomize the liquid fuel and ignite. As the liquid fuel increases, the combustion temperature increases, and the generation of NOx increases. However, since the excess nitrogen 21 is introduced into the combustor 4, the generation of NOx is suppressed. Immediately before switching the fuel to gasified fuel, the supply of the purge nitrogen 45 is stopped, and the gasified fuel 41 is introduced.

According to the present embodiment, pure water which has been conventionally used for reducing NOx generated during the combustion of liquid fuel becomes unnecessary, the piping around the gas turbine can be reduced, and the maintainability can be improved. become.

Further, according to the present embodiment, the spray air 31 shown in FIG.
In addition, since the purge system 42 for cooling the liquid nozzle is not required, the piping around the gas turbine can be reduced, so that not only the maintainability can be improved, but also the number of devices to be controlled can be reduced, thereby improving the reliability. Can be achieved.

Further, according to the present embodiment, the system of the purge nitrogen 40 shown in FIG. 8 can also be eliminated, whereby the piping around the gas turbine can be reduced,
Not only is the maintainability improved, but also the number of devices to be controlled is reduced, thereby improving reliability.

Further, according to the present embodiment, the purge nitrogen supply system 41 shown in FIG. 8 can be replaced by a purge nitrogen 45 system branched from the downstream of the heat exchanger 6 as shown in FIG. Therefore, the gasification fuel system 16 can be warmed up, the drainage of water in the gasification fuel can be suppressed, and the startup time can be shortened.

Second Embodiment (FIGS. 3 and 4) FIG. 3 is a system diagram showing a second embodiment of the present invention. The system configuration of the present embodiment is almost the same as that of the first embodiment, except that a check valve 47 is provided in a system of purge nitrogen 45 branched from excess nitrogen 24. In addition, about the other structure, FIG. 4 attaches | subjects the same code | symbol as FIG. 15, and abbreviate | omits description.

In the case of the present embodiment, the gasified fuel 1
6 is not supplied, the pressure in the pipe of the gasification fuel system 16 becomes the same as that of the inside of the combustor 4. However, since the pressure of the excess nitrogen 21 in the combustor injection nitrogen system 24 is higher, the check valve 47 is opened, and a part of the surplus nitrogen 21 flows into the gasification fuel system 16 as purge nitrogen 45.

On the other hand, when the gasified fuel 14 is burned, the check valve 47 is closed because the pressure of the surplus nitrogen 21 is lower than that of the gasified fuel 14.

FIG. 4 shows the control operation of this embodiment. In FIG. 4, the same shaft as that of FIG. 2 shown in the first embodiment is used. In the present embodiment, as shown in FIG. 4, there is no line indicating the operation of the purge nitrogen 45 as compared with the case of FIG. That is, by providing the check valve 47, control of the purge nitrogen 45 becomes unnecessary, control can be further simplified, and reliability can be further improved.

Third Embodiment (FIGS. 5 to 7) FIG. 5 is a system diagram showing a third embodiment of the present invention. The system configuration of the present embodiment is also substantially the same as that of the first embodiment, but the system of the purge nitrogen 45 branched from the combustor injection nitrogen system 24 for supplying the surplus nitrogen 21 is omitted. Instead, a fuel nozzle 49 having the shape shown in FIG.

That is, FIG. 6 is an enlarged view of the fuel nozzle 49 as viewed from the inside of the combustor. A liquid fuel ejection path 53 is provided at the nozzle center position of the fuel nozzle 49, and different types of fluid ejection paths 50, 51, and 52 are provided on the outer peripheral side of the fuel nozzle 49 at intervals in the circumferential direction as shown by different types of hatching. Are formed. That is, the gasification fuel ejection path 50 and the air ejection path 51 are alternately arranged, and the nitrogen ejection path 52 is arranged between them.

FIG. 7 is an expanded view showing a cross section taken along the arrow A along the circumferential direction of the fuel nozzle 49 shown in FIG. The upper part of FIG. Each fluid 50,5
1 and 52 flow upward as indicated by arrows a, b and c, respectively. Of the path partition plate 54, the nitrogen ejection path 52
A communication hole 5 is provided in a partition plate 54a between the
5 is drilled. As shown in FIG. 7, the communication hole 55 has an inclination along the flow direction of nitrogen.

In such an embodiment, the same control as in FIG. 4 is performed. As a result, the gasified fuel does not flow during the liquid fuel firing, and a part of the nitrogen is ejected from the fuel ejection port through the communication hole 55. At the time of gas fuel sintering, gasified fuel and nitrogen also flow, so that a pressure difference between the two causes a flow to any one through the communication hole 55, but the flow amount is small, and the mixed gas does not flow back through the pipe. It flows out into the combustor 4.

According to the third embodiment having such a configuration,
During the liquid fuel firing, the nitrogen gas always flows out from the fuel injection port, and the high temperature combustion gas in the combustor 4 flows back into the fuel nozzle 49 and circulates into the fuel manifold without requiring any special control. Can be prevented, and the reliability of the system can be improved.

[0065]

As described above, according to the present invention, the driving force around the gas turbine can be reduced by injecting excess nitrogen into the combustor at the time of using the ignition start-up fuel or using it instead of the atomized air. Thus, a gas turbine system having excellent maintainability can be provided. Further, by using a surplus nitrogen system for purging a fuel pipe and further increasing the temperature of the surplus nitrogen by a heat exchanger, it is possible to provide a gas turbine system with a quick start-up. Furthermore, by using excess nitrogen for purging the fuel pipe and providing a check valve or communicating with the fuel nozzle in that case, it is possible to improve reliability without requiring complicated control, etc. Excellent effects are achieved.

