JPH10110630A - Fuel plant for gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To stabilize combustion gas for premixing combustion over a wide operation range by adding vapor in a vapor system to fuel, which is fed from a fuel supply system of a fuel tank, providing a fuel reformer generating reformed fuel, and feeding the reformed fuel generated from the fuel reformer to a gas turbine combustor. SOLUTION: In a starting operation, fuel fed from a fuel tank 26 to a fuel reformer 29 is divided into two flows to a burner 30 and to a reforming catalyst 31. The burner 30 is operated so as to generate combustion gas from the fuel fed from the fuel tank 26, and if reformed fuel is generated from the reforming catalyst 31, a part of the reformed fuel is fed for combustion via a bypass system 32. The fuel reformer 29 increases a combustion gas temperature in the burner 30, and when the reforming catalyst 31 starts generating reformed fuel, the reformed fuel is fed to a burner 30 using the bypass system 32, so that NOx concentration of exhaust gas discharged from an exhaust duct 34 is suppressed low. Then, the reformed fuel is fed to a gas turbine combustor 19 as fuel for turbine driving combustion gas.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a fuel plant for a gas turbine combustor.
The present invention relates to a gas turbine combustor fuel plant that produces low x-concentration fuel.

[0002]

2. Description of the Related Art A plurality of gas turbine combustors used in a gas turbine plant or a combined cycle power plant are incorporated between an air compressor and a gas turbine, and are provided with high-pressure air guided from the air compressor. LNG
Such a gaseous fuel is added to generate combustion gas, and the combustion gas drives a gas turbine.

[0003] It is known that the thermal efficiency of a gas turbine increases in proportion to an increase in the temperature of the combustion gas, and the temperature of the combustion gas is increased in order to improve the thermal efficiency of the turbine.

[0004] However, the gas turbine combustor is subject to various restrictions such as the limit of the strength of heat-resistant material and the clearing of the pollution regulation value of the NOx concentration contained in exhaust gas when the temperature of the combustion gas is increased.

[0005] The main factor of NOx generated from the combustion gas of the gas turbine combustor is often local high temperature of the combustion gas in the gas turbine combustor. Is proportional to the temperature of the combustion gas. In particular, NOx is often generated when the fuel-air ratio is close to 1 during diffusion combustion of fuel and air.

As a means for suppressing the NOx concentration to a low level, there is known a lean premixed combustion system in which air is added to fuel in advance to burn the fuel in a lean state.

[0007] A gas turbine combustor to which the lean premixed combustion system is applied accommodates a combustor liner 3 as an inner cylinder forming a combustion chamber 2 in the center of an outer cylinder 1 as shown in FIG.
A pilot fuel supply unit 4 for diffusion combustion and a premixed fuel supply unit 5 for premixed combustion concentrically arranged on the pilot fuel supply unit 4 are provided on the head side of the combustor liner 3. It is configured to be installed.

The gas turbine combustor has a main fuel supply section 6 for premix combustion along a side surface of the combustor liner 3, and a combustion gas 9 is supplied to the gas turbine 7 downstream of the combustor liner 3. Is provided with a transition piece (tail tube) 8 for guiding the user.

The pilot fuel supply section 4 has a pilot fuel passage section 10 and a pilot nozzle 11, and uses, for example, a combustion gas 9 of gaseous fuel injected from the pilot nozzle 11 into the combustion chamber 2 as a flame (fire type). It has become.

The premixed fuel supply section 5 includes a fuel passage section 12 and a premixed fuel nozzle 13.
High pressure air 1 supplied from the air compressor 14 to the fuel 2
5 to make a lean premixed fuel, the premixed fuel nozzle 13
The fuel is injected into the combustion chamber 2 from the gas turbine 7 and is used up to a predetermined load of the gas turbine 7.

The main fuel supply section 6 includes a main fuel nozzle 16 and a premix duct 17. The high pressure air 15 supplied from the air compressor 14 is supplied to the fuel injected from the main fuel nozzle 16 by the premix duct 17. To make the fuel concentration lean, and the lean fuel is injected into the combustion chamber 2 from a predetermined load of the gas turbine 7 to be used for driving the gas turbine.

