JP6883464B2 - Combustor nozzle, combustor and gas turbine - Google Patents

Description

The present invention relates to combustor nozzles, combustors and gas turbines.

A general gas turbine uses a compressor that compresses external air to generate high-pressure air, a combustor that mixes and burns high-pressure air and fuel to generate high-temperature and high-pressure combustion gas, and combustion gas. It is equipped with a rotationally driven turbine.
As an example of a combustor used in such a gas turbine, the one described in Patent Document 1 below is known. The combustor according to Patent Document 1 mainly includes a combustion cylinder through which combustion gas flows, and a plurality of nozzles that form a flame in the combustion cylinder. The flame formed by the nozzle produces high-temperature and high-pressure combustion gas in the combustion cylinder.

Japanese Unexamined Patent Publication No. 5-203146

By the way, inside the combustor as described above, a phenomenon called flashback may occur in the process of circulation of fuel and air. Flashback is a phenomenon in which a flame propagates to a fuel staying in an unexpected region in a combustor, causing abnormal combustion. In particular, since a swirling flow is formed by the swirling blades on the front side of the nozzle, there is a possibility that the flashback may occur due to the fuel staying in the vortex core.

The present invention has been made to solve the above problems, and an object of the present invention is to provide a combustor nozzle, a combustor, and a gas turbine capable of suppressing the occurrence of flashback.

According to the first aspect of the present invention, the combustor nozzle has a main outer peripheral surface extending along the axis and a reduced outer peripheral surface whose diameter gradually decreases from the main outer peripheral surface toward the front side in the axial direction. And a plurality of shaft bodies extending outward in the radial direction from the main outer peripheral surface of the shaft body and at intervals in the circumferential direction of the shaft line, and a fuel ejection hole for ejecting fuel is formed on the surface. and the swirl vane, the main outer circumferential surface first cylindrical portion surrounding the outer peripheral side only, and, the front side of the axial direction together with continuously in said first cylindrical portion surrounds only the reduced diameter outer peripheral surface from the outer periphery A flow path forming cylinder having a second cylinder portion whose diameter gradually decreases toward the direction of

In this configuration, a flow path forming cylinder is provided on the outer peripheral side of the main outer peripheral surface of the shaft body. Further, the diameter of the second cylinder portion of the flow path forming cylinder is gradually reduced toward the front side in the axial direction. As a result, the flow velocity of the fluid flowing on the inner peripheral side of the flow path forming cylinder in the axial direction can be increased. That is, air can be positively supplied to the vortex core of the swirling flow formed on the front side of the shaft body. Therefore, the fuel concentration in the vortex core can be lowered, and the risk of flashback can be reduced.

According to the second aspect of the present invention, in the above combustor nozzle, the swirl vanes are located on the inner peripheral side of the flow path forming cylinder and on the outer peripheral side of the flow path forming cylinder. It has a swivel blade main body located, and the fuel ejection hole may be formed only in the swivel blade main body.

According to this configuration, the fuel ejection hole is formed only in the swirl vane main body located on the outer peripheral side. Therefore, the fuel concentration can be further reduced on the front side of the support portion located on the inner peripheral side of the swivel blade main body. That is, the fuel concentration in the vortex core can be lowered, and the risk of flashback can be further reduced.

According to the third aspect of the present invention, in the combustor nozzle, the support portion extends from the rear side to the front side in the axial direction and has an airfoil cross-sectional shape with the axis as the axis of symmetry. You may be doing it.

According to this configuration, it is possible to suppress the occurrence of pressure loss when the fluid flowing from the rear side in the axial direction passes around the support portion. As a result, the flow velocity of the fluid flowing on the inner peripheral side of the flow path forming cylinder in the axial direction can be increased. That is, air can be positively supplied to the vortex core of the swirling flow formed on the front side of the shaft body. Therefore, the fuel concentration in the vortex core can be lowered, and the risk of flashback can be reduced.

According to the fourth aspect of the present invention, in the combustor nozzle described above, the rear edge of the support portion and the rear edge of the swivel blade body may be flush with each other.

According to this configuration, the front edge of the support portion and the front edge of the swirl vane body are flush with each other, so that the fluid flow is disturbed or the pressure is generated around these edge edges. The risk of loss can be reduced.

According to the fifth aspect of the present invention, in the above combustor nozzle, the swirl blade main body has a curved tip portion located on the outer side in the radial direction and a notch portion on the front side located on the inner side in the radial direction. It may have a root portion having a.

