JP2001141241A - Gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine combustor which suppresses combustive vibrations to a low level while a combustion gas is generated in a combustion chamber. SOLUTION: A gas turbine combustor is provided with a resistor 16 on the upstream side of a swirler 10 surrounding a nozzle 4 for diffuse combustion which is inserted into an air passage 9 for diffuse combustion.

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 producing combustion gas by mixing fuel with air.
In particular, the present invention relates to a gas turbine combustor that suppresses combustion vibration generated during generation of combustion gas.

[0002]

2. Description of the Related Art A gas turbine must be operated in a wide output range corresponding to a large load change from a start operation to a rated load operation. Therefore, it is one of the essential conditions of a gas turbine combustor to generate stable combustion gas even when the operating conditions such as the air flow rate and the fuel flow rate change greatly from the start-up operation to the rated load operation.

On the other hand, for gas turbine combustors, there is a strong demand for a combustion method capable of keeping the NOx concentration low. As a combustion method with a low NOx concentration, there is premixed combustion in which air is preliminarily mixed with fuel and the premixed gas is burned. This is to prevent the premix combustion temperature from locally increasing by performing the premix combustion.

In general, the NOx concentration increases exponentially as the combustion flame temperature increases. Therefore, if air and fuel are mixed in advance, the combustion flame temperature can be reduced, and the NOx concentration can be reduced.

[0005] In recent years, the ratio of lean premixed combustion occupies an increasingly large demand for low NOx.

In general, lean premixed combustion has a narrower stable combustion range than diffusion combustion. Therefore, premixed combustion is stabilized by using a diffusion combustion pilot flame as a fire. However, in lean premixed combustion, pressure fluctuations tend to occur easily, and combustion vibration is excited under conditions corresponding to the pressure fluctuations. This combustion oscillation is a factor that hinders the operability and reliability of the gas turbine combustor, such as pollutant emission and damage to combustor components due to non-uniformity of combustion pressure.

[0007] Therefore, in order to avoid an operation range in which abnormal pressure fluctuations are generated, for example, a method of attenuating thermoacoustic vibration by influencing the pressure fluctuations of the combustion chamber by a speaker, or a method of controlling the flow rate of fuel, There is proposed a method of changing the ratio in a timely manner.

[0008]

In recent years, from the viewpoint of environmental protection, it has become necessary to operate harmful exhaust gas as little as possible, and a gas turbine capable of generating stable combustion gas over a wide operation range. There is a need for a combustor. For this purpose, it is indispensable to suppress pressure oscillation generated during generation of combustion gas, that is, combustion oscillation, in order to generate stable combustion gas over a wide operating range.

According to the present invention, even when the lean premix combustion ratio for reducing the NOx concentration is increased and the air flow rate and the fuel flow rate are changed over a wide range, the combustion vibration is low and the combustion gas An object of the present invention is to provide a gas turbine combustor that can ensure stability.

[0010]

According to a first aspect of the present invention, there is provided a gas turbine combustor having a diffusion combustion air provided at a center of a head side of a combustion chamber. In a gas turbine combustor provided with a diffusion combustion nozzle inserted into a passage and a premixed combustion nozzle concentrically disposed outside the diffusion combustion nozzle, a diffusion combustion nozzle inserted into the diffusion combustion air passage is provided. A resistor is provided on the upstream side of the swirler installed around the nozzle.

In order to achieve the above object, the gas turbine combustor according to the present invention, as described in claim 2, connects the resistor to the diffusion combustion air passage in a vertical direction and a transverse direction. , At least one of them.

In order to achieve the above object, a gas turbine combustor according to the present invention has a resistor formed in one of a rod shape and a plate shape.

In order to achieve the above object, the gas turbine combustor according to the present invention is inserted into a diffusion combustion air passage provided at the center of the combustion chamber on the head side. In a gas turbine combustor including a diffusion combustion nozzle and a premix combustion nozzle concentrically disposed outside the diffusion combustion nozzle, the gas turbine combustor surrounds the diffusion combustion nozzle inserted into the diffusion combustion air passage. A resistor is provided between the swirler blades set up and the adjacent swirler blades.

