JPH0886407A - Gas turbine combustor - Google Patents

Abstract

PURPOSE: To provide a gas turbine combustor with higher reliability which achieves a further lowering of NOx below the conventional type. CONSTITUTION: A combustor has a first cylindrical combustion chamber 3 formed on the downstream side of a premixer 1, a premixer 2 which comprises a plurality of premixing chambers divided in the circumferential direction of the first combustion chamber 3 and is arranged surrounding the first combustion chamber 3 and a second cylindrical combustion chamber 4 which is larger in sectional area with respect to the direction of the main stream of a combustion gas than the first combustion chamber 3 and formed on the downstream side of the first combustion chamber 3. The premixer 2 is made to communicate with the circumferential surface of the first combustion chamber 3 by a communication means while the communication means is provided with a means to make premixed gases 12 formed in the individual premixing chambers jet to the first combustion chamber 3 in such a manner as to have a swirl component in the same direction.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a combustor, and more particularly to a gas turbine combustor for electric power suitable for reducing nitrogen oxides.

[0002]

2. Description of the Related Art A gas turbine combustor employs a premixed combustion system in which fuel and air are premixed and burned in order to reduce nitrogen oxides (hereinafter referred to as NOx) contained in combustion gas. . Compared with the diffusion combustion method in which the fuel and air are separated and burned, this premixed combustion method reduces the fuel concentration to prevent the local high temperature region from being generated, and the amount of NOx contained in the exhaust gas. It is excellent in that it can reduce

As a gas turbine combustor capable of reducing the amount of NOx contained in the exhaust gas, a gas turbine combustor which controls the fuel flow rate is known.

The control means for controlling the fuel flow rate supplies fuel to the premixer up to the rated rotation speed (no-load operation) of the gas turbine, that is, up to the rotation speed of the gas turbine at which the generator can be connected to generate electricity. Only air is supplied without jetting. After that, when the gas turbine reaches the rated speed, the load is input (the generator is connected to the gas turbine to generate electricity), that is, from the load increase operation of the gas turbine to the rated load operation, fuel is gradually supplied to the air to perform premixing. It is the formation of Qi.

A gas turbine combustor capable of reducing the amount of NOx contained in exhaust gas is disclosed in, for example, Japanese Patent Laid-Open No.
The one described in 5-264037 is known.

[0006]

The above-mentioned conventional technique is one of the effective means for reducing the amount of NOx contained in the exhaust gas. However, on the other hand, the N contained in the exhaust gas
Regulation of Ox amount is becoming more and more strict.

However, in the above-mentioned conventional technique,
It has not been possible to sufficiently reduce NOx, and it is feared as a major issue in the future.

The present invention has been made in view of the above points, and an object thereof is to provide a highly reliable gas turbine combustor capable of further reducing NOx as compared with a conventional gas turbine combustor. , Providing equipment using the gas turbine combustor.

[0009]

The above objects are achieved by the following. In the following description, the main flow direction of the combustion gas means the direction of the central axis of the combustor unless otherwise specified.

In order to achieve the above object, a premixing chamber for forming a premixed mixture by mixing fuel and air is formed around a cylindrical combustion chamber, and the premixed mixture is burned to obtain a combustion gas. In the gas turbine combustor, the premixing chamber is arranged so as to surround the tubular combustion chamber, and a plurality of communication means for communicating the premixing chamber and the tubular combustion chamber are provided, and the plurality of communication means are provided. The premixed gas produced in the premixing chamber is injected through the communicating means so as to have a swirling component in the same direction.

Further, in order to achieve the above object, a premixing chamber for forming a premixed mixture by mixing fuel and air is formed around a cylindrical combustion chamber, and the premixed mixture is burned to form combustion gas. In the gas turbine combustor for obtaining the above, a plurality of the premixing chambers are arranged in the circumferential direction so as to surround the cylindrical combustion chamber, and a communication means for communicating each premixing chamber with the cylindrical combustion chamber is provided. , The premixed gas produced in each of the premixing chambers is injected through the communicating means so as to have a swirl component in the same direction.

Further, in order to achieve the above object, a premixing chamber for forming a premixed mixture by mixing fuel and air is formed around a cylindrical combustion chamber, and the premixed mixture is burned to form combustion gas. In the gas turbine combustor for obtaining the above, a plurality of the premixing chambers are arranged in the circumferential direction so as to surround the cylindrical combustion chamber, and a communication means for communicating each premixing chamber with the cylindrical combustion chamber is provided. The premixed gas produced in each of the premixing chambers is injected through the communicating means while being inclined in the circumferential direction of the cylindrical combustion chamber.

In order to achieve the above object, a premixing chamber for forming a premixed mixture by mixing fuel and air is formed around a cylindrical combustion chamber, and the premixed mixture is burned to form combustion gas. In the gas turbine combustor to obtain, a plurality of the premixing chambers are arranged in the circumferential direction so as to surround the tubular combustion chamber, and an opening portion that connects each premixing chamber and the tubular combustion chamber is provided, In addition, a structure constructed by tilting in the circumferential direction of the cylindrical combustion chamber is provided in the opening.

In order to achieve the above-mentioned object, a premixing chamber for forming a premixed mixture by mixing fuel and air is formed around a cylindrical combustion chamber, and the premixed mixture is burned to form combustion gas. In the gas turbine combustor for obtaining the above, the premixing chamber is arranged so as to surround the cylindrical combustion chamber, and a plurality of communication pipes that connect the premixing chamber and the cylindrical combustion chamber are provided, and The plurality of communication pipes are inclined in the circumferential direction of the cylindrical combustion chamber.

In order to achieve the above object, a premixing chamber for forming a premixture by mixing fuel and air is formed around the cylindrical first combustion chamber, and the premixture is burned. In a gas turbine combustor for obtaining combustion gas by means of a cylindrical first combustion chamber, a downstream side of the cylindrical first combustion chamber has a cross-sectional area in the main flow direction of the combustion gas larger than that of the cylindrical first combustion chamber. Two combustion chambers are provided, and a plurality of the premixing chambers are circumferentially arranged so as to surround the cylindrical first combustion chamber, and an opening portion that connects each premixing chamber and the cylindrical combustion chamber to each other. And a structure constructed by tilting in the circumferential direction of the cylindrical first combustion chamber is provided in the opening.

