JP2003148732A - Combustor and gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a combustor and gas turbine combustor having low NOx and excellent flame stability and preventing blow-off of flame by enabling generation of the Lanchester vortex within a premixer. SOLUTION: In the combustor having the premixer for making a premixed fuel-air mixture by mixing air and fuel, a winglike structure for generating a vortex having a center shaft of a rotation in a main stream direction of the premixed fuel-air mixture is provided within the premixer. Or in the gas turbine combustor having a premixer for making a premixed fuel-air mixture by mixing air and fuel and obtaining combustion gas by burning the premixed fuel-air mixture, a pilot burner for performing diffusion combustion for the air and fuel by individually jetting the air and fuel is provided at the center part of the combustor, a plurality of the premixers are arranged in the peripheral direction to surround the pilot burner, and the premixer incorporates a winglike structure for generating a vortex having a center shaft of a rotation in a main stream direction of the premixed fuel-air mixture.

Description

Detailed Description of the Invention

[0001]

TECHNICAL FIELD The present invention relates to a combustor having a premixer and a gas turbine combustor.

[0002]

2. Description of the Related Art In a combustor, for example, a gas turbine combustor, a premixed combustion system is used in which fuel and air are premixed and burned in order to reduce nitrogen oxides (hereinafter referred to as NOx). Compared with the diffusion combustion method in which fuel and air are separated and burned, this premixed combustion method reduces the fuel concentration and prevents the generation of a local high temperature region, thereby reducing the amount of NOx contained in exhaust gas. It is excellent in that it can be reduced.

However, in the premixed combustion system which prevents the local occurrence of the high temperature region, the flame is liable to become unstable due to the absence of the high temperature region, and the flame is easily blown off or the flashback is apt to occur. Further, since the premixed gas is not spatially and uniformly mixed, there is a problem that the effect of reducing NOx is small. Therefore, various solutions have been considered to solve this problem.

For example, as described in JP-A-1-203809 (Patent Document 1) and JP-A-2-275221 (Patent Document 2), the premixer is formed in a conical shape, and the tip of the cone is formed. By injecting fuel in the axial direction from the nozzle installed in the machine and injecting air from the tangential direction of the conical side surface to generate a swirling flow in the circumferential direction inside the premixer, the premixed gas is made uniform, and A flame is stabilized at the outlet of the premixer as described in JP-A-4-103906 (Patent Document 3), in which an axial circulation flow is formed at the outlet of the premixer to stabilize the flame. Is provided to stabilize the flame by generating a circulating flow in the axial direction on the downstream side of the flame stabilizer, and a swirl flow is applied to the premixed gas to generate a backflow near the center of swirl. It is known to hold a high temperature burned material in the reverse flow and use this as an ignition source to stabilize the flame. There is.

[0005]

[Patent Document 1] Japanese Unexamined Patent Publication No. 1-203809

[Patent Document 2] Japanese Unexamined Patent Publication No. 2-275221

[Patent Document 3] Japanese Unexamined Patent Publication No. 4-103906

[0006]

In the combustor, it is necessary to reduce the size of the combustor and stably maintain the flame over a wide range from starting to rated operation. In addition, in a gas turbine combustor that connects multiple combustors with a flame propagation tube, it is essential to reliably ignite each combustor at startup and to transfer the fire from the startup combustor to another combustor when the output rises. Is a requirement.

However, among the above-mentioned conventional examples, in the case where the premixer is formed in a conical shape, the premixed gas is mixed sufficiently uniformly in the conical premixer, and the circulation flow is made to the outlet of the premixer. Since a sufficient premixer length is required in the axial direction to form the premixer, the premixer cannot be downsized. Further, if the flow velocity of the premixed gas decreases, the circulation flow at the outlet cannot be stably formed, and the flame becomes unstable. Therefore, it cannot be applied to continuous load operation of a gas turbine. Further, since the pressure loss at the air inlet and the tip of the cone is large, the efficiency as a combustor is poor.

Further, in the case where a flame stabilizer is provided at the outlet of the premixer, the flame stabilizer is exposed to high-temperature combustion gas, so cooling of the flame stabilizer is indispensable to prevent burnout, and complicated cooling is required. Requires structure. Therefore, the size of the premixer cannot be reduced.

Further, in the case of giving a swirling flow to the premixed air, a stagnation region where the flow velocity becomes zero occurs near the center of the backflow region generated by the action of swirling, so that the flame becomes unstable and the flame blows off. And causes combustion vibration.

Further, since no particular consideration is given to the mixing of air and fuel in the premixer, sufficient uniformity of the premixed gas cannot be obtained and the NOx reduction effect is small. Also,
In the above-mentioned conventional example, no consideration is given to reliable ignition of each combustor when starting a gas turbine combustor in which a plurality of combustors are connected by a flame propagation tube, and reliable transfer of fire to another combustor when the output rises. It has not been.

The present invention has been made in view of the above problems, and an object thereof is to enable the generation of Lanchester vortices in a premixer, to reduce NOx and to improve flame stability and to blow a flame. It is an object of the present invention to provide a combustor and a gas turbine combustor capable of preventing disappearance.

[0012]

The above object can be achieved by the following features.

The combustor of the present invention is characterized in that it is provided in the premixer in a blade-shaped structure for generating a vortex having a central axis of rotation in the mainstream direction of the premixed gas.

In the following description, unless otherwise specified, the main flow direction of the premixed gas indicates the direction of the center line connecting the centers of the inlet and the outlet of the premixer.

[0015]

BEST MODE FOR CARRYING OUT THE INVENTION In the embodiments of the present invention, a structure for generating a vortex having a central axis of rotation in the mainstream direction of a premixed gas is provided in the premixer, so that NOx is reduced because the air and fuel can be spatially homogeneously mixed in the premixer using the large mixing action of the radial flow due to the circumferential flow of the vortex and the pressure difference between the center of the vortex and the surroundings. be able to. Further, at the outlet of the premixer, the pressure at the vortex center at the outlet becomes higher than the pressure at the vortex center inside the premixer because the flow is generated from the high pressure portion around the vortex to the low pressure portion at the vortex center. So
Flow to the upstream side occurs. Further, as the vortex advances in the mainstream direction, the radius of gyration of the vortex increases. Further, as the vortex advances in the mainstream direction, the angular momentum of the vortex increases. Therefore, since the circulation flow can be formed in the center of the premixer outlet and the main flow can be formed outside the circulation flow, flame blow-off and flashback can be prevented and stabilized. Further, when the mixing action by such a vortex is used, the air and the fuel are mixed in a short time to obtain the premixed gas, so that the premixer can be downsized.

Further, a structure having an elevation angle with respect to the main flow direction of the premixed gas is provided in the premixer, and the structure has a portion which is not in contact with the inner surface of the premixer.
A strong vortex called Lanchester vortex is generated by the three-dimensional effect on the lift of the structure. Therefore, due to the action of the vortex described above, the flame can be stabilized and NOx can be reduced even with a small premixer.

Further, preferably, by providing a means for generating a turbulent flow on the structure, the turbulent flow having no direction generated by this means and the vortex generated by the structure are combined to form air. The mixing action of the fuel can be enhanced. Further, since this turbulent flow has an action of suppressing the phenomenon (separation of flow) in which the main flow of the premixed gas separates from the surface of the structure, this also has the action of strengthening the mixing action and can reduce NOx.

Further, preferably, by providing a plurality of vortex generating means on the structure, a plurality of vortices generated by the vortex generating means and a vortex generated by the structure are combined to mix air and fuel. Can be strengthened.

Further, preferably, by providing a plurality of the structures, vortices generated from the plurality of structures interfere with each other,
The vortex shape collapses and becomes a turbulent state. As a result, the mixing action of the premixed air can be further enhanced.