Further, in the gas turbine combustor according to the present invention, in order to achieve the above object, the resistor is formed in a spherical shape as described in claim 5.

Further, in order to achieve the above object, the gas turbine combustor according to the present invention is inserted into a diffusion combustion air passage provided at the center on the head side of the combustion chamber. In a gas turbine combustor including a diffusion combustion nozzle and a premix combustion nozzle concentrically disposed outside the diffusion combustion nozzle, the gas turbine combustor surrounds the diffusion combustion nozzle inserted into the diffusion combustion air passage. A resistor is provided on the upstream side of the swirler, which can be moved in and out of the diffusion combustion air passage.

Further, in order to achieve the above object, the gas turbine combustor according to the present invention comprises a resistor having a diameter capable of freely moving in and out of the diffusion combustion air passage. A plurality of different kinds of cylindrical resistors are formed, and a cylindrical resistor having a smaller diameter can be inserted into a cylindrical resistor having the largest diameter one after another.

In order to achieve the above object, the gas turbine combustor according to the present invention is inserted into a diffusion combustion air passage provided at the center of the combustion chamber on the head side. In a gas turbine combustor including a diffusion combustion nozzle and a premix combustion nozzle concentrically disposed outside the diffusion combustion nozzle, the gas turbine combustor surrounds the diffusion combustion nozzle inserted into the diffusion combustion air passage. On the upstream side of the installed swirler, there is provided a resistor that can move in and out of the diffusion combustion air passage so as to be able to move in and out, and a resistor driving unit that drives the resistor.

In the gas turbine combustor according to the present invention, in order to achieve the above object, the resistor driving unit converts the pressure detected from the combustion chamber into an electric signal. A pressure transducer and a signal from this pressure transducer are subjected to frequency analysis, the frequency is subjected to Fourier transform, and when the signal after Fourier transform exceeds a predetermined threshold, a driving force signal is generated based on the deviation. And a drive operation unit that receives a calculation signal from the calculation control unit and drives the resistor.

In order to achieve the above object, the gas turbine combustor according to the present invention is inserted into a diffusion combustion air passage provided at the center of the combustion chamber on the head side. In a gas turbine combustor including a diffusion combustion nozzle and a premix combustion nozzle concentrically disposed outside the diffusion combustion nozzle, the gas turbine combustor surrounds the diffusion combustion nozzle inserted into the diffusion combustion air passage. On the upstream side of the installed swirler, a plurality of types of resistors having different diameters which can be freely moved in and out of the diffusion combustion air passage, and a resistor for driving the plurality of types of resistors having different diameters are selected. And a drive unit.

[0020] In the gas turbine combustor according to the present invention, in order to achieve the above object, the resistor selection drive section converts the pressure detected from the combustion chamber into an electric signal. And a signal from the pressure transducer to perform a frequency analysis, perform a Fourier transform on the frequency, and when the signal after the Fourier transform exceeds a predetermined threshold value, corresponds to the magnitude of the excess. Then, a signal from the resistor size selection section is supplied to a selection drive section to select and drive the size of the resistor, and an arithmetic control section is combined.

In order to achieve the above object, the gas turbine combustor according to the present invention is inserted into a diffusion combustion air passage provided at the center of the combustion chamber on the head side. In a gas turbine combustor provided with a diffusion combustion nozzle and a premix combustion nozzle concentrically disposed outside the diffusion combustion nozzle, a diffusion combustion nozzle and a swirler inserted into the diffusion combustion air passage are provided. An air passage is provided between the air passages, and air is supplied from the air passage to the combustion chamber according to the diffusion combustion ratio.

In order to achieve the above object, the gas turbine combustor according to the present invention is inserted into a diffusion combustion air passage provided at the center of the combustion chamber on the head side. In a gas turbine combustor provided with a diffusion combustion nozzle and a premix combustion nozzle concentrically disposed outside the diffusion combustion nozzle, a diffusion combustion nozzle and a swirler inserted into the diffusion combustion air passage are provided. And a valve opening signal calculated based on the deviation when the calculation signal exceeds a predetermined threshold when the calculation signal exceeds a predetermined threshold value. And a calculation control unit that provides the control valve with the control valve provided in the air passage, and controls the air supplied according to the diffusion combustion ratio of the combustion chamber.