Further, in order to achieve the above object, a premixing chamber for forming a premixed mixture by mixing fuel and air is formed around the cylindrical first combustion chamber, and the premixed mixture is burned. In a gas turbine combustor for obtaining combustion gas by providing a pilot burner for injecting and diffusing the fuel and air separately, the pilot burner is provided in the center of the combustor, and the tubular first combustion is provided downstream of the pilot burner. A chamber, and a tubular second combustion chamber having a cross-sectional area with respect to the main flow direction of the combustion gas larger than that of the tubular first combustion chamber is provided downstream of the tubular first combustion chamber. At the same time, a plurality of the premixing chambers are circumferentially arranged so as to surround the cylindrical first combustion chamber, and an opening is provided to connect each premixing chamber and the cylindrical combustion chamber, and the opening is provided. Structure in which a portion is inclined in the circumferential direction of the cylindrical first combustion chamber In which the provided.

A premixer having a premixing chamber for mixing the fuel and air to form a premixed gas is provided in the center of the combustor, and the premixed gas is provided in the circumferential direction of the premixer. Swirling means for swirling may be provided on the outlet side of the premixer.

[0018]

The premixing chamber is arranged so as to surround the tubular combustion chamber, and a plurality of communicating means for communicating the premixing chamber and the tubular combustion chamber are provided, and the premixing chamber is provided through the plurality of communicating means. A swirling flow is formed in the cylindrical combustion chamber by injecting the premixed gas produced in (1) so as to have a swirling component in the same direction.

In the swirling flow, a plurality of premixing chambers are arranged in the circumferential direction so as to surround the cylindrical combustion chamber, and a communication means is provided for communicating each premixing chamber with the cylindrical combustion chamber.
It is formed by injecting the premixed gas produced in each premixing chamber via the communicating means so as to have a swirl component in the same direction.

In the swirling flow, a plurality of premixing chambers are arranged in the circumferential direction so as to surround the cylindrical combustion chambers, and a communication means for communicating each premixing chamber with the cylindrical combustion chamber is provided.
It is formed by injecting the premixed gas produced in each premixing chamber through the communicating means while inclining it in the circumferential direction of the cylindrical combustion chamber.

In the swirling flow, a plurality of premixing chambers are arranged in the circumferential direction so as to surround the cylindrical combustion chamber, and an opening is provided to connect each premixing chamber with the cylindrical combustion chamber. It is formed by providing the opening with a structure that is inclined in the circumferential direction of the cylindrical combustion chamber.

In the swirling flow, a premixing chamber is arranged so as to surround a cylindrical combustion chamber, a plurality of communication pipes for connecting the premixing chamber and the cylindrical combustion chamber are provided, and a plurality of communication pipes are provided. It is formed by tilting the tube in the circumferential direction of the cylindrical combustion chamber.

The swirling flow thus formed was obtained by a pilot burner provided in the center of the combustor in another tubular combustion chamber provided on the downstream side of the tubular combustion chamber. Combustion gas is drawn in and flows in. That is, when the tubular combustion chamber is referred to as a tubular first combustion chamber, the tubular first combustion chamber is provided downstream of the tubular first combustion chamber and has a tubular cross-sectional area in the main flow direction of the combustion gas.
The combustion gas is entrained and flows into the second combustion chamber having a cylindrical shape larger than the combustion chamber. At this time, since the cross-sectional area of the cylindrical second combustion chamber with respect to the main flow direction of the combustion gas is large, the swirling flow flowing into the cylindrical second combustion chamber has a rapid axial flow velocity. A large circulation flow is formed in the second combustion chamber, which is reduced and has a cylindrical shape. This circulation flow causes the mixed gas of the combustion gas and the premixed gas formed in the premixing chamber arranged so as to surround the cylindrical first combustor to stay for a long time. This can promote combustion of the pilot flame.
That is, the unburned fuel of the pilot flame can be reliably burned in the cylindrical second combustion chamber.

Further, since the mixed gas of the combustion gas and the premixed gas formed in the premixing chamber arranged so as to surround the cylindrical first combustor is retained for a long time, it is supplied from the premixing chamber. Even if the premixed gas is leaner than the flame propagation limit, the premixed gas can sufficiently react and the reaction heat can be taken out. As a result, the load can be taken even in the state of the premixture leaner than the flame propagation limit. Therefore, premixed combustion can be performed in a wide load range, and NOx can be reduced.

Further, due to the above circulation flow, the flame formed in the combustion chamber 3 in the cylindrical second combustion chamber can be stabilized.

Further, as in the present invention, a premixer having a premixing chamber for mixing a fuel and air to form a premixed gas is provided at the center of the combustor, and the premixed gas is supplied to the periphery of the premixer. By providing the swirling means for swirling in the direction on the outlet side of the premixer, the following effects can be obtained. That is, it can be explained by the following theoretical consideration. When the pressure is P, the density is ρ, the swirling flow velocity is W, the axial distance is x, the radial distance is r, and the radius of the combustor is R, the following relationships are established in the swirling flow field.

[0027]

[Equation 1] (∂P / ∂x) _{r = 0} ~ (∂P / ∂x) _{r = R} −∂∫ (ρW ² / r) dr / ∂x (1) The central axis pressure gradient is centrifugal. It increases in proportion to the axial damping rate of the force. The backflow velocity increases as the pressure gradient of the central axis increases. Therefore, in order to increase the backflow velocity, the centrifugal force may be weakened toward the downstream side. Compared to the case where the turning strength is constant in the radial direction, when the turning strength at the outer peripheral portion is made smaller than that at the inner peripheral portion as in the present invention, the inner circumference that strongly affects the centrifugal force The swirling flow velocity in the portion (r: small) can be effectively attenuated in the axial direction. Therefore, it is possible to increase the backflow velocity and improve the stability of the flame.

[0028]

Embodiments of the present invention will now be described in detail with reference to the drawings.

FIG. 1 is a sectional view showing a cross section of a combustor which is a first embodiment of the present invention, FIG. 4 is a detailed view around an outlet of the premixer 1 of FIG. 1, and FIG. 10 is a premixing of FIG. It is the sectional view which looked at the circumference of the exit of the burner 2 from the central axis direction of the combustor.

In the drawing, a cylindrically formed combustor has a first premixer 1 arranged in the central portion thereof. The first premixer 1 has a plurality of fuel nozzles 5 for injecting fuel 9 at its inlet side, and a fuel nozzle 7 (pilot for extending to its outlet side and injecting fuel 9 at the outlet side of the first premixer 1). Fuel nozzle for combustion). Further, the first premixer 1 is provided with a swirl vane 8 which swirls the premixed gas 11 on the outlet side thereof.