Further, a plurality of structures for generating vortices having a central axis of rotation in the main flow direction of the premixed gas are provided in the premixer,
By combining a plurality of vortices generated downstream of the plurality of structures to form one vortex, the flame can be stabilized and NOx can be reduced by the small premixer by the same action as described above. it can.

Further, three structures for generating vortices having a central axis of rotation in the main flow direction of the premixed gas are provided in the premixer,
The vortex circulation (the flow rate of the premixed gas flowing as a vortex around the central axis) generated by each structure is Γ ₁ , Γ ₂ , and Γ ₃ , respectively, and the distances between the centers of the vortices are r ₁₂ and r ₂₃ , respectively. , R ₃₁ (r _ij is the vortex i
And the center distance of vortex j),

[0022]

[Formula 1] Γ ₁ · Γ ₂ + Γ ₂ · Γ ₃ + Γ ₃ · Γ ₁ = 0 (1)

[0023]

[Equation 2] By arranging each structure so as to satisfy Γ ₁ · Γ ₂ · r ₁₂ ² + Γ ₂ · Γ ₃ · r ₂₃ ² + Γ ₃ · Γ ₁ · r ₃₁ ² = 0 (2) Since three vortices can be combined to form one vortex, the flame is stabilized by a small premixer by the same action as described above, and NO is generated.
x can be reduced.

Further, three structures for generating vortices having a central axis of rotation in the main flow direction of the premixed gas are provided in the premixer,
Circulation of vortices generated by each structure (flow rate of premixture flowing as a vortex around the central axis) is Γ, Γ, −Γ / 2 (negative sign indicates that the vortices rotate in opposite directions) Also, by arranging each structure so that the center of each vortex is at the apex position of an equilateral triangle, one vortex can be formed from three vortices. The flame can be stabilized and NOx can be reduced.

Further, preferably, the premixer is provided with a pressure difference adjusting means for increasing a pressure difference between the center and the periphery of the vortex on the downstream side of the structure, so that the pressure difference between the center and the periphery of the vortex is adjusted. The base flow in the radial direction becomes stronger, so that the mixing action of the premixed gas can be further strengthened.

Further, preferably, the premixer is provided with a pressure adjusting means for increasing the pressure at the center of the vortex on the downstream side of the pressure difference adjusting means, so that the vortex center of the vortex center upstream and downstream of the pressure adjusting means can be improved. An upstream flow occurs due to the pressure difference. This forms a circulating flow inside the premixer, which can be used to further enhance the mixing action of the premixed gas.

Further, preferably, the premixer is provided with a pressure adjusting means for increasing the pressure at the center of the vortex at the outlet side, so that the premixer is upstream based on the pressure difference between the vortex center upstream and downstream of the pressure adjusting means. Flow to the side occurs. This forms a circulating flow at the outlet of the premixer, so that flame jump can be prevented and the flame can be stabilized.

Further, preferably, the premixer is provided with a flow velocity adjusting means for increasing the flow velocity around the vortex at the outlet side, so that a high-speed flow can be formed around the vortex at the outlet, so that the reverse flame It can prevent fire and stabilize flame.

Further, preferably, the premixer is arranged in the circumferential direction of the combustor, and a pilot burner for separately injecting air and fuel for diffusion combustion is provided at the premixer outlet, whereby the premixer is provided. Since the flame can be sufficiently stabilized only by the circulation flow formed at the outlet, the combustor can be operated stably even if the pilot burner is sufficiently small. Furthermore,
At the outlet of the premixer, the diffusion flame of the pilot burner is instantaneously entrained in the vortex of the premixed gas and burns the unburned gas, so the transfer characteristics of the diffusion flame (pilot flame) can be effectively improved and the flame is further stabilized. Can be converted.

Further, preferably, a pilot burner for jetting and diffusing the air and the fuel separately is provided in the center of the combustor, and the premixer is surrounded in the circumferential direction of the combustor so as to surround the pilot burner. Even by providing the above, the flame can be sufficiently stabilized only by the circulation flow formed at the outlet of the premixer, so that the stable operation of the combustor can be performed even if the pilot burner is sufficiently small.

Further, preferably, the premixer is provided with a means for generating a swirling flow having a main flow direction of the premix air as a circumferential direction on the inlet side, and the main flow direction of the premix gas is from the circumferential direction to the axial direction. By providing the structure on the downstream side of the position at which the transition occurs to, the mixing action of the swirling flow can be utilized, so that uniform mixing of air and fuel is promoted, and NOx can be further reduced.

Further, the premixer has a built-in structure for generating a vortex having a central axis of rotation in the mainstream direction of the premixed gas, and the circulating flow is provided at the center of the outlet side and the mainstream is provided outside the circulating flow. By forming the flame, it is possible to prevent the flame from blowing off and the flashback, so that the flame can be stabilized. Further, NOx can be reduced by the action of the vortex described above.

Further, by generating a diffusion combustion flame on the upstream side of the premixing combustion flame generated in the premixer, the excellent flame stability performance of the diffusion combustion flame at the exit of the premixer is utilized and combustion is performed. The excellent low NOx performance of the premixed combustion flame can be utilized at the outlet of the unit.

Further, a pilot burner for separately injecting air and fuel for diffusion and combustion is provided in the center of the combustor, and a plurality of premixers are circumferentially arranged so as to surround the pilot burner, and the premixer is also provided. Contains a structure that generates a vortex having a central axis of rotation in the mainstream direction of the premixed gas, and determines the direction of rotation of the vortex discharged from at least one premixer of the vortex discharged from another premixer. By making the direction opposite to the rotation direction, the same vortex action as described above is used to generate NO
x can be reduced. In addition, since the vortex discharged from another premixer and the vortex whose rotation direction is opposite to each other induces a flow from the center to the periphery of the combustor between adjacent vortices, use this flow to The partial diffusion flame can be effectively transported to the premixer. Therefore, the transfer characteristic to the premixed gas can be improved, and the flame can be stabilized. Further, by miniaturizing the plurality of premixers and operating them stepwise according to the load, substantially continuous load operation becomes possible.

Further, a pilot burner for separately injecting air and fuel to diffuse and burn is provided in the center of the combustor, and the premixers are arranged in concentric circles so as to surround the pilot burner, and the premixer is premixed. The device has a built-in structure that generates a vortex having a central axis of rotation in the mainstream direction of the premixed gas, and the vortices emitted from the premixers adjacent to each other in the circumferential direction and the radial direction are rotated in opposite directions. Also by the same operation as described above, the flame stability is excellent and the NOx can be reduced by the small premixer, and the continuous load operation becomes possible.

Further, the premixer has a built-in structure for generating a vortex having a central axis of rotation in the mainstream direction of the premixed gas, is provided with a plurality of the premixers, and the vortex discharged from the adjacent premixers is included. By making the rotation directions of (1) and (2) opposite to each other, the premixed gas can be spatially made uniform, so that NOx can be reduced. In this case, since each vortex induces a flow in the opposite direction on both sides, this flow can be used to draw the combustion gas burned at the premixer outlet near the center of the combustor into each premixer. Therefore, since each premixer functions as a pilot burner, the transfer characteristics of the pilot flame can be effectively improved, and the flame can be stabilized. Further, by miniaturizing the plurality of premixers and operating them stepwise according to the load, substantially continuous load operation becomes possible.