In order to achieve the above object, the gas turbine combustor according to the present invention is provided with a perforated plate on the outlet side of the air passage as described in claim 14.

[0024]

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 drawings and reference numerals attached to the drawings.

FIG. 1 is a partially cutaway schematic sectional view showing a first embodiment of a gas turbine combustor according to the present invention.

The gas turbine combustor according to the present embodiment
A pilot fuel nozzle 3 for injecting pilot fuel is provided on a head side of a combustion chamber 2 formed in the combustor liner 1. The pilot fuel nozzle 3 includes a pilot diffusion combustion nozzle 4 on the center side and a pilot premixed combustion nozzle 5 on the peripheral side, and is jetted from each of the nozzles 4 and 5 into the combustion chamber 2.

The fuel passage 6 of the pilot diffusion combustion nozzle 4 is formed in a concentric double tube structure, a pilot diffusion fuel first passage 7 for supplying the first diffusion fuel F ₁ pilot toward the center, this passage And a _second pilot diffusion fuel passage 8 through which the pilot second diffusion fuel F2 flows.

An annular pilot diffusion combustion air passage 9 is formed in the pilot diffusion combustion nozzle 4 so as to surround the pilot diffusion fuel second passage 8. The pilot diffusion combustion air passage 9 is provided with a swirler 10 on the outlet side to give a swirling flow to the air.

The pilot premix combustion nozzle 5 of the pilot fuel nozzle 3 has a structure surrounding the pilot diffusion combustion nozzle 4. The pilot premixed combustion nozzle 5 includes a pilot premixed combustion air passage 11 formed concentrically outside the pilot diffusion combustion air passage 9.
1 has an annular shape. The pilot premixed combustion air passage 11 has a swirler 12 at its inlet and a pilot premixed combustion nozzle 13 protruding on the way. The pilot premixed fuel nozzle 13, pilot premixed fuel F ₃ is supplied through the pilot premixed header 14, premix fuel passage 15.

The pilot premixed combustion air passage 1
A main fuel supply unit for supplying a premixed gas obtained by adding air to the fuel in advance to the combustion chamber 2 is provided outside the fuel cell 1.
Here, the description is omitted.

On the other hand, a pilot diffusion combustion air passage 9 through which a pilot diffusion combustion nozzle 4 facing the combustion chamber 2 formed by the combustor liner 1 is inserted, as shown in FIG.
On the upstream side of the swirler 10, for example, a rod-shaped or plate-shaped resistor 16 is provided.

As shown in FIG. 3, the resistor 16 is arranged in a single shape or a cross shape extending in at least one of the vertical direction and the transverse direction of the pilot diffusion combustion nozzle 4. A vortex street is forcibly applied to the flow of air before flowing into the air to disturb the flow.

In general, a gas turbine combustor uses NO of premixed combustion to burn a premixed gas by using a flame of diffusion combustion as a fire.
It is considered preferable because the x concentration can be kept low.

However, in the gas turbine combustor, when performing premix combustion, combustion oscillation tends to increase in an operation region where the premix ratio is high or an operation region where the combustion temperature is high.

This combustion vibration is kneading vibration caused by fluctuations (heat, speed, pressure, etc.) when a flame is generated. Therefore, by controlling the flame, the combustion oscillation characteristics can be changed. Further, the flame is generated by interference between the combustion air flow field and the fuel, and the flame characteristics can be changed by controlling the combustion air or the fuel.

The inventor has sufficiently considered such basic technical matters. If a resistor is arranged in a passage, the air flow field is manipulated, and the flame is changed, and the flame is changed. Invented to suppress combustion oscillation without changing the combustion range.

That is, FIG. 4 is a graph comparing the presence / absence of the reduction of the combustion vibration. FIG. 4A shows the vibration value when the resistor 16 according to the present embodiment is not installed on the upstream side of the swirler 10. b) has a diameter (D) of 8 mm as the resistor 16;
Are vibration values when six cylinders are arranged at equal intervals.