According to this configuration, since the notch portion is formed in the swirl blade main body, the flow velocity in the axial direction of the air flowing inside the swirl blade main body in the radial direction can be further increased. That is, more air can be supplied to the vortex core of the swirling flow formed on the front side of the shaft body.

According to the sixth aspect of the present invention, in the combustor nozzle, the angle formed by the tangent line tangent to the average warp line of the swirling blade body at the front edge of the swirling blade body and the axis line is the same. The radial inside of the front edge of the swivel blade body is 0 to 10 degrees, and the radial outside of the front edge of the swivel blade body is larger than the radial inside angle of the front edge of the swivel blade body. It may be an angle.

According to this configuration, by reducing the turning angle inside the swirling blade body in the radial direction, the flow velocity in the axial direction of the air flowing inside the swirling blade body in the radial direction can be further increased. That is, more air can be supplied to the vortex core of the swirling flow formed on the front side of the shaft body.

According to the seventh aspect of the present invention, in the combustor nozzle, the portion of the first cylinder portion including the rear edge in the axial direction has a radial dimension from the front side to the rear side. May be gradually reduced.

According to this configuration, when a fluid flows into the inner peripheral side of the first cylinder portion, it is possible to reduce the possibility of causing turbulence in the flow of the fluid or causing pressure loss.

According to the eighth aspect of the present invention, in the combustor nozzle, the flow path forming cylinder is connected to the end of the first cylinder portion on the rear side in the axial direction, and is more than the first cylinder portion. It may have an introduction portion having a large inner diameter dimension.

Here, it is desirable that the cross-sectional area of the space surrounded by the flow path forming cylinder and the shaft body is constant over the entire area in the axial direction so that pressure loss does not occur in the fluid flowing in the space. In the above configuration, since the inner diameter of the introduction portion is larger than the inner diameter of the first cylinder portion, the decrease in the cross-sectional area due to the provision of the support portion can be compensated by the introduction portion.

According to the ninth aspect of the present invention, in the combustor nozzle, the front edge of the second cylinder portion in the axial direction is directed from the rear side to the front side in a cross-sectional view including the axis. The radial dimension may be gradually reduced accordingly.

According to this configuration, when the fluid flows out from the inner peripheral side of the second cylinder portion, it is possible to reduce the possibility that the flow of the fluid is turbulent or pressure loss occurs.

According to the ninth aspect of the present invention, in the above combustor nozzle, assuming that the diameter of the shaft body is D and the inner diameter of the first cylinder portion is B, the ratio D / B of the diameter D and the inner diameter B is. It may be 0.5 ≦ D / B ≦ 0.8.

According to this configuration, by securing the air flow path inside the first cylinder portion, the flow rate of the air flowing through the air flow path can be increased, and the air toward the vortex core can be increased. That is, more air can be supplied to the vortex core of the swirling flow formed on the front side of the shaft body.

According to the tenth aspect of the present invention, the combustor includes a combustor nozzle according to any one of the above aspects and a tubular body that covers the combustor nozzle from the outer peripheral side.

According to this configuration, it is possible to obtain a combustor in which the occurrence of flashback is suppressed.

According to the eleventh aspect of the present invention, the gas turbine relates to the tenth aspect of the above tenth aspect, in which a compressor for generating high-pressure air and the high-pressure air and fuel are mixed and burned to generate combustion gas. It includes a combustor and a turbine driven by the combustion gas.

According to this configuration, a gas turbine that can be operated stably can be obtained.

According to the present invention, it is possible to provide a combustor nozzle, a combustor and a gas turbine capable of suppressing the occurrence of flashback.

It is a schematic diagram which shows the structure of the gas turbine which concerns on 1st Embodiment of this invention. It is sectional drawing which shows the structure of the combustor which concerns on 1st Embodiment of this invention. It is an enlarged sectional view of the main part of the combustor which concerns on the 1st Embodiment of this invention. It is a side view which shows the structure of the combustor nozzle which concerns on 1st Embodiment of this invention. It is sectional drawing which shows the structure of the combustor nozzle which concerns on 1st Embodiment of this invention. It is explanatory drawing which shows the cross-sectional shape of the support part of the swirl vane of the combustor nozzle which concerns on 2nd Embodiment of this invention. It is sectional drawing which shows the structure of the combustor nozzle which concerns on 3rd Embodiment of this invention. It is sectional drawing which shows the structure of the combustor nozzle which concerns on 4th Embodiment of this invention. It is a side view which shows the structure of the combustor nozzle which concerns on 5th Embodiment of this invention. It is explanatory drawing which shows the shape of the swirl vane of the combustor nozzle which concerns on 5th Embodiment of this invention. It is sectional drawing which shows the structure of the combustor nozzle which concerns on 6th Embodiment of this invention.