The first swirl of the premixed gas in the circumferential direction
And a second means located at the outer peripheral portion of the means for swirling the premixed gas in the same circumferential direction as the means are provided at the outlet of the premixer, and the first means is generated. The strength of the swirl represented by the ratio of the circumferential flow velocity to the axial flow velocity of the swirl flow is made larger than the swirl intensity of the swirl flow generated by the second means. Also, preferably, the strength of the swirl represented by the ratio of the circumferential flow velocity to the axial flow velocity of the swirl flow generated in the vicinity of the swirl axis by the second means is greater than the swirl intensity at the outer peripheral portion of the swirl flow. By also increasing, the stagnation region near the central axis, which causes blowout of flame and combustion oscillation, can be reduced. Therefore, it is possible to prevent blowout of the flame and improve the stability of the flame.

That is, this action can be explained by the following theoretical consideration. Here, if 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.

[0039]

[Equation 3] (∂P / ∂x) _{r = 0} ~ (∂P / ∂x) _{r = R} −∂∫ (ρW ² / r) dr / ∂x (3) That is, the pressure gradient of the central axis is , Increases in proportion to the axial damping rate of centrifugal 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.
As a result, by reducing the strength of the swirl at the outer peripheral portion of the swirl flow compared to the inner peripheral portion of the swirl flow, the swirl flow velocity at the inner peripheral portion (r: small) that strongly affects the centrifugal force is effective in the axial direction. Can be attenuated. Therefore, it is possible to increase the backflow velocity and improve the stability of the flame. Further, a pilot burner is provided in the center of the combustor, and a plurality of premixers are arranged in the circumferential direction so as to surround the pilot burner, and each combustor includes the pilot burner. When the outer peripheral portions of the swirl flow discharged from the premixer have the same rotational direction on a straight line by a flame propagation tube, the flow induced by the swirl flow causes the pilot burner to move to the premixer of the outer peripheral portion. The flame can be easily transferred, and the premixed combustion flame can be reliably propagated to the premixer of another combustor through the flame propagation tube. Further, since the premixed gas supplied from each premixer burns while maintaining flame holding by the circulation flow formed at the outlet, it is possible to stabilize the premixed flame.

(Embodiment) An embodiment of the present invention will be described below with reference to the drawings.

FIG. 1 is a perspective view showing a vertical cross section of a gas turbine combustor according to a first embodiment of the present invention, FIG. 2 is a detailed view around the outlet of the premixer of FIG. 1, and FIG. 3 is a wing shape of FIG. It is an A direction arrow line view of a structure.

In the drawing, a cylindrical combustor 5 has a fuel injection nozzle 6a and an air injection nozzle 6b at the center thereof.
And a premixer 1 is arranged so as to surround the pilot burner 6. The premixer 1 is composed of a plurality of premixing chambers divided in the circumferential direction, and each premixing chamber has a fuel injection nozzle 2 on the inlet side and an inner surface on the downstream side thereof with respect to the mainstream direction 11a of the premixed gas. The wing structure 9 having an appropriate elevation angle α is provided. Here, as shown in FIG. 3, the wing-shaped structure 9 has a triangular pyramid shape, and has a triangular surface having 9 a, 9 b, and 9 c as three vertices (vertex 9 a and sides 9 b-9 c (vertices 9 b and 9 c are The line (broken line in FIG. 3) connecting the midpoints of the sides (the ends) is fixed to the inner surface of the premixing chamber so as to form an elevation angle α with respect to the mainstream direction 11a of the premixed gas.

In the premixer 1, the combustion air 3 supplied from the inlet and the fuel 4 injected from the fuel injection nozzle 2
Form a premixture 11 while being mixed by diffusion,
It flows in the premixer 1. At that time, the blade-shaped structure 9 is rotated in the mainstream direction of the premixed air mixture 11 called Lanchester vortex behind the end portion, that is, the protrusion (vertex 9d in FIG. 3) at a portion away from the inner surface of the premixer 1. A vortex (longitudinal vortex) having a central axis of is formed, and the Lanchester vortex 10 moves toward the outlet of the premixer 1 while entraining and mixing fuel and air.
The flow of the Lanchester vortex 10 includes a flow in the mainstream direction in the premixing 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 10 has a strong mixing action because the radius of rotation of the vortex increases and the angular momentum increases as it advances downstream. Since the premixed gas 11 is spatially and uniformly mixed by the mixing action of the Lanchester vortex 10, a local high temperature region due to uneven concentration does not occur, and NO
x can be reduced.

The Lanchester vortex 10 has a higher pressure in the surroundings than the central pressure of the vortex in the premixing chamber, but at the outlet of the premixing chamber, a flow is generated from the surrounding high pressure portion to the central low pressure portion. By doing so, the pressure at the center of the vortex is increased. As a result, the pressure at the center of the vortex becomes higher at the outlet of the premixing chamber than at the outlet of the premixing chamber, so a flow to the upstream side is generated based on this pressure difference, and the circulation flow 8 is formed. The action of this circulation flow 8 prevents the premixed flame 12a from blowing off,
The flame can be stabilized. Further, since the backflow of the premixed flame 12a can be prevented by the action of the main flow 7 flowing outside the circulation flow 8, the flame can be further stabilized. Although FIG. 3 shows an example in which the wing-shaped structure 9 is tilted clockwise with respect to the mainstream direction 11a as the elevation angle α, the mainstream direction 11a is shown.
By tilting the wing structure 9 in the counterclockwise direction, the Lanchester vortex 10 in the opposite direction can be generated.

In the present embodiment, the flow rate of the flow swirling around the main flow direction as the central axis in the flow of the Lanchester vortex 10 is set in the range of 30 to 50% of the total flow rate, so that the above-mentioned premixed gas 11 is uniformly mixed. Also, the premixed flame 12a can be effectively stabilized. In order to perform such flow distribution, the wing-shaped structure 9 has an elevation angle of 10 ° to 20 ° with respect to the main flow, and a height from the surface of the premix chamber in a plane perpendicular to the main flow in the plane perpendicular to the premix. 3 of the average inner diameter of the chamber
The range may be 0 to 50%. At this time, the separation effect of the flow of the premixed air 11 separating from the surface of the blade-shaped structure 9 can be suppressed, and the mixing effect of the premixed air 11 can be further enhanced. Further, since the diffusion flame 12 is formed on the downstream side of the pilot burner 6, the stability of the premixed flame 12a is further enhanced by this.

Since the action of the Lanchester vortex 10 described above can be sufficiently obtained even if the premixing chamber of the premixer 1 is made small, it is possible to stabilize the flame and reduce NOx even if the combustor 5 is made small. it can. Therefore, it is possible to realize substantially continuous load operation by downsizing a plurality of premixing chambers as in this embodiment or by installing a plurality of small premixers and operating these in stages according to the load. Becomes With the above configuration, it is possible to suppress the non-uniformity of the premixed gas, which is a factor of NOx generation, and the accompanying generation of the high temperature region in the premixed flame. It is possible to achieve a concentration.

Next, a method of operating the gas turbine combustor of this embodiment will be described. At the time of starting the combustor 5, first, the pilot burner 6 is started, and the flow rates of the air 3 and the fuel 4 supplied thereto are gradually increased to increase the diffusion combustion output. Next, the premixer 1 is started when the output reaches a predetermined ratio of the rated value, and the flow rate of the premixed gas 11 is increased to increase the premixed combustion output. At this time, the air 3 supplied to the pilot burner 6
By reducing the flow rate of the fuel 4 and the ratio of the diffusion combustion output to the premixed combustion output, the NOx is reduced. When the output reaches the rated value, the flow rates of the air 3 and the fuel 4 supplied to the premixer 1 and the pilot burner 6 are made constant, and the combustor 5 is operated at the rated output. When the combustor 5 is stopped, the operation opposite to that at the start-up may be performed. By properly setting the above-mentioned predetermined ratio, the instability of the premixed flame at low output can be compensated for by the stability of the diffusion flame, while the low NOx performance of the premixed flame can be effectively utilized, so that the low NOx With this, it is possible to operate the combustor having excellent flame stability. Further, by controlling the output increase of the plurality of premixing chambers of the premixer 1 in a stepwise manner, a substantially continuous load operation as a combustor becomes possible. As described above, in the present embodiment, the vortex is generated in the premixer by the structure, but the present invention is not limited to this, and the vortex is generated in the premixer including the shape deformation of the premixer described later and swirl vanes. Generate
Moreover, any means that does not hinder the operation of the combustor may be used.

