JPH11264542A - Gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To lower the NOx of combustion gas by supplying the interior of a combustion chamber with nitrogen efficiently, in the diffused combustion using the fuel for gasification high in occurrence rate of NOx of combustion gas. SOLUTION: This gas turbine combustor is provided with a jet nozzle 45 for coal gasification fuel, a nitrogen jet nozzle 42, and an air jet nozzle 49 in circular arrangement in roughly the same radial directions on the periphery side of a liquid fuel nozzle part 39, and each jet nozzle is arranged so that both neighbors of the jet nozzle 45 for coal gasification fuel may be free nitrogen jet nozzles 42 and that both neighbors of the air jet nozzle 49 may be the nitrogen jet nozzles 42. Then, each jet nozzle is arranged to jet coal gasification fuel, nitrogen, and air respectively, and they are diffused and combusted in a combustion chamber.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustor for use in a gas turbine power plant or a combined cycle power plant, and more particularly, to supplying nitrogen together with gasified fuel and air into a combustion chamber to cause local high temperature in diffusion combustion. The present invention relates to a gas turbine combustor that suppresses combustion and reduces NOx in combustion gas.

[0002]

2. Description of the Related Art A gas turbine power plant or a combined cycle power plant incorporates a plurality of gas turbine combustors, and fuel burned by the gas turbine combustors is guided to a gas turbine as combustion gas.
The gas turbine is driven. In such a gas turbine, when the gas turbine inlet temperature is increased, the gas turbine thermal efficiency is improved. Therefore, the gas turbine inlet temperature, that is, the outlet temperature of the gas turbine combustor is increased, and the power plant is made more efficient.

[0003] However, if the temperature of the combustion gas in the combustion region of the gas turbine combustor is excessively increased, the amount of generated NOx increases. Further, the combustion gas temperature is restricted by the heat resistance limit of the material of the turbine section and the combustor section.

In a gasification combined cycle power plant, coal, heavy oil, and the like are gasified by a gasification furnace, then purified by a gas purification device, and supplied to a gas turbine combustor as gasification fuel. In the case of coal gasified fuel, the fuel composition and calorific value vary depending on the type of gasifier. For example, in the case of an oxygen-blown gasifier, the fuel calorific value is about 10 to 13 MJ / NM ^3.
A medium calorie gasified fuel is refined and its fuel composition is dominated by hydrogen and carbon monoxide. The oxygen-blown gasifier uses oxygen separated from nitrogen in the air by an oxygen production plant. When the gas purification method is a dry method, ammonia is contained in the gasified fuel. Even in such a combined gasification combined cycle power plant, in order to increase the efficiency of the gas turbine, it is necessary to increase the temperature and simultaneously reduce NOx due to environmental problems.

In a conventional gas turbine combustor, NO
As a technique for suppressing the generation of x, there is known a lean premixing method in which fuel and air are mixed in advance in a fuel-lean state and burned.

However, when the lean premixing method is used for a fuel containing a large amount of hydrogen, such as gasified fuel, the combustion speed of the combustion gas exceeds the lean premixed gas ejection speed because the combustion speed of hydrogen is high. A phenomenon in which the flame flows back into the fuel nozzle, a so-called flashback phenomenon, occurs, and there is a possibility that the combustor parts may be burned.

For this reason, it is difficult to employ a gaseous fuel in a lean premix system. Therefore, it is necessary to employ a diffusion combustion method in which fuel and air are diffused and mixed in the combustion chamber and burned. However, the temperature of the combustion gas due to diffusion combustion locally becomes high near the adiabatic flame temperature. For example, the adiabatic flame temperature of coal gasified fuel containing a large amount of hydrogen and carbon monoxide is equal to or higher than the adiabatic flame temperature of LNG fuel even for medium calorie fuel. , And generate a large amount of NOx, which is equivalent to the case of diffusing and burning LNG fuel.

[0008] In recent years, studies have been made to effectively utilize nitrogen separated from oxygen in an oxygen production plant from the viewpoint of improving the efficiency of an integrated gasification combined cycle power plant and preserving the environment. That is, in a gas turbine combustor, by supplying nitrogen not directly involved in combustion into the combustion chamber, a local high-temperature portion of the combustion gas is suppressed, and the amount of NOx generated in the combustion gas is reduced. For example, the AS of 1994
ME (THE AMERICANSOCIETY OF MECHANICAL ENGINEERS
), Nitrogen is supplied from the head of a gas turbine combustor in the same manner as in the case of steam injection, and air and nitrogen are mixed and sent to a combustion chamber, where the oxygen concentration is increased. Is burned by the reduced air.

FIG. 17 is a schematic configuration diagram illustrating a gas turbine combustor of a conventional integrated coal gasification combined cycle power plant utilizing such nitrogen gas.

As shown in FIG. 17, a gas turbine combustor 1 contains a combustor liner 4 as an inner cylinder inside an outer cylinder 2 and a flow sleeve 3, and a transition piece 5 is provided downstream of the combustor liner 4. Are connected. A combustion chamber 6 is formed in the combustor liner 4.
An annular air flow path 7 is formed between the outer cylinder 2 and the flow sleeve 3 and the combustor liner 4. Air compressed by an air compressor (not shown) is guided to the head side of the combustor liner 4 through the air passage 7.

A fuel nozzle 9 supported via a head plate 8 is connected to the head side of the combustor liner 4. This fuel nozzle 9 has a liquid fuel supply port 9 at the base end side.
a, a liquid fuel spray air supply port 9b and a coal gasification fuel supply port 9c,
The liquid fuel a ₀ , the liquid fuel spray air b _0, and the coal gasified fuel c ₀ supplied from the liquid fuel spray air pipe and the coal gasified fuel pipe are introduced. Then, the liquid fuel a ₀ introduced from each of the supply ports 9a to 9c,
The liquid fuel spray air b ₀ and the coal gasified fuel c ₀ are ejected into the combustor liner 4 from the ejection ports on the nozzle tip side via the passages in the fuel nozzle 9.

In this embodiment, a nitrogen supply port 10 is provided on the outer peripheral side of the fuel nozzle 9 of the head plate 8 so that nitrogen d ₀ supplied from a nitrogen pipe (not shown) is introduced. Nitrogen d ₀ introduced from the nitrogen supply port 10
Is injected from the nitrogen outlet 10 a provided in the head plate 8 to the outer peripheral side of the tip of the fuel nozzle 9. This injected nitrogen mixes with the air e ₀ flowing in through the air flow path 7 on the outer peripheral side of the tip of the fuel nozzle 9, whereby the air e ₀
Is supplied to the combustion chamber 8 from the tip of the fuel nozzle 9 in a state where the oxygen concentration is reduced.

At the time of plant operation, the starting ignition operation is first performed by supplying the liquid fuel a ₀ , and thereafter, the operation is switched to the supply of the gasified fuel c ₀ as the main fuel, and the operation is shifted to the normal operation. At the time of this normal operation, nitrogen d ₀ is supplied, and gasified fuel c ₀ is burned with air e ₀ having a reduced oxygen concentration, thereby lowering the combustion temperature and suppressing NOx.

[0014]

However, in the above-described conventional gas turbine combustor, the air e in the air flow path 7 is merely used.
Nitrogen d ₀ to a portion of ₀ is only flows necessarily sufficient mixing has tended to flow into the combustion chamber 6 is not performed. Moreover, the air e ₀ and the nitrogen d _{0 correspond} to the fuel nozzle 9
Flows randomly into the combustion chamber 6 from the surroundings, so that the nitrogen d ₀ does not always flow into the contact portion between the gasified fuel c ₀ and the air e ₀ ejected to the central region of the combustion chamber 6. there were. That is, in the conventional structure, since there is a high probability that the gasification fuel c ₀ and air e ₀ will contact prior to mixing with the air e ₀ and nitrogen d ₀ is the air e ₀ and gasification fuel c ₀ High temperature phenomenon occurs in the local combustion area where
Although the amount of generated NOx was smaller than that in a state where no nitrogen d ₀ was supplied, a large amount of NOx was still generated in some cases.