[First Embodiment]
The first embodiment of the present invention will be described with reference to the drawings. As shown in FIG. 1, the gas turbine 100 according to the present embodiment includes a compressor 1 that generates high-pressure air, a combustor 3 that mixes fuel with high-pressure air and burns it, and a combustion gas. It comprises a turbine 2 driven by.

The compressor 1 has a compressor rotor 11 that extends along the main axis Am and is rotatable around the main axis Am, and a compressor casing 12 that covers the compressor rotor 11 from the outer peripheral side. The compressor rotor 11 has a columnar shape centered on the main axis Am. A plurality of compressor moving blade stages 13 arranged at intervals in the main axis Am direction are provided on the outer peripheral surface of the compressor rotor 11. Each compressor moving blade stage 13 has a plurality of compression moving blades 14 arranged at intervals in the circumferential direction of the main axis Am on the outer peripheral surface of the compressor rotor 11.

The compressor casing 12 has a cylindrical shape centered on the main axis Am. A plurality of compressor stationary blade stages 15 arranged at intervals in the main axis Am direction are provided on the inner peripheral surface of the compressor casing 12. Each compressor stationary blade stage 15 has a plurality of compressor stationary blades 16 arranged at intervals in the circumferential direction of the main axis Am on the inner peripheral surface of the compressor casing 12. The compressor moving blade stage 13 and the compressor stationary blade stage 15 are arranged alternately so as to be staggered in the main axis Am direction.

A plurality of combustors 3 are provided in a region between the compressor casing 12 and the turbine casing 22, which will be described later, at intervals in the circumferential direction of the main axis Am. Each combustor 3 has a tubular shape centered on the combustor axis Ac extending in a direction intersecting the main axis Am. All of these combustors 3 are communicated with the space inside the compressor casing 12. That is, the high-pressure air flowing through the compressor casing 12 is distributed to each of the plurality of combustors 3 via the compressor casing 12.

The turbine 2 has a turbine rotor 21 that extends along the main axis Am and is rotatable around the main axis Am, and a turbine casing 22 that covers the turbine rotor 21 from the outer peripheral side. The turbine rotor 21 has a columnar shape centered on the main axis Am. A plurality of turbine blade stages 23 arranged at intervals in the main axis Am direction are provided on the outer peripheral surface of the turbine rotor 21. Each turbine blade stage 23 has a plurality of turbine blades 24 arranged at intervals in the circumferential direction of the main axis Am on the outer peripheral surface of the turbine rotor 21.

The turbine casing 22 has a cylindrical shape centered on the main axis Am. A plurality of turbine stationary blade stages 25 arranged at intervals in the main axis Am direction are provided on the inner peripheral surface of the turbine casing 22. Each turbine vane stage 25 has a plurality of turbine vanes 26 arranged at intervals in the circumferential direction of the main axis Am on the inner peripheral surface of the turbine casing 22. The turbine blade stage 23 and the turbine blade stage 25 are alternately arranged so as to be staggered in the main axis Am direction.

The compressor rotor 11 and the turbine rotor 21 are coaxially connected in the Am direction of the main axis to form the gas turbine rotor 91. Further, the compressor casing 12 and the turbine casing 22 are connected in the main axis Am direction to form the gas turbine casing 92. That is, the compressor rotor 11 and the turbine rotor 21 can rotate integrally around the main axis Am as the gas turbine rotor 91.

Subsequently, the detailed configuration of the combustor 3 will be described with reference to FIGS. 2 and 3. The combustor 3 has a tubular combustor main body 3M centered on the combustor axis Ac and a fuel nozzle 3N for supplying fuel to the combustor main body 3M. The combustor main body 3M has a first cylinder 41 for accommodating the fuel nozzle 3N and a second cylinder 42 connected to the first cylinder 41 along the combustor axis Ac. In the following description, the side in which the first cylinder 41 is located when viewed from the second cylinder 42 in the extending direction of the combustor axis Ac is referred to as the rear side, and the second cylinder when viewed from the first cylinder 41. The side on which the body 42 is located is called the front side. That is, the combustion gas generated in the combustor 3 flows from the rear side to the front side.