4 (a) and 4 (b), the vibration value of (b) in which the resistor 16 is installed on the upstream side of the swirler 10 is lower than that of (a). all right.

As described above, in the present embodiment, the resistor 16 is provided on the upstream side of the swirler 10 in the pilot diffusion combustion air passage 9.
Is provided to forcibly impart a vortex street to the flow of air to disturb the flow, so that when combustion gas is generated in the combustion chamber 2, the generation of combustion vibration can be suppressed low, and the premix ratio is high. Even in the operating range or the operating range where the combustion temperature is high, the operating width can be expanded by maintaining the combustion gas in a stable state.

FIG. 5 is a partially cutaway conceptual view showing a second embodiment of the gas turbine combustor according to the present invention. The same components as those of the first embodiment are denoted by the same reference numerals.

The gas turbine combustor according to the present embodiment
Swirlers 10, 10 in pilot diffusion combustion air passage 9
Is provided with a spherical resistor 17 at an intermediate position.

As shown in FIG. 6, this spherical resistor 17 is installed at an intermediate position on the outer peripheral side of the swirlers 10, 10 to further amplify the swirling flow given to the air from the swirlers 10, 10. The disorder is given.

As described above, in the present embodiment, the swirler 10,
Since a spherical resistor 17 is provided at an intermediate position of 10 to give more turbulence to the flow of air, when generating combustion gas in the combustion chamber 2, it is possible to further suppress the occurrence of combustion oscillation. it can.

FIG. 7 is a partially cutaway conceptual view showing a third embodiment of the gas turbine combustor according to the present invention. The same components as those of the first embodiment are denoted by the same reference numerals.

The gas turbine combustor according to the present embodiment
This is a variable type in which, for example, a rod-shaped or plate-shaped resistor 16 can be freely moved in and out of the pilot diffusion combustion air passage 9.

As shown in FIG. 8, the resistor 16 can be moved into and out of the pilot diffusion combustion air passage 9 in any of a vertical direction and a transverse direction.

As described above, in the present embodiment, the resistor 16 can be moved in and out of the pilot diffusion combustion air passage 9 so as to be able to move in and out of the pilot diffusion combustion air passage 9 only. It is inserted into the use air passage 9 to give a large turbulence to the flow of air, thereby suppressing the combustion vibration. The pressure loss of the air when the combustion vibration does not occur is always lower than when the resistor 16 is installed. Can be suppressed.

FIG. 9 is a partially cutaway conceptual view showing a fourth embodiment of the gas turbine combustor according to the present invention. The same components as those of the first embodiment are denoted by the same reference numerals.

The gas turbine combustor according to the present embodiment
Resistor that moves in and out of pilot diffusion combustion air passage 9
16, three types of resistors 1 having different diameters, for example, are cylindrical.
6a ₁, 16a₂, 16a₃Prepare these resistors
16a₁, 16a₂, 16a ₃Can be freely moved in and out
It is a variable format that can be changed.

These resistors 16a ₁ , 16a ₂ , 16a
_As shown in FIG. 10, ₃ allows the pilot diffusion combustion air passage 9 to enter and exit from both the vertical direction and the transverse direction, and for example, the resistors 16 a ₁ and 16 a _{2 having} the largest diameter. , diameter 16a ₃ is second smallest resistor 16a _2, are adapted to receive one after another the smallest resistor 16a ₁ further diameter.

The resistors 16a ₁ , 16a ₂ , 16a
For example, when the cylinder ₃ is a cylinder, its diameter can be obtained from the following equation. Now, let the vortex street frequency generated from the cylinder be n
(Pieces / sec), the number of straw hulls is S, the temperature around the cylinder is U (m / sec), and the diameter of the cylinder is D
(M), the vortex street frequency n is

## EQU1 ## where n = (SU) / D.

Therefore, when the frequency of the combustion oscillation is known, each resistor 16a ₁ ,
The apertures of 16a ₂ and 16a ₃ may be obtained from the above equation.