Therefore, as a means for enhancing the NOx suppressing function under the above-described configuration, it is necessary to increase the amount of nitrogen d ₀ blown into the combustion chamber 6 to increase the mixing ratio of nitrogen d _{0 to} the air e ₀ . Conceivable.

However, simply increasing the amount of nitrogen supply to the combustion chamber 6 lowers the temperature of the flame, and although effective for reducing NOx, the amount of nitrogen supply becomes excessive and the flame temperature drops excessively. However, there is a possibility that another problem such as unstable combustion or remaining of carbon monoxide which is an unburned component in the fuel gas may occur.

On the other hand, as another alternative, it is conceivable to mix nitrogen in the gasified fuel pipe and mix nitrogen and gasified fuel in advance. However, for that purpose, it is necessary to increase the nitrogen pressure by a compressor or the like above the gasification fuel pressure, and in this case, there is a problem that the efficiency of the combined cycle plant is reduced.

The present invention has been made in view of the above circumstances, and has as its object to efficiently supply nitrogen into a combustion chamber in diffusion combustion using a gasified fuel having a high NOx generation rate. It is an object of the present invention to provide a gas turbine combustor capable of reducing NOx in combustion gas.

[0019]

According to a first aspect of the present invention, there is provided a gas turbine combustor using a gasified fuel as a main fuel and a liquid fuel as a fuel for starting ignition. A fuel nozzle selectively ejected from a fuel nozzle provided on the head side of the combustor liner into the combustor liner to diffuse and combust with combustion air, and reduce combustion temperature in a combustion zone. In supplying nitrogen, a nitrogen supply unit is provided in the fuel nozzle, and the nitrogen supply unit supplies nitrogen alone at a contact portion between the gasified fuel and air, or as a nitrogen mixture to the gasified fuel. It is configured to have a path for jetting into the combustor liner.

A gas turbine combustor according to a second aspect of the present invention is a gas turbine combustor having a fuel nozzle on a head side of a combustor liner, wherein a liquid fuel nozzle portion is provided at a center position of a front end portion of the combustion nozzle. A plurality of jet ports for jetting gasified fuel, nitrogen, and air independently into the combustor liner in an annular arrangement at substantially the same radial position on the outer peripheral side of the liquid fuel nozzle portion are provided at intervals. Are alternately arranged such that both sides of the gasified fuel outlet are nitrogen outlets and both sides of the air outlet are nitrogen outlets.

A gas turbine combustor according to a third aspect of the present invention is a gas turbine combustor having a fuel nozzle on the head side of a combustor liner, wherein a liquid fuel nozzle portion is provided at a center position of a front end portion of the fuel nozzle. A plurality of jet ports for jetting gasified fuel, nitrogen, and air alone into the combustor liner concentrically and with different diameters are provided on the outer peripheral side of the liquid fuel nozzle portion at intervals. The jet ports are arranged in the order of gasified fuel jet port, nitrogen jet port, and air jet port from the inner peripheral side.

According to a fourth aspect of the present invention, there is provided a gas turbine combustor having a fuel nozzle on a head side of a combustor liner, wherein a liquid fuel nozzle portion is provided at a center position of a tip end of the fuel nozzle. A plurality of jet ports for jetting gasified fuel, nitrogen, and air alone into the combustor liner concentrically and with different diameters are provided on the outer peripheral side of the liquid fuel nozzle portion at intervals. The jet ports are arranged in the order of a nitrogen jet port, a gasified fuel jet port, and an air jet port from the inner peripheral side.

A gas turbine combustor according to a fifth aspect of the present invention is a gas turbine combustor having a fuel nozzle on the head side of a combustor liner, wherein a liquid fuel nozzle portion is provided at a center position of a tip end of the fuel nozzle. A plurality of gasified fuel injection ports for injecting gasified fuel into the combustor liner are provided in an annular arrangement on the outer peripheral side of the liquid fuel nozzle portion, and at substantially the same radial position on the outer peripheral side of the gasified fuel injection port, A plurality of nitrogen ejection ports for ejecting nitrogen and air ejection ports for ejecting air are alternately arranged in the circumferential direction in a circular arrangement.

A gas turbine combustor according to a sixth aspect of the present invention is a gas turbine combustor having a fuel nozzle on a head side of a combustor liner, wherein a liquid fuel nozzle portion is provided at a center position of a tip end of the fuel nozzle. A plurality of nitrogen outlets for injecting nitrogen into the combustor liner are provided in an annular arrangement on the outer peripheral side of the liquid fuel nozzle portion, and gasified fuel is injected at substantially the same radial position on the outer peripheral side of the nitrogen outlet. A plurality of gasified fuel jets and air jets for jetting air are alternately arranged in a circumferential direction in an annular arrangement.

A gas turbine combustor according to a seventh aspect of the present invention is a gas turbine combustor having a fuel nozzle on a head side of a combustor liner, wherein a liquid fuel nozzle portion is provided at a center position of a tip end of the fuel nozzle. A plurality of jet ports for jetting gasified fuel, nitrogen / gasified fuel mixture, and air into the combustor liner concentrically on the outer peripheral side of the liquid fuel nozzle portion and with different diameters are arranged at intervals. These gas jets are arranged such that an outer peripheral side of the liquid fuel nozzle portion is a gasified fuel jet, and an outer peripheral side of the gasified fuel jet is a nitrogen / gasified fuel mixture jet and an air jet, and The nitrogen / gasified fuel mixture jets and air jets are arranged alternately in the circumferential direction.

A gas turbine combustor according to an eighth aspect of the present invention is the gas turbine combustor having a fuel nozzle on the head side of the combustor liner, wherein a liquid fuel nozzle portion is provided at the center of the tip of the fuel nozzle. A plurality of injection ports for respectively injecting the nitrogen / gasified fuel mixture and air into the combustor liner in an annular arrangement at substantially the same radial position on the outer peripheral side of the liquid fuel nozzle portion are provided at intervals to provide nitrogen / gasification. The fuel mixture jets and the air jets are arranged alternately in the circumferential direction.

According to a ninth aspect of the present invention, there is provided the gas turbine combustor according to any one of the first to eighth aspects, wherein a swirler is provided at each of the injection ports of the fuel nozzle.

[0028]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, embodiments of a gas turbine combustor according to the present invention will be described with reference to the accompanying drawings. The following embodiments are applied to a gas turbine combustor of a combined cycle power plant using coal gasification fuel.

First Embodiment (FIGS. 1 to 4) FIG. 1 is a schematic view showing an arrangement of a gas turbine combustor according to a first embodiment of the present invention. As shown in FIG. 1, an air compressor 14 is provided coaxially with the main shaft 13a of the gas turbine 13. The gas turbine combustor 11 includes an air compressor 14
At an intermediate position between the shaft 13a and the gas turbine 13
, Around 14 to 18, for example.

During operation of the gas turbine, the air compressor 14
The high-pressure air discharged by the driving of the gas turbine is guided to the gas turbine combustor 11, and fuel is burned in a combustion chamber 16 formed in a combustor liner 15 of the gas turbine combustor 11. The combustion gas is guided to the gas turbine 13 via the transition piece 17, and the gas turbine 13 is driven to perform work, and a generator (not shown) connected to the gas turbine 13 is rotationally driven.

FIG. 2 is an enlarged view of the configuration of the gas turbine combustor 11 according to the present embodiment.

As shown in FIG. 2, the gas turbine combustor 11 has a structure in which a combustor liner 22 is housed as an inner cylinder inside an outer cylinder 20 and a flow sleeve 21. Transition piece 1 on the side
7 is connected. The combustion chamber 1 is provided in the combustor liner 22.
6 are formed. Outer cylinder 20 and flow sleeve 2
An annular air flow path 23 is formed between 1 and the combustor liner 22.