The diameter dimension of the first cylinder body 41 is set smaller than the diameter dimension of the second cylinder body 42. As a result, the front end of the first cylinder 41 is inserted into the rear end of the second cylinder 42. The first cylinder 41 has a cylindrical shape centered on the combustor axis Ac. The diameter of the second tubular body 42 gradually decreases from the rear side to the front side. The fuel nozzle 3N mainly supplies fuel from the rear side toward the inside of the second cylinder 42. More specifically, the fuel nozzle 3N has a first fuel nozzle 51 (combustor nozzle) and a second fuel nozzle 52.

As shown enlarged in FIG. 4 or 5, a plurality of first fuel nozzles 51 are provided at intervals in the circumferential direction of the combustor axis Ac. Each first fuel nozzle 51 is covered with a tubular nozzle cylinder 70 from the outer peripheral side. The nozzle cylinder 70 has a cylindrical shape centered on the first axis. An extension tube 80 is provided on the front side of the nozzle cylinder 70. The first fuel nozzle 51 has a shaft body 51M extending along the first axis A1 (axis line) parallel to the combustor axis Ac, and a plurality of swivels arranged at intervals in the circumferential direction on the outer peripheral side of the shaft body 51M. It has a blade 60 and a tubular flow path forming cylinder 51T that covers the shaft body 51M from the outer peripheral side.

The shaft body 51M has a circular cross section when viewed from the first axis A1 direction. The shaft body 51M has a shaft body main portion 51B forming a portion on the rear side in the direction of the first axis A1 and a reduced diameter portion 51S integrally formed with the shaft body main portion 51B. The shaft body main portion 51B has a uniform outer diameter over the entire area in the direction of the first axis A1. On the other hand, the diameter-reduced portion 51S has a pointed shape by gradually reducing the diameter from the rear side to the front side in the direction of the first axis A1. Here, the outer peripheral surface of the shaft body main portion 51B is the main outer peripheral surface Pm. The main outer peripheral surface Pm in the present embodiment has the same outer diameter dimension over the entire area in the direction of the first axis A1. The outer peripheral surface of the reduced diameter portion 51S is the reduced diameter outer peripheral surface Ps.

Each swivel blade 60 has a support portion 61 connected to the outer peripheral surface of the shaft body 51M, and a swivel blade main body 62 provided on the radial outer side of the support portion 61. As will be described in detail later, the support portion 61 refers to a portion of the swivel blade 60 located on the inner peripheral side of the flow path forming cylinder 51T, and the swivel blade main body 62 refers to the flow path forming cylinder 51T. It refers to the part located on the outer peripheral side. That is, the swirl vane 60 is provided so as to penetrate the flow path forming cylinder 51T in the radial direction.

The support portion 61 has a plate shape extending outward in the radial direction from the main outer peripheral surface Pm of the shaft body main portion 51B. The swivel blade main body 62 has a larger dimension than the support portion 61 in the direction of the first axis A1. Specifically, the portion including the front end portion of the swivel blade main body 62 is located further forward than the front end portion of the support portion 61 in the direction of the first axis A1. On the other hand, the rear edge of the swivel blade main body 62 is flush with the front edge of the support portion 61. That is, these rear edges form one surface continuous in the radial direction of the first axis A1.

Each swivel blade main body 62 has a blade surface that is twisted in the circumferential direction from the rear side in the first axis A1 direction toward the front side. More specifically, the swivel blade main body 62 has a blade cross-sectional shape curved to one side in the circumferential direction when viewed from the radial direction. That is, the surface of the swirl blade main body 62 on one side in the circumferential direction projects on the curved surface toward the one side. On the other hand, the surface of the swirl vane body 62 on the other side in the circumferential direction is recessed on the curved surface toward the other side.

Further, on the surface of the swivel blade main body 62 (that is, each surface facing both sides in the circumferential direction), a plurality of first ejection holes H1 (fuel ejection holes) for ejecting fuel guided from the fuel supply source to the outside are formed. Has been done. The plurality of first ejection holes H1 are arranged on the surface of the swirl vane main body 62 at intervals in the first axis A1 direction and the radial direction. It should be noted that such a first ejection hole H1 is not formed in the support portion 61. That is, in the present embodiment, the first ejection hole H1 is formed only in the swivel blade main body 62.