On the downstream side of the first premixer 1, a cylindrical first
Of the first combustion chamber 3 is formed around the first combustion chamber 3.
A plurality of premixing chambers divided in the circumferential direction of the combustion chamber 3 of
The second premixer 2 arranged so as to surround the combustion chamber 3 of the
Is formed. The second premixer 2 communicates with the peripheral surface of the first combustion chamber 3 by a communicating means, and the premixed gas 12 formed in each premixing chamber is connected to this communicating means with a swirling component in the same direction. It also has means for injecting it into the first combustion chamber 3. In this embodiment, as the communication means,
An opening (an outlet of the second premixer 2) that opens on the circumferential surface of the first combustion chamber 3 is formed, and a predetermined elevation angle in the circumferential direction of the first combustion chamber 3 is formed in this opening. It is provided with a blade-shaped structure 6 having a substantially triangular shape inclined with respect to.

Further, the second premixer 2 has its inlet in the longitudinal direction of the second premixer 2 so that the air 10 supplied to the inlet side becomes a turbulent flow in each premixing chamber. It is formed almost at a right angle. In this example,
Although the above-mentioned configuration is adopted as the means for generating the turbulent flow, it is not limited to this, and a swirl vane may be provided on the inlet side of the premixer 5a, or a slit portion may be formed at the inlet. Let's do it.

On the downstream side of the first combustion chamber 3, a cylindrical second combustion chamber 4 having a larger cross-sectional area in the main flow direction of the combustion gas than the first combustion chamber 3 is formed. here,
The cross-sectional area of the second combustion chamber 4 in the main flow direction of the combustion gas is larger than that of the first combustion chamber 3 because the combustion gas flowing from the first combustion chamber 3 into the second combustion chamber 4 is As described above in order to reduce the flow velocity, as is clear from the figure, the boundary between the first combustion chamber 3 and the second combustion chamber 4 is the second combustion chamber 3 to the second combustion chamber 3. It can be seen that the chamber 4 has a step down.

In this embodiment, the shapes of the first combustion chamber 3 and the second combustion chamber 4 formed in a tubular shape (the shape of the cross section)
There are various shapes, but in this embodiment,
As a shape for achieving the operation described later, a circular shape is particularly preferable. Further, the structure 6 provided in the opening formed on the peripheral surface of the first combustion chamber 3 and inclined with a predetermined elevation angle is a blade having a substantially triangular shape, but is not limited to this. Instead, the premixed gas 12 discharged from each premixing chamber may be injected into the first combustion chamber 3 so as to have a swirl component in the same direction.

The combustor of this embodiment is constructed as described above, and its operation will be described in detail below.

The air 10 supplied to the inlet side of the first premixer 1 and the fuel 9 ejected from the plurality of fuel nozzles 5 are diffused in the first premixer 1 by premixing. 11
While flowing toward the outlet side of the first premixer 1 and is discharged to the first combustion chamber 3 via the swirl vanes 8 to form the premix flame 13. At this time, a strong swirl is applied to the premixed gas 11 by the swirl vanes 8 in the circumferential direction of the first premixer 1 to form a swirl flow. At this time, the high temperature burned gas 14 obtained by the combustion of the premixed flame 13 is the swirling blade 8
Due to the action of the swirling flow formed by, an inverse region is formed near the central axis of the premixed flame 13, and the stagnation region near the central axis of the premixed flame 13 is reduced. This allows premixed flame 1
The circulating flow generated near the central axis of 3 can be stabilized. Therefore, it is possible to prevent the premixed flame 13 from being blown out and to stabilize the premixed flame 13. Further, since the circulation flow generated near the central axis of the premixed flame 13 can be stabilized, the vibration associated with the fluctuation of the flame can be reduced.

Fuel 9 is injected from the fuel nozzle 7 to the outlet side of the first premixer 1. The fuel 9 reacts with the high-temperature burned gas obtained by the combustion of the premixed flame 13 and burns to form a diffusion flame 107 inside the premixed flame 13. Thereby, the premix flame 13 can be further stabilized.

The present embodiment is also effective for supplying the fuel 9 through the fuel nozzle 7 for pilot combustion, but when pilot combustion is used together, flame stability is better and lean fuel is used. Since combustion is possible, NOx can be reduced.

On the other hand, each premix chamber of the second premixer 2 is supplied with air 10 from its inlet side and mixes with the fuel injected from the fuel nozzle 5 to form a premixture. On this occasion,
The air 10 becomes a turbulent flow because the inlet of the premix chamber is formed substantially at right angles to the longitudinal direction of the second premixer 2, and promotes mixing with the fuel 9. The premixed gas 12 formed in each premixing chamber flows toward the outlet side of the premixing chamber,
The gas is discharged into the first combustion chamber 3 through the communication means, that is, the opening, formed on the peripheral surface of the first combustion chamber 3. At this time, the premixed gas 12 formed in each of the premixing chambers has a substantially triangular blade-like structure inclined at a predetermined elevation angle in the circumferential direction of the first combustion chamber 3 provided in the opening. By item 6,
The fuel is injected while being inclined in the circumferential direction of the first combustion chamber 3. That is, the premixed gas 12 formed in each premixing chamber is injected so as to have a swirling component in the same direction, whereby a large swirling flow 16 is formed in the first combustion chamber 3. Swirling flow 16
Is entrained in the combustion gas obtained in the first premixer 1 and flows into the second combustion chamber 4 formed on the downstream side of the first combustion chamber 3.

Here, the second combustion chamber 4 is the first combustion chamber 3
Since the cross-sectional area of the combustion gas in the main flow direction is larger than that of the combustion gas, the swirling flow 16 flowing into the second combustion chamber 4 is
The flow velocity in the rotation axis direction is sharply reduced, and a large circulation flow 17 is formed in the second combustion chamber 4. In the present embodiment, the circulation flow 17 formed in the second combustion chamber 4 causes the mixed gas of the high temperature combustion gas obtained by the combustion of the premixed flame 13 and the premixed gas 12 to stay for a long time.

The configuration and operation of the combustor of this embodiment have been described above in detail. The combustor of this embodiment is operated according to the operation method described below.

First, a method of operating the first premixer 1 will be described with reference to FIG. FIG. 19 shows the NOx amount on the vertical axis
(ppm), the fuel-air ratio of the premixed gas is plotted on the horizontal axis, and the NOx emission amount with respect to the fuel-air ratio of the premixed fuel at atmospheric pressure is a characteristic diagram obtained by experiments. Here, the curve 28 is the NOx emission amount with respect to the fuel-air ratio of the premixed gas when fuel is not jetted from the fuel nozzle 7 (fuel nozzle for pilot combustion), and the curve 27 is the fuel nozzle 7 (for pilot combustion). 2 shows the NOx emission amount with respect to the fuel-air ratio of the premixed gas when fuel is ejected from the fuel nozzle).