As described above, in this embodiment, for example, three types of resistors 16a ₁ , 16a ₂ , 16a ₃ having different diameters are selected in the pilot diffusion combustion air passage 9 so as to match the level of combustion vibration. It is designed to be able to move in and out freely, so that each resistor 1 can be adjusted according to the level of combustion vibration.
The frequency of swirl generated from 6a ₁ , 16a ₂ , 16a ₃ is given to the flow of air, so that combustion vibration can be suppressed to a low level, and the combustion gas can be maintained in a stable state.

FIG. 11 is a partially cutaway conceptual view showing a fifth embodiment of the gas turbine combustor according to the present invention. The same components as those of the first embodiment are denoted by the same reference numerals.

The gas turbine combustor according to the present embodiment
The pilot diffusion combustion air passage 9 is provided with a resistor driving unit 18 that allows a rod-shaped or plate-shaped resistor 16 to move in and out, for example.

The resistor driving unit 18 detects a pressure change in the combustion chamber 2 and converts it into an electric signal.
A drive operation for amplifying and frequency-analyzing the electric signal from the pressure transducer 19, performing a Fourier transform on the frequency, and moving the resistor 16 forward and backward when the signal after the Fourier transform exceeds a preset threshold value. The configuration includes an operation control unit 21 that supplies an operation signal based on the deviation to the unit 20.

As shown in FIG. 12, the resistor 16 can be moved into and out of the pilot diffusion combustion air passage 9 in any of a vertical direction and a transverse direction.

As described above, in the present embodiment, since the resistor driving unit 18 is provided for inserting and removing the resistor 16 into and out of the pilot diffusion combustion air passage 9, the resistor 16 is automated. In addition, the combustion oscillation can be suppressed more quickly and the combustion gas can be maintained in a stable state.

FIG. 13 is a partially cutaway conceptual view showing a sixth embodiment of the gas turbine combustor according to the present invention. The same components as those of the first embodiment are denoted by the same reference numerals.

The gas turbine combustor according to the present embodiment
Resistor that moves in and out of pilot diffusion combustion air passage 9
16, three types of resistors 1 having different diameters, for example, are cylindrical.
6a ₁, 16a₂, 16a₃Prepare these and advance and retreat
While trying to automate so that it can be put in and out,
Resistor 16a according to the magnitude of vibration₁, 16a₂, 16
a₃Select a resistor to select one of them properly.
The moving part 22 is provided.

The resistor selection drive section 22 detects the pressure fluctuation of the combustion chamber 2 and converts it into an electric signal.
When the electric signal from the pressure transducer 19 is amplified and subjected to frequency analysis, the frequency is subjected to Fourier transform, and when the signal after the Fourier transform exceeds a preset threshold value, the magnitude of the signal exceeds the predetermined threshold value. And a calculation control unit 23 for providing a signal from the resistor size selection unit 24 to the selection drive operation unit 25 in correspondence therewith. The selection drive operation unit 25 selects and selects the resistor 16 according to the magnitude of the combustion vibration. The resistor 16 is moved in and out of the pilot diffusion combustion air passage 9 so as to be able to advance and retreat.

As shown in FIG. 14, the resistor 16 allows the pilot diffusion / combustion air passage 9 to enter and exit the pilot diffusion combustion air passage 9 in both the vertical direction and the transverse direction. Resistor 16a
₃ , the resistor 16a ₂ having the next smallest diameter and the resistor 16a ₁ having the smallest diameter can be accommodated one after another. The diameters of the resistors 16a ₁ , 16a ₂ , 16a ₃ can be obtained from the above-described equation of the vortex row frequency n.

As described above, according to the present embodiment, the resistor selection drive unit 22 is provided for selecting the diameter of the resistor and inserting / removing the air into / out of the pilot diffusion combustion air passage 9, thereby achieving automation. With the selection of 16 and the response of faster driving, the combustion oscillation can be suppressed faster and lower to stabilize the combustion gas.

FIG. 15 is a partially cutaway conceptual view showing a seventh embodiment of the gas turbine combustor according to the present invention. The same components as those of the first embodiment are denoted by the same reference numerals.