The flow path forming cylinder 51T has a tubular shape centered on the first axis A1. More specifically, in the flow path forming cylinder 51T, the first cylinder portion T1 surrounding the main outer peripheral surface Pm from the outer peripheral side and the reduced diameter outer peripheral surface Ps continuous with the first cylinder portion T1 from the outer peripheral side. It has a second tubular portion T2 that surrounds it. That is, the first tubular portion T1 is provided on the outer peripheral side of the shaft body main portion 51B having a constant outer diameter dimension, and the second tubular portion T2 is provided on the outer peripheral side of the reduced diameter portion 51S whose outer diameter dimension is gradually reduced. It is provided. The space formed between the outer peripheral surface of the shaft body 51M and the inner peripheral surface of the flow path forming cylinder 51T is an air flow path F for flowing air guided from the rear side.

The first tubular portion T1 has a straight tubular shape extending in the direction of the first axis A1. That is, they have the same inner diameter dimension and outer diameter dimension over the entire area in the direction of the first axis A1. The first tubular portion T1 is provided at a position separated radially outward from the main outer peripheral surface Pm by the size of the support portion 61 in the radial direction. In other words, the inner peripheral surface of the first tubular portion T1 is connected to the outer peripheral end of the support portion 61. A swivel blade main body 62 integrally connected to the support portion 61 extends outward in the radial direction from the outer peripheral surface of the flow path forming cylinder 51T.

The second tubular portion T2 is integrally connected to the front end of the first tubular portion T1 so as to be continuous. In other words, no step or the like is formed between the first cylinder portion T1 and the second cylinder portion T2. The diameter of the second tubular portion T2 is gradually reduced toward the front side in the direction of the first axis A1. Further, the cross-sectional area of the space (air flow path F) surrounded by the inner peripheral surface of the second tubular portion T2 and the reduced diameter outer peripheral surface Ps of the shaft body 51M (diameter reduced portion 51S) is the entire area in the first axis A1 direction. It is constant over. In other words, the value of the inner diameter dimension of the second tubular body 42 is appropriately determined based on the value of the outer diameter dimension of the reduced outer peripheral surface Ps and the value of the cross-sectional area described above.

The second fuel nozzle 52 is arranged on the combustor axis Ac. That is, the second fuel nozzle 52 is surrounded on the outer peripheral side by a plurality of first fuel nozzles 51. More specifically, the second fuel nozzle 52 has a second fuel nozzle body 52M extending along the first axis A1 and a flame holder 52C extending forward of the second fuel nozzle body 52M. ..

A flow path (not shown) for circulating fuel is formed inside the second fuel nozzle main body 52M. A second ejection hole H2 for ejecting the fuel toward the front side is formed at the front end portion of the second fuel nozzle main body 52M. That is, the fuel supplied through the above flow path is blown out toward the front side through the second ejection hole H2. Further, in the vicinity of the second ejection hole H2, an igniter (not shown) for igniting the fuel ejected from the second ejection hole H2 is provided. The flame holder 52C is a cone-shaped member that covers the front end of the second fuel nozzle body 52M from the outer peripheral side.

The operation of the gas turbine 100 configured as described above will be described. In operating the gas turbine 100, first, the compressor rotor 11 (gas turbine rotor 91) is rotationally driven by an external drive source. As the compressor rotor 11 rotates, the external air is sequentially compressed to generate high-pressure air. This high-pressure air is supplied into the combustor 3 through the compressor casing 12. In the combustor 3, the fuel supplied from the fuel nozzle 3N is mixed with the high-pressure air and burned to generate high-temperature and high-pressure combustion gas. The combustion gas is supplied into the turbine 2 through the turbine casing 22. In the turbine 2, rotational driving force is applied to the turbine rotor 21 (gas turbine rotor 91) by sequentially colliding the combustion gas with the turbine blade stage 23 and the turbine stationary blade stage 25. This rotational energy is used to drive the generator G or the like connected to the shaft end.

Next, the detailed operation of the combustor 3 will be described with reference to FIG. 3 again. As shown in the figure, the high-pressure air generated by the compressor 1 is supplied into the first cylinder 41 from one side (rear side) of the combustor axis Ac. The high-pressure air introduced into the first cylinder 41 reaches the inside of the second cylinder 42 on the front side via the space on the inner peripheral side of the nozzle cylinder 70. Here, in the nozzle cylinder 70, the fuel injected from the first injection hole 63 formed on the blade surface of the swirl vane 60 is mixed with the high-pressure air. As a result, a premixed gas containing fuel and high-pressure air is generated in the nozzle cylinder 70. At this time, the flow of the premixed gas contains a swirling flow component given by the swirling vanes 60.