The combustion gas of the fuel injected from each of the nozzles 11, 13 and 16 is guided from the combustion chamber 2 to the gas turbine 7 through the transition piece 8, and the generator 18 is rotated by the expansion work of the gas turbine 7. I was

As described above, the conventional gas turbine combustor performs diffusion combustion in order to secure a flame from fuel ignition to a predetermined load. Thereafter, diffusion combustion is minimized, premixed combustion is performed, and rated operation is performed. The NOx concentration at that time was kept below the pollution regulation value.

However, recent gas turbine plants are:
Along with the increase in the temperature of the combustion gas accompanying the increase in output, a further reduction in the NOx concentration is also required. Therefore, the development of a new gas turbine combustor has become necessary.

[0015]

In the conventional gas turbine combustor shown in FIG. 14, there is a possibility that the combustion gas may blow out during the premixed combustion. Therefore, it is necessary to extend the operation range of the diffusion combustion. However, if the operating range of diffusion combustion is widened, there is a problem that the NOx concentration is greatly increased and cannot be suppressed within the pollution regulation value.

Further, in the conventional gas turbine combustor, the NOx concentration was able to be reliably suppressed within the pollution regulation value in the operation after the predetermined load, but the weight of diffusion combustion occupied from fuel ignition to the initial load of the gas turbine. , The NOx concentration often exceeded the pollution regulation value.

In recent gas turbine plants, which are required to increase the temperature of combustion gas due to the increase in output, the operating range of diffusion combustion for preventing combustion gas blowout in premixed combustion is increased, and the NOx concentration is reduced. At the same time, it has reached its limit in simultaneously fulfilling the conflicting function of keeping it within the pollution control value, and new development of the fuel itself has been required.

The present invention has been made in view of such circumstances, and aims to stabilize the combustion gas of premixed combustion over a wide operating range from fuel ignition to rated load, and to reduce the NOx concentration during this period. It is an object of the present invention to provide a gas turbine combustor fuel plant that can be controlled to a level within pollution control values.

[0019]

SUMMARY OF THE INVENTION A gas plant combustor fuel plant according to the present invention has the following objects.
As described in claim 1, a fuel reformer that generates a reformed fuel by adding a steam of a steam system to a fuel supplied from a fuel supply system of a fuel tank, and a reformer generated from the fuel reformer. And a reformed fuel supply system for supplying high quality fuel to the gas turbine combustor.

In order to achieve the above object, a fuel plant for a gas turbine combustor according to the present invention has a fuel supply system for a fuel tank, comprising: a gas turbine combustor and a fuel reformer; Each is connected to a burner.

According to a third aspect of the present invention, a fuel plant for a gas turbine combustor according to the present invention includes a bypass system for supplying reformed fuel to a burner. It is a thing.

According to a fourth aspect of the present invention, a fuel plant for a gas turbine combustor according to the present invention comprises a fuel reformer comprising a pilot fuel supply section and a main fuel supply section for the gas turbine combustor. A reformed fuel supply system for supplying reformed fuel to at least one of the supply units is provided.

In order to achieve the above object, the gas turbine combustor fuel plant according to the present invention is configured such that the gas turbine combustor includes at least a pilot fuel supply unit and a premixed fuel supply unit. One of the outlets is provided with a fuel catalyst.

In order to achieve the above object, a fuel plant for a gas turbine combustor according to the present invention has a reformed fuel supply system provided with a reformed fuel tank.

In order to achieve the above object, a fuel plant for a gas turbine combustor according to the present invention is arranged such that the reforming fuel tank is provided with a pilot fuel supply section and a main fuel supply for the gas turbine combustor. At least one of the supply units is provided with a reformed fuel supply system.

In order to achieve the above object, a fuel plant for a gas turbine combustor according to the present invention adds steam of a steam system to fuel supplied from a fuel supply system of a fuel tank. A reforming catalyst for producing reformed fuel is provided in a transition piece of a gas turbine combustor, and a reformed fuel supply system for supplying the produced reformed fuel to a fuel injection unit is provided.

In order to achieve the above object, the fuel plant for a gas turbine combustor according to the present invention is produced from a reforming catalyst provided in a transition piece of the gas turbine combustor. A reformed fuel supply system for supplying reformed fuel to a fuel injection unit is provided with a reformed fuel tank.

In order to achieve the above object, the fuel plant for a gas turbine combustor according to the present invention is produced from a reforming catalyst provided in a transition piece of the gas turbine combustor. The reformed fuel supply system for supplying the reformed fuel to the fuel injection unit is connected to at least one of the premixed fuel supply unit and the main fuel supply unit of the gas turbine combustor.