A fuel nozzle 26 supported via a head plate 24 is connected to the head side of the combustor liner 22. The fuel nozzle 26 has a liquid fuel supply port 27, a liquid fuel spray air supply port 28, a coal gasification fuel supply port 29, and a nitrogen supply port 31 on the base end side thereof. Liquid fuel a, liquid fuel spray air b, coal gasified fuel c and nitrogen d supplied from a pipe, a coal gasified fuel pipe and a nitrogen pipe are introduced.

The liquid fuel a, the liquid fuel spray air b, and the coal gasified fuel c introduced from the respective supply ports 27 to 31
The nitrogen and the nitrogen d are ejected into the combustor liner 22 from an ejection port described later through a passage in the fuel nozzle 26. Note that, as the nitrogen d, nitrogen generated when oxygen is separated from air in an oxygen production plant of a coal gas purification device (not shown) is used. The air e compressed by the air compressor 14 is supplied to the outer peripheral side of the tip of the fuel nozzle 26 through the air flow path 23.

FIG. 3 is an enlarged sectional view of the fuel nozzle 26 shown in FIG. 2, and FIG. 4 is a right side view (end view) of FIG.

As shown in FIGS. 3 and 4, the fuel nozzle 26 has a cylindrical shape, and a liquid fuel passage 33 is provided at an axial position of the fuel nozzle 26. The liquid fuel passage 33 communicates with the liquid fuel supply port 27 on the base end side of the fuel nozzle 26 and has a liquid fuel ejection port 34 opened on the end face on the distal end side of the fuel nozzle 26.
Is in communication with The plurality of liquid fuel injection ports 34 are formed at intervals in the circumferential direction of the fuel nozzle 26, and open with an inclination gradually outward from the axis of the fuel nozzle 26. As a result, the liquid fuel a is
After flowing from the base end to the tip end, the liquid fuel is ejected radially from the liquid fuel ejection port 34 in the centrifugal direction with respect to the axis of the fuel nozzle 26.

A liquid fuel spray air passage 36 is formed in an annular shape on the outer peripheral side of the liquid fuel passage 33. The liquid fuel spray air passage 36 is also connected to the liquid spray air supply port 28 in the same manner as described above.
And a plurality of liquid fuel spray air outlets 3 opening at the end face of the fuel nozzle 26 at the tip end side thereof.
It communicates with 7. Each of the liquid fuel spray air outlets 37
Are gradually opened toward the axis of the fuel nozzle 26. A liquid fuel spray air swirler 38 is provided near the tip of the liquid fuel spray air passage 36.

Then, the liquid fuel spray air b flows from the base end of the liquid fuel spray air passage 36 to the distal end thereof, and is then given a swirling flow by the swirler 38 for liquid fuel spray air. Are spouted toward the axis of the fuel nozzle 26. As a result, the liquid fuel a jetted outward from the axis of the fuel nozzle 26
Are atomized by collision with the liquid fuel spray air b ejected toward the axis of the fuel nozzle 26 and sprayed into the combustion chamber 16. That is, the liquid fuel jet port 34 and the liquid fuel spray air jet port 37 form a liquid fuel nozzle portion 39.

On the outer peripheral side of the liquid fuel spray air passage 36, a coal gasified fuel passage 40 communicating with the coal gasified fuel supply port 27 at the base end side thereof is formed in an annular shape. A nitrogen passage 41 communicating with the nitrogen supply port 31 at the base end side thereof is formed in an annular shape on the outer peripheral side of the oxidized fuel passage 40. The vicinity of the leading end of the coal gasified fuel passage 40 is bent toward the radially enlarged side by the guide portion 40a, and the nitrogen passage 41 is formed.
Are arranged at substantially the same radial position as the tip of the. The coal gasification fuel passage 40 and the nitrogen passage 41
Are branched into a plurality of portions from the annular base end portion at their distal end portions, and the branched portions are alternately arranged along the circumferential direction of the fuel nozzle 26.

Each of the branched distal ends of the nitrogen passage 41 has a plurality of nitrogen outlets 4 opening at the same radial position around the liquid fuel nozzle portion 39 on the distal end surface of the fuel nozzle 26.
2 and a nitrogen swirler 43 is provided at each of the nitrogen passage outlets 42. This allows
The nitrogen d flows from the base end to the tip end of the nitrogen passage 41, is divided at each branch portion, is given a swirling flow by a nitrogen swirler 43, and is ejected from each nitrogen outlet 42.

Similarly, each of the branched end portions of the coal gasification fuel passage 40 has substantially the same radius as the plurality of nitrogen injection ports 42 arranged annularly around the liquid fuel nozzle portion 35 on the front end surface of the fuel nozzle 26. It communicates with a plurality of coal gasification fuel outlets 45 that open to the position, and each of the coal gasification fuel outlets 45 is also provided with a coal gasification fuel swirler 46. Thereby, coal gasification fuel c
Flows from the base end to the tip end of the coal gasified fuel passage 40, is branched at each branch portion, is given a swirling flow by a coal gasified fuel swirler 46, and is ejected from each coal gasified fuel outlet 45. It is supposed to.

The coal gasified fuel passage 40 is directed toward the front end, and is gradually narrowed in the radial direction of the fuel nozzle 26 due to the taper of the partition wall 40b on the outer peripheral side. The gas is gradually pressurized in the nozzle 26 and jetted from the coal gasified fuel jet port 45. In addition, the coal gasified fuel jet port 45 and the nitrogen jet port 42 gradually become closer to the axial center near the tip of the fuel nozzle 26 due to the taper of the outer wall 41a at the tip of the fuel nozzle 26 and the partition wall 41b with the air passage 48 described below. , So that the coal gasified fuel c and the nitrogen d are ejected toward the center of the combustor liner 22.

Further, a plurality of air passages 48 communicating with the air flow passage in the flow sleeve are provided on the outer peripheral side of the leading end portion of the coal gasification fuel passage 40. These air passages 4
Numeral 8 communicates with an air outlet 49 provided on the outer wall of the tip of the fuel nozzle. These air outlets 49 are arranged annularly around the liquid fuel nozzle portion 39 and are disposed between the nitrogen outlet 42 and the coal gasification fuel outlet 45 at substantially the same radial position. A plurality is provided. Each of the air outlets 42 is opened with an inclination toward the axis of the fuel nozzle 26, and an air swirler 50 is provided in each of the openings. Thereby, the air e
Flows from the proximal end to the distal end of the air passage 48,
The swirling flow is given by the air swirler 50 and the air
, And is ejected toward the center of the combustor liner 22.

That is, in the present embodiment, as shown in FIG. 4, a liquid fuel nozzle portion 39 is provided at the center position of the tip of the fuel nozzle 26, and the liquid fuel nozzle portion 39 is provided in an annular arrangement at substantially the same radial position. Coal gasification fuel injection port 45,
A plurality of nitrogen outlets 42 and a plurality of air outlets 49,
They are provided at intervals. Further, the respective ejection ports are alternately arranged such that the two sides of the coal gasification fuel ejection port 40 become the nitrogen ejection ports 42 and the both sides of the air ejection port 49 become the nitrogen ejection ports 42.

Next, the operation will be described.

When the gas turbine 13 is started, the liquid fuel a is sprayed from the liquid fuel nozzle 35 to burn the liquid fuel a. Thereafter, as the load of the gas turbine 13 increases, the supply amount of the coal gasified fuel c as the main fuel is increased, the supply amount of the liquid fuel is reduced, and the gas turbine 13 is shifted to the normal operation.

During normal operation of the gas turbine 13, coal gasified fuel c, nitrogen d and air e are ejected from the coal gasified fuel jet 45, nitrogen jet 42 and air jet 49 at the tip of the fuel nozzle 26, respectively. Then, diffusion combustion is performed in the combustion chamber 16. At each of the jets 42, 45, and 49, swirlers 43, 46, and 50 respectively cause the coal gasified fuel c,
A swirling flow is given to the nitrogen d and the air e to make each of the jet ports 42, 4
Since the fuel is ejected from 5, 49, the coal gasified fuel c, the nitrogen d, and the air e can be efficiently mixed.