On the other hand, the fuel injected from the second ejection hole H2 of the second fuel nozzle 52 is ignited by an igniter (not shown) to generate a diffuse combustion flame extending from the second fuel nozzle 52 toward the front side. Form. By propagating the diffusion combustion flame to the premixed gas existing in the nozzle cylinder 70, the premixed combustion flame is formed on the front side of the first fuel nozzle 51. The premixed combustion flame extends from the rear side to the front side in the second cylinder 42 together with the above-mentioned swirling flow component, and generates high-temperature and high-pressure combustion gas. The combustion gas flows in the second cylinder from the rear side to the front side, and then is introduced into the turbine casing 22 to drive the turbine 2.

By the way, inside the combustor 3 as described above, a phenomenon called flashback may occur in the process of circulation of fuel and air. Flashback is a phenomenon in which abnormal combustion occurs when a flame propagates to a fuel staying in an unexpected region in the combustor 3. In particular, since a swirling flow is formed by the swirling vanes 60 on the front side of the first fuel nozzle 51, there is a possibility that the flashback may occur due to the fuel staying in the vortex core.

However, in the present embodiment, the flow path forming cylinder 51T is provided on the outer peripheral side of the main outer peripheral surface Pm of the shaft body 51M. Further, the diameter of the second cylinder portion T2 of the flow path forming cylinder 51T is gradually reduced toward the front side in the axial direction. As a result, the flow velocity of the fluid (air) flowing on the inner peripheral side of the flow path forming cylinder 51T in the direction of the first axis A1 can be increased. That is, air can be positively supplied to the vortex core of the swirling flow formed on the front side of the shaft body 51M. Therefore, the fuel concentration in the vortex core can be lowered, and the risk of flashback can be reduced.

Further, in the present embodiment, the first ejection hole H1 is formed only in the swivel blade main body 62. Therefore, the fuel concentration can be further reduced on the front side of the support portion 61 located on the inner peripheral side of the swivel blade main body 62. That is, the fuel concentration in the vortex core can be lowered, and the risk of flashback can be further reduced.

In addition, in the present embodiment, since the front edge of the support portion 61 and the front edge of the swivel blade body 62 are flush with each other, the fluid flow is disturbed around these edge edges. It is possible to reduce the risk of occurrence or pressure loss.

[Second Embodiment]
Next, the second embodiment of the present invention will be described with reference to FIG. The same components as those in the first embodiment are designated by the same reference numerals, and detailed description thereof will be omitted. In the present embodiment, the configuration of the support portion 61 in the swivel blade 60 is different from that in the first embodiment. That is, in the first embodiment, an example in which the support portion 61 has a rectangular cross section when viewed from the radial direction has been described.
As shown in FIG. 6, in the present embodiment, the cross-sectional shape of the support portion 61 is an airfoil when viewed from the radial direction. More specifically, the support portion 61 extends from the rear side in the direction of the first axis A1 toward the front side, and has an airfoil cross-sectional shape with the first axis A1 as the axis of symmetry. In other words, the surfaces of the support portion 61 on both sides in the circumferential direction have a spindle shape that bulges on a curved surface toward both sides in the circumferential direction. Further, the front edge of the support portion 61 (the rear edge in the first axis A1 direction) has a larger dimension in the circumferential direction than the trailing edge (the front edge in the first axis A1 direction).

According to such a configuration, it is possible to suppress the occurrence of pressure loss when the fluid flowing from the rear side in the direction of the first axis A1 passes around the support portion 61. As a result, the flow velocity of the fluid flowing on the inner peripheral side of the flow path forming cylinder 51T in the axial direction can be increased. That is, air can be positively supplied to the vortex core of the swirling flow formed on the front side of the shaft body 51M. Therefore, the fuel concentration in the vortex core can be lowered, and the risk of flashback can be reduced.

[Third Embodiment]
Subsequently, the third embodiment of the present invention will be described with reference to FIG. The same components as those in the above embodiments are designated by the same reference numerals, and detailed description thereof will be omitted. In the present embodiment, the configuration of the flow path forming cylinder 51T is different from each of the above embodiments. In the present embodiment, the flow path forming cylinder 51T has, in addition to the above-mentioned first cylinder portion T1 and second cylinder portion T2, an introduction portion T3 connected to the rear end portion of the first cylinder portion T1. ing.

More specifically, the introduction portion T3 is provided at a position corresponding to the position where the support portion 61 is provided in the direction of the first axis A1. In other words, the support portion 61 is arranged in the region between the rear end portion and the front side end portion of the introduction portion T3.