In order to achieve the above object, the fuel plant for a gas turbine combustor according to the present invention is produced from a reforming catalyst provided in a transition piece of the gas turbine combustor. The reformed fuel supply system that supplies the reformed fuel to the fuel injection unit includes a reformed fuel tank.

[0030]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A fuel plant for a gas turbine combustor according to the present invention will be described below with reference to the drawings.

FIG. 1 is a schematic system diagram showing an embodiment of a fuel plant for a gas turbine combustor according to the present invention.

The gas turbine combustor 19 includes the air compressor 2
0 and a plurality of gas turbines 21 are provided between the gas turbine 21 and the fuel, and fuel is added to the high-pressure air 22 of the air compressor 20 to generate combustion gas 23, and the combustion gas 23 is guided to the gas turbine 21.
The expansion work drives the generator 24 to rotate.

The fuel plant 25 for supplying the fuel to the gas turbine combustor 19 is provided with a fuel in a fuel tank 26, for example, L
A fuel supply system 27 for directly supplying gaseous fuel such as NG to the gas turbine combustor 19, and a reformed fuel supply system 2 for reforming the fuel in the fuel tank 26 and supplying the reformed fuel to the gas turbine combustor 19
And 8.

The reformed fuel supply system 28 includes a fuel reformer 29 that converts the fuel supplied from the fuel tank 26 into reformed fuel. The fuel reformer 29 includes a burner 30 that burns fuel from the fuel tank 26 and supplies a heat source necessary for a fuel reforming reaction, and a reforming catalyst 31 that chemically reacts the fuel using the combustion gas of the burner 30 as a heat source. And an exhaust duct 34 that allows the combustion gas to flow out of the device. The fuel reformer 29 includes a bypass system 32 that supplies a part of the reformed fuel for burning the burner 30 and a steam system 33 that supplies the reforming catalyst 31 with steam required for generating the reformed fuel. Are provided respectively. The steam system 33 is connected, for example, to a middle stage of a steam turbine of a combined cycle power plant, and a relatively high pressure and high temperature steam is supplied to the reforming catalyst 31.
To be supplied. The reforming catalyst 31 is filled with, for example, a nickel catalyst using alumina as a carrier.

Next, the operation will be described.

The fuel supplied from the fuel tank 26 to the fuel reformer 29 is initially supplied to the burner 30 and the reforming catalyst 3.
1 and are separated. The burner 30 performs an operation of generating combustion gas from fuel from the fuel tank 26, and when reformed fuel is generated from the reforming catalyst 31, a part of the reformed fuel is switched for combustion through the bypass system 32 and operated. Is to be performed.

The fuel reformer 29 sets the combustion gas temperature of the burner 30 to 1200 ° C. as a heat source necessary for generating reformed fuel from the reforming catalyst 31,
Although the concentration tends to increase, when the reforming catalyst 31 starts generating reformed fuel, a switching operation of supplying the reformed fuel containing a large amount of hydrogen to the burner 30 using the bypass system 32 is performed. In addition, the NOx concentration of the exhaust gas discharged from the exhaust duct 34 of the fuel reformer 29 can be kept low.

The fuel in the fuel tank 26 is supplied to the steam system 3
3 and is supplied to the reforming catalyst 31. In this case, the conditions for generating the reformed fuel were a design pressure of 35 atm, a designed reforming reaction temperature of 580 ° C., and a steam amount of 2.5 in the molar ratio of methane in the fuel. About 95% by weight of the fuel is produced in a reformed fuel containing hydrogen as a main component. This reformed fuel has a calorific value of about 50 Kcal / mole (about 70 Kcal / mole excluding steam).
Even at 0 ° C. or higher, a sufficiently stable combustion gas can be generated. The reformed fuel was charged into the gas turbine combustor 19, and the NOx concentration was measured.
The low NOx concentration was less than (equivalent to 16% oxygen).

As described above, in the present embodiment, the reformed fuel containing hydrogen as a main component is applied to the fuel for the turbine driving combustion gas, and even when the combustion gas temperature at which the NOx concentration is generated in a relatively large amount is 1600 ° C. or higher. Since the combustion gas can be stabilized, the NOx concentration can be sufficiently reduced even if the operation range of the diffusion combustion is expanded without depending on the premixed combustion as in the past, and the operation range of the diffusion combustion can be reduced. The increase can reliably prevent the combustion gas from blowing off.