FIG. 4 is a diagram showing a premixer according to a second embodiment of the present invention. In the present embodiment, the wing structure 9 having an appropriate elevation angle α ₁ with respect to the mainstream direction 11a of the premixed air is installed on the inner side surface of the premixer 1, and the wing structure 9 on the wing structure 9 with respect to the mainstream direction 11a. A plurality of winglets 13 having an appropriate elevation angle α ₂ are installed. In the premixer 1, the combustion air 3 supplied from the inlet of the premixer 1 and the fuel 4 injected from the fuel injection nozzle 2 mix by diffusion to form a premixed gas, which flows in the premixer 1. Then, by the same operation as in the first embodiment, the Lanchester vortex 10 of the premixed gas is formed behind the open end of the blade-shaped structure 9 and the winglet 1
From 3 also, a plurality of small Lanchester vortices 10a are generated. The small Lanchester vortices 10a interfere with each other to entrain and mix the fuel and air, reach the premixer outlet while being entrained in the larger Lanchester vortex 10 and are burned at the outlet. According to the present embodiment, the premixed gas 11 produced by the premixer 1 is more uniform than the first embodiment due to the combination of a plurality of small Lanchester vortices 10a and one large Lanchester vortex 10. Mixed. As described in the first embodiment, the elevation angle α ₁ ,
The above effect can be obtained by setting α ₂ in the range of 10 ° to 20 °. In addition, the small Lanchester vortex 10a generated by the plurality of small wings 13 is
Since the main flow of the premixed gas has the effect of suppressing the separation phenomenon of the flow leaving the surface of the blade-shaped structure 9 when the elevation angle of is increased, this also promotes the mixing of the premixed gas.
Therefore, it is possible to prevent the occurrence of a local high temperature region due to uneven concentration, and thus it is possible to further enhance the NOx reduction effect.

In this embodiment, the elevation angle α ₂ of the plurality of winglets 13 is the same.
_{Even if 2} is different from the others, the above effect can be obtained. Even if a means for generating a turbulent flow such as a wire (thin wire) is provided on the blade-shaped structure 9 perpendicularly to the mainstream direction of the premixed gas 11 instead of the small blades 13, the same effect as described above can be achieved. it can.

FIG. 5 is a diagram showing a premixer according to a third embodiment of the present invention. In this embodiment, a plurality of blade-shaped structures 9 having an appropriate elevation angle α (10 ° to 20 °) with respect to the mainstream direction 11a of the premixed gas are installed on the inner surface of the premixer 1. In the premixer 1, the combustion air 3 supplied from the inlet of the premixer 1 and the fuel 4 injected from the fuel injection nozzle 2 mix by diffusion to form a premixed gas, which flows in the premixer 1. Then, by the same operation as in the first embodiment,
A Lanchester vortex 10 of premixed gas is formed behind the open ends of the plurality of blade-shaped structures 9. Multiple Lanchester Vortex 1
In the case of 0, the fuel and air are entrained and mixed while interfering with each other, and the vortex shape collapses to be in a turbulent state. The premixed gas 11 thus mixed is combusted at the outlet of the premixer. According to this embodiment, the premixed gas 11 produced by the premixer 1 is more uniformly mixed by the synergistic effect of the mixing action of the plurality of Lanchester vortices 10. Therefore, as in the previous example, N
The Ox reduction effect can be further enhanced.

FIG. 6 is a diagram showing a cross section of a premixer according to a fourth embodiment of the present invention. In the present embodiment, three triangular pyramid-shaped delta vanes 16 having an appropriate elevation angle with respect to the mainstream direction of the premixed air are provided on the inner surface of the premixer 1 having a rectangular cross section.
a, 16b, 16c (the structure is the same as in FIG. 3) are installed. The height of the delta vanes 16b and 16c in the horizontal direction in the figure is set to 1/3 of the distance between the inner surfaces of the premixer 1, and the height of the delta vanes 16a in the vertical direction is set to the premixer 1.
It is set to ⅓ of the inner surface interval, and the tips of each delta wing are arranged so as to have three apexes of an equilateral triangle. With this arrangement, the circulation of the Lanchester vortices 10a and 10c generated from the delta vanes 16a and 16c (flow rate flowing as a vortex around the central axis) is Γ, and the circulation of the Lanchester vortex 10b generated from the delta vanes 16b is −Γ / 2. (The negative sign indicates that the direction of rotation of the vortex is opposite), and the elevation angle of each delta wing is adjusted within the range of 10 ° to 20 °. As a result, the three Lanchester vortices generated from each delta wing 1
Since 0 satisfies the conditions of the above equations 1 and 2, they merge while drawing a spiral orbit and one strong Lanchester vortex 1
5 is formed. According to this embodiment, the premixed gas 11 produced by the premixer 1 is more uniformly mixed by the action of the strong Lanchester vortex 15, so that the occurrence of a local high temperature region due to uneven concentration is prevented, The NOx reduction effect can be further enhanced.

FIG. 7 is a vertical sectional view of a premixer according to a fifth embodiment of the present invention. In the present embodiment, the wing structure 9 having an appropriate elevation angle α with respect to the main flow direction 11a of the premixed gas is installed on the inner wall of the premixer 1, and the reduced flow path and the expansion are provided on the downstream side of the wing structure 9. A throat portion 17 formed of a combination of flow paths is provided. The Lanchester vortex 10 formed by the wing-shaped structure 9 is stretched in the mainstream direction when passing through the contraction flow path of the throat portion 17, and the pressure difference between the center of the vortex and the surroundings increases, so that a stronger vertical vortex is generated. can get. The mixing action of the radial flow based on the pressure difference between the center of this strong longitudinal vortex and the surroundings is used to further promote the mixing of air and fuel. Further, when the Lanchester vortex 10 passes through the enlarged flow path of the throat portion 17, a flow is generated from the high pressure portion around the vortex to the low pressure portion around the vortex, so that the pressure at the vortex center rises. A flow to the upstream side occurs based on the pressure difference between the vortex centers on the upstream side and the downstream side of the expanded flow path. As a result, the circulation flow 8b is formed inside the premixer 1,
The premixed gas 11 can be further mixed by using the circulation flow 8b. Therefore, the NOx reduction effect can be further enhanced. In addition, the circulation flow 8 formed at the outlet of the premixer 1 can prevent flame blow-off and stabilize the flame. Although the example in which one wing-shaped structure 9 is installed is shown in the present embodiment, three wing-shaped structures 9 are provided as described above.
The same effect can be obtained even for a premixer in which is installed to form one Lanchester vortex. FIG. 8 is a diagram showing a premixer according to a sixth embodiment of the present invention. In the present embodiment, the premixer main body is composed of a cylindrical container 20 containing a wing-shaped structure 9 having an appropriate elevation angle with respect to the mainstream direction of the premixed gas, and the diffuser 2 which is an expanded flow path at the outlet thereof.
1 is provided. Combustion air 3 is supplied into the premixer from the inlet of the cylindrical container 20, and fuel 4 is injected from a fuel injection nozzle 2 installed on the inlet side of the premixer. Then, as in the first embodiment, the Lanchester vortex 10 generated from the wing structure 9 moves toward the premixer outlet while mixing air and fuel. In the diffuser 21, a flow is generated from the high pressure portion around the Lanchester vortex 10 to the low pressure portion at the center of the vortex, so that the pressure at the vortex center rises. Therefore, the circulation flow 8 is formed in the diffuser 21 due to the pressure difference between the center of the Lanchester vortex 10 in the cylindrical container 20 and the center of the diffuser 21. The circulation flow 8 prevents the flame from being blown off and stabilizes the flame well.