Further, at substantially the same radial position on the outer peripheral side of the liquid fuel nozzle portion 39, the arrangement of the coal gasification fuel jet port 45, the nitrogen jet port 42 and the air jet port 49, which are provided in an annular arrangement, are alternately arranged. The coal gasified fuel c, nitrogen d, and air e are ejected from each of the outlets by setting the nitrogen adjoining port 42 on both sides of the fueled fuel outlet 45 and the nitrogen jetting port 42 on both sides of the air outlet 49. The fuel is supplied to the combustion chamber 16 in such a manner that the fuel c is wrapped by nitrogen d and the air e is wrapped by nitrogen d, that is, the coal gasified fuel c and the air e do not directly contact each other. For this reason, it is possible to prevent the local high temperature of the combustion gas generated by burning in the portion where the coal gasified fuel c and the air e are in direct contact with each other, and to reduce the NOx of the combustion gas. be able to.

As described above, according to the present embodiment, the nitrogen d is jetted directly into the combustor liner 15 through the fuel nozzle 26, and the coal gasified fuel c and the air e do not come into direct contact with each other due to the nitrogen d. In the state, the combustor liner 15
By injecting the gas into the inside, it is possible to prevent the combustion gas from being locally heated to a high temperature and to reduce the NOx of the combustion gas.

Second Embodiment (FIGS. 5 and 6) FIG. 5 is an enlarged sectional view showing a fuel nozzle of a gas turbine combustor according to a second embodiment of the present invention, and FIG.
5 is a right side view (end view) of FIG.

In the present embodiment, the arrangement of the ejection ports at the tip of the fuel nozzle 26a is different from that of the first embodiment. That is, the provision of the liquid fuel nozzle portion 39 at the center position of the tip of the fuel nozzle 26a is the same as that of the first embodiment, but the outer peripheral side of the liquid fuel nozzle portion 39 is provided with a concentric triple annular shape. The difference is that a coal gasified fuel jet port 45, a nitrogen jet port 42, and an air jet port 49 are provided sequentially from the inside.

More specifically, as shown in FIGS. 5 and 6, the fuel nozzle 26a has a cylindrical shape, and the liquid fuel passage 33, the liquid fuel Injection port 34, liquid fuel spray air passage 36
And a liquid fuel nozzle portion 39 including a liquid fuel spray air jet port 37 and the like.

First, on the outer periphery side of the liquid fuel spray air passage 36, a coal gasification fuel passage 40 communicating with the coal gasification fuel supply port 29 at the base end thereof is formed in an annular shape. The distal end of the coal gasified fuel passage 40 communicates with a plurality of coal gasified fuel jets 45 that are open at the tip end of the fuel nozzle 26a. A fuel swirler 46 is provided. As a result, the coal gasified fuel c is supplied to the coal gasified fuel swirler 46 immediately outside the liquid fuel nozzle portion 39.
To give a swirling flow, and jets from each coal gasified fuel jet port 45.

Next, on the outer peripheral side of the coal gasification fuel passage 40, a nitrogen passage 41 communicating with the nitrogen supply port 30 at the base end side is provided.
Are provided in an annular shape. The distal end side of the nitrogen passage 41 communicates with a plurality of nitrogen outlets 42 opened at the distal end surface of the fuel nozzle 26a, and each of the nitrogen outlets 42 is provided with a nitrogen swirler 43. Thereby, the nitrogen d is given a swirling flow by the nitrogen swirler 43 and is spouted from each nitrogen spout 42 into the region on the outer peripheral side of the coal gasified fuel c.

Further, a plurality of air passages 48 communicating with the air passage 23 in the flow rib 21 are provided on the outer peripheral side of the distal end portion of the nitrogen passage 41. These air passages 4
Numeral 8 communicates with a plurality of air outlets 49 provided on the outer wall of the tip end of the fuel nozzle 26a, and these air outlets 49 are provided with air swirlers 50. Thereby, the air e is given a swirling flow by the air swirler 50 and the air jet 49
From the outer peripheral region of nitrogen.

That is, in this embodiment, as shown in FIG. 6, a liquid fuel nozzle portion 39 is provided at the center of the tip of the fuel nozzle 26a, and the liquid fuel nozzle portion 39 is provided on the outer peripheral side of the liquid fuel nozzle portion 39. A plurality of coal gasification fuel outlets 45, a plurality of nitrogen outlets 42, and a plurality of air outlets 49 are sequentially provided from the inner peripheral side to the outer peripheral side in an annular arrangement having different diameters around the center 39.

The other structure is almost the same as that of the first embodiment described above. Therefore, the same reference numerals as in FIGS. 3 and 4 are used in FIGS. 5 and 6 and the description is omitted.

According to the present embodiment having the above-described structure, the swirlers 43, 46, and 5 are respectively provided at the ejection ports 42, 45, and 49.
By setting 0, a swirl flow is given to the coal gasified fuel c, the nitrogen d and the air e, so that the coal gasified fuel c, the nitrogen d and the air e can be efficiently mixed.

In the case of this embodiment, the coal gasified fuel outlet 45, the nitrogen outlet 42, and the air outlet 49 are arranged concentrically on the outer peripheral side of the liquid fuel nozzle portion 39 and with different diameters from the inner side. Since the ejection ports are arranged in each case, nitrogen d is sandwiched between the coal gasified fuel c ejected to the inner peripheral area in the combustion chamber 16 and the air e ejected to the outer peripheral area in the combustion chamber 16. Supplied in the form. That is, the coal gasified fuel c and the air e are supplied to the combustion chamber 16 in a state where the coal gasified fuel c does not directly contact the air e.
Direct contact with the combustion gas can be suppressed, thereby preventing a local high temperature of the combustion gas and reducing NOx of the combustion gas.

As described above, also in the present embodiment, nitrogen d is directly supplied to the combustor liner 15 through the fuel nozzle 26a.
And this nitrogen d causes coal gasification fuel c
Since the fuel gas is ejected into the combustion chamber 16 in a state where the fuel gas and the air e do not directly contact each other, it is possible to prevent a local increase in the temperature of the combustion gas and reduce the NOx of the combustion gas.

Third Embodiment (FIGS. 7 and 8) FIG. 7 is an enlarged sectional view showing a fuel nozzle of a gas turbine combustor according to a third embodiment of the present invention, and FIG.
5 is a right side view (end view) of FIG.

The fuel nozzle according to the present embodiment has a configuration in which NOx can be reduced while ensuring combustion stability in consideration of using a coal gasified fuel having relatively low flammability.

That is, the raw coal used in the coal gasifier has different characteristics depending on the place of production and the like, and the difference in the characteristics causes a difference in the combustibility of the coal gasified fuel. When a highly combustible coal gasified fuel is used, stable diffusion combustion is performed.
It is only necessary to reduce the amount of Ox generated, and from the viewpoint of suppressing direct contact between fuel and air, nitrogen may be supplied over the entire contact area.

However, when a coal gasified fuel having low flammability is used, if the contact with air is insufficient, combustion may become unstable or carbon monoxide may remain as an unburned component. There is. For this reason, the fuel nozzle that jets low-combustibility coal gasified fuel must maintain a jetting function that allows sufficient contact between the fuel and air, and also use nitrogen gas to prevent the occurrence of local high-temperature zones. It is desired to supply

Therefore, in this embodiment, the fuel nozzle 26b
A liquid fuel nozzle portion 39 is provided at the center of the tip of the liquid fuel nozzle portion 39, and is arranged in a concentric triple annular arrangement on the outer peripheral side of the liquid fuel nozzle portion 39. The configuration is such that a jet port 45 and an air jet port 49 are provided.

That is, also in this embodiment, the fuel nozzle 26
b has a cylindrical shape, and the liquid fuel passage 33, the liquid fuel jet port 34, the liquid fuel spray air path 36, the liquid fuel spray air jet port 37 and the like are provided at the axial center position of the fuel nozzle 26b as in the above embodiments. Is formed.