FIG. 2 is a schematic system diagram showing a first embodiment of the first embodiment of the gas turbine combustor fuel plant according to the present invention. The same parts as those of the first embodiment are denoted by the same reference numerals.

In this embodiment, a reformed fuel supply system 28A and a fuel passage 38 are provided in a pilot fuel supply 37 having a pilot fuel passage 35 and a pilot nozzle 36.
Premix fuel supply section 4 having a premix fuel nozzle 39 and a premix fuel nozzle 39
0 is connected to the fuel supply system 27.
Further, in this embodiment, a reformed fuel supply system 28B and a fuel supply system 27 are connected to a main fuel supply section 43 having a main fuel nozzle 41 and a premix duct 42, and a reformer 29 from the fuel reformer 29 is connected. It is possible to selectively supply high quality fuel and gaseous fuel from the fuel tank 26.

In this embodiment, the reformed fuel is generated from the fuel reformer 29 under the same design conditions as the first embodiment, and the reformed fuel is supplied to the pilot fuel supply unit 37 and the main fuel supply unit 43, respectively. And the fuel from the fuel tank 26 to the premixed fuel supply unit 40,
When the concentration was measured, it was 10 ppm (in terms of 16% oxygen,
1.5 MPa), which is significantly lower than the NOx concentration of 20 to 30 ppm when gaseous fuel from the fuel tank 26 is supplied to each of the pilot fuel supply unit 37, the premixed fuel supply unit 40, and the main fuel supply unit 43. And got good results. Also, the combustion state was stabilized.

As described above, in this embodiment, the reformed fuel is supplied to each of the pilot fuel supply section 37 and the main fuel supply section 43, and the gaseous fuel in the fuel tank 26 is supplied to the premixed fuel supply section 40. Since different fuel types are properly used, the NOx concentration can be kept low, and stable combustion without blowout can be achieved even if the diffusion combustion operation range is expanded.

FIG. 3 is a schematic system diagram showing a second embodiment of the first embodiment of the fuel plant for a gas turbine combustor according to the present invention. The first embodiment of the first embodiment
The same components as those of the embodiment are denoted by the same reference numerals.

In this embodiment, at least one of the outlets of the pilot fuel supply section 37 and the premixed fuel supply section 40 is provided with a honeycomb-shaped combustion catalyst 44 in a transverse direction in the catalytic combustion direction.

In this embodiment, water quality fuel is generated from the fuel reformer 29 under the same design conditions as in the first embodiment, and the reformed fuel is supplied to the pilot fuel supply unit 37 and the main fuel supply unit 43, respectively. Gas fuel from the fuel tank 26 to the premixed fuel supply unit 40
When the x concentration was measured, it was 7 ppm (in terms of 16% oxygen,
1.5 MPa), and NOx when fuel is supplied from the fuel tank 26 to each of the pilot fuel supply unit 37, the premixed fuel supply unit 40, and the main fuel supply unit 43
The concentration was significantly lower than the concentration of 20 to 30 ppm.

As described above, in this embodiment, the combustion catalyst 44
The chemical reaction of the reformed fuel containing hydrogen as the main component
Even if the high-pressure air 22 of the air compressor 20 is equivalent to 380 ° C., sufficiently stable combustion gas can be obtained, and the NOx concentration can be kept low.

FIG. 4 is a schematic system diagram showing a second embodiment of a fuel plant for a gas turbine combustor according to the present invention. The same parts as those of the first embodiment are denoted by the same reference numerals.

In this embodiment, a reformed fuel tank 45 is provided in the fuel reformer 29, and the reformed fuel is supplied to the gas turbine combustor 19 from a start-up operation to a predetermined load.

The reformed fuel stored in the reformed fuel tank 45 is
The fuel gas is generated from the fuel reformer 29 under the same design conditions as in the first embodiment, and is supplied to the gas turbine combustor 19 up to a predetermined load of, for example, 80% as shown in FIG. The gas turbine combustor 1 is switched to fuel, and air is added thereto to produce a fuel-lean premixed fuel.
9 to generate turbine driving combustion gas.

As described above, as a result of the operation using two types of fuels, the NOx concentration was 13 ppm or less over the entire operation range from the ignition of the fuel to the rated load.

In this embodiment, since the reformed fuel in the reformed fuel tank 45 is supplied to the gas turbine combustor from the fuel ignition to a predetermined load, the NOx concentration generated in a large amount during the start-up operation as in the prior art is reduced. It can be kept even lower.