The gas turbine combustor according to the present embodiment
An air passage 26 is provided concentrically with the pilot diffusion combustion nozzle 4 between the pilot diffusion combustion nozzle 4 inserted into the pilot diffusion combustion air passage 9 and the swirlers 10 and 10, and a perforated plate 27 is provided at the outlet side thereof. In addition, a flow valve 28 is provided on the inlet side.

In this embodiment, when the combustion gas is generated in the combustion chamber 2 and the diffusion combustion ratio is high, the opening of the flow valve 28 is opened more and the air passage 26 is opened as shown in FIG.
Thus, more air is supplied to the combustion chamber 2 through the perforated plate 27 to stabilize diffusion combustion.

Further, in the present embodiment, when the ratio of the lean premixed fuel is high (the diffusion combustion ratio is low), the opening of the flow valve 28 is narrowed to allow the air from the air passage 26 to the combustion chamber 2 via the perforated plate 27. The supply of air is reduced to stabilize diffusion combustion. At this time, the perforated plate 27 functions as a flame holding plate. Also, since the amount of air supplied from the air passage 26 to the combustion chamber 2 via the perforated plate 27 increases or decreases the amount of air supplied to the pilot diffusion combustion air passage 9, the total amount of air supplied to the gas turbine combustor is adjusted. There is no change in air volume.

As described above, in the present embodiment, the air passage 26 is provided concentrically outside the pilot diffusion combustion nozzle 4 and the air passage 2 is provided in accordance with the diffusion combustion ratio of the combustion gas.
Since air is supplied to the combustion chamber 2 from 6, the diffusion combustion can be stabilized and the combustion oscillation can be suppressed low.

FIG. 17 is a partially cutaway conceptual view showing an eighth embodiment of the gas turbine combustor according to the present invention. The same components as those of the first embodiment are denoted by the same reference numerals.

The gas turbine combustor according to the present embodiment
Similarly to the seventh embodiment, the pilot diffusion combustion nozzle 4 inserted into the pilot diffusion combustion air passage 9 and the swirler 1
0 and 10, an air passage 26 is provided concentrically with the pilot diffusion combustion nozzle 4, and a perforated plate 27
Is provided with an adjusting valve 31 on the inlet side, respectively, and an arithmetic control unit 30 for controlling the valve opening of the adjusting valve 31 is provided.

The arithmetic and control unit 30 amplifies the signal from the pressure converter 29 which detects the pressure fluctuation in the combustion chamber 2 and converts it into an electric signal, analyzes the frequency, performs a Fourier transform on the frequency, and performs a Fourier transform. When the signal exceeds a preset threshold value, a valve opening signal is calculated based on the deviation, and the valve opening calculation signal is given to the regulating valve 31 to control the valve opening, thereby adjusting the valve opening. As shown in FIG. 18, air is supplied from the valve 31 to the combustion chamber 2 through the air passage 26.

As described above, according to the present embodiment, the air passage 26 is provided concentrically outside the pilot diffusion combustion nozzle 4, and the regulating valve 31 interposed in the air passage 26 is provided.
And an arithmetic control unit 30 for giving a valve opening / closing signal calculated based on the pressure fluctuation of the combustion chamber 2.
Since the air supplied from is controlled and the diffusion combustion ratio is adjusted to an appropriate value, it is possible to automatically stabilize the diffusion combustion and suppress the combustion oscillation.

[0073]

As described above, the gas turbine combustor according to the present invention suppresses combustion vibration in a wide load range from low load to high load, and therefore prevents the wear of the combustor components. It is possible to maintain stable and reliable operation for a long time.

[Brief description of the drawings]

FIG. 1 is a partially cut-away schematic sectional view showing a first embodiment of a gas turbine combustor according to the present invention.

FIG. 2 is a partially enlarged conceptual view of a combustion chamber head side shown in FIG.

FIG. 3 is a sectional view taken in the direction of arrows AA in FIG. 2;

4A and 4B are graphs in which combustion vibration reduction of the gas turbine combustor according to the present invention is compared, wherein FIG. 4A is a graph of a vibration value when the resistor according to the present invention is not installed, and FIG. 6 is a graph of a vibration value when the resistor according to the present invention is installed.