Further, the introduction portion T3 has an inner diameter larger than that of the first cylinder portion T1. More specifically, the introduction portion T3 is gradually reduced in diameter from the rear side to the front side in the direction of the first axis A1. That is, the opening diameter at the rear end of the introduction portion T3 is larger than the opening diameter at the front end.

In addition, in the present embodiment, the front end portion and the rear end portion of the flow path forming cylinder 51T have a shape different from that of each of the above embodiments. More specifically, the rear end of the flow path forming cylinder 51T is formed so as to gradually become thinner from the front side to the rear side in a cross-sectional view including the first axis A1. More specifically, the rear end of the flow path forming cylinder 51T (first cylinder portion T1) gradually becomes smaller in radial dimension from the front side to the rear side. Similarly, the front end of the flow path forming cylinder 51T (second cylinder T2) is gradually reduced in radial dimension from the rear side to the front side.

According to this configuration, since the rear end of the first cylinder portion T1 is formed to be thin as described above, when the fluid flows into the inner peripheral side of the first cylinder portion T1. In addition, it is possible to reduce the risk of turbulence in the flow of the fluid and pressure loss. Further, since the front end of the second tubular portion T2 is formed to be thin, when the fluid flows out from the inner peripheral side of the second tubular portion T2, the flow of the fluid is disturbed. It is possible to reduce the risk of occurrence or pressure loss.

Further, in the above configuration, the flow path forming cylinder 51T has an introduction portion T3. Here, the cross-sectional area of the space (air flow path F) surrounded by the flow path forming cylinder 51T and the shaft body 51M is in the direction of the first axis A1 so that pressure loss does not occur in the fluid flowing in the space. It is desirable to be constant over the entire area. In the above configuration, since the inner diameter of the introduction portion T3 is larger than the inner diameter of the first cylinder portion T1, the decrease in the cross-sectional area due to the provision of the support portion 61 is compensated by the introduction portion T3. Can be done. As a result, the possibility of causing a pressure loss in the flow of air flowing through the air flow path F is reduced, and air can be efficiently supplied toward the vortex core. That is, the flashback can be suppressed more effectively.

[Fourth Embodiment]
Subsequently, the fourth embodiment of the present invention will be described with reference to FIG. The same components as those in the above embodiments are designated by the same reference numerals, and detailed description thereof will be omitted. In the present embodiment, the configuration of the swivel blade main body 62 is different from each of the above-described embodiments. The swivel blade main body 62E of the present embodiment has a notch 66.

As shown in FIG. 8, the swivel blade 60 of the present embodiment has a support portion 61 connected to the outer peripheral surface of the shaft body 51M and a swivel portion 61 provided on the radial outer side of the support portion 61 and having a notch portion 66. It has a blade body 62E and. The swivel blade main body 62E of the present embodiment is not connected to the flow path forming cylinder 51T from the front end of the swivel blade main body 62E to the rear end of the swivel blade main body 62E.
The swivel blade main body 62E has a curved tip portion 64 which is located on the radial outer side and swirls the premixed gas in the swirl direction, and a root portion 65 which is located on the radial inner side of the tip portion 64. ing. The anterior edge of the root portion 65 is formed by a notch 66.

The cutout portion 66 is formed so that the cutout portion 66 is on the front side of the support portion 61. The radial width W1 of the cutout portion 66 is formed substantially uniformly along the axial direction.
The ratio W2 / W1 of the radial width W2 of the swivel blade main body 62E outside the notch 66 in the radial direction to the radial width W1 of the notch 66 may be 3 ≦ W2 / W1 ≦ 4. preferable.

According to this configuration, since the notch 66 is formed in the swirl blade main body 62E, the flow velocity of the air flowing inside the swirl blade main body 62E in the radial direction in the first axis A1 direction can be further increased. That is, more air can be supplied to the vortex core of the swirling flow formed on the front side of the shaft body 51M.

[Fifth Embodiment]
Subsequently, the fifth embodiment of the present invention will be described with reference to FIGS. 9 and 10. The same components as those in the above embodiments are designated by the same reference numerals, and detailed description thereof will be omitted. In the present embodiment, the configuration of the swivel blade main body 62 is different from each of the above-described embodiments.

As shown in FIG. 9, the front side of the swivel blade main body 62F of the present embodiment becomes more curved in the radial direction from the inner side in the radial direction to the outer side in the radial direction.
In FIG. 10, the dotted line indicates the blade shape at the radial inner end of the swivel blade main body 62F. In FIG. 10, the solid line shows the blade shape at the radial outer end of the swivel blade main body 62F.