FIG. 6 is a schematic system diagram showing a first embodiment of the second embodiment of the fuel plant for a gas turbine combustor according to the present invention. The first embodiment of the first embodiment
The same parts as those of the embodiment are denoted by the same reference numerals.

In the present embodiment, the reformed fuel supply system 28A for supplying the reformed fuel from the reformed fuel tank 45 to the pilot fuel supply section 37 and the pilot fuel supply section 43, respectively.
And a fuel supply system 27 of a fuel tank 26 connected to a premixed fuel supply unit 40. In this embodiment, the fuel supply system 27 of the fuel tank 26 is connected to the main fuel supply unit 43 so that either the reformed fuel or the gaseous fuel can be selectively supplied.

The fuel plant of the gas turbine combustor according to the present embodiment generates reformed fuel from the fuel reformer 29 under the same design conditions as in the first embodiment, and temporarily supplies the reformed fuel to the reformed fuel tank. 45, the reformed fuel is supplied to the pilot fuel supply unit 37 from the fuel ignition of the gas turbine combustor 19 to a predetermined load of the gas turbine 21, for example, 80% load, and the gas fuel in the fuel tank 26 is supplied to the premixed fuel. Part 4
0 to perform premix combustion, and the gas turbine 21
When the load reaches a predetermined load, the supply of the reformed fuel is stopped, and the gaseous fuel in the fuel tank 26 is supplied to the main fuel supply unit 43 to perform the premixed combustion operation. As a result, 12 ppm is obtained over the entire operation range. It was below. The ratio between the reformed fuel and the gaseous fuel is 3:97 in terms of the calorific value.

As described above, in the present embodiment, the reformed fuel tank 4
Since the reformed fuel No. 5 and the gaseous fuel in the fuel tank 26 are used together up to a predetermined load, the NOx concentration can be significantly reduced even in the low load operation range as compared with the conventional case, and the combustion gas can be stabilized. it can.

FIG. 7 is a schematic system diagram showing a second embodiment of the second embodiment of the fuel plant for a gas turbine combustor according to the present invention. The second embodiment in the first embodiment
The same components as those of the embodiment are denoted by the same reference numerals.

In this embodiment, in addition to the first embodiment in the second embodiment, a honeycomb-shaped combustion catalyst 44 is installed transversely at at least one of the outlets of the pilot fuel supply section 37 and the premixed fuel supply section 40. And a catalytic combustion system. When the fuel of the gas turbine combustor 19 is ignited, the combustion gas temperature is low, and the catalyst 44 does not react with the combustion gas. Therefore, the concentration of the reformed fuel is increased in advance, and when the combustion gas temperature reaches a predetermined value, The concentration of reformed fuel was reduced.

In this embodiment, the reformed fuel is supplied to the pilot fuel supply unit 37 from the fuel ignition to the predetermined load of the gas turbine to perform catalytic combustion, and the gaseous fuel in the fuel tank 26 is supplied to the premixed fuel supply unit 40. When the gas turbine 21 reaches a predetermined load by supplying and performing premix combustion,
Since the reformed fuel in the pilot fuel supply unit 37 is cut off and the gaseous fuel in the fuel tank 26 is supplied to the main fuel supply unit 43, the combined use of the catalytic combustion and the premixed combustion reduces the NOx concentration even in the low load operation range. It can be further reduced.

FIG. 8 is a schematic system diagram showing a third embodiment of the fuel plant for a gas turbine combustor according to the present invention.

In this embodiment, a combustor liner 47 as an inner cylinder accommodated in an outer cylinder 46 of the gas turbine combustor 19 is used.
The reforming catalyst 49 is filled along the transition piece 48 and the reforming catalyst 49 is used to change the gaseous fuel in the fuel tank 26 into reformed fuel and supply the fuel to the fuel injection unit 51 as fuel. It was done.

A part of the gaseous fuel in the fuel tank 26 is supplied to the fuel injection section 51 of the combustor liner 47, and the remaining part is mixed with steam from the steam system 33 and supplied to the reforming catalyst 49. It has become. The reformed fuel generated by the reforming catalyst 49 passes through the reformed fuel supply system 50 and the gaseous fuel in the fuel tank 26 and the fuel injector 51 of the combustor liner 47.
To generate the combustion gas 23, guide the combustion gas 23 to the gas turbine 21, and rotate the generator 24 by expansion of the gas turbine. In this case, the NOx concentration contained in the combustion gas 23 was 3 to 5 ppm (1
(Equivalent to 6% oxygen). The reforming design conditions for producing the reformed fuel are as follows: the pressure is 20 MPa, the amount of vapor mixed with the gaseous fuel is 2.5 in methane molar ratio, and the reforming reaction temperature for reforming the gaseous fuel is 1000 to 1000. 1500 ° C.