In the characteristic diagram, when the two curves are compared, the case where fuel is ejected from the fuel nozzle 7 (curve 2) is compared with the case where fuel is not ejected from the fuel nozzle 7 (curve 28).
It can be seen that in 7), it is possible to burn up to a premixed gas with a smaller fuel-air ratio. Therefore, from the relationship of this characteristic diagram, the first premixer 1 is operated as follows. In the description of this embodiment, the limit value (dotted line) of the NOx amount contained in the combustion gas is 20 ppm (16% oxygen paraphrase).

At the beginning (the fuel-air ratio of the premixed gas is low), fuel is jetted from the fuel nozzle 7 to burn the premixed gas 11, and the amount of NOx discharged reaches or is close to the limit value. When the fuel-air ratio of the premixed air becomes high, the injection of fuel from the fuel nozzle 7 is stopped and only the premixed air 11 is burned. That is, the first along the illustrated ABCD (thick line)
The premixer 1 is operated. As a result, the first premixer 1 can be operated from the point a to the point c when the fuel-air ratio of the premixed gas is from the point a to the point c (when the fuel nozzle 7 is not injected). Compared with, it can be operated in a wider load range. It should be noted that this operating method is not only effective during load operation of the gas turbine, but also effective when starting the gas turbine.

On the other hand, the second premixer 2 starts from the fuel nozzle 5 up to the rated rotational speed of the gas turbine (no-load operation), that is, up to the rotational speed of the gas turbine capable of generating power by connecting the generator. Only the air 10 is discharged to the first combustion chamber 3 through the opening of each premixing chamber formed on the peripheral surface of the first combustion chamber 3 without ejecting fuel. As described above, the premixed gas formed in the premixing chamber 12 is formed in the opening of each premixing chamber.
Is provided with a vane-shaped structure 6 having a substantially triangular shape inclined at a predetermined elevation angle in the circumferential direction of the first combustion chamber 3 so that the components have swirling components in the same direction. A swirling flow 16 of air 10 is formed in the combustion chamber 3,
The swirling flow 16 entrains the premixed flame 13 and flows into the second combustion chamber 4 formed on the downstream side of the first combustion chamber 3.

As described above, the second combustion chamber 4 formed on the downstream side of the first combustion chamber 3 has a larger cross-sectional area in the main flow direction of the combustion gas than that of the first combustion chamber 3. Since it is formed, the swirl flow 1 that has flowed into the second combustion chamber 4
6, the flow velocity in the axial direction is sharply reduced, and a large circulation flow 17 is formed in the second combustion chamber 4. This allows
In the second combustion chamber 4, the mixed gas of the combustion gas obtained in the first premixer 1 and the air 10 discharged from the second premixer 2 stays for a long time, and the premixed flame 14 Promotes complete combustion. That is, the unburned fuel of the premixed flame 14 can be reliably burned in the second combustion chamber 4.

After the gas turbine reaches the rated speed and the load is applied (the generator is connected to the gas turbine to generate electricity), that is, from the load increasing operation to the rated load operation of the gas turbine,
Combustion 9 is injected into each premixing chamber from the fuel nozzle 5 and mixed with air 10 supplied from the inlet side of each premixing chamber to form a premixed gas 12. The formed premixed gas 12 is discharged into the first combustion chamber 3 from the opening of each premixing chamber formed on the peripheral surface of the first combustion chamber 3. At this time, the premixed gas 12 is discharged into the combustion chamber 2 via the blades 12 arranged at the outlet of the vessel 5a provided at the opening. As described above, the premixed gas 12 formed in the premixing chamber has a predetermined elevation angle in the circumferential direction of the first combustion chamber 3 so that the premixed gas 12 formed in the premixing chamber has a swirling component in the same direction. Since the inclined vane-shaped structure 6 having a substantially triangular shape is provided, the swirl flow 16 due to the premixed gas 12 is formed in the first combustion chamber 3, and the swirl flow 16 is The second gas formed in the downstream side of the first combustion chamber 3 by entraining the combustion gas obtained in the premixer 1
Flows into the combustion chamber 4.

As described above, the second combustion chamber 4 formed on the downstream side of the first combustion chamber 3 has a larger cross-sectional area in the main flow direction of the combustion gas than that of the first combustion chamber 3. Since it is formed, the swirl flow 1 that has flowed into the second combustion chamber 4
6, the flow velocity in the axial direction is sharply reduced, and a large circulation flow 17 is formed in the second combustion chamber 4. This allows
The mixed gas of the combustion gas obtained in the first premixer 1 and the premixed gas 12 discharged from the second premixer 2 stays in the second combustion chamber 4 for a long time. As a result, even if the premixed gas 12 supplied from the second premixer 2 is leaner than the flame propagation limit (in this case, the fuel is lean), the reaction heat can be sufficiently taken out, that is, the slow combustion can be performed. It can be performed, and a load can be taken even in such a state. Therefore, premixed combustion (combustor operation) can be performed in a wide load range, and the amount of NOx emission can be reduced by lean fuel. Further, the flame can be stabilized by the circulation flow 17 formed in the second combustion chamber 4.

Further, according to the present embodiment, the fuel control can be performed in accordance with the air flow rate determined by the width of the air flow path, so that the air provided at the inlet of the premixer and supplied to the inlet of the premixer can be controlled. It can also be applied to a gas turbine combustor having adjusting means for adjusting the amount. This eliminates the need for highly accurate control of the air flow width, which has been used to prevent backfire and blowout of flames, and makes the control system simple.

Further, since the amount of air supplied to the gas turbine combustor, which is usually installed in about 1 to 14 cans, is not required for each combustor, the operability of the gas turbine combustor can be improved. it can.

The second embodiment of the present invention will be described in detail with reference to FIG. 2 is a sectional view showing a section of the combustor as in FIG. The combustor formed in a cylindrical shape has an injection hole for injecting fuel in the central portion thereof, and an intake port for taking in the air 10. The air 10 taken in through the intake port causes the fuel to be injected from the injection port. A pre-mixing chamber is provided around the pilot burner 18, which is provided with a plurality of fuel nozzles 5 on the upstream side thereof.

Further, as in the previous example, a plurality of premixing chambers divided in the circumferential direction of the first combustion chamber 3 are arranged around the first combustion chamber 3 so as to surround the first combustion chamber 3. The second premixer 2 is formed, and each premixing chamber and the circumferential surface of the first combustion chamber 3 are communicated with each other by a communicating means (opening), and each premixing chamber is connected to this communicating means. Premixture 1 formed by
Means for injecting 2 into the first combustion chamber 3 so as to have a swirling component in the same direction (a vane-shaped structure having a substantially triangular shape inclined at a predetermined elevation angle in the circumferential direction of the first combustion chamber 3) 6) is provided. Further, on the downstream side of the first combustion chamber 3, a cylindrical second combustion chamber 4 having a larger cross-sectional area in the flow direction of the combustion gas than that of the first combustion chamber 3 is formed. The cross-sectional area with respect to the flow direction is larger than that of the first combustion chamber 3. The other parts, operation and operating method of the combustor of this embodiment are the same as those of the first embodiment, and therefore their explanations are omitted.