FIG. 9 is a diagram showing a blade-like structure in a premixer according to a seventh embodiment of the present invention. In this embodiment, a plurality of fuel injection holes 18 are provided on the surface of the blade-shaped structure 9 which is installed on the inner side surface of the premixer 1 and generates the Lanchester vortex 10, from which fuel 19 is fed. Supplied within. This also promotes the mixing of fuel and air in the region where the air 3 supplied from the inlet side of the premixer 1 forms the Lanchester vortex 10 behind the wing structure 9.
Ox can be reduced.

FIG. 10 is a diagram showing a cross section of a gas turbine combustor according to an eighth embodiment of the present invention. In this embodiment, eight premixers 1 shown in FIG. 8 are arranged in the circumferential direction of the combustor 5, and a small-sized fuel injection nozzle and an air injection nozzle are provided at the center of the outlet of each premixer 1. The pilot burner 6 is installed. As described above, each premixer 1
Since the circulation flow 8 is formed at the outlet of, the flame can be stabilized by the action of this circulation flow. Therefore, even if each pilot burner 6 is made small, stable operation of the combustor can be performed. Further, the diffusion flame generated in each pilot burner 6 is caught in the Lanchester vortex 10 discharged from the outlet of each premixer 1 and burns the unburned premixed gas. As a result, the transfer characteristic of the diffusion flame to the premixed gas can be effectively improved. According to this embodiment, the flame can be stabilized even if the pilot burner is made small, and NO
x can be reduced.

FIG. 11 is a cross sectional view of a gas turbine combustor according to a ninth embodiment of the present invention. In this embodiment, a pilot burner 6 including a fuel injection nozzle 6a and an air injection nozzle 6b is installed at the center of the combustor 5, and the premixer 1 shown in FIG. It is installed in the circumferential direction. Moreover, each premixer 1 is arrange | positioned so that the direction of the Lanchester vortex 10 discharged from the adjacent premixer 1 may become reverse.
Thus, by making adjacent Lanchester vortices 10 in opposite directions, a flow 14 from the combustor center to the premixer is induced. The diffusion flame formed at the outlet of the pilot burner 6 is transported to the premixer 1 by the flow 14 and burns the unburned premixed gas. As described above, since the premixed gas supplied from each premixer 1 burns while being flame-held by the circulation flow 8 formed at the outlet, stabilization of the premixed flame is realized. Therefore, according to the present embodiment, NOx
It is also possible to improve the transfer characteristic of the diffusion flame to the premixed gas and stabilize the flame. In addition, in the present embodiment, an example in which all the Lanchester vortices 10 emitted from the adjacent premixers 1 are opposite to each other is shown, but if at least one of the Lanchester vortices 10 is opposite, the vortices are reversed. Since the flow 14 is generated next to, the premixed flame can be similarly stabilized.

FIG. 12 is a cross-sectional view of a gas turbine combustor which is a tenth embodiment of the present invention. In the present embodiment, a pilot burner 6 including a fuel injection nozzle 6a and an air injection nozzle 6b is installed in the center of the combustor 5, and the pilot burner 6 is surrounded by the pilot burner 6 as shown in FIG.
The premixer 1 shown by is installed concentrically in two stages. Further, the premixers 1 are arranged such that the Lanchester vortices 10 emitted from the premixers 1 adjacent to each other in the circumferential direction and the radial direction are opposite in direction. In this way, by making adjacent Lanchester vortices 10 in opposite directions even between radial stages, a flow 14 from the center of the combustor to the premixer is induced. This flow 14 can be generated more effectively by increasing the number of steps in the radial direction. Therefore, by the action similar to that of the ninth embodiment shown in FIG. 11, NOx can be reduced and the flame can be stabilized.

FIG. 13 is a cross-sectional view of a gas turbine combustor which is an eleventh embodiment of the present invention. In the present embodiment, the premixers shown in FIG. 8 are arranged in a lattice in the combustor 5, and the Lanchester vortex 1 emitted from the adjacent premixer 1 is discharged.
The direction of 0 is reversed on all grid points. One premixer (for example, premixer 1a) on the lattice point is surrounded by a maximum of eight premixers (premixers 1b to 1i).
Since the Lanchester vortices discharged from the eight premixer outlets are in opposite directions, the premixer 1a located at the center
To the premixer located in the periphery of the premixer 1a is induced, and the combustion gas combusted at the outlet of the premixer 1a is drawn into each premixer. Such an action occurs on each grid point. Therefore, since each premixer also serves as a pilot burner, the flame transfer characteristics can be effectively improved and the flame can be stabilized. Further, since diffusion combustion is not included, the generation of NOx can be easily suppressed.

FIG. 14 is a view showing a cross section of a gas turbine combustor according to a twelfth embodiment of the present invention. In this embodiment, the combustor 5 is divided into six sectors by the triangular prism structure composed of the plates 19. Inside each triangular prism structure, two premixers 1 for supplying a premixed air and fuel mixture.
And, one swirler 22 that supplies only air is installed,
Each center is arranged so that it forms an equilateral triangle.
Each of the premixers 1 and the swirler 22 has a blade structure inside, and the outlet of the swirler 22 is arranged downstream of the circulation flow 8 formed at the outlet of the premixer 1. The direction of the vertical vortex discharged from each premixer 1 in the triangular prism structure and the circulation strength are the same, and the direction of the vertical vortex discharged from the swirler 22 is opposite to the direction of the vertical vortex of the premixer 1. The circulation strength is set to be half that of the vertical vortex discharged from the premixer 1. By doing so, the above-described Equations 1 and 2 are satisfied, and each premixer 1
Also, the three vertical vortices emitted from the swirler 22 can be combined into one vertical vortex. The premixed gas supplied from each premixer 1 is burned in the circulation flow 8 formed at its outlet, and the flame is cooled downstream of the circulation flow 8 by the combination of the three vertical vortices described above. The high temperature portion where NOx is generated can be limited to the inside of the circulation flow 8, and the generation of NOx can be easily suppressed. As in the present embodiment, the vertical vortex is generated not only in the premixer but also in the means for supplying only air or only fuel, so that NOx reduction and flame stabilization can be achieved.

FIG. 15 is a schematic diagram showing a gas turbine combustor which is a thirteenth embodiment of the present invention. The premixer according to the present embodiment is a cylindrical container 2 having swirl vanes 23 on the inlet side.
It consists of zero. Combustion air 3 from the inlet of the premixer
Is supplied through the swirl vane 23, and the fuel 4 is injected from the fuel injection nozzle 2 installed at the center of the swirl vane 23. The swirl vanes 23 form a swirl flow 24 of the combustion air 3 and mix the fuel 4. The premixed gas thus formed on the inlet side of the premixer flows as it flows downstream,
The mainstream direction shifts from the circumferential direction to the axial direction. Lanchester vortices 10 are formed in the premixer by the blade-shaped structure 9 installed on the downstream side of the position where the main flow direction shifts to the axial direction. In this case, by using the mixing action of both the swirling flow 24 and the Lanchester vortex 10, a uniform premixed gas 11 can be obtained on the outlet side, so NOx
Can be further enhanced. Further, the flame can be stabilized by the circulation flow 8 formed at the outlet of the premixer.