As described above, in this embodiment, the transition piece 48 is filled with the reforming catalyst 49, and the reformed fuel is generated under the high-temperature reaction temperature of the combustion gas passing through the transition piece 48, and the reformed fuel is produced. Since the combustion gas is generated by adding the gaseous fuel in the fuel tank 26 to the high quality fuel, the combustion gas can be stabilized.

FIG. 9 is a schematic system diagram showing a first example of the third embodiment of the fuel plant for a gas turbine combustor according to the present invention. The same parts as those of the third embodiment are denoted by the same reference numerals.

In this embodiment, a reforming fuel tank 45 is provided in a reforming fuel supply system 50 that connects a reforming catalyst 49 filled in a transition piece 48 and a combustor liner 47.

In the case of the present embodiment, by providing the reformed fuel tank 45 in the reformed fuel supply system 50, the reformed fuel in the reformed fuel tank 45 can be supplied to the fuel injection section 51 of the combustor liner 47. , As in startup operation, the combustion gas temperature is low,
This is effective when reformed fuel cannot be generated from the reforming catalyst 49.

FIG. 10 is a schematic system diagram showing a second example of the third embodiment of the fuel plant for a gas turbine combustor according to the present invention. The same parts as those of the third embodiment are denoted by the same reference numerals.

In this embodiment, the reforming catalyst 49 is filled along the transition piece 48 in the same manner as in the third embodiment.
The reformed fuel generated from the reforming catalyst 49 is supplied to each of the premixed fuel supply section 40 and the main fuel supply section 43 via the reformed fuel supply system 50.

In this embodiment, the gaseous fuel in the fuel tank 26 is supplied to the pilot fuel supply part 37, and the gaseous fuel in the fuel tank 26 is selectively supplied to the main fuel supply part 43. It is.

In this embodiment, the gaseous fuel in the fuel tank 26 is supplied to the pilot fuel supply unit 37 to ensure the minimum flame, while the reformed fuel of the reforming catalyst 49 is supplied to the premixed fuel supply unit 40 and the main fuel supply unit 40. Since the fuel is supplied to each of the fuel supply units 43 and the premixed combustion is performed by adding the high-pressure air 22 of the air compressor 20, the combustion gas generation is stabilized while the minimum flame of the pilot fuel supply unit 37 is secured. be able to. In the present embodiment, the ratio of the reformed fuel supplied to each of the premixed fuel supply unit 40 and the main fuel supply unit 43 is distributed to 10:90 in terms of a calorific value, and the gas turbine combustor outlet temperature is reduced to about 1400. When the NOx concentration was measured under the condition of ° C, a good result of 10 ppm (16% oxygen conversion, pressure 1.5 MPa) was obtained.

FIG. 11 is a schematic system diagram showing a third embodiment of the third embodiment of the gas turbine combustor fuel plant according to the present invention. The same parts as those of the third embodiment are denoted by the same reference numerals.

In this embodiment, a reformed fuel supply system 50 for supplying reformed fuel generated from a reforming catalyst 49 to a premixed supply section 40 and a main fuel supply section 43 is connected to a reformed fuel supply system 50. It is provided.

In the case of this embodiment, when the combustion gas temperature is low and the reformed fuel cannot be generated from the reforming catalyst 49 as in the start-up operation, the reformed fuel stored in the reformed fuel tank 45 is premixed. Since the fuel can be supplied to each of the fuel supply unit and the main fuel supply unit 43, the start-up operation time can be reduced.

FIG. 12 is a schematic system diagram showing a fourth embodiment of the third embodiment of the fuel plant for a gas turbine combustor according to the present invention. The same parts as those of the third embodiment are denoted by the same reference numerals.

In this embodiment, as in the third embodiment, the transition piece 48 is filled with the reforming catalyst 49, and the reformed fuel generated from the reforming catalyst 49 is reserved through the reformed fuel supply system 50. A honeycomb-shaped fuel catalyst 44 is provided at at least one of the outlets of the pilot fuel supply unit 37 and the premixed fuel supply unit 40, while supplying the fuel to the mixed fuel supply unit 40 and the main fuel supply unit 43, respectively.