According to the present embodiment, the swirling flow 16 of the air 10 is kept in the pilot burner up to the rated rotational speed of the gas turbine (no-load operation), that is, up to the rotational speed of the gas turbine at which the generator can be connected to generate electric power. The combustion gas obtained in 18 is entrained and flows into the second combustion chamber 4. As a result, the mixed gas of the high-temperature combustion gas obtained by the combustion of the pilot flame and the air 10 discharged from the second premixer 2 stays for a long time and promotes complete combustion of the pilot flame. That is, the unburned fuel of the pilot flame can be reliably burned in the second combustion chamber 4.

After the gas turbine reaches the rated speed and the load is applied (the generator is connected to the gas turbine to generate electricity), that is, from the load increasing operation to the rated load operation of the gas turbine,
A swirl flow 16 due to the premixed gas 12 is formed in the first combustion chamber 3, and the swirl flow 16 is formed downstream of the first combustion chamber 3 by entraining the combustion gas obtained by the pilot burner 18. The mixed gas of the combustion gas obtained by the pilot burner 18 and the premixed gas 12 discharged from the second premixer 2 flows into the second combustion chamber 4 and stays there for a long time. As a result, even if the premixed gas 12 supplied from the second premixer 2 is leaner than the flame propagation limit (in this case, the fuel is lean), the reaction heat can be sufficiently taken out, that is, the slow combustion can be performed. It can be performed, and a load can be taken even in such a state. Therefore, premixed combustion (combustor operation)
Can be used in a wide load range, and NO
The emission amount of x can be reduced. Further, the flame can be stabilized by the circulation flow 17 formed in the second combustion chamber 4.

The third embodiment of the present invention will be described in detail with reference to FIG. FIG. 3 is a sectional view showing a section of the combustor as in FIG. The first premixer 1 is arranged in the central part of the combustor formed in a cylindrical shape. First of the present embodiment
The premixer 1 includes a swirl vane 8 formed in a tapered shape on the inlet side thereof, and a fuel nozzle 5 having one end connected to the central portion of the swirl vane 7 and injecting fuel 9 from the central portion. .

From the inlet side of the first premixer 1 the swirl vane 8
The air 10 supplied into the premixer 1 via is swirled in the circumferential direction of the first premixer 1 by the swirl vane 8,
The formed swirl flow is the fuel 9 injected from the fuel nozzle 5.
Are mixed to form a premixed gas 11. The swirling flow of the premixed gas 11 advances toward the downstream side and is discharged to the first combustion chamber 3. When the swirling flow of the premixed gas 11 is discharged to the first combustion chamber 3, the flow velocity in the rotation axis direction is reduced, so that the first combustion chamber 3 is obtained with the fuel of the premixed gas 11. A circulating stream 19 is formed by the hot burnt gas. The circulating flow 19 serves as a flame holding mechanism, and thereby a premixed flame (not shown) can be stably held.

Further, as in the previous example, a plurality of premixing chambers divided in the circumferential direction of the first combustion chamber 3 are arranged around the first combustion chamber 3 so as to surround the first combustion chamber 3. The second premixer 2 is formed, and each premixing chamber and the circumferential surface of the first combustion chamber 3 are communicated with each other by a communicating means (opening), and each premixing chamber is connected to this communicating means. Premixture 1 formed by
Means for injecting 2 into the first combustion chamber 3 so as to have a swirling component in the same direction (a vane-shaped structure having a substantially triangular shape inclined at a predetermined elevation angle in the circumferential direction of the first combustion chamber 3) 6) is provided. Further, on the downstream side of the first combustion chamber 3, a cylindrical second combustion chamber 4 having a larger cross-sectional area in the flow direction of the combustion gas than that of the first combustion chamber 3 is formed. Is formed to have a cross-sectional area in the main flow direction larger than that of the first combustion chamber 3. In addition, other parts,
The operation and operating method of the combustor of this embodiment are the same as those of the first embodiment, so the description thereof will be omitted.

According to this embodiment, the swirling flow 16 of the air 10 reaches the first rotation speed up to the rated rotation speed of the gas turbine (no-load operation), that is, up to the rotation speed of the gas turbine capable of generating power by connecting the generator. The combustion gas obtained in the premixer 1 is entrained and flows into the second combustion chamber 4. As a result, the mixed gas of the combustion gas obtained in the first premixer and the air 10 discharged from the second premixer 2 stays for a long time and promotes complete combustion of the premixed flame. That is, the unburned fuel of the premixed flame can be reliably burned in the second combustion chamber 4.

After the gas turbine reaches the rated speed and the load is applied (the generator is connected to the gas turbine to generate electricity), that is, from the load increasing operation to the rated load operation of the gas turbine,
A swirl flow 16 is formed in the first combustion chamber 3 by the premixed gas 12. The swirl flow 16 entrains the combustion gas obtained in the first premixer 1 and is downstream of the first combustion chamber 3. Mixture gas of the combustion gas obtained in the first premixer 1 and the premixed gas 12 discharged from the second premixer 2 flows into the second combustion chamber 4 formed in To do. As a result, even if the premixed gas 12 supplied from the second premixer 2 is leaner than the flame propagation limit (in this case, the fuel is lean), the reaction heat can be sufficiently taken out, that is, the slow combustion can be performed. It can be performed, and a load can be taken even in such a state. Therefore, the premixed combustion (the operation of the combustor) can be performed in a wide load band, and the NOx emission amount can be reduced by the lean fuel. Further, the flame can be stabilized by the circulation flow 17 formed in the second combustion chamber 4.

FIGS. 5 to 9 show another embodiment of the above-described FIGS. 1 and 3, and show detailed views around the outlet of the first premixer 1.

FIG. 5 is a detailed view showing another embodiment of the fuel nozzle 7 (fuel nozzle for pilot combustion). In this embodiment, the fuel injection hole at the outlet is formed in a two-fold shape (Y shape). When the fuel nozzle 7 is formed in this way, the fuel 9 injected from the fuel nozzle 7 is injected not toward the swirl axis direction of the swirl flow formed by the swirl vanes 8 but toward the swirl flow. As a result, the fuel 9 injected from the fuel nozzle 7 does not immediately flow out to the downstream side, but the residence time in the first combustion chamber 3 increases due to the swirling swirling flow. Therefore, the unburned amount can be reduced.