Immediately outside the liquid fuel spray air passage 36, an annular nitrogen passage 41 communicating with the nitrogen supply port 30 at the base end thereof is provided. The distal end side of the nitrogen passage 41 communicates with a plurality of nitrogen outlets 42 opened at the distal end face of the fuel nozzle 26b.
Are provided with a nitrogen swirler 43. Thereby, the nitrogen d is given a swirling flow by the nitrogen swirler 43 immediately on the outer peripheral side of the liquid fuel nozzle portion 39, and each nitrogen jet 4
It is to be spouted from 2.

On the outer peripheral side of the nitrogen passage 41, a coal gasification fuel passage 40 communicating with the coal gasification fuel supply port 29 at the base end thereof is formed in an annular shape. The distal end of the coal gasified fuel passage 40 communicates with a plurality of coal gasified fuel jets 45 that are open at the tip end of the fuel nozzle 26a. A fuel swirler 46 is provided. Thus, the coal gasified fuel c is given a swirling flow by the swirler 46 for the coal gasified fuel, and is spouted from the respective coal gasified fuel spouts 45 into the region on the outer peripheral side of the nitrogen d.

Further, a plurality of air passages 48 communicating with the air passages 23 in the flow-through rib 21 are provided on the outer peripheral side of the leading end portion of the coal gasification fuel passage 40. These air passages 48 communicate with a plurality of air outlets 49 provided on the outer wall of the tip of the fuel nozzle 26b.
9 is provided with an air swirler 50. Thereby, the air e is given a swirling flow by the air swirler 50 and is ejected from the air ejection port 49 to a region on the outer peripheral side of the coal gasified fuel c.

That is, in this embodiment, as shown in FIG. 6, a liquid fuel nozzle portion 39 is provided at the center of the tip of the fuel nozzle 26b, and the liquid fuel nozzle portion 39 is provided on the outer peripheral side of the liquid fuel nozzle portion 39. A plurality of nitrogen outlets 42, coal gasification fuel outlets 45, and air outlets 49 are sequentially provided from the inner peripheral side to the outer peripheral side in an annular arrangement with different diameters centering on 39.

Since other structures are almost the same as those in the first embodiment, the same reference numerals as in FIGS. 3 and 4 are used in FIGS. 7 and 8, and the description is omitted.

According to this embodiment having such a structure,
In each of the jets 42, 45, 49, swirlers 43, 4
Since the swirling flow is given by 6,50, the coal gasified fuel c, the nitrogen d, and the air e can be efficiently mixed.

In this case, the nitrogen jet port 42, the coal gasified fuel jet port 45, and the air jet port 49 are arranged on the tip end face of the fuel nozzle 26b in order from the inner side to the outer side, so that the inside of the combustion chamber 16 is formed. Gasification fuel c in the area on the outer peripheral side of
And the air e come into direct contact with the combustion chamber 1
Nitrogen d ejected from the inner peripheral side of 6 mixes with coal gas c and air a.

Therefore, in this embodiment, even when the supplied coal gasified fuel c has low flammability, the coal gasified fuel c can maintain stable combustion by direct contact with the air e, and the combustion gas The concentration of carbon monoxide, which is an unburned component therein, can be reduced, and the temperature of the combustion gas can be efficiently reduced by the action of nitrogen d diffusing from the inside of the fuel nozzle 26b toward the combustion region, whereby
NOx reduction can be sufficiently achieved.

Fourth Embodiment (FIGS. 9 and 10) FIG. 9 is an enlarged sectional view showing a fuel nozzle of a gas turbine combustor according to a fourth embodiment of the present invention, and FIG. 10 is a right side view of FIG. It is a figure (end view).

Similar to the third embodiment of the present embodiment, the fuel nozzle 26c has a structure suitable for using a coal gasified fuel having low flammability. However, in the present embodiment, the third
Unlike the embodiment, a coal gasified fuel jet 45, a nitrogen jet 42, and an air jet 42 are provided on the outer peripheral side of the liquid fuel nozzle portion 39 at the center position of the fuel nozzle 26c in a concentric double annular arrangement. It is provided.

That is, in this embodiment, FIG. 9 and FIG.
As shown in FIG. 0, the fuel nozzle 26c has a cylindrical shape, and the liquid fuel passage 3 provided at the center of the fuel nozzle 26c.
3, a liquid fuel injection port 34 at the tip end of the fuel nozzle 26c communicating therewith, a liquid fuel spray air passage 36 provided on the outer periphery of the liquid fuel passage 33, and a fuel nozzle 2 communicating therewith
A liquid fuel nozzle portion 39 is formed by the liquid fuel spray air outlet 37 at the tip of 6c.

On the outer peripheral side of the liquid fuel atomizing air passage 36, a coal gasification fuel passage 40 communicating with the coal gasification fuel supply port 29 at the base end side thereof is provided in an annular shape. The distal end side of the nozzle 40 communicates with a plurality of coal gasified fuel jet ports 45 which are open at the distal end face of the fuel nozzle 26c. Each of the coal gasified fuel injection ports 45 is provided with a coal gasified fuel swirler 46.

On the outer peripheral side of the coal gasification fuel passage 40, a plurality of nitrogen passages 41 and air passages 48 are provided alternately in the circumferential direction in an annular arrangement. The proximal end of the nitrogen passage 41 communicates with the nitrogen supply port 30, and the distal end communicates with the nitrogen outlet 42. A nitrogen swirler 43 is provided at the nitrogen outlet 42. Further, the proximal end side of the air passage 48 is
The distal end side is in communication with the air outlet 49. The air outlet 49 is provided with an air swirler 50.

The nitrogen passage 41 and the air passage 48 are inclined such that the leading ends thereof are gradually directed toward the center of the fuel nozzle 26c.
6 squirt toward the center.

Since other structures are almost the same as those of the first embodiment, the same reference numerals as in FIGS. 3 and 4 are used in FIGS. 9 and 10, and the description is omitted.

In the present embodiment having such a configuration, during normal operation of the gas turbine 13, the coal gasification fuel injection port 45, the nitrogen injection port 42, and the air injection port 49 at the tip of the fuel nozzle 26c are used to perform coal gasification. Fuel c, nitrogen d, and air e are ejected and diffused and burned in the combustion chamber 16. Swirler 4 at each of the jets 45, 42, 49
Since the swirling flow is given by 6, 43, and 50, the coal gasified fuel c, the nitrogen d, and the air e can be efficiently mixed.

Further, the coal gasified fuel c is jetted from the coal gasified fuel jet port 45 into the region inside the combustion chamber 16, and the nitrogen d and the air e are supplied to the nitrogen jet port 42 and the air jet port 4.
9, the fuel gas is ejected toward the center of the combustion chamber 16 in an outer region of the coal gasified fuel c in a state of being adjacent to each other in the circumferential direction. Therefore, while the nitrogen d and the air e are in a good mixing state in the outer region in the combustion chamber 16 in the circumferential direction, the coal gasified fuel c in the inner region in the middle of the mixing in the radial direction.
Therefore, when the coal gasified fuel c has low flammability, the coal gasified fuel c is sufficiently brought into contact with the air e, and the cooling effect by the nitrogen d is given as a whole.

Therefore, according to the present embodiment, when the coal gasified fuel c having low flammability is used, the combustion of the combustion gas is stabilized by the direct contact between the coal gasified fuel c and the air e, and the monoxide of the combustion gas is monoxide. At the same time as the carbon concentration can be reduced, by directly supplying nitrogen d from the fuel nozzle 26c into the combustion chamber 16, the temperature of the combustion gas can be reduced, and the NOx of the combustion gas can be reduced.

Fifth Embodiment (FIGS. 11 and 12) FIG. 11 is an enlarged sectional view showing a fuel nozzle of a gas turbine combustor according to this embodiment. FIG. 12 is a right side view (end view) of FIG. ).

In the present embodiment, the fourth embodiment
This is a configuration in which the coal gasification fuel outlet 45 and the nitrogen outlet 42 are interchanged.