FIG. 16 is a schematic diagram showing a gas turbine combustor according to a fourteenth embodiment of the present invention. The premixer main body in the present embodiment is formed of a cylindrical container 20 provided with a slit portion 25 on the side surface, and a reduction channel 21a is provided on the outlet side thereof. Combustion air 3 is supplied from the slit portion 25 into the cylindrical container 20, and the fuel 4 is injected from the fuel injection nozzle 2 installed at the inlet of the premixer. The combustion air 3 mixes the fuel 4 while forming a swirling flow 24 in the cylindrical container 20. The premixed gas thus formed on the inlet side of the premixer shifts its main flow direction from the circumferential direction to the axial direction as it flows downstream. Due to the blade-shaped structure 9 installed on the downstream side of the position where the main flow direction shifts to the axial direction, a Lanchester vortex 10 is formed in the premixer to uniformly mix the premixed gas. Further, in the reduced flow path 21a, the pressure around the Lanchester vortex 10 rises and the pressure at the center of the vortex decreases, so that the premixed gas mixture is caused by the mixing action of the radial flows based on the pressure difference between the center of the vortex and the surroundings. Uniformity is increased. Therefore, since the uniform premixed gas 11 can be obtained by these actions, the generation of NOx can be further suppressed. On the other hand, at the outlet of the reduction channel 21a, the high-pressure portion around the Lanchester vortex 10 expands in the radial direction, increasing the pressure at the center of the vortex. Circulation flow 8 is formed by the pressure difference between the outlet of the reduction channel 21a and the center of the vortex inside, and blowout of flame can be prevented. Further, since the reduction flow passage 21a has an effect of increasing the flow velocity in the axial direction around the Lanchester vortex 10, a high-speed main flow 7 is formed around the circulation flow 8 at the outlet, thereby preventing flash backfire. be able to. Therefore, the flame can be further stabilized.

FIG. 17 is a vertical cross-sectional view showing in detail around the outlet of the premixer according to the fifteenth embodiment of the present invention, and FIG. 18 is shown in FIG.
It is a block diagram which shows the structure of the turning blade of FIG.

In the drawing, the premixer 1 is provided with a swirl vane 23 shown in FIG. 18 on the outlet side thereof. Swirl blade 2
3 comprises an outer swirl vane 23a and an inner swirl vane 23b formed inside the outer swirl vane 23a, and a fuel pipe 26 having one end connected to the fuel system is connected to the central portion. In the premixer 1, the combustion air supplied from the inlet side and the fuel are mixed by diffusion to form the premixed gas 11,
It flows in the premixer 1 and is discharged into the fuel chamber. At this time, the premixed gas 11 is mixed with the swirl vanes 2 provided on the outlet side of the premixer 1.
3 (outer swirl vane 23a, inner swirl vane 23b) is swirled in the circumferential direction to form a swirl flow. Further, the fuel flows out from the fuel pipe 26 into the combustion chamber and reacts with the premixed gas 11 and burns to form a diffusion flame 12. At this time, the burnt high-temperature burnt gas 27 forms a backflow region near the central axis of the diffusion flame 12 due to the swirling flow formed by the swirl vanes 23 (the outer swirl vanes 23a and the inner swirl vanes 23b). In this case, in the present embodiment, the swirl number is represented by the ratio of the circumferential momentum to the axial momentum of the swirling flow generated by the inner swirl vane 23b, in other words, the ratio of the circumferential flow velocity to the axial flow velocity. The swirl strength is set to be larger than that of the swirl flow generated by the outer swirl vanes 23a. By doing so, the backflow region is enlarged by the swirling action of the outer swirling vanes 23a, and the stagnation region near the central axis that causes blowout of the flame is reduced. Therefore, the circulation flow generated in the vicinity of the central axis of the diffusion flame 12 can be stabilized, the blowout of the flame can be prevented, and the stability of the flame can be improved. Further, by stabilizing the circulation flow generated near the central axis, it is possible to reduce the vibration associated with the fluctuation of the flame.
Further, in this embodiment, the fuel pipe 26 is used for pilot combustion.
It is also effective for other than those that supply fuel through, but when using diffusion (pilot) flames together, flame stability is better and combustion with lean fuel is possible,
NOx can be reduced.

Further, by providing the swirl vanes 23 (outer swirl vanes 23a, inner swirl vanes 23b) in the present embodiment in a tapered shape, the swirl strength near the central axis of the swirl flow can be further increased. This way,
The backflow region formed near the central axis is localized. As a result, the flame length can be shortened and a compact combustor can be realized. Further, when the strength of the swirl is enhanced, the diffusion flame 12 spreads in the radial direction under the influence of the centrifugal force of the swirl flow, and promotes the combustion of the premixed gas in the outer peripheral portion of the swirl flow. As a result, the amount of unburned fuel and the amount of carbon monoxide emission can be reduced. When the strength of the swirl near the central axis is strengthened, the pressure loss near the central axis becomes higher than the pressure loss at the outer peripheral portion and the flow rate is reduced, so the flow velocity near the diffusion flame is reduced and the flame is kept stable. be able to.
The effect of this embodiment can be achieved by increasing the angle of the swirl blade with respect to the swirl axis. However, as in the present embodiment, the tapered swirl vanes are provided downstream of the swirl flow. The turning strength can be enhanced on the side as well.

FIG. 19 is a schematic view showing a gas turbine combustor which is a sixteenth embodiment of this embodiment. The premixer in the present embodiment is provided with the first swirl vane 23 (outer swirl vane 23a, inner swirl vane 23b) shown in FIG. 18 inside and the second swirl vane 23 (outer swirl vane 23) at the outlet. Feather 23c
And the inner swirl vane 23d) are supported by the support rod 28. The second swirl vane 23 is
It is supported at a distance from the cylindrical container 20. The combustion air supplied from the inlet of the premixer and the fuel injected from the fuel injection nozzle are mixed by the first swirl vane 23 provided inside the premixture, and flow toward the downstream in the premixer. Flowing. Then, the support rod 2 is provided on the outlet side of the premixer.
A swirl is applied by a second swirl vane supported at 8. In the present embodiment, the action of the second swirl vanes 23 can strengthen the swirl strength in the vicinity of the center of the swirl flow, so that the same effect as the previous example can be obtained. In addition, in this embodiment, since the swirl flow is also formed inside the premixer, the mixing of the combustion air and the fuel is promoted, and the local high temperature region of the flame due to the spatial nonuniformity of the fuel is generated. Occurrence can be prevented. Therefore, NO
x can be reduced. Further, if a backfire occurs and the flame spreads in the premixer, the present embodiment can easily release the pressure increase in the premixer, which is excellent in safety.

Further, instead of the first swirl vane 23 of this embodiment, a rectangular premixer inlet is formed tangentially to the side surface of the premixer. The premixer inlet thus formed is mounted eccentrically with respect to the central axis of the premixer, so that it forms a swirling flow of the combustion air supplied into the premixer, and Fuel injected from (not shown) is mixed to form a premixture. Then, the swirl vanes 23 supported by the support rods 28 are swirled on the outlet side of the premixer to strengthen the swirl strength in the vicinity of the center of the swirl flow, so that the same effect as described above can be obtained.