FIG. 6 shows another embodiment of the swirl vane 8 provided on the outlet side of the first premixer 1. In this embodiment, the swirl vane 8 is provided in a tapered shape. By doing so, the swirl strength of the swirl flow near the swirl axis becomes stronger, the stagnation region near the central axis of the premixed flame can be reduced, and the circulating flow near the central axis can be stabilized. . Therefore, it is possible to prevent blowout of the flame and improve the stability of the flame. Further, the stability of the circulating flow near the central axis can reduce vibrations associated with fluctuations of the flame.

The above effect can be further improved by the double swirl vane shown in FIG. That is, the swirling flow formed in the double swirl vanes (inner swirl vane 7a, outer swirl vane 7b) forms an inverse region near the center of the premixed flame, but at this time, it is formed by the inner swirl vane 7a. The swirl number represented by the ratio of the circumferential momentum to the axial momentum of the swirling flow, in other words, the strength of the swirl represented by the ratio of the circumferential flow velocity to the axial flow velocity, is formed by the outer swirling splashes 7b. Greater than swirling flow. As a result, the reverse region formed near the center of the premixed flame is expanded. Therefore, the stagnation region near the center of the premixed flame can be further reduced, so that the above effect can be further improved.

Further, as shown in FIG.
It goes without saying that the above effect can be improved by tapering a or by tapering both the inner swirl vane 7a and the outer swirl vane 7b as shown in FIG.

In the embodiment shown in FIGS. 5 to 9, the mixing of fuel and air is promoted, so NOx can be reduced as compared with diffusion combustion.

11 and 12 are the same as those shown in FIGS.
It is another embodiment, and shows a cross-sectional view and a perspective view of the periphery of the outlet of the second premixer 2 as seen from the flow direction of the combustion gas.

In FIG. 11, the second premixer 2 formed around the first combustion chamber 3 so as to surround the first combustion chamber 3 comprises one premixing chamber. The second premixer 2 communicates with the peripheral surface of the first combustion chamber 3 by a plurality of communicating means, and the plurality of communicating means distributes the premixed gas 12 formed in the premixing chamber in the same direction. The first combustion chamber 3 is inclined by a predetermined angle in order to inject it into the first combustion chamber 3 so as to have a swirling component. In this embodiment, as the communication means, a communication pipe is connected to the peripheral surface of the first combustion chamber 3, and the communication pipe is inclined at a predetermined angle in the circumferential direction of the first combustion chamber 3. is there. When the second premixer 2 is formed in this way, the premixed gas 12 formed in the premixing chamber is
Similar to the embodiment of FIG. 10 described above, the fuel is injected while being inclined in the circumferential direction of the first combustion chamber 3. That is, the premixed gas 12 formed in each premixing chamber is injected so as to have a swirling component in the same direction, whereby a large swirling flow 16 is formed in the first combustion chamber 3. According to the present embodiment, the premixed gas 12 can be surely injected so as to have a swirl component in the same direction. Therefore, the reliability of the combustor can be improved. Further, it is not necessary to partition the inside of the second premixer 2 and a structure for generating a swirling flow is not required, so that the structure of the combustor can be simplified.

FIG. 11 shows the first combustion chamber 3 shown in FIG.
5 is another embodiment of the vane-shaped structure 6 having a substantially triangular shape inclined at a predetermined elevation angle in the circumferential direction. In this embodiment, an L-shaped baffle plate 21 is provided in the communication means (opening) that connects the premixing chamber and the peripheral surface of the first combustion chamber 3. In this way, the premixed gas 12 formed in the premixing chamber is injected into the first combustion chamber 3 via the communication means that communicates with the circumferential surface of the first combustion chamber 3. On this occasion,
The premixed gas 12 is injected by being inclined in the circumferential direction of the first combustion chamber 3 by the L-shaped baffle plate 21. That is, the premixed gas 12 formed in each premixing chamber is injected so as to have a swirling component in the same direction, whereby a large swirling flow 16 is formed in the first combustion chamber 3. Therefore, as shown in FIG.
It is possible to obtain the same effect as that of the embodiment.

FIG. 13 is a sectional view showing the structure of the second premixer 2 which is another embodiment of FIGS. 1 to 3 described above.

In this embodiment, the length of the fuel nozzle 5 is increased in the longitudinal direction, and the fuel 9 injected from the tip of the fuel nozzle 5 toward the outlet of the premix chamber is supplied from several parts of the fuel nozzle 5. Fuel injection holes are formed so as to inject a desired fuel 9 in a dispersed manner. When the pressure fluctuation occurs due to the fluctuation of the flow velocity in the combustor, the pressure fluctuation is transmitted to the inside of the premixer. As a result, the flow rate of the air flowing inside the premixer also changes periodically. On the other hand, the fuel injected from one fuel nozzle into the premixer has a constant supply amount, and therefore the fuel-air ratio of the premixed air also periodically changes due to the periodically changing air amount. To do.
Further, the fact that the fuel-air ratio changes periodically means that the pressure generated when the premixed gas burns also changes periodically. As a result, when this fluctuation period matches the natural frequency inside the combustor, remarkable combustion vibration is generated.

Therefore, in this embodiment, the length of the fuel nozzle 5 is increased in the longitudinal direction, and the fuel 9 injected from the tip of the fuel nozzle 5 toward the outlet of the premix chamber is replaced by the number of fuel nozzles 5. A plurality of fuel injection holes are formed so as to inject a desired fuel 9 in a dispersed manner from the portion of the portion. With this configuration, while the air supplied from the inlet side is passed through the predetermined distance, the fuel is dispersed from several places and the desired fuel is injected to gradually increase the fuel-air ratio, and the desired fuel-air ratio is obtained. A premixture can be obtained. Therefore, the fuel-air ratio can be kept constant regardless of the instantaneous change in the air flow rate, and the increase in pressure fluctuation due to the interaction between the calorific value and the pressure fluctuation can be prevented.

Before explaining another embodiment, the resonance frequency will be described in detail with reference to FIG. FIG. 18 is a basic conceptual diagram of a resonance tube for explaining the resonance frequency.
In the resonance tube formed as shown in the drawing, the volume of the tube: V (24), the length of the outlet tube of the tube: L (26), the cross-sectional area of the outlet tube of the tube: S (25) and the speed of sound: C Then, the frequency f of the resonance tube is obtained as follows.

[0073]

F = C / 2π√S / VL (2) When the resonance tube is placed in a container having a natural frequency of sound equal to the resonance frequency of the resonance tube, the pressure fluctuation in the container is It is possible to absorb and attenuate energy and suppress vibration inside the container.