That is, as shown in FIGS. 11 and 12, in the present embodiment, a plurality of nitrogen outlets 42 are annularly provided around the liquid fuel nozzle 39 on the outer peripheral side of the liquid fuel nozzle 39. This nitrogen jet 4
2 and at substantially the same radial position around the fuel nozzle 39, the coal gasified fuel outlet 45 and the air outlet 4
9 are provided in a ring shape. The coal gasified fuel jets 45 and the air jets 49 are arranged alternately in the circumferential direction.

Since the other structure is almost the same as that of the fourth embodiment, the same reference numerals as in FIGS. 9 and 10 are used in FIGS. 11 and 12, and the description is omitted.

In this embodiment having such a configuration,
During normal operation of the gas turbine 13, the coal gasified fuel c, nitrogen d and air e are supplied from the nitrogen jet 42, the coal gasified fuel jet 45 and the air jet 49, respectively, to the swirler 4.
The swirling flow is given by 3, 46, and 50, and is injected into the combustion chamber 16, thereby efficiently mixing the coal gasified fuel c, the nitrogen d, and the air e as in the fourth embodiment. Can be.

Further, by ejecting the coal gasified fuel c and the air e from the coal gasified fuel jet port 45 and the air jet port 49 to the outer peripheral area in the combustion chamber 16 outside the liquid fuel nozzle portion 39, Coal gasification fuel c in that area
And the air e are brought into direct contact, so that even if the coal gasified fuel c used has low flammability, the combustion can be sufficiently stabilized and the unburned components in the combustion gas Can be reduced.

Further, while the coal gasified fuel c and the air e are ejected toward the center of the combustion chamber 16,
6, nitrogen d is spouted from the nitrogen spouting port 42 into the inner peripheral area, and a cooling function by the nitrogen d can be sufficiently exerted by mixing these to lower the temperature of the combustion gas.
It is possible to effectively reduce the NOx of the combustion gas.

Sixth Embodiment (FIGS. 13 and 14) FIG. 13 is an enlarged sectional view showing a fuel nozzle of a gas turbine combustor according to this embodiment, and FIG. 14 is a right sectional view (end view) of FIG. ).

The present embodiment employs a configuration in which nitrogen d and coal gasified fuel c are mixed in a fuel nozzle 26e and injected into the combustion chamber 16 as a nitrogen / coal gasified fuel mixture f. .

That is, in this embodiment, as shown in FIGS. 13 and 14, the fuel nozzle 26e has a cylindrical shape, and the liquid fuel passage 3 is located at the axial position of the fuel nozzle 26e.
3 are provided. The liquid fuel passage 33 communicates with the liquid fuel supply port 27 at the base end side of the fuel nozzle 26e, as in the above-described embodiments.
At the front end side of e, it communicates with a liquid fuel outlet 34 opened at the end face. A liquid fuel spray air passage 36 is formed in an annular shape on the outer periphery of the liquid fuel passage 33, and the liquid fuel spray air passage 36 is also provided at the base end side of the fuel nozzle 26e in the same manner as in the above-described embodiments. A liquid fuel spray air swirler communicates with a plurality of liquid fuel spray air outlets 37 which are connected to the port 28 and which are open at the front end side of the fuel nozzle 26e. 38 are provided. As a result, the liquid fuel jet port 34 and the liquid fuel spray air jet port 37 form a liquid fuel nozzle portion 39.

On the outer peripheral side of the liquid fuel spray air passage 36,
A coal gasification fuel passage 40 communicating with the coal gasification fuel supply port 29 at the base end thereof is provided in an annular shape, and a distal end side of the coal gasification fuel passage 40 has a plurality of coal gasification fuel injection ports 4.
It is in communication with 5. Further, the coal gasified fuel injection port 45
Are provided with a swirler 46 for coal gasified fuel, respectively, to give a swirling flow to the coal gasified fuel c.

On the outer peripheral side of the coal gasification fuel passage 40, an annular nitrogen passage 41 communicating with the nitrogen supply port 30 at the base end thereof is provided. A coal gasified fuel mixing jetting section 52 for jetting coal gasified fuel e from the coal gasified fuel passage 40 is provided at a position halfway toward the front end side of the nitrogen passage 41. This coal gasification fuel mixing jetting section 52
Has a plurality of communication holes 5 communicating with the coal gasification fuel passage 40.
2a and the ejection holes 52b projecting from the periphery of the communication holes 52a toward the nitrogen passage 41 in the direction of passage in the nitrogen passage 41.
Is opened, and a part of the coal gasified fuel c is ejected into the nitrogen passage 41 to mix the nitrogen d with a part of the coal gasified fuel c.

The leading end side of the nitrogen passage 41 communicates with a plurality of nitrogen / coal gasified fuel mixture jets 51 which are open at the tip end of the fuel nozzle 26c. Is provided with a swirler 53 for a nitrogen / coal gasified fuel mixture, which gives a swirling flow to the jetted nitrogen / coal gasified fuel mixture f. Note that the nitrogen / coal gasified fuel injection port 51 is open with a tendency toward the center of the combustion chamber 16.

As a result, the nitrogen d flows from the base end to the tip end of the nitrogen passage 41 and mixes with a part of the coal gasified fuel c in the nitrogen passage 41 to form a nitrogen / coal gasified fuel mixture f. And a swirler 53 for a mixture of nitrogen and coal gasified fuel
After the swirling flow is given, the gas is jetted from the nitrogen / coal gasified fuel jet port 51 toward the center side of the combustion chamber 16.

Further, a plurality of air passages 48 communicating with the air flow passage 23 at the base end thereof are provided alternately at the same radial position as the nitrogen passage 41 on the outer peripheral side of the distal end portion of the coal gasification fuel passage 40. The tip of each air passage 48 is connected to the fuel nozzle 2.
6e communicates with an air outlet 49 that opens at the tip end surface. An air swirler 50 is provided at each of the air outlets 49, and the swirler 50 gives a swirling flow to the air e. The air outlet 49 opens with an inclination toward the axial center of the fuel nozzle 26 e, whereby the air e is blown out toward the center of the combustion chamber 16.

In this embodiment having such a configuration, the fuel switching from the start of the gas turbine 13 to the normal operation is performed in the same manner as in each of the above embodiments, and during normal operation, the coal gasified fuel c is supplied. In this case, the coal gasified fuel c is ejected from the coal gasified fuel outlet 45 through the coal gasified fuel passage 40 to an inner peripheral area in the combustion chamber 16, and a part of the gas is discharged. Mixing spout 52
Flows into the nitrogen passage 41 through the passage and mixes with the nitrogen d supplied to the nitrogen passage 41 to form a nitrogen-coal gasified fuel mixture f
As a result, the gas is jetted from the nitrogen / coal gasified fuel mixture jet port 51 toward the center in the outer peripheral area in the combustion chamber 16. In this case, the air e is ejected from the air ejection port 49 into the combustion chamber 16 through the air passage 48 to the same outer region as the air-coal gasified fuel mixture f.

As a result, the air e first merges with the nitrogen-coal gasified fuel mixture f in the combustion chamber 16, but in this case, nitrogen d is mixed in advance with the coal gasified fuel c in the fuel nozzle 26e. Therefore, direct contact between the coal gasified fuel c and the air e is effectively suppressed. The coal gasified fuel c ejected from the coal gasified fuel ejection port 45 is supplied to the combustion chamber 1.
6, a part of the air e comes into contact with the independently jetted coal gasified fuel c.

Therefore, according to the present embodiment, the coal gasified fuel c, the nitrogen d, and the air e can be efficiently mixed, the temperature of the combustion gas can be reduced, and the NOx of the combustion gas can be reduced. Since a part of the coal gasified fuel c is supplied alone, the combustion is stabilized, and the concentration of carbon monoxide, which is an unburned component of the combustion gas, can be reduced.

As described above, according to the present embodiment, since the nitrogen d and a part of the coal gasified fuel c are mixed in the nitrogen passage 41, the nitrogen d and a part of the coal gasified fuel c are efficiently mixed. Can be effectively mixed, thereby effectively lowering the combustion temperature of the combustion gas and reducing NOx of the combustion gas.

Further, according to the present embodiment, a part of the coal gasified fuel c is directly supplied to the combustion chamber 16, so that the combustion is stabilized and the concentration of carbon monoxide which is an unburned component of the combustion gas can be reduced. .

Seventh Embodiment (FIGS. 15 and 16) FIG. 15 is an enlarged sectional view showing a fuel nozzle of a gas turbine combustor according to this embodiment, and FIG. 16 is a right side view (end view) of FIG. ).

The sixth embodiment is characterized in that nitrogen d and all of the coal gasified fuel c are mixed in the nitrogen passage 41.
Different from the embodiment. Parts other than the fuel nozzle 26f are not different from those of the first embodiment, so that illustration and description are omitted.

In this embodiment, as shown in FIGS. 15 and 16, the fuel nozzle 26f has a cylindrical shape, and a liquid fuel passage 33 is provided at an axial position of the fuel nozzle 26f. The liquid fuel passage 33 communicates with the liquid fuel supply port 27 on the base end side of the fuel nozzle 26f and the liquid fuel outlet 34 opened on the end face on the distal end side of the fuel nozzle 26f, as in the above embodiments. Communicating. A liquid fuel spray air passage 36 is formed in an annular shape on the outer periphery of the liquid fuel passage 33, and the liquid fuel spray air passage 36 is also provided at the base end side of the fuel nozzle 26f in the same manner as in the above-described embodiments. A liquid fuel spray air swirler is provided near the distal end of the liquid fuel spray air passage 36 and communicates with a plurality of liquid fuel spray air outlets 37 opened at the end of the fuel nozzle 26f. 38 are provided. As a result, the liquid fuel ejection port 34 and the liquid fuel spray air ejection port 37
And a liquid fuel nozzle 39.

At the outer peripheral side of the liquid fuel spray air passage 36 and at the base end side of the fuel nozzle 26f, a coal gasified fuel supply port 2 is provided.
A coal gasification fuel passage 40 communicating with the base 9 at the base end side thereof is provided in an annular shape. At the outer peripheral side of the liquid fuel spray air passage 36 and at the tip side of the fuel nozzle 26f, the nitrogen supply port 3
A nitrogen passage 41 that communicates with the base 0 at the base end side thereof is provided in an annular shape. The leading end of the coal gasified fuel passage 40 and the base end of the nitrogen passage 41 communicate with each other through a coal gasified fuel mixing jetting section 52. The coal gasified fuel mixing spout 52 is provided with a coal gasified fuel swirler 46. As a result, the coal gasified fuel c is transferred to the coal gasified fuel passage 40.
Flows from the base end to the tip end, and after being given a swirling flow by the swirler 46 for coal gasification fuel, is jetted to the base end of the nitrogen passage 41 to mix with nitrogen d.

The annular nitrogen passage 41 at the base end side is branched into a plurality at the tip end side, and each of the branched portions communicates with the nitrogen / coal gasified fuel mixture gas injection port 51. Each of the nitrogen / coal gasified fuel mixture jet ports 51 is provided with a nitrogen coal gasified fuel swirler 53. In addition, the nitrogen passage 41 has a narrow passage at the front end side, so that the pressure of the nitrogen-coal gasified fuel mixture f is increased. Thereby, the nitrogen d is supplied to the coal gasified fuel c at the base end of the nitrogen passage 41.
Is to be mixed with. The nitrogen-coal gasified fuel mixture f flows in the nitrogen passage 41 from the base end to the front end, branches off at the front end of the nitrogen passage 41, and is pressurized.
After the swirling flow is given by the swirler 53 for the nitrogen / coal gasified fuel mixture, it is ejected from the nitrogen / coal gasified fuel mixture spout 51.

A plurality of air passages 48 are provided on the outer peripheral side of the distal end of the liquid fuel spray air passage 36 at the base end side thereof. The air passage 48 communicates with the air outlet 49 on the tip end side. This air outlet 49
Are gradually opened toward the axis of the fuel nozzle 26f. Further, air swirlers 50 are provided at the air outlets 49, respectively, to give a swirling flow to the air. Further, the air passage 48 has a narrow passage at the front end side, and pressurizes air. As a result, the air e flows from the proximal end to the distal end of the air passage 48, rises in pressure at the distal end of the air passage 48, is given a swirling flow by the air swirler 50, and is ejected from the air outlet 49. It is supposed to be.

In this embodiment, when the gas turbine 13 is started, the liquid fuel a is sprayed from the liquid fuel nozzle 39 and the liquid fuel a is burned. As the load on the gas turbine 13 increases, coal gasified fuel c as the main fuel
And the supply amount of the liquid fuel a is reduced, and the gas turbine 13 is shifted to the normal operation.

During normal operation of the gas turbine 13, a nitrogen / coal gasified fuel mixture f and air e are ejected from the nitrogen / coal gasified fuel mixture jet 51 and the air jet 49 at the tip of the fuel nozzle 26f, respectively. Then, diffusion combustion is performed in the combustion chamber 16.

Since the nitrogen / coal gasified fuel mixture gas jet 51 and the air jet 49 are provided with a nitrogen / coal gasified fuel mixture swirler 53 and an air swirler 50, respectively.
Nitrogen d, coal gasification fuel c and air e can be efficiently mixed.

Further, a coal gasified fuel mixing spout 52 is provided in the nitrogen passage 41, and the coal gasified fuel c is spouted from the coal gasified fuel mixing spout 52 and
Since nitrogen d and coal gasification fuel c are mixed in 1,
Nitrogen d and coal gasified fuel c can be efficiently mixed. Further, the nitrogen / coal gasified fuel mixture f is jetted from the nitrogen / coal gasified fuel mixture jet 51,
Since it is supplied into the combustion chamber 16, regardless of the degree of mixing of the coal gasified fuel c, nitrogen d, and air e in the combustion chamber 16,
The temperature of the combustion gas can be reduced, and the NOx of the combustion gas can be reduced.

Further, a nitrogen / coal gasified fuel gas mixture jet 51 and an air jet 49 are provided in an annular arrangement at substantially the same radial position on the outer peripheral side of the liquid fuel nozzle portion 39, and these nitrogen / coal gasified fuel are provided. Mixture jet 51 and air jet 4
9 are alternately arranged in the circumferential direction, and the nitrogen / coal gasified fuel mixture f and the air e are jetted from the jet ports 51 and 49, so that the coal gasified fuel c, the nitrogen d and the air e are efficiently mixed. Can be done.

As described above, according to the present embodiment, the coal gasified fuel c and the nitrogen d are mixed in the nitrogen passage 41 and supplied to the combustion chamber 16. It is possible to lower the temperature of the combustion gas and reduce the NOx of the combustion gas irrespective of the degree of mixing of the converted fuel c, the nitrogen d, and the air e.

In the above embodiments, the case where coal gasified fuel is used has been described. However, the present invention can be similarly applied to the case where another gasified fuel such as heavy oil is used.

[0118]

As described above, according to the gas turbine combustor of the present invention, nitrogen is efficiently supplied into the combustion chamber in diffusion combustion using gasified fuel having a high NOx generation rate. Thus, similarly to the case where nitrogen is completely mixed with fuel or air, the local high temperature portion of the combustion gas is suppressed, and the NOx of the combustion gas can be reduced.

[Brief description of the drawings]

FIG. 1 is a schematic configuration diagram showing a first embodiment of a gas turbine combustor according to the present invention.

FIG. 2 is an enlarged sectional view showing the gas turbine combustor shown in FIG. 1;

FIG. 3 is an enlarged sectional view showing the fuel nozzle shown in FIG. 2;

FIG. 4 is a right side view (end view) of FIG. 3;

FIG. 5 is a cross-sectional view showing a second embodiment of a gas turbine combustor according to the present invention, in which a fuel nozzle is enlarged.

FIG. 6 is a right side view (end view) of FIG. 5;

FIG. 7 shows a third embodiment of the gas turbine combustor according to the present invention, and is an enlarged sectional view showing a fuel nozzle.