In this embodiment, since the combustion gas generated from the fuel in the pilot fuel supply unit 37 suppresses the NOx concentration by the chemical reaction of the combustion catalyst 44, the NOx concentration can be reduced even if it is used as diffusion combustion as in the prior art. It can be greatly reduced.

FIG. 13 is a schematic system diagram showing a fifth embodiment of the third embodiment of the fuel plant for a gas turbine combustor according to the present invention. The same parts as those of the third embodiment are denoted by the same reference numerals.

This embodiment is different from the fifth embodiment in the third embodiment in that a reformed fuel tank 45 is provided in a reformed fuel supply system 50.

This embodiment is effective when the amount of the reformed fuel generated from the reforming catalyst 49 is small.

[0080]

As described above, the fuel plant for a gas turbine combustor according to the present invention is provided with a fuel reformer, and changes the fuel in the fuel tank to a reformed fuel containing hydrogen as a main component.
Since the reformed fuel is supplied to the gas turbine combustor for generating the combustion gas, the NOx concentration can be significantly suppressed by the chemical reaction of hydrogen as compared with the conventional case.

At that time, the fuel reformer was provided with a bypass system so that the reformed fuel generated from the reforming catalyst could be used as the fuel of the burner that supplies the combustion gas as a heating source to the reforming catalyst. In addition, the NOx concentration of the combustion gas generated from the burner can be suppressed.

Further, the fuel plant for a gas turbine combustor according to the present invention uses the reformed fuel generated from the fuel reformer to
A reformed fuel supply system that can supply at least one of the pilot fuel supply, premixed fuel supply, and main fuel supply of the gas turbine combustor is provided. The NOx concentration of the generated combustion gas can be suppressed, and the turbine driving can be performed from each of the premixed fuel supply unit and the main fuel supply unit while ensuring the minimum flame of the combustion gas generated from the pilot fuel supply unit. Since the combustion gas is generated, the combustion gas can be stabilized.

At this time, a reformed fuel tank is provided in the reformed fuel supply system so that the reformed fuel can be quickly supplied to each fuel supply unit, so that the starting operation or the restarting operation after the load is cut off can be shortened. Can be achieved.

Further, in the fuel plant of the gas turbine combustor according to the present invention, since the combustion catalyst is provided in the pilot fuel supply unit, NOx generated from the pilot fuel supply unit by the chemical reaction of the combustion catalyst can be reduced.

Further, in the fuel plant for a gas turbine combustor according to the present invention, the reforming catalyst is charged along the transition piece, and the fuel supplied from the fuel tank is used as the heat source by the combustion gas passing through the transition piece. Instead of reformed fuel, the reformed fuel was supplied to each of the premixed fuel supply section and the main fuel supply section to reduce NOx and stabilize combustion gas. The operation can be easily performed.

[Brief description of the drawings]

FIG. 1 is a schematic system diagram showing a first embodiment of a fuel plant for a gas turbine combustor according to the present invention.

FIG. 2 is a schematic system diagram showing a first example of the first embodiment of the fuel plant for a gas turbine combustor according to the present invention.

FIG. 3 is a schematic system diagram showing a second example of the first embodiment of the fuel plant for a gas turbine combustor according to the present invention.

FIG. 4 is a schematic system diagram showing a second embodiment of a fuel plant for a gas turbine combustor according to the present invention.

FIG. 5 is a graph showing distribution of reformed fuel and gaseous fuel supplied to a gas turbine combustor in relation to load.

FIG. 6 is a schematic system diagram showing a first example of a second embodiment of the fuel plant for a gas turbine combustor according to the present invention.

FIG. 7 is a schematic system diagram showing a second example of the second embodiment of the fuel plant for a gas turbine combustor according to the present invention.

FIG. 8 is a schematic system diagram showing a third embodiment of the fuel plant for the gas turbine combustor according to the present invention.

FIG. 9 is a schematic system diagram showing a first example of a third embodiment of the fuel plant for a gas turbine combustor according to the present invention.

FIG. 10 is a schematic system diagram showing a second example of the third embodiment of the fuel plant for a gas turbine combustor according to the present invention.

FIG. 11 is a schematic system diagram showing a third example of the third embodiment of the fuel plant for a gas turbine combustor according to the present invention.