In the radial inner blade shape shown by the dotted line, the average warp line (skeleton line) is L11, and the tangent line tangent to the average warp line L11 at the front edge of the swivel blade main body 62F is L12. In the blade shape on the outer peripheral side shown by the solid line, the average warp line (skeleton line) is L21, and the tangent line tangent to the average warp line L21 at the front edge of the swivel blade is L22.

As shown in FIG. 10, at the front edge of the swivel blade main body 62F, the angle formed by the tangent line L12 on the inner peripheral side and the first axis line A1 is 0 degree, and the tangent line L22 and the first axis line A1 on the outer peripheral side The angle formed by is larger than the angle on the inner circumference side.
According to the research of the inventor of the present application, when the angle formed by the tangent line and the axis line in contact with the front edge of the swivel blade with respect to the average warp line is increased from the inner peripheral side to the outer peripheral side, the inside (a) It was found that it is optimal to set the angle on the circumferential side to 0 to 10 degrees and (b) the angle on the outer peripheral side to 25 to 35 degrees.

According to this configuration, by reducing the turning angle inside the swirling blade main body 62F in the radial direction, the flow velocity of the air flowing inside the swirling blade main body 62F in the radial direction in the first axis A1 direction can be further increased. That is, more air can be supplied to the vortex core of the swirling flow formed on the front side of the shaft body 51M.

[Sixth Embodiment]
Subsequently, the sixth embodiment of the present invention will be described with reference to FIG. The same components as those in the above embodiments are designated by the same reference numerals, and detailed description thereof will be omitted. In the present embodiment, the configuration of the shaft body 51M is different from each of the above embodiments.
As shown in FIG. 11, the diameter D of the shaft body 51MG of the first fuel nozzle 51 of the present embodiment is larger than the diameter D0 of the shaft body 51M (indicated by the alternate long and short dash line) of the first to fifth embodiments. small. Specifically, assuming that the inner diameter of the first cylinder portion T1 of the flow path forming cylinder 51T is B, the ratio D / B of the diameter D of the shaft body 51MG and the inner diameter B of the first cylinder portion T1 is 0.5 ≦ D. It is preferable that / B ≦ 0.8.

According to this configuration, by securing the air flow path F inside the first cylinder portion T1, the flow rate of the air flowing through the air flow path F can be increased, and the air toward the vortex core can be increased. That is, more air can be supplied to the vortex core of the swirling flow formed on the front side of the shaft body.

Each embodiment of the present invention has been described above. It is possible to make various changes to each of the above configurations as long as the gist of the present invention is not deviated. For example, as for the cross-sectional shape of the swivel blade main body 62, in addition to the shape described in each of the above embodiments, various shapes can be adopted depending on the design and specifications.

1 ... Compressor 2 ... Turbine 3 ... Combustor 11 ... Compressor rotor 12 ... Compressor casing 13 ... Compressor moving blade stage 14 ... Compressor moving blade 15 ... Compressor stationary blade stage 16 ... Compressor stationary blade 21 ... Turbine rotor 22 ... Turbine casing 23 ... Turbine moving blade stage 24 ... Turbine moving blade 25 ... Turbine stationary blade stage 26 ... Turbine stationary blade 41 ... First cylinder 42 ... Second cylinder 51 ... First fuel nozzle 52 ... Second fuel nozzle 60 ... Swivel vanes 61 ... Supports 62, 62E, 62F ... Swivel blades 63 ... First injection hole 64 ... Tip 65 ... Root 66 ... Notch 70 ... Nozzle cylinder 80 ... Extension pipe 91 ... Gas turbine rotor 92 ... Gas turbine casing 100 ... Gas turbine 3M ... Compressor body 3N ... Fuel nozzle 51B ... Shaft body main part 51M, 51MG ... Shaft body 51S ... Reduced diameter part 51T ... Flow path forming cylinder 52C ... Flame holder 52M ... Second fuel nozzle Main body A1 ... First axis Ac ... Compressor axis Am ... Main axis F ... Air flow path H1 ... First ejection hole H2 ... Second ejection hole Pm ... Main outer peripheral surface Ps ... Reduced diameter outer peripheral surface T1 ... First cylinder T2 … Second cylinder part T3… Introduction part

Claims (12)

A shaft body having a main outer peripheral surface extending along the axis and a reduced outer peripheral surface whose diameter gradually decreases toward the front side in the axial direction from the main outer peripheral surface.
A swirl vane extending from the main outer peripheral surface of the shