JP2000008880A - Gas turbine combustion device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To reduce the generation of NOx caused by the partial increase of a temperature of a combustion gas by the diffusion combustion by comprising an air temperature adjusting means for adjusting the air of an air piping outside a casing connected to an air path for diffused combustion reaching a combustion zone of a combustion chamber, to be lower than that of the air of an air path inside the casing. SOLUTION: In the operation of a plant, the heat exchange is performed by a cooler 12, and the heated fuel (c) is guided to a basic end part of a pilot diffusion fuel pat 19 through a fuel piping 13 to be jetted to a pilot combustion zone 4a in the upstream of a combustion chamber 4 from an injection port 20 as the fuel (d) for pilot diffusion combustion. On the other hand, the air (b) in an air piping outside of the casing of which the temperature is adjusted to be lower than that of the air in an air path 8 inside the casing by the heat exchange with the fuel by the coolder 12, is introduced from a basic end part of a pilot diffusion air path 21 as the air (e) for pilot diffusion combustion to be jetted to the pilot combustion zone 4a from the injection port 22. Whereby the diffusion combustion is performed while lowering the combustion temperature, and the generation of NOx can be reduced.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustion device applied to a gas turbine plant, a combined cycle plant, and the like. NOx
The present invention relates to a gas turbine combustion device that stably combusts while reducing the fuel consumption.

[0002]

2. Description of the Related Art In a conventional gas turbine combustion device, a cylindrical combustor liner is provided inside a combustor casing.
A combustion chamber is formed inside the combustor liner.
A diffusion fuel nozzle for supplying diffusion combustion fuel to the combustion chamber is provided at the head of the combustor liner. An air passage in the casing that supplies air from the air compressor to the combustion chamber is formed between the combustor casing and the combustor liner.

[0003] However, when fuel and air are diffused and burned in the combustion chamber of such a gas turbine combustion device,
A locally high-temperature portion is generated in the combustion gas, which causes generation of NOx in the combustion gas.

[0004] In recent years, in gas turbine plants and combined cycle plants, the turbine inlet temperature, that is, the outlet temperature of the gas turbine combustion device, has been increased to improve the thermal efficiency of the gas turbine. However, as the outlet temperature of the gas turbine combustion device increases, the locally high temperature of the combustion gas due to diffusion combustion also increases, and the NOx concentration of the combustion gas also increases.

[0005] In order to reduce the NOx concentration of such a combustion gas, a gas turbine combustion apparatus has been proposed in which water, steam, or the like is injected into the combustion gas to prevent the combustion gas from being locally heated to a high temperature by diffusion combustion. . However, in such a gas turbine combustion device, the configuration of the device becomes complicated, and a portion where the temperature becomes uneven in the combustor liner is generated, and there is a possibility that the components may be damaged by thermal stress.

[0006] Further, in order to reduce NOx in combustion gas, a gas turbine combustion apparatus employing a lean premixed combustion system has been proposed. This is because, for pilot use, high-temperature combustion gas is generated by diffusion combustion in the pilot combustion zone upstream of the combustion chamber, and lean premixed fuel in which fuel and air are premixed in the main combustion zone downstream of the pilot combustion zone is used. The combustion is performed to perform lean premixed combustion in which almost no NOx is generated. However, even in the lean premixed combustion system, local high temperature occurs due to diffusion combustion in the pilot combustion region, and NOx is generated. Also,
If the flow rate of diffusion combustion is reduced, unstable combustion such as incomplete combustion or misfire, or combustion oscillation may occur, and the components may be damaged.

[0007]

In the conventional gas turbine combustion apparatus, a local high temperature portion is generated by diffusion combustion, which is a factor of generating NOx of combustion gas. Also,
Even in lean premixed combustion, if the flow rate of the pilot diffusion fuel is reduced, unstable combustion such as incomplete combustion or misfire, or combustion oscillation may occur, and the components may be damaged.

The present invention has been made in view of the above circumstances, and a first object of the present invention is to provide a gas turbine combustion system which reduces the generation of NOx due to local high temperature of combustion gas by diffusion combustion. It is to provide a device.

A second object of the present invention is to provide a gas turbine combustion apparatus using a lean premixed combustion system, which aims to reduce NOx caused by local high temperature of combustion gas due to diffusion combustion and achieve stable combustion. To provide a gas turbine combustion device that performs the following.