FIG. 12 is a schematic system diagram showing a fourth example of the third embodiment of the fuel plant for a gas turbine combustor according to the present invention.

FIG. 13 is a schematic system diagram showing a fifth example of the third embodiment of the fuel plant for a gas turbine combustor according to the present invention.

FIG. 14 is a schematic system diagram showing a conventional gas turbine plant.

[Description of Signs] 1 outer cylinder 2 combustion chamber 3 combustor liner 4 pilot fuel supply section 5 mixed fuel supply section 6 main fuel supply section 7 gas turbine 8 transition piece 9 combustion gas 10 pilot fuel passage section 11 pilot nozzle 12 fuel Passage 13 Premixed fuel nozzle 14 Air compressor 15 High pressure air 16 Main fuel nozzle 17 Premix duct 18 Generator 19 Gas turbine combustor 20 Air compressor 21 Gas turbine 22 High pressure air 23 Combustion gas 24 Generator 25 Fuel plant 26 Fuel tank 27 Fuel supply system 28 Reformed fuel supply system 28A, 28B Reformed fuel supply system 29 Fuel reformer 30 Burner 31 Reforming catalyst 32 Bypass system 33 Steam system 34 Exhaust duct 35 Pilot fuel passage section 36 Pilot nozzle 37 Pilot Fuel supply unit 38 Charge passage section 39 Premixed fuel nozzle 40 Premixed fuel supply section 41 Main fuel nozzle 42 Premixed duct 43 Main fuel supply section 44 Honeycomb-shaped combustion catalyst 45 Reformed fuel tank 46 Outer cylinder 47 Combustor liner 48 Transition piece 49 Reforming catalyst 51 fuel injection unit 50 reformed fuel supply system

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁶ Identification code FI F23R 3/40 F23R 3/40 B

Claims (11)

[Claims] 1. A fuel reformer for producing a reformed fuel by adding a vapor of a vapor system to a fuel supplied from a fuel supply system of a fuel tank, and converting the reformed fuel produced from the fuel reformer into a gas. A fuel plant for a gas turbine combustor, comprising a reformed fuel supply system for supplying the gas to the turbine combustor. 2. The fuel plant according to claim 1, wherein the fuel supply system of the fuel tank is connected to burners of the gas turbine combustor and the fuel reformer, respectively. 3. The fuel plant according to claim 1, wherein the fuel reformer includes a bypass system for supplying the reformed fuel to the burner. 4. The fuel reformer according to claim 1, further comprising a reformed fuel supply system for supplying reformed fuel to at least one of a pilot fuel supply unit and a main fuel supply unit of the gas turbine combustor. 2. A fuel plant for a gas turbine combustor according to claim 1. 5. A fuel plant for a gas turbine combustor, wherein the gas turbine combustor includes a fuel catalyst at at least one outlet of a pilot fuel supply unit and a premixed fuel supply unit. 6. The gas turbine combustor fuel plant according to claim 1, wherein the reformed fuel supply system includes a reformed fuel tank. 7. The gas turbine combustion according to claim 6, wherein the reformed fuel tank includes a reformed fuel supply system in at least one of a pilot fuel supply section and a main fuel supply section of the gas turbine combustor. Vessel fuel plant. 8. A reforming catalyst for producing reformed fuel by adding vapor-based steam to fuel supplied from a fuel supply system of a fuel tank is provided in a transition piece of a gas turbine combustor, and the produced reforming catalyst is produced. A fuel plant for a gas turbine combustor, comprising a reformed fuel supply system for supplying reformed fuel to a fuel injection unit. 9. A reformed fuel supply system for supplying reformed fuel generated from a reforming catalyst provided in a transition piece of a gas turbine combustor to a fuel injection unit, wherein a reformed fuel tank is provided. The fuel plant for a gas turbine combustor according to claim 8, wherein 10. A reformed fuel supply system for supplying a reformed fuel generated from a reforming catalyst provided in a transition piece of a gas turbine combustor to a fuel injection unit includes a premixed fuel supply for the gas turbine combustor. The fuel plant for a gas turbine combustor according to claim 9, wherein the fuel plant is connected to at least one of the section and the main fuel supply section. 11. A reformed fuel supply system for supplying reformed fuel generated from a reforming catalyst provided in a transition piece of a gas turbine combustor to a fuel injection unit, wherein a reformed fuel tank is provided. Characteristic fuel plant for gas turbine combustor.