[Brief description of the drawings]

FIG. 1 is a system diagram showing a system configuration according to a first embodiment of the present invention.

FIG. 2 is a graph showing the operation of the first embodiment.

FIG. 3 is a system diagram showing a system configuration according to a second embodiment of the present invention.

FIG. 4 is a graph showing the operation of the second embodiment.

FIG. 5 is a system diagram showing a system configuration according to a third embodiment of the present invention.

FIG. 6 is a diagram showing a configuration of a fuel nozzle applied in a third embodiment.

FIG. 7 is a sectional view taken along line AA of FIG. 6;

FIG. 8 is a system diagram showing a conventional system configuration.

FIG. 9 is a graph showing the operation of the conventional example.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Gas turbine intake air 2 Gas turbine compressor 3 Combustion air 4 Combustor 5 Bleed air 6 Heat exchanger 7 Air separator (ASU) 8 Oxygen 9 Booster 10 High calorie fuel 11 Gasification furnace 12 Generated gas 13 Gas purification device 14 Gasified Fuel 15 Flare Stack System 16 Gasified Fuel System 17 Combustion Gas 18 Turbine 19 Exhaust 20 Generator 21 Excess Nitrogen 23 Booster 24 Combustor Nitrogen System 30 Gas Turbine Ignition Start Fuel 31 Spray Air 32 Booster 33 Pure Water Reference Signs List 40 purge air 41 nitrogen supply system 42 system 43 separate system air intake 44 booster 34 spray nitrogen 45 purge nitrogen 46 booster 47 check valve 49 fuel nozzle 50 gasified fuel ejection path 51 air ejection path 52 nitrogen ejection path 53 liquid Fuel injection path 54 Partition plate 55 Communication hole

Claims (8)

[Claims] 1. A gas turbine combustor using high-concentration oxygen separated from air to gasify a combustible component of high-calorie liquid fuel or solid fuel in a gasification furnace and using the obtained gas as a gasification fuel. A gas turbine system for performing main combustion by supplying to a combustor at the time of main combustion excess nitrogen generated during air separation
Wherein the excess nitrogen is supplied to the combustor as an injection fluid for reducing nitrogen oxides generated in a local high-temperature region when the fuel for starting gas turbine ignition is burned. For gas turbine systems. 2. A gas turbine combustor using high-concentration oxygen separated from air to gasify a combustible component of a high-calorie liquid fuel or solid fuel in a gasification furnace, and using the obtained gas as a gasification fuel. A gas turbine system for performing main combustion by supplying to a combustor at the time of main combustion excess nitrogen generated during air separation
A gas turbine system for gasified fuel, wherein the excess nitrogen is supplied as a fuel spray fluid when the gas turbine ignition start-up fuel is burned. 3. A gas turbine combustor using high-concentration oxygen separated from air to gasify combustible components of high-calorie liquid fuel or solid fuel in a gasification furnace, and using the obtained gas as a gasification fuel. A gas turbine system for performing main combustion by supplying to a combustor at the time of main combustion excess nitrogen generated during air separation
A gas turbine system for gasified fuel, wherein a part of the surplus nitrogen is injected into a gasified fuel system when the combustor is a multi-can type. 4. A gas turbine system for gasified fuel according to claim 3, further comprising a check valve between the gasified fuel system and a system for injecting surplus nitrogen, which allows a flow only from the surplus nitrogen side. A gas turbine system for gasified fuel, characterized in that: 5. The gas turbine system for gasified fuel according to claim 3, wherein the fuel nozzle of the combustor comprises:
It has a fuel injection path for starting ignition in the center of the nozzle, and has a gasification fuel injection path and a surplus nitrogen injection path adjacent to each other via a partition wall around it, and these gasification fuel injection paths and the excess A gas turbine system for gasified fuel, which communicates with a nitrogen ejection path by a communication hole formed in the partition plate. 6. A gas turbine combustor using high-concentration oxygen separated from air to gasify a combustible component of a high-calorie liquid fuel or solid fuel in a gasification furnace and using the obtained gas as a gasification fuel. A gas turbine system for performing main combustion by supplying to a combustor at the time of main combustion excess nitrogen generated during air separation
In the system that reduces the amount of excess nitrogen, the excess nitrogen is heated by a heat exchanger during combustion of the gas turbine ignition start-up fuel.
A gas turbine system for gasification fuel, comprising a system for injecting into a gasification fuel system. 7. A gas turbine combustor using high-concentration oxygen separated from air to gasify combustible components of a high-calorie liquid fuel or solid fuel in a gasification furnace, and using the obtained gas as a gasification fuel. A gas turbine system for performing main combustion by supplying to a combustor at the time of main combustion excess nitrogen generated during air separation
A gas turbine system for gasifying fuel, wherein the excess nitrogen is supplied to a gas turbine ignition start-up fuel ejection portion of a fuel nozzle of the combustor during combustion of the gasified fuel. 8. A gas turbine combustor using high-concentration oxygen separated from air to gasify a combustible component of a high-calorie liquid fuel or solid fuel in a gasifier, and using the obtained gas as a gasified fuel. A gas turbine system for performing main combustion by supplying to a combustor at the time of main combustion excess nitrogen generated during air separation
And supplying the surplus nitrogen to a fuel nozzle of the combustor as a fuel spray fluid during combustion of a gas turbine ignition start-up fuel, and a gas of the fuel nozzle during combustion of the gasified fuel. A gas turbine system for gasified fuel, wherein the gas is supplied to a fuel injection section for starting turbine ignition.