FIG. 8 is a right side view (end view) of FIG. 7;

FIG. 9 is a sectional view showing a fourth embodiment of the gas turbine combustor according to the present invention, in which a fuel nozzle is enlarged.

FIG. 10 is a right side view (end view) of FIG. 9;

FIG. 11 shows a third embodiment of the gas turbine combustor according to the present invention, and is an enlarged sectional view showing a fuel nozzle.

FIG. 12 is a right side view (end view) of FIG. 11;

FIG. 13 is a sectional view showing a sixth embodiment of the gas turbine combustor according to the present invention, in which a fuel nozzle is enlarged.

FIG. 14 is a right side view (end view) of FIG. 13;

FIG. 15 is a cross-sectional view showing a seventh embodiment of a gas turbine combustor according to the present invention, in which a fuel nozzle is enlarged.

FIG. 16 is a right side view (end view) of FIG. 15;

FIG. 17 is a sectional view showing a conventional gas turbine combustor.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Gas turbine combustor 2 Outer cylinder 3 Flow sleeve 4 Combustor liner 5 Transition piece 7 Air flow path 8 Head plate 9 Fuel nozzle 10 Nitrogen supply port 11 Gas turbine combustor 13 Gas turbine 13a Main shaft 14 Air compressor 15 Combustor liner Reference Signs List 16 combustion chamber 17 transition piece 20 outer cylinder 21 flow sleeve 22 combustor liner 23 air passage 24 head plate 26 fuel nozzle 27 liquid fuel supply port 28 liquid fuel spray air supply port 29 coal gasification fuel supply port 30 nitrogen supply port 33 Liquid fuel passage 34 Liquid fuel jet port 36 Expected fuel spray air path 37 Obtained fuel spray air jet port 38 Swirler for liquid fuel spray air 39 Liquid fuel nozzle section 40 Coal gasification fuel path 40a Guide section 40b Partition wall 41a Tip outer wall 41b Partition wall 4 Nitrogen passage 42 Nitrogen injection port 43 Nitrogen swirler 45 Coal gasification fuel injection port 46 Coal gasification fuel swirler 48 Air passage 49 Air injection port 50 Air swirler 51 Nitrogen coal gasification fuel mixture gas injection port 52 Coal gasification fuel mixture Spout part 52a Communication hole 52b Spout hole 52c Nozzle part 53 Swirler for nitrogen / coal gasified fuel mixture a Liquid fuel b Liquid fuel spray air c Coal gasified fuel d Nitrogen e Air f Nitrogen / Coal gasified fuel mixture

────────────────────────────────────────────────── ─── Continued on the front page (51) Int.Cl. ⁶ Identification symbol FI // F02C 3/28 F02C 3/28 7/22 7/22 A (72) Inventor Yasunori Iwai Suehiro-cho, Tsurumi-ku, Yokohama-shi, Kanagawa 2-4-4 Toshiba Keihin Works Co., Ltd. (72) Inventor Akihiro Onoda 2-4 Suehirocho, Tsurumi-ku, Yokohama-shi, Kanagawa Prefecture Toshiba Keihin Works

Claims (9)

[Claims] 1. A gas turbine combustor using a gasified fuel as a main fuel and a liquid fuel as an ignition start-up fuel, wherein each of the fuels is selectively provided from a fuel nozzle provided on a head side of a combustor liner. Injecting into the combustor liner and diffusing and burning with combustion air, and supplying nitrogen to the combustion zone for lowering the combustion temperature,
A nitrogen supply unit is provided in the fuel nozzle, and the nitrogen supply unit injects into the combustor liner the nitrogen alone at the contact portion between the gasified fuel and air or as a nitrogen mixture to the gasified fuel. A gas turbine combustor having a configuration having a path. 2. A gas turbine combustor having a fuel nozzle on a head side of a combustor liner, wherein a liquid fuel nozzle portion is provided at a center position of a tip portion of the combustion nozzle, and an outer peripheral side of the liquid fuel nozzle portion is provided. A plurality of injection ports for individually jetting gasified fuel, nitrogen and air into the combustor liner in an annular arrangement at substantially the same radial position are provided at intervals, and these injection ports are alternately provided with gasified fuel injection ports. A gas turbine combustor characterized in that both sides of the gas turbine combustor are arranged as nitrogen outlets, and both sides of the air outlet are arranged as nitrogen outlets. 3. A gas turbine combustor having a fuel nozzle on a head side of a combustor liner, wherein a liquid fuel nozzle portion is provided at a center position of a front end portion of the fuel nozzle, and an outer peripheral side of the liquid fuel nozzle portion is provided. A plurality of jet ports for jetting gasified fuel, nitrogen and air independently into the combustor liner concentrically and with different diameters are provided at intervals, and these jet ports are provided with gas from the inner peripheral side. Fuel jet,
A gas turbine combustor, wherein a nitrogen jet port and an air jet port are arranged in this order. 4. A gas turbine combustor having a fuel nozzle on a head side of a combustor liner, a liquid fuel nozzle portion is provided at a center position of a tip portion of the fuel nozzle, and a liquid fuel nozzle portion is provided on an outer peripheral side of the liquid fuel nozzle portion. A plurality of jet ports for jetting gasified fuel, nitrogen and air alone concentrically and with different diameters into the combustor liner are provided at intervals, and these jet ports are provided with nitrogen from the inner peripheral side. A gas turbine combustor characterized in that an injection port, a gasified fuel injection port, and an air injection port are arranged in this order. 5. A gas turbine combustor having a fuel nozzle on a head side of a combustor liner, a liquid fuel nozzle portion is provided at a center position of a front end portion of the fuel nozzle, and an outer peripheral side of the liquid fuel nozzle portion is provided. A plurality of gasified fuel jets for jetting gasified fuel into the combustor liner are provided in an annular arrangement, and a nitrogen jet for jetting nitrogen and air are provided at substantially the same radial position on the outer peripheral side of the gasified fuel jet. A gas turbine combustor characterized in that a plurality of air outlets for discharging air are arranged alternately in a circumferential direction in an annular arrangement. 6. A gas turbine combustor provided with a fuel nozzle on a head side of a combustor liner, a liquid fuel nozzle portion is provided at a center position of a tip portion of the fuel nozzle, and an outer peripheral side of the liquid fuel nozzle portion is provided. A plurality of nitrogen jets for jetting nitrogen into the combustor liner are provided in an annular arrangement, and a gasified fuel jet for jetting gasified fuel and air are jetted at substantially the same radial position on the outer peripheral side of the nitrogen jet. A gas turbine combustor characterized in that a plurality of air outlets are alternately arranged in a circumferential direction in an annular arrangement. 7. A gas turbine combustor provided with a fuel nozzle on a head side of a combustor liner, a liquid fuel nozzle portion is provided at a center position of a tip portion of the fuel nozzle, and an outer peripheral side of the liquid fuel nozzle portion is provided. A plurality of nozzles are provided concentrically and with different diameters for injecting gasified fuel, nitrogen-gasified fuel mixture and air into the combustor liner at intervals, and these nozzles are provided with the liquid The outer peripheral side of the fuel nozzle portion is a gasified fuel jet port, the outer peripheral side of the gasified fuel jet port is arranged as a nitrogen / gasified fuel mixture jet port and an air jet port, and the nitrogen / gasified fuel mixed gas jet port is provided. A gas turbine combustor characterized in that air outlets are alternately arranged in a circumferential direction. 8. A gas turbine combustor provided with a fuel nozzle on a head side of a combustor liner, a liquid fuel nozzle portion is provided at a center position of a front end portion of the fuel nozzle, and an outer peripheral side of the liquid fuel nozzle portion is provided. A plurality of nozzles for injecting the nitrogen / gasified fuel mixture and air into the combustor liner in an annular arrangement at substantially the same radial position are provided at intervals, and a nitrogen / gasified fuel mixture / air outlet and an air outlet are provided. Is a gas turbine combustor characterized by being alternately arranged in the circumferential direction. 9. The gas turbine combustor according to claim 1, wherein a swirler is provided at each injection port of the fuel nozzle.