[0010]

In order to solve the above-mentioned problems, a first aspect of the present invention provides a combustor casing and a combustor liner provided in the combustor casing to form a cylindrical combustion chamber. A diffusion fuel nozzle that is provided at an axial center position of a head of the combustor liner and supplies fuel for diffusion combustion to a combustion area of the combustion chamber, and is provided between the combustor casing and the combustor liner. An air passage in a casing for supplying air from an air compressor to the combustion chamber, a diffusion combustion air passage provided in the diffusion fuel nozzle and supplying diffusion combustion air to a combustion region of the combustion chamber, An outside casing air pipe for supplying diffusion combustion air from outside the combustor casing to the diffusion combustion air passage, and an outside casing air pipe connected to the outside casing air pipe for supplying air from the outside casing air pipe to the casing. Characterized in that than air in single air passage and a diffusion combustion air temperature adjusting means for adjusting the low temperature.

[0011] The invention according to a second aspect provides a combustor casing,
A combustor liner provided in the combustor casing and forming a cylindrical combustion chamber; and a pilot diffusion member provided at an axial center position of a head of the combustor liner and upstream of the combustion chamber in a pilot combustion region. A pilot diffusion fuel nozzle for supplying fuel for combustion, a main premixed fuel nozzle provided on the outer peripheral side of the combustor liner, and for premixing the main premixed combustion fuel and the main premixed combustion air; An air compressor provided between the combustor casing and a combustor liner, the main premixed fuel duct supplying premixed fuel to a main combustion area downstream of a pilot combustion area of the combustion chamber; An air passage in a casing for supplying air from the air, and a pilot diffusion combustion air provided in the pilot diffusion fuel nozzle and in a pilot combustion region of the combustion chamber. A pilot spreading air passage for supplying, connected to the proximal end portion of the pilot spreading air passage,
An air pipe outside the casing that supplies pilot diffusion combustion air from outside the combustor casing, and connected to the air pipe outside the casing to adjust the air in the air pipe outside the casing to a temperature lower than the air in the air passage in the casing. And a diffusion combustion air temperature control means.

[0012] The invention according to claim 3 is characterized in that a combustor casing,
A combustor liner provided in the combustor casing to form a cylindrical combustion chamber; and a pilot diffusion combustion fuel provided in an axial center position of a head of the combustor liner and in a pilot combustion region of the combustion chamber. And a pilot premixed fuel of pilot premixed combustion fuel and pilot premixed combustion air is provided on the outer peripheral side of the pilot diffusion fuel nozzle to supply pilot fuel to the pilot combustion region of the combustion chamber. A pilot premixed fuel nozzle, a main premixed fuel nozzle provided on the outer peripheral side of the combustor liner for premixing the main combustion fuel and the main combustion air, and a main premixed fuel nozzle for supplying the main premixed fuel to the combustion chamber. A main premix fuel duct for supplying to the main combustion zone,
An air passage in the casing provided between the combustor casing and the combustor liner for supplying air from the air compressor to the combustion chamber; and a pilot combustion fuel chamber provided in the pilot diffusion fuel nozzle. A pilot diffusion air passage for supplying pilot diffusion combustion air to the region, an outside casing air pipe for supplying pilot diffusion combustion air to the pilot diffusion air passage from outside the combustor casing, and a connection to the casing outside air piping. And a diffusion combustion air temperature adjusting means for adjusting the temperature of the air outside the casing air pipe to a temperature lower than that of the air inside the casing air passage.

According to a fourth aspect of the present invention, in the gas turbine combustion apparatus according to any one of the first to third aspects, the air pipe outside the casing is configured to extract air from the air compressor, and the air for diffusion combustion is provided. The temperature control means is a cooler for cooling the extracted air.

According to a fifth aspect of the present invention, in the gas turbine combustion apparatus according to the fourth aspect, the air pipe outside the casing is provided with:
A booster for boosting air is connected.

According to a sixth aspect of the present invention, in the gas turbine combustion apparatus according to the fourth or fifth aspect, the cooling medium of the cooler is gas turbine fuel.

According to a seventh aspect of the present invention, in the gas turbine combustion apparatus according to the fourth or fifth aspect, the cooling medium of the cooler is water, steam, air, or a combination thereof.

According to an eighth aspect of the present invention, in the gas turbine combustion apparatus according to any one of the first to seventh aspects, the fuel is a liquid fuel, and the diffusion fuel nozzle, the pilot diffusion fuel nozzle, and the main premix nozzle are: A liquid fuel passage for supplying the liquid fuel to the combustion chamber; and a liquid fuel atomizing air passage provided on an outer peripheral side of the liquid fuel passage and supplying air for atomizing the liquid fuel. The air passage for atomizing fuel is connected to an air pipe outside the casing.

According to a ninth aspect of the present invention, in the gas turbine combustion apparatus according to any one of the sixth to eighth aspects, an air temperature detecting means for detecting a temperature of air in the air pipe outside the casing, and the air temperature detecting means And control means for controlling the flow rate of the cooling medium based on the detected value.

According to a tenth aspect of the present invention, in the gas turbine combustion apparatus according to any one of the sixth to ninth aspects, the exhaust gas NO for detecting the NOx amount of the gas turbine exhaust gas is provided.
It is characterized by comprising x amount detecting means and control means for controlling the flow rate of the cooling medium based on the detection value of the exhaust gas NOx amount detecting means.

[0020]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a gas turbine combustion apparatus according to the present invention will be described below with reference to FIGS.

First Embodiment (FIGS. 1 and 2) FIG. 1 is a schematic system diagram showing a gas turbine combustion device according to the present embodiment. In the present embodiment, gas fuel is used as the fuel. In the present embodiment, as shown in FIG. 1, a gas turbine combustion device 1 is provided with a cylindrical combustor liner 3 inside a combustor casing 2, and a combustion chamber is provided inside the combustor liner 3. 4 are formed. A pilot fuel nozzle 5 for supplying pilot fuel to the combustion chamber 4 is provided on the head side of the combustor liner 3. A flow sleeve 6 is provided on the outer peripheral side of the combustor liner 3 and the pilot fuel nozzle 5, and the downstream side of the combustor liner 3 is connected to a transition piece 7. Between the combustor casing 2 and the combustor liner 3,
An in-casing air passage 8 for supplying air a from an air compressor (not shown) to the combustion chamber 4 is formed. Further, the combustor casing 2 is connected to a combustor casing 9 upstream, and the combustor casing 9 is further connected to a head plate 10.

Outside the combustor casing 2, an outside casing air pipe 11 is provided. The outside casing air pipe 11 communicates with the inside casing air passage 8 to extract air a in the inside casing air passage 8 from an air compressor (not shown). In the middle of the outside casing air pipe 11, the outside casing air pipe 1 is provided.
A cooler 12 is connected as air temperature adjusting means for adjusting the temperature of the first air b to be lower than that of the air a in the air passage 8 in the casing. A fuel pipe 13 is connected to the cooler 12, and the fuel d in the fuel pipe 13 is used as a cooling medium. Then, the air b of the air pipe 11 outside the casing extracted from the air b of the air passage 8 in the casing is introduced into the cooler 12 and is adjusted to be lower in temperature than the air a in the air passage 8 in the casing. . The fuel c in the fuel pipe 13
Is introduced into the cooler 12 as a cooling medium,
The temperature of the fuel c is increased inside the fuel cell.

In the course of the air pipe 11 outside the casing,
Downstream from the cooler 12, an air temperature detector 14 for detecting the temperature of the air b in the cooled outside casing air pipe 11 is provided.
Is provided. An exhaust duct (not shown) for discharging used combustion gas is provided with N
A NOx amount detector (not shown) for detecting the Ox amount is provided. Further, in the course of the fuel pipe 13, the cooler 1
A valve 15 for adjusting the flow rate of the fuel c in the fuel pipe 13 as a cooling medium is provided on the upstream side of 2. A control device 16 as control means for controlling the cooling medium is connected to the air temperature detector 14, the NOx amount detector and the valve 15 via a signal wiring 17. And the valve 15 is controlled based on the detection values of the NOx amount detector and the fuel pipe 13 as a cooling medium.
Of the fuel c, and the temperature of the air b in the air pipe 11 outside the casing.

At the axial center position of the pilot fuel nozzle 5,
A pilot diffusion fuel nozzle 18 for supplying pilot diffusion combustion fuel d is provided in a pilot combustion region 4a on the upstream side of the combustion chamber 4, and a pilot diffusion combustion fuel passage 19 is provided in the pilot diffusion fuel nozzle 18. . The pilot diffusion fuel passage 19 is connected at its base end to the fuel pipe 13. As the pilot diffusion combustion fuel d, the fuel pipe 1 whose temperature has been increased inside the cooler 12 is used.
3 fuel c is used. In addition, the pilot diffusion fuel passage 19 communicates with a plurality of pilot diffusion fuel injection ports 20 that open outward from the axis of the combustion chamber 4 at the distal end.

A pilot diffusion air passage 21 for supplying pilot diffusion combustion air d to a pilot combustion area 4 a of the combustion chamber 4 is provided in an annular shape around the pilot diffusion fuel passage 19 in the pilot diffusion fuel nozzle 18. .
The pilot diffusion air passage 21 is connected at a base end thereof to the air pipe 11 outside the casing, and the pilot diffusion combustion air e is cooled by the cooler 12 to a temperature lower than the air a in the air passage 8 in the casing. The air b of the outside air pipe 11 is used. Further, the pilot diffusion air passage 21 is branched at the distal end side, and communicates with the plurality of pilot diffusion air jet ports 22. Further, a swirl vane 23 is provided at the pilot diffusion air jet port 22 to give a swirl flow to the pilot diffusion combustion air e.

A pilot premixed fuel nozzle 24 is provided on the outer periphery of the pilot diffusion fuel nozzle 18. The pilot premixed fuel nozzle 24 supplies pilot premixed combustion air f to its proximal end. An air passage 25 is provided in an annular shape, and a pilot premixed fuel passage 26 that supplies pilot premixed fuel g to a pilot combustion area 4 a of the combustion chamber 4 is provided in an annular shape on the distal end side. Further, a fuel pipe 13 for supplying pilot premixed combustion fuel h is provided behind the pilot premixed air passage 25. Fuel g for pilot premixed combustion
As the fuel, the fuel c whose temperature has been increased in the cooler 12 is used. And the pilot premix air passage 25 is
The base end communicates with the in-casing air passage 8, and the distal end communicates with the pilot premixed fuel passage 26 and the fuel pipe 13. In addition, the pilot premix air passage 25 includes:
A swirl vane 27 is provided on the tip side, and the pilot premixed combustion air f is provided with a swirl flow on the tip side, mixes with the pilot premixed combustion fuel h, and flows from the base end of the pilot premixed fuel passage 26. It is being introduced. Then, the pilot premixed fuel passage 26 branches off at the tip end side,
The plurality of pilot premix fuel injection ports 28 communicate with each other.

A main premixed fuel nozzle 29 for mixing the main combustion fuel i and the main combustion air j is provided on the outer periphery of the pilot fuel nozzle 5. The main premixed fuel nozzle 29 has a main fuel passage 30. Is provided. The main fuel passage 30 has a fuel pipe 13 at the base end.
And the main fuel outlet 31 at the tip
Is in communication with As the main combustion fuel i, the fuel c whose temperature has been raised inside the cooler 12 is introduced from the base end of the main fuel passage 30 through the fuel pipe 13.

In front of the main premixed fuel nozzle 29, on the outer peripheral side of the combustor liner 3, the main premixed fuel k is supplied to the main combustion zone 4b of the combustion chamber 4 downstream of the pilot combustion zone 4a. A mixed fuel duct 32 is provided. The main combustion fuel i ejected from the main fuel ejection port 31 is supplied to the air a in the casing air passage 8.
And is introduced from the base end of the main premixing duct 32. The leading end of the main premixing duct 32 communicates with a plurality of main premixed fuel injection ports 33 that open on the outer periphery of the combustor liner 3.

In such a gas turbine combustion apparatus 1,
During plant operation, heat is exchanged inside the cooler 12,
The fuel c whose temperature has been increased is introduced from the base end of the pilot diffusion fuel passage 19 through the fuel pipe 13, and is used as a pilot diffusion combustion fuel d from the pilot diffusion fuel injection port 20 to the pilot upstream of the combustion chamber 4. It is ejected to the combustion zone 4a. Further, the air b in the outside casing air pipe 11 adjusted to a lower temperature than the air in the casing inside air passage 8 by the cooler 12 is introduced from the base end of the pilot diffusion air passage 21 as pilot diffusion combustion air e. The fuel is jetted from the pilot diffusion air jet port 22 into the pilot combustion zone 4 a of the combustion chamber 4. At this time, the temperature of the air b in the air pipe 11 outside the casing is detected by the air temperature detector 14 connected to the air pipe 11 outside the casing, and a valve provided in the fuel pipe 13 by the control device 16 based on the detected value. 15 to control the flow rate of the fuel c as a cooling medium to adjust the temperature of the pilot diffusion combustion air e. Then, since the temperature of the pilot diffusion combustion air e is lower than the air a in the air passage 8 in the casing and supplied,
The fuel for pilot diffusion combustion d and the air for pilot diffusion combustion e ejected to the pilot combustion region 4a of the combustion chamber 4 reduce the combustion temperature and perform diffusion combustion.

FIG. 2 is a graph showing the relationship between the NOx concentration ratio and the diffusion combustion air temperature ratio. The vertical axis represents the NOx concentration ratio, and the horizontal axis represents the diffusion combustion air temperature ratio. As shown in FIG. 2, as the temperature of the air for diffusion combustion decreases, the NOx concentration also decreases. That is, the reduction rate of NOx is improved by lowering the diffusion combustion air temperature.

When the pilot diffusion combustion air e is supplied at a reduced temperature, the pilot diffusion combustion fuel d is reduced in combustion temperature, that is, while the pilot diffusion mixed fuel d is diffused and combusted with low NOx, the pilot premixed fuel Pilot premixed fuel g is injected from the injection port 28 into the pilot combustion area 4 a of the combustion chamber 4. The pilot premixed fuel g is stably burned by the flame of diffusion combustion. Further, the main premixed fuel k is injected from the main premixed fuel injection port 33 into the main combustion zone 4b downstream of the pilot combustion zone 4a of the combustion chamber 4, and is stably burned by the flame of the pilot combustion zone 4a.

The combustion gas burned in the combustion chamber 4 drives a gas turbine (not shown) and is discharged from an exhaust duct (not shown). Further, the NOx amount of the exhaust gas is detected by an exhaust gas NOx amount detector (not shown) provided in the exhaust duct, and the control device 16 controls the valve 15 provided in the fuel pipe 13 based on the detected value. By controlling the flow rate of the fuel c as the cooling medium, the temperature of the pilot diffusion combustion air e is adjusted, the combustion temperature of the pilot diffusion combustion is lowered, and the NOx of the exhaust gas is reduced.

According to the present embodiment, the pilot diffusion combustion air c is supplied at a temperature lower than the temperature of the air a in the air passage 8 in the casing, so that the combustion temperature of the pilot diffusion combustion is lowered and the combustion gas is reduced in NOx. Can be achieved. Further, based on the detection values from the air temperature detector 14 and the exhaust gas NOx amount detector, the flow rate of the fuel c as the cooling medium is controlled and the temperature of the pilot diffusion combustion air e is adjusted. Can be performed more reliably. Further, since the temperature of the diffusion combustion is reduced, the NOx of the combustion gas by the diffusion combustion can be reduced without reducing the flow rate of the pilot diffusion combustion fuel d. Without generating unstable combustion such as complete combustion and misfire,
Main premixed fuel k can be stably burned.
Furthermore, by using the fuel c as the cooling medium of the cooler 12, the temperature of the fuel c increases, and the pressure of the fuel c injected into the combustion chamber 4 increases, so that the fuel c can be stably burned. In addition, damage to components due to unstable combustion or combustion vibration can be prevented, the gas turbine can be operated stably, and the safety of the gas turbine plant is improved.

Conventionally, when the flow rate of the pilot diffusion combustion fuel d is reduced in order to prevent the local increase in the temperature of the combustion gas due to diffusion combustion which causes NOx generation, for example, the flow rate of the diffusion combustion fuel d is reduced If the flow rate of the fuel c is set to 3% or less, unstable combustion such as incomplete combustion or misfire may occur, or combustion vibration may occur, and the components may be damaged. However, according to the present embodiment, the cooling effect of the combustion gas is improved by cooling and supplying the pilot diffusion combustion air e, and the flow rate of the pilot diffusion combustion fuel d is not reduced. Even if the flow rate of d is 4% to 10% of the flow rate of the entire fuel c, stable combustion can be obtained, and the NOx of the combustion gas can be reduced.

In this embodiment, the fuel c is used as the cooling medium of the cooler 12 for cooling the pilot diffusion combustion air e. However, the cooling medium may be water, steam, air or a combination thereof. A sufficient cooling effect can be obtained even if is used. In addition, air pipe 1 outside the casing
1 may be connected to a booster. If the air pressurized by the booster is supplied as pilot diffusion combustion air e, more stable pilot diffusion combustion can be obtained and the configuration of the cooler can be simplified. .

In this embodiment, air a in the air passage 8 in the casing is extracted as air b in the air pipe 11 outside the casing, but outside air is introduced as air b in the air pipe 11 outside the casing. It may be. In this case, the introduced air b is boosted by a booster,
If the temperature is adjusted to be lower than the temperature of the air a in the air passage 8 in the casing by the heat exchanger and the air is supplied to the combustion chamber 4 as pilot diffusion combustion air e, the same effect as in the present embodiment can be obtained.

Second Embodiment (FIG. 3) FIG. 3 is a schematic system diagram showing a gas turbine combustion device according to this embodiment. In the present embodiment, a liquid fuel is used as the fuel. In the present embodiment, as shown in FIG. 3, a pilot diffusion fuel passage 19 is provided in a pilot diffusion fuel nozzle 18 provided at an axial position of the pilot fuel nozzle 5.
A pilot diffusion fuel atomization air passage 34 for supplying pilot diffusion combustion fuel atomization air 1 for atomizing the pilot diffusion combustion fuel d is provided in an annular shape on the outer peripheral side. This atomized air passage 3 for pilot diffusion combustion fuel
Reference numeral 4 denotes a base end connected to the outside casing air pipe 11, branched at the tip end side, and communicates with a plurality of pilot diffusion fuel atomizing air injection ports 35 opening toward the axial direction of the combustion chamber 4. I have. The pilot diffusion fuel atomizing air jet port 35 is provided with a swirling blade 36.

The main premix fuel nozzle 29 provided on the outer peripheral side of the pilot fuel nozzle 5 is provided with a main fuel passage 30. On the outer peripheral side of the main fuel passage 30, the main combustion fuel i is atomized. Main fuel atomizing air passage 37 for supplying main combustion fuel atomizing air m
Are provided in an annular shape. The main fuel atomizing air passage 37 is connected to the outer casing air pipe 11 at the base end, branched at the distal end side, and opens toward the axial direction of the main premixed fuel nozzle 29. It communicates with the air outlet 38. The main fuel atomizing air injection port 38 is provided with a swirling blade 39.

Water n is used as a cooling medium in the cooler 12 connected to the air pipe 11 outside the casing, and a pipe 40 for supplying the water n is connected to the cooler 12.
Further, the cooler 1 on the way of the air pipe 11 outside the casing 1
The air b on the air pipe 11 outside the casing is located downstream of
Is connected. Other configurations are the same as those in the first embodiment, and therefore, the same reference numerals as in FIG.

In such a gas turbine combustion apparatus 1a, the pilot diffusion combustion fuel d is ejected from the pilot diffusion fuel ejection port 20 toward the centrifugal direction from the axis of the combustion chamber 4, and the pilot diffusion combustion fuel is atomized air. m is given a swirling flow by a swirling blade 36, and is ejected from the pilot-diffused fuel atomized air jet port 34 toward the axial direction of the combustion chamber 4, and these pilot-diffused fuel d and pilot-diffused fuel are atomized. The air 1 collides with the liquefied air 1 to atomize and diffuse and burn in the pilot combustion area 4 a of the combustion chamber 4.
Further, the main combustion fuel i is jetted from the main fuel outlet 31 toward the centrifugal direction from the axis of the main premixed fuel nozzle 29, and the main combustion fuel atomized air m is given a swirling flow by the swirling blade 39. The main fuel atomizing air is injected from the main fuel atomizing air injection port 38 in the axial direction of the main premixed fuel nozzle 29, and the main combustion fuel i and the main combustion fuel atomizing air m collide with each other to atomize the fuel. The main premixed fuel duct 3 mixes with the air a in the air passage 8
2, the main combustion zone 4b of the combustion chamber 4
And perform premix combustion.

According to the present embodiment, the same effects as in the first embodiment can be obtained even when a liquid fuel is used as the fuel c.

[0042]

As described above in detail, according to the gas turbine combustion apparatus of the present invention, in the diffusion combustion having a high NOx generation rate, the temperature of the diffusion combustion air is made lower than the air from the air compressor. By supplying, the combustion gas can be prevented from locally increasing its temperature due to diffusion combustion, and the NO
x concentration can be reduced. In a gas turbine combustion system using the lean premixed combustion system, the diffusion combustion air is supplied at a lower temperature than the air from the air compressor to locally increase the temperature of the combustion gas due to diffusion combustion. NOx can be reduced without reducing the flow rate of pilot diffusion combustion fuel, unstable combustion such as misfire or incomplete combustion, and damage to components due to combustion vibration can be prevented. The gas turbine plant can operate stably, and the reliability of the gas turbine plant can be improved.

[Brief description of the drawings]

FIG. 1 is a schematic system diagram showing a first embodiment of a gas turbine combustion device according to the present invention.

FIG. 2 is a graph showing a relationship between a NOx concentration ratio and a diffusion combustion air temperature ratio.

FIG. 3 is a schematic system diagram showing a second embodiment of the gas turbine combustion device according to the present invention.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1, 1a Gas turbine combustion apparatus 2 Combustor casing 3 Combustor liner 4 Combustion chamber 4a Pilot combustion area 4b Main combustion area 5 Pilot fuel nozzle 6 Flow sleeve 7 Transition piece 8 Casing air passage 9 Combustor outer cylinder 10 Head plate 11 Outer casing air pipe 12 Cooler 13 Fuel pipe 14 Air temperature detector 15 Valve 16 Control device 17 Signal wiring 18 Pilot diffusion fuel nozzle 19 Pilot diffusion fuel passage 20 Pilot diffusion fuel jet 21 Pilot diffusion air passage 22 Pilot diffusion air jet 23 Swirl vane 24 Pilot premix nozzle 25 Pilot premix air passage 26 Pilot premix fuel passage 27 Swirl blade 28 Pilot premix fuel jet 29 Main premix fuel nozzle 30 Main fuel passage 31 Main Fuel Injection Port 32 Main Premixed Duct 33 Main Premixed Fuel Injection Port 34 Pilot Diffusion Fuel Atomizing Air Passage 35 Pilot Diffusion Fuel Atomization Air Injection 36 Swirl Blade 37 Main Fuel Atomization Air Passage 38 Main Fuel Atomization Air Spout 39 Swirling vane 40 Piping 41 Compressor

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Kenji Takahara 2-4, Suehirocho, Tsurumi-ku, Yokohama-shi, Kanagawa Prefecture Inside the Toshiba Keihin Works Co., Ltd. (72) Inventor Hiroyuki Ito 2-chome, Suehirocho, Tsurumi-ku, Yokohama-shi, Kanagawa Address: Toshiba Keihin Works Co., Ltd.

Claims (10)

[Claims] 1. A combustor casing, a combustor liner provided in the combustor casing and forming a cylindrical combustion chamber, and a combustor liner provided at an axial position of a head of the combustor liner,
A diffusion fuel nozzle for supplying fuel for diffusion combustion to a combustion zone of the combustion chamber, and air in a casing provided between the combustor casing and a combustor liner for supplying air from an air compressor to the combustion chamber. A passage, a diffusion combustion air passage provided in the diffusion fuel nozzle for supplying diffusion combustion air to a combustion zone of the combustion chamber, and a diffusion combustion air passage from outside the combustor casing to the diffusion combustion air passage. An air pipe outside the casing that supplies air, and an air temperature control unit for diffusion combustion that is connected to the air pipe outside the casing and that adjusts the air in the air pipe outside the casing to a temperature lower than the air in the air passage in the casing. A gas turbine combustion device characterized in that: 2. A combustor casing, a combustor liner provided in the combustor casing and forming a cylindrical combustion chamber, and a combustor liner provided at an axial position of a head of the combustor liner,
A pilot diffusion fuel nozzle for supplying pilot diffusion combustion fuel to a pilot combustion zone upstream of the combustion chamber;
A main premixed fuel nozzle provided on the outer peripheral side of the combustor liner for performing premixing of the main premixed combustion fuel and the main premixed combustion air, and the main premixed fuel from the pilot combustion region of the combustion chamber; A main premixed fuel duct that supplies the downstream main combustion zone, a casing air passage that is provided between the combustor casing and the combustor liner, and supplies air from an air compressor to the combustion chamber; A pilot diffusion air passage provided in the pilot diffusion fuel nozzle, for supplying pilot diffusion combustion air to a pilot combustion region of the combustion chamber, connected to a base end of the pilot diffusion air passage, An outer casing air pipe for supplying air for pilot diffusion combustion from outside, and the casing connected to the outer casing air pipe; Gas turbine combustion apparatus characterized by comprising air grayed out air pipe and a diffusion combustion air temperature adjusting means for adjusting the temperature lower than the air in the casing air passage. 3. A combustor casing, a combustor liner provided in the combustor casing and forming a cylindrical combustion chamber, and a combustor liner provided at an axial center position of a head of the combustor liner,
A pilot diffusion fuel nozzle for supplying pilot diffusion combustion fuel to a pilot combustion region of the combustion chamber; and a pilot premixed combustion fuel and a pilot premix combustion fuel provided on an outer peripheral side of the pilot diffusion fuel nozzle. A pilot premix fuel nozzle for supplying a pilot premix fuel with the premix combustion air, and a main premix provided on the outer peripheral side of the combustor liner for premixing the main combustion fuel and the main combustion air. A fuel nozzle and a main premixed fuel duct for supplying the main premixed fuel to a main combustion zone of the combustion chamber; and a fuel nozzle provided between the combustor casing and a combustor liner, and the combustion chamber is provided with an air compressor. An air passage in a casing for supplying air; and a pilot passage for the combustion chamber provided in the pilot diffusion fuel nozzle. A pilot diffusion air passage for supplying pilot diffusion combustion air to the sintering zone, a casing outside air pipe for supplying pilot diffusion combustion air to the pilot diffusion air passage from outside the combustor casing, and a casing outside air pipe. A gas turbine combustion device, comprising: a diffusion combustion air temperature adjusting means connected to adjust the temperature of the air outside the casing to a lower temperature than the air in the air passage inside the casing. 4. The gas turbine combustion device according to any one of claims 1 to 3, wherein the air pipe outside the casing is configured to extract air from an air compressor, and the diffusion combustion air temperature adjusting means includes: A gas turbine combustion device, which is a cooler for cooling extracted air. 5. The gas turbine combustion device according to claim 4, wherein a booster for increasing the pressure of the air is connected to the air pipe outside the casing. 6. The gas turbine combustion device according to claim 4, wherein the cooling medium of the cooler is gas turbine fuel. 7. The gas turbine combustion device according to claim 4, wherein the cooling medium of the cooler is water, steam, air, or a combination thereof. 8. The gas turbine combustion apparatus according to claim 1, wherein the fuel is a liquid fuel, and a diffusion fuel nozzle, a pilot diffusion fuel nozzle, and a main premix nozzle burn the liquid fuel. A liquid fuel passage for supplying air to the chamber, and a liquid fuel atomizing air passage provided on an outer peripheral side of the liquid fuel passage and supplying air for atomizing the liquid fuel. The gas turbine combustion device, wherein the passage is connected to an air pipe outside the casing. 9. The gas turbine combustion device according to claim 6, wherein an air temperature detecting means for detecting the temperature of the air in the air pipe outside the casing, and a value detected by the air temperature detecting means. Control means for controlling a flow rate of a cooling medium. 10. A gas turbine combustion device according to claim 6, wherein exhaust gas NOx amount detecting means for detecting the NOx amount of the gas turbine exhaust gas,
Control means for controlling the flow rate of the cooling medium based on the detected value of the exhaust gas NOx amount detecting means.