In the present embodiment, based on the above, the volume of each premixing chamber of the second premixer 2, the size of the outlet portion, and the cross-sectional area of the outlet portion are determined by the sound of the second premixer 2. The resonance frequency and the natural frequency of the combustor are set to be equal.
Thereby, the energy of the pressure fluctuation in the first combustion chamber 3 can be absorbed and attenuated. Therefore, the occurrence of combustion vibration can be suppressed.

14 and 15 show the above-described FIGS. 1 to 3.
14 is a block diagram showing the configuration of the second premixer 2, and FIG. 15 is a sectional view of the second premixer 2 as seen from the flow direction of the combustion gas.

FIG. 14 shows another embodiment showing the structure of the second premixer 2. In the present embodiment, the second premixer 2 is divided into two along the direction of the center line connecting the centers of the inlet and the outlet thereof, and the first premixing chamber 2a formed on the upstream side of the combustor is divided.
And a second premixing chamber 2b formed on the downstream side of the combustor. Then, the volume of the first premixing chamber 2a and the second premixing chamber 2b, the size of the outlet portion, and the cross-sectional area of the outlet portion are set to the resonance frequency of the sound of the second premixer 2 and the characteristic of the combustor. Set so that the frequency is equal. In this case, the first
The premixing chamber 2a and the second premixing chamber 2b are set so that the volume, the size of the outlet and the cross-sectional area of the outlet are different from each other. By forming the second premixer 2 in this way, it is possible to suppress the generation of two types of combustion oscillations. That is, a Helmholtz resonance tube for a plurality of frequencies can be achieved. Therefore, the occurrence of combustion vibration can be effectively suppressed.

FIG. 15 shows the second premixer 2 as in FIG.
It is another embodiment showing the configuration of. In this embodiment, the first
Of the pre-mixing chamber 2a formed to be large in the circumferential direction of the combustion chamber 3 and the pre-mixing chamber 2 formed to be smaller than the pre-mixing chamber 2a
and b are arranged so as to surround the first combustion chamber 3.
By forming the second premixer 2 in this way, it is possible to suppress the generation of two types of combustion oscillations, as in the previous example. That is, a Helmholtz resonance tube for a plurality of frequencies can be achieved. Therefore, the occurrence of combustion vibration can be effectively suppressed.

FIG. 16 is a view showing another embodiment of the combustor shown in FIGS. 1 to 3, and is a detailed view showing the internal structure of the second premixer 2 in detail. In this embodiment, the triangular pyramidal wing-shaped structure 22 is provided on the inner surface of the second premixer 2. In this way, the air 10 supplied to the inlet side of the second premixer 2 and the fuel 9 injected from the fuel nozzle 5 form a premixed gas by diffusion, and proceed to the downstream side of the premixing chamber. To do. At that time, behind the end portion (projection portion) of the triangular pyramid-shaped wing-shaped structure 22 located away from the inner surface of the second premixer 2, the main flow direction of the premixed gas (premixing) called a Lanchester vortex Vortex (longitudinal vortex) with a central axis of rotation in the direction of the center line connecting the centers of the inlet and outlet of the vessel 2
3 is formed, and this Lanchester vortex is directed toward the outlet of the second premixer 2 while entraining the fuel and air. The flow of the Lanchester vortex includes a flow in the mainstream direction in the premix chamber and a flow swirling around this mainstream direction as a central axis, and the flow rate in the mainstream direction accounts for more than half of the total flow rate. The Lanchester vortex has a strong mixing action because the radius of vortex rotation and the angular momentum also increase as the vortex advances downstream in the premixing chamber. Due to the mixing action of the Lanchester vortices, the premixed gas 12 is spatially uniformly mixed, and a local high temperature region due to uneven concentration is prevented from being generated. Therefore, NOx
It is possible to reduce the emission amount of.

Further, in the present embodiment, the second premixer 2 is formed such that the vicinity of the inlet of each premixing chamber is larger than the downstream side. This is the air 10 supplied from its inlet.
And the fuel 9 injected from the fuel nozzle 5 to increase the action of mixing by diffusion, and by doing so, a more uniform premixed gas 12 can be obtained.

FIG. 19 is a view showing a power generation system using any of the above-mentioned combustors. In this embodiment, the high temperature combustion gas 30 generated in the combustor 29 is the gas turbine 3
1 to drive this. Part of the power generated by the combustion gas 30 in the gas turbine 31 is used to drive the air compressor 32, and the remaining power is used to drive the generator 33. The air compressor 32 supplies the generated combustion air 10 to the combustor 29. The combustion gas 30 drives the gas turbine 31 and then, when passing through the exhaust heat recovery boiler 34, steam 3
5 is emitted to the outside through the chimney 38. The steam 35 generated from the exhaust heat recovery boiler 34 is generated by the steam turbine 36.
To drive the generator 37.

In the present embodiment, by using any of the above-mentioned combustors as the combustor 29, it is possible to achieve stable combustion with low NOx and a highly efficient power generation system.

The present embodiment is not limited to the power generation system configured as described above, but a gas turbine engine that supplies the high temperature combustion gas 30 generated in the combustor 29 to the gas turbine 31 and drives it. Alternatively, the high-temperature combustion gas 30 generated in the combustor 29 may be supplied to the gas turbine 31 and driven to drive the generator 33 to be used in a gas turbine power generation facility or the like.

[0083]

According to the present invention, it is possible to provide a highly reliable gas turbine combustor capable of further reducing NOx as compared with the conventional gas turbine combustor, and equipment using the gas turbine combustor. .

[Brief description of drawings]

FIG. 1 is a cross-sectional view showing a cross section of a combustor that is a first embodiment of the present invention.

FIG. 2 is a sectional view showing a section of a combustor that is a second embodiment of the present invention.

FIG. 3 is a cross-sectional view showing a cross section of a combustor that is a third embodiment of the present invention.

FIG. 4 is a detailed view around the outlet of the first premixer of FIG.

FIG. 5 is a detailed view around the outlet of the first premixer according to another embodiment.

FIG. 6 is a detailed view around the outlet of the first premixer according to another embodiment.

FIG. 7 is a detailed view around the outlet of the first premixer according to another embodiment.

FIG. 8 is a detailed view around the outlet of the first premixer according to another embodiment.

FIG. 9 is a detailed view around the outlet of the first premixer according to another embodiment.

10 is a central axial cross-sectional view of the combustor around the outlet of the second premixer of FIG.

FIG. 11 is a sectional view in the central axis direction of the combustor around the outlet of the second premixer according to another embodiment.

FIG. 12 is a perspective view around an outlet of a second premixer according to another embodiment.

FIG. 13 is a sectional view of a second premixer according to another embodiment.

FIG. 14 is a sectional view of a second premixer according to another embodiment.