FIG. 20 is a vertical sectional view showing a gas turbine combustor according to a seventeenth embodiment of the present invention. This example is 2
1 shows a stage premixing type combustor, in which the combustor 5 is provided with a plurality of first stage premixers 29 around a pilot burner 6 installed at the center and a plurality of second stage premixers downstream thereof. The container 30 is provided. The pilot burner 6 injects the combustion air 3 and the fuel 4 from the nozzle, and the diffusion flame 12
To form. The first-stage premixer 29 mixes the combustion air 3 and the fuel 4 by using the vertical vortex generated by the blade-shaped structure 9 to form the premixed gas 11 and the circulation flow 8 at the outlet. As described above, since the premixed gas 11 is spatially and uniformly mixed by the action of the vertical vortex, the premixed flame 12a does not have a local high temperature region due to uneven concentration, and thus NOx can be reduced. The premixed flame 12 can be formed by the action of the circulation flow 8
a can be stabilized. Further, by making the rotation directions of the vertical vortices generated from the adjacent first-stage premixers 26 opposite to each other, the flame from the diffusion flame 12 to the premix flame 12a can be fired as in the embodiment shown in FIG. The transfer characteristics can be improved and the premixed flame 12a can be stabilized. In this embodiment, the second stage premixer 30 is also used as the first stage premixer 2.
Similar to 6, the premixed gas 11 is mixed by using the vertical vortex generated by the blade-shaped structure 9 to form the circulation flow 8 at the outlet. The premixed flame 12a formed at the outlet of the first stage premixer 26 diffuses to the downstream side and is transferred to the premixed flame at the outlet of the second stage premixer 27 to generate the premixed flame 12b. even here,
The action of the circulation flow 8 achieves the stabilization of the premixed flame 12b. Therefore, the action of the vertical vortex generated in both the first-stage premixer 29 and the second-stage premixer 30 can be combined to reduce the NOx of the combustor 5 and stabilize the flame.
In this embodiment, the flow rate of the premixed gas required in the combustor 5 is appropriately distributed to the first-stage premixer 26 and the second-stage premixer 27 to burn the premixed gas in an ultra-lean burn. Therefore, the effect of reducing NOx can be enhanced.
Further, by supplying a part of the air 3 from the upstream side of the second stage premixer 30 to the generation region of the premix flame 12a,
The structure in the combustor can be cooled to prevent burnout, and the premixed flame 12a can be cooled to further enhance the NOx reduction effect.

Next, a method of operating the gas turbine combustor of this embodiment will be described. At the time of starting the combustor 5, first, the pilot burner 6 is started, and the flow rates of the air 3 and the fuel 4 supplied thereto are gradually increased to increase the diffusion combustion output. Next, when the output reaches the first predetermined ratio of the rated value, the first-stage premixer 29 is activated to increase the flow rate of the premixed gas 11 supplied thereto, whereby the first-stage premixer 29 is mixed. Increase combustion output. At this time,
NOx is reduced by reducing the flow rates of the air 3 and the fuel 4 supplied to the pilot burner 6 and reducing the ratio of the diffusion combustion output to the premixed combustion output. When the output reaches the second predetermined rate of the rating, the first stage premixer 29
And the flow rates of the air 3 and the fuel 4 supplied to the pilot burner 6 are made constant, and the second stage premixer 30 is activated to increase the flow rate of the premixed gas 11 supplied thereto. Increase the premixed combustion power of. When the output reaches the rated value, the flow rates of the air 3 and the fuel 4 supplied to the second stage premixer 27 are kept constant, and the combustor 5 is operated at the rated output. When the combustor 5 is stopped, the operation opposite to that at the start-up may be performed. By appropriately setting the first and second predetermined ratios described above, the instability of the premixed flame at low output is compensated by the stability of the diffusion flame, while the low NOx performance of the premixed flame becomes effective. Since it can be used, it is possible to operate a combustor with low NOx and excellent flame stability. Further, by controlling the output increases of the plurality of first-stage premixers 29 and the second-stage premixers 30 in a stepwise manner, a substantially continuous load operation as a combustor becomes possible.

FIG. 21 is a vertical sectional view showing a gas turbine combustor which is an eighteenth embodiment of the present invention, and FIG. 22 is B of FIG.
It is a sectional view of -B '. The present embodiment shows a two-stage premixing type combustor. The combustor 5 is provided with a plurality of first stage premixers 29 around a pilot burner 6 installed at the center and a plurality of first stage premixers. A plurality of second stage premixers 30 are provided around the mixer 29. In this embodiment,
The pilot burner 6, the first-stage premixer 29, and the second-stage premixer 30 are provided with a swirl vane 23 composed of an outer swirl vane 23a and an inner swirl vane 23b formed inside thereof on the outlet side thereof. Then, swirl is added to the premixed air to form a swirl flow. At this time, the swirl number represented by the ratio of the circumferential momentum to the axial momentum of the swirl flow generated by the inner swirl vane 23b, in other words, the swirl strength represented by the ratio of the circumferential flow velocity to the axial flow velocity. But outside swirl vanes 23
Since it is larger than the swirl flow generated by a, the outer swirl vanes 2
The backflow region formed by the burnt gas of high temperature burned by the swirling action of 3a is enlarged, and the stagnation region near the central axis that causes blowout of the flame is reduced. This allows the diffusion flame 1
The circulation flow generated near the central axis of 2 can be stabilized, blowout of the flame can be prevented, and the stability of the flame can be improved. The swirl vanes of this embodiment form the combustor shown in FIG. 21, that is, a premixture of fuel and air,
Not limited to a combustor that injects fuel at the outlet and burns it together with the premixed air, a combustor that forms a premixed air of fuel and air and burns the premixed air, or a fuel that is separately injected and burned It can be applied to various combustors.

Further, in the present embodiment, the start and stop of the gas turbine combustor is performed in the same order as in the previous example in the order of the pilot banner 6, the plurality of first premixers 29, and the plurality of second premixers 30. By carrying out the operation method described above, it is possible to perform the same effect as the previous example, that is, the operation of the combustor with low NOx and excellent flame stability. Further, by controlling the output increases of the plurality of first-stage premixers 29 and the second-stage premixers 30 in a stepwise manner, it is possible to obtain the effect of enabling substantially continuous load operation as a combustor. .

FIG. 23 is a sectional view showing a gas turbine combustor composed of a plurality of combustors which is a nineteenth embodiment of the present invention. In the drawing, a plurality of combustors 5a, 5b, 5
c is connected by a flame propagation tube 31 to form a combustor group, and each combustor includes a premixer aligned on the same line of the flame propagation tube 32, for example, a pilot burner 6 of the combustor 5a. The swirling flows 24 generated by 1a, 1b, 1c and 1d are arranged so that the swirling directions are the same. Further, the premixer is arranged so that the swirling direction of the swirling flow 24 generated by the concentric premixer is opposite to that of the adjacent concentric premixers. According to the combustor of the present embodiment in which the premixer is arranged in this way, the swirl flow generated in each premixer causes a flow 14 (substantially heart-shaped) shown in the drawing at four points symmetrical about the center of the combustor. Type) is induced. As a result, the diffusion flame formed by the pilot burner 6 is transported to the premixer at the outer peripheral portion by the flow 14 and burns the unburned premixed gas. Further, the premixed flame is transported from the premixer 1d to the premixer of the other combustor 5b through the flame propagation pipe 31, and burns the unburned premixed gas. In this case, the stream 14 formed by the swirling flow 24 transports the premixed flame to the center of the combustor. Further, the premixed gas supplied from each premixer burns while maintaining flame holding by the circulation flow formed at the outlet, thus stabilizing the premixed flame.
According to the present embodiment, it is possible to improve the transfer characteristic of the diffusion flame to the premixer and also to transfer the transfer flame to another combustor. Also, NOx can be reduced.