FIG. 5 is a partially cutaway conceptual view showing a second embodiment of the gas turbine combustor according to the present invention.

FIG. 6 is a sectional view taken in the direction of arrows BB in FIG. 5;

FIG. 7 is a partially cutaway conceptual view showing a third embodiment of the gas turbine combustor according to the present invention.

FIG. 8 is a sectional view taken in the direction of arrows CC in FIG. 7;

FIG. 9 is a partially cutaway conceptual view showing a fourth embodiment of the gas turbine combustor according to the present invention.

FIG. 10 is a sectional view taken in the direction of arrow DD in FIG. 9;

FIG. 11 is a partially cutaway conceptual view showing a fifth embodiment of the gas turbine combustor according to the present invention.

FIG. 12 is a sectional view taken along the line EE in FIG. 11;

FIG. 13 is a partially cutaway conceptual view showing a sixth embodiment of the gas turbine combustor according to the present invention.

FIG. 14 is a sectional view taken along the line FF in FIG. 13;

FIG. 15 is a partially cutaway conceptual view showing a seventh embodiment of the gas turbine combustor according to the present invention.

FIG. 16 is a sectional view taken in the direction of arrows GG in FIG. 15;

FIG. 17 is a partially cutaway conceptual view showing an eighth embodiment of the gas turbine combustor according to the present invention.

FIG. 18 is a sectional view taken along the line HH of FIG. 17;

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Combustor liner 2 Combustion chamber 3 Pilot fuel nozzle 4 Pilot diffusion combustion nozzle 5 Pilot premix combustion nozzle 6 Fuel passage 7 Pilot diffusion fuel first passage 8 Pilot diffusion fuel second passage 9 Pilot diffusion combustion air passage 10, Reference Signs List 12 swirler 11 pilot premixed combustion air passage 13 pilot premixed combustion nozzle 14 pilot premixed header 15 premixed fuel passage 16, 17 resistor 18 resistor driver 19 pressure converter 20 drive operation unit 21 arithmetic control unit 22 Resistor selection drive unit 23 Operation control unit 24 Resistor sieve selection unit 25 Selection drive operation unit 26 Air passage 27 Perforated plate 28 Flow valve 29 Pressure transducer 30 Operation control unit 31 Adjustment valve

 ──────────────────────────────────────────────────続 き Continuing from the front page (72) Inventor Masanori Shimizu 4-1 Egasakicho, Tsurumi-ku, Yokohama-shi, Kanagawa Prefecture Inside the Energy and Environmental Research Laboratory, Tokyo Electric Power Company (72) Inventor Ya Yanaka Tsurumi, Yokohama-shi, Kanagawa Prefecture 2-4 Suehirocho, Ward Toshiba Keihin Works, Inc. (72) Inventor Fukuo Maeda 2-4 Suehirocho, Tsurumi-ku, Yokohama-shi, Kanagawa Prefecture Toshiba Keihin Works, Inc.

Claims (14)