FIG. 15 is a sectional view in the central axis direction of the combustor around the outlet of the second premixer which is another embodiment.

FIG. 16 is a detailed view showing in detail the internal structure of a second premixer which is another embodiment.

FIG. 17 is a basic conceptual diagram of a resonance tube for explaining a resonance frequency.

FIG. 18 is a graph showing N versus the fuel-air ratio of the premixed mixture at atmospheric pressure.
The characteristic view which shows the discharge amount of Ox.

FIG. 19 is a diagram showing a power generation system using a combustor according to the present invention.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... 1st premixer, 2 ... 2nd premixer, 3 ... 1st combustion chamber, 4 ... 2nd combustion chamber, 5, 7 ... Fuel nozzle, 6 ...
Structures, 8 ... Swirl vanes, 9 ... Fuel, 10 ... Air, 11,
12 ... Premixed gas, 13 ... Premixed flame, 14 ... Burned gas,
15 ... diffusion flame, 16 ... swirl flow, 17, 19 ... circulating flow,
18 ... Pilot burner, 20 ... Flame stabilizer, 21 ... Baffle plate, 22 ... Wing structure, 23 ... Vortex, 29 ... Combustor, 30
... Combustion gas, 31 ... Gas turbine, 32 ... Air compressor,
33, 37 ... Generator, 34 ... Exhaust heat recovery boiler, 35 ... Steam, 36 ... Steam turbine, 38 ... Chimney.

Front page continuation (72) Inventor Naruyoshi Kobayashi 502 Jinritsucho, Tsuchiura, Ibaraki Prefecture

Claims (11)

[Claims] 1. A gas turbine combustor in which a fuel and air are mixed around a cylindrical combustion chamber to form a premixed mixture, and the premixed mixture is burned to obtain combustion gas. The premixing chamber is arranged so as to surround the cylindrical combustion chamber,
A plurality of communicating means for communicating the premixing chamber and the cylindrical combustion chamber are provided, and the premixed gas produced in the premixing chamber has a swirling component in the same direction through the plurality of communicating means. A gas turbine combustor characterized by being injected as described above. 2. A gas turbine combustor in which a fuel and air are mixed around a cylindrical combustion chamber to form a premixed mixture, and the premixed mixture is burned to obtain combustion gas. A plurality of the premixing chambers are arranged in the circumferential direction so as to surround the tubular combustion chamber, and a communication means for communicating each premixing chamber with the tubular combustion chamber is provided, and the premixing chamber is provided via the communication means. A gas turbine combustor characterized by injecting premixed gas produced in each premixing chamber so as to have swirling components in the same direction. 3. A gas turbine combustor in which a fuel and air are mixed around a cylindrical combustion chamber to form a premixed mixture, and the premixed mixture is burned to obtain combustion gas. A plurality of the premixing chambers are arranged in the circumferential direction so as to surround the tubular combustion chamber, and a communication means for communicating each premixing chamber with the tubular combustion chamber is provided, and the premixing chamber is provided via the communication means. A gas turbine combustor characterized by injecting premixed gas produced in each premixing chamber while inclining it in the circumferential direction of the cylindrical combustion chamber. 4. A gas turbine combustor in which a fuel and air are mixed around a cylindrical combustion chamber to form a premixed chamber, and the premixed mixture is burned to obtain combustion gas. A plurality of the premixing chambers are arranged in the circumferential direction so as to surround the tubular combustion chamber, an opening is provided that connects each premixing chamber and the tubular combustion chamber, and the tubular shape is provided in the opening. A gas turbine combustor provided with a structure configured to be tilted in the circumferential direction of the combustion chamber. 5. A gas turbine combustor in which a fuel and air are mixed around a cylindrical combustion chamber to form a premixed mixture, and the premixed mixture is burned to obtain combustion gas. The premixing chamber is arranged so as to surround the cylindrical combustion chamber,
A gas turbine combustor, characterized in that a plurality of communication pipes that connect the premixing chamber and the tubular combustion chamber are provided, and the plurality of communication pipes are inclined in the circumferential direction of the tubular combustion chamber. . 6. A gas turbine combustion system in which a premixing chamber for mixing a fuel and air to form a premixed gas is formed around a cylindrical first combustion chamber, and the premixed gas is burned to obtain a combustion gas. In the reactor, a tubular second combustion chamber having a cross-sectional area in the main flow direction of the combustion gas larger than that of the tubular first combustion chamber is provided on the downstream side of the tubular first combustion chamber, A plurality of the premixing chambers are arranged in the circumferential direction so as to surround the tubular first combustion chamber, and an opening is provided that connects each premixing chamber and the tubular combustion chamber, and the opening is provided in the opening. A gas turbine combustor, comprising a structure configured to be inclined in a circumferential direction of the cylindrical first combustion chamber. 7. A gas turbine combustion system in which a premixing chamber for mixing a fuel and air to form a premixed mixture is formed around a cylindrical first combustion chamber, and the premixed mixture is burned to obtain a combustion gas. In the burner, a pilot burner for individually injecting and diffusing and burning the fuel and air is provided in the center of the combustor, and the tubular first combustion chamber is arranged downstream of the pilot burner. A tubular second combustion chamber having a cross-sectional area in the main flow direction of the combustion gas larger than that of the tubular first combustion chamber, is provided on the downstream side of the tubular first A plurality of the premixing chambers are arranged in the circumferential direction so as to surround the combustion chambers, and an opening is provided to connect each premixing chamber to the cylindrical combustion chamber, and the cylindrical first A gas tank provided with a structure that is inclined in the circumferential direction of the combustion chamber of Turbine combustor. 8. A premixer having a premixing chamber for mixing the fuel and air to form a premixed gas is provided at the center of the combustor, and the premixed gas is provided in the circumferential direction of the premixer. The gas turbine combustor according to claim 7, wherein swirling means for swirling is provided on an outlet side of the premixer. 9. A gas turbine combustor according to claim 1, a gas turbine driven by the combustion gas generated in the gas turbine combustor, and an air compressor operating in conjunction with the driving of the gas turbine. A gas turbine engine characterized in that. 10. A gas turbine combustor according to claim 1,
A gas turbine power generation facility comprising: a gas turbine driven by combustion gas generated in the gas turbine combustor; and a generator that generates power by driving the gas turbine. 11. A gas turbine system for driving a gas turbine by the combustion gas generated in the gas turbine combustor according to claim 1, and driving a generator by the drive to generate electricity.
An exhaust heat recovery boiler that generates steam by using combustion gas discharged from the gas turbine system as a heat source, and a steam turbine that is driven by the steam that is generated by the exhaust heat recovery boiler. A power generation system having a steam turbine system for performing.