FIG. 24 is a sectional view showing a gas turbine combustor composed of a plurality of combustors which is a twentieth embodiment of the present invention. In the drawing, a plurality of combustors 5a, 5b, 5
c is connected by a flame propagation tube 31 to form a combustor group, and each combustor includes a pilot burner 6 and a premixer 1.
The swirling flows 24 generated in a, 1b, 1c and 1d have the same swirling direction and are arranged in an annular type. Also, the premixers 1a and 1b, 1b and 1c, 1c and 1d, 1d and 1a.
A fan-shaped premixer 32 is arranged between the two. According to the combustor of the present embodiment in which the premixer is arranged in this way, the swirling flow generated in the premixers 1a, 1b, 1c, 1d and the premixed gas formed by the fan-type premixer 32 are used. A flow 14 (substantially square) as shown in the figure is induced. As a result, the diffusion flame formed by the pilot burner 6 as in the previous example is caused by the flow 14 in the premixers 1a, 1a of the outer peripheral portion.
b, 1c, 1d and the fan-type premixer 32 are transported to burn the unburned premixed gas. Further, the premixed flame is transported from the premixer 1d to the premixer of the other combustor 5b through the flame propagation pipe 31, and burns the unburned premixed gas. According to this embodiment, the transfer characteristic of the diffusion flame to the premixer is further improved.

FIG. 25 is a diagram showing a power generation system using any of the above-described combustors of the present invention. In this embodiment, the high temperature combustion gas 34 generated in the combustor 33 is supplied to the gas turbine 36 to drive it. Part of the power generated by the combustion gas 34 in the gas turbine 36 is used to drive the air compressor 35, and the remaining power is used to drive the generator 38. The air compressor 35 generates the combustion air 3
Are supplied to the combustor 33. The combustion gas 34, after driving the gas turbine 36, generates steam 40 when passing through the waste heat recovery boiler 39, and is discharged from the chimney 37 to the outside air. The steam 40 generated from the waste heat recovery boiler 40 is sent to the steam turbine 41 and drives the generator 42. By using any of the above-described combustors as the combustor 33, 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, and the gas turbine engine that supplies the high temperature combustion gas 34 generated in the combustor 33 to the gas turbine 36 and drives it. Alternatively, the high temperature combustion gas 34 generated in the combustor 33 may be supplied to the gas turbine 36 and driven to drive the generator 38, which may be used as a gas turbine power generation facility.

[0074]

According to the present invention, a combustor and a gas turbine combustor capable of generating Lanchester vortices in a premixer, achieving low NOx, excellent flame stability, and preventing blowout of flame are provided. The effect of being able to provide.

[Brief description of drawings]

FIG. 1 is a perspective view showing a vertical cross section of a gas turbine combustor according to a first embodiment of the present invention.

FIG. 2 is a detailed view around the premixer outlet of FIG.

3 is a view of the wing-shaped structure of FIG. 2 as seen from the direction of arrow A. FIG.

FIG. 4 is a diagram showing a premixer according to a second embodiment of the present invention.

FIG. 5 is a diagram showing a premixer according to a third embodiment of the present invention.

FIG. 6 is a diagram showing a cross section of a premixer according to a fourth embodiment of the present invention.

FIG. 7 is a view showing a vertical cross section of a premixer according to a fifth embodiment of the present invention.

FIG. 8 is a diagram showing a premixer according to a sixth embodiment of the present invention.

FIG. 9 is a view showing a blade-shaped structure in a premixer according to a seventh embodiment of the present invention.

FIG. 10 is a view showing a cross section of a gas turbine combustor according to an eighth embodiment of the present invention.

FIG. 11 is a diagram showing a cross section of a gas turbine combustor according to a ninth embodiment of the present invention.

FIG. 12 is a diagram showing a cross section of a gas turbine combustor according to a tenth embodiment of the present invention.

FIG. 13 is a diagram showing a cross section of a gas turbine combustor which is an eleventh embodiment of the present invention.

FIG. 14 is a view showing a cross section of a gas turbine combustor which is a twelfth embodiment of the present invention.

FIG. 15 is a schematic diagram showing a gas turbine combustor that is a thirteenth embodiment of the present invention.

FIG. 16 is a schematic diagram showing a gas turbine combustor that is a fourteenth embodiment of the present invention.

FIG. 17 is a detailed view around the premixer outlet which is the fifteenth embodiment of the present invention.

FIG. 18 is a configuration diagram showing the configuration of the swirl vane of FIG. 17.

FIG. 19 is a schematic diagram showing a gas turbine combustor which is a sixteenth embodiment of the present invention.

FIG. 20 is a view showing a cross section of a gas turbine combustor which is a seventeenth embodiment of the present invention.

FIG. 21 is a view showing a cross section of a gas turbine combustor which is an eighteenth embodiment of the present invention.

22 is a sectional view taken along the line BB ′ of FIG.

FIG. 23 is a view showing a cross section of a gas turbine combustor including a plurality of combustors according to a nineteenth embodiment of the present invention.

FIG. 24 is a view showing a cross section of a gas turbine combustor including a plurality of combustors according to a twentieth embodiment of the present invention.

FIG. 25 shows a power generation system using a combustor according to the present invention.

[Explanation of symbols]

1 ... Premixer, 2 ... Fuel injection nozzle, 3 ... Air, 4 ... Fuel, 5 ... Combustor body, 6 ... Pilot burner, 6a ...
Fuel injection nozzle, 6b ... Air injection nozzle, 7 ... Mainstream, 8
... Circulating flow, 9 ... Wing-like structure, 10, 15 ... Lanchester vortex, 11 ... Premixed gas, 11a ... Mainstream direction, 12 ... Diffusion flame, 12a, 12b ... Premixed flame, 13 ... Small blade, 14
... Flow, 16a, 16b, 16c ... Delta blade, 17 ... Throat part, 18 ... Fuel injection hole, 19 ... Plate, 20 ... Cylindrical container, 21 ... Diffuser, 21a ... Reduction channel, 22 ...
Swirler, 23 ... swirl vane, 24 ... swirl flow, 25 ... slit part, 26 ... fuel pipe, 27 ... burned gas, 28 ... support rod, 29 ... first stage premixer, 30 ... second stage premix Bowl, 3
1 ... Flame propagation tube, 32 ... Fan type premixer, 33 ... Combustor,
34 ... Combustion gas, 35 ... Air compressor, 36 ... Gas turbine, 37 ... Chimney, 38, 42 ... Generator, 39 ... Exhaust heat recovery boiler, 40 ... Steam, 41 ... Steam turbine.

Claims (6)

[Claims] 1. A combustor having a premixer for mixing air and fuel to form a premixed gas, wherein a blade-shaped structure for generating a vortex having a central axis of rotation in the mainstream direction of the premixed gas is used as the premixer. A combustor provided in a mixer. 2. The combustor according to claim 1, wherein a plurality of the structures are provided in the premixer, and a plurality of vortices generated downstream of the plurality of structures are combined. vessel. 3. A gas turbine combustor having a premixer for mixing air and fuel to produce a premixed gas, and combusting the premixed gas to obtain combustion gas, the air and the fuel are jetted separately. A pilot burner for diffusive combustion is provided in the center of the combustor, and a plurality of the premixers are circumferentially arranged so as to surround the pilot burner, and the premixer rotates in the main flow direction of the premixed gas. A gas turbine combustor characterized by having a built-in wing-shaped structure that generates a vortex with the central axis of the. 4. The gas turbine combustor according to claim 3, wherein the rotation directions of the vortices emitted from the adjacent premixers of the premixers are opposite to each other. . 5. The gas turbine combustor according to claim 3, wherein means for generating a swirling flow of air in the circumferential direction of the premixer is provided in the premixer. vessel. 6. A combustor having a premixer for mixing air and fuel to form a premixed gas, wherein an wing structure for generating a vortex having a central axis of rotation in the mainstream direction of the premixed gas is provided. A combustor, wherein the combustor is provided in the premixer, and a circulation flow is formed in a central portion on an outlet side of the premixer and a main flow is formed outside the circulation flow.