[Claims] 1. A diffusion combustion nozzle which is inserted into a diffusion combustion air passage provided at a center of a head side of a combustion chamber, and a premix combustion nozzle which is arranged concentrically outside the diffusion combustion nozzle. A gas turbine combustor characterized in that a resistor is provided upstream of a swirler provided surrounding a diffusion combustion nozzle inserted into the diffusion combustion air passage. 2. The gas turbine combustor according to claim 1, wherein the resistor is disposed in at least one of a vertical direction and a transverse direction with respect to the diffusion combustion air passage. 3. The gas turbine combustor according to claim 1, wherein the resistor is formed in one of a rod shape and a plate shape. 4. A nozzle for diffusion combustion inserted in an air passage for diffusion combustion provided at the center of the head side of the combustion chamber, and a nozzle for premix combustion disposed concentrically outside the nozzle for diffusion combustion. In a gas turbine combustor, a resistor is provided between a swirler blade surrounding a diffusion combustion nozzle inserted into the diffusion combustion air passage and an adjacent swirler blade. Turbine combustor. 5. The gas turbine combustor according to claim 4, wherein the resistor is formed in a spherical shape. 6. A diffusion combustion nozzle inserted in a diffusion combustion air passage provided at the center of the head side of the combustion chamber, and a premix combustion nozzle disposed concentrically outside the diffusion combustion nozzle. In the gas turbine combustor, on the upstream side of the swirler installed surrounding the diffusion combustion nozzle that is inserted into the diffusion combustion air passage, a resistor that can freely move in and out of the diffusion combustion air passage is provided. A gas turbine combustor characterized in that: 7. A plurality of types of resistors having different diameters are formed in the diffusion combustion air passage so as to be able to move in and out of the air passage for diffusion combustion. 7. The gas turbine combustor according to claim 6, wherein a configuration is such that a small cylindrical resistor can be inserted. 8. A diffusion combustion nozzle inserted in a diffusion combustion air passage provided at the center of the head side of the combustion chamber, and a premix combustion nozzle arranged concentrically outside the diffusion combustion nozzle. In the gas turbine combustor, on the upstream side of the swirler installed surrounding the diffusion combustion nozzle inserted into the diffusion combustion air passage, a resistor that can freely move in and out of the diffusion combustion air passage, A gas turbine combustor comprising: a resistor driving unit that drives the resistor. 9. A resistor driving unit includes: a pressure converter for converting a pressure detected from a combustion chamber into an electric signal; a frequency analysis of a signal from the pressure converter; a Fourier transform of the frequency; When a signal exceeds a predetermined threshold value, a calculation control unit that calculates a driving force signal based on the deviation, and a drive operation unit that receives the calculation signal from the calculation control unit and drives the resistor 9. The gas turbine combustor according to claim 8, wherein: 10. A diffusion combustion nozzle which is inserted into a diffusion combustion air passage provided at the center of the head side of the combustion chamber, and a premix combustion nozzle which is arranged concentrically outside the diffusion combustion nozzle. In the gas turbine combustor, a plurality of pipes having different diameters which can be freely moved in and out of the diffusion combustion air passage are provided on the upstream side of a swirler provided surrounding the diffusion combustion nozzle inserted into the diffusion combustion air passage. A gas turbine combustor comprising: a resistor of the above-described type; and a resistor selection driving unit that drives the plurality of types of the resistors having different diameters. 11. A resistor selection driving unit includes: a pressure converter for converting pressure detected from a combustion chamber into an electric signal; a frequency analysis of a signal from the pressure converter; a Fourier transform of the frequency; and a Fourier transform. When the subsequent signal exceeds a predetermined threshold value, a signal from the resistor size selection section is provided to the selection drive section in accordance with the magnitude of the excess, and the resistor size is selected and driven. The gas turbine combustor according to claim 10, wherein the gas turbine combustor is combined with an arithmetic control unit that causes the gas turbine combustor to operate. 12. A diffusion combustion nozzle inserted into a diffusion combustion air passage provided at the center of the head side of the combustion chamber, and a premix combustion nozzle disposed concentrically outside the diffusion combustion nozzle. In the gas turbine combustor, an air passage is provided between the swirler and a diffusion combustion nozzle inserted into the diffusion combustion air passage, and air is supplied from the air passage to the combustion chamber in accordance with the diffusion combustion ratio. A gas turbine combustor characterized in that: 13. A diffusion combustion nozzle which is inserted into a diffusion combustion air passage provided at the center of the head side of the combustion chamber, and a premix combustion nozzle which is arranged concentrically outside the diffusion combustion nozzle. In the gas turbine combustor, the calculation is performed based on the air passage provided between the swirler and the diffusion combustion nozzle inserted into the diffusion combustion air passage, and the pressure fluctuation detected from the combustion chamber, and the calculation signal is obtained. An arithmetic control unit that, when a predetermined threshold value is exceeded, provides a valve opening signal calculated based on the deviation to a regulating valve interposed in the air passage; and a diffusion combustion ratio of the combustion chamber. A gas turbine combustor, characterized in that air supplied is controlled according to the height of a gas turbine. 14. The gas turbine combustor according to claim 12, wherein a perforated plate is provided on an outlet side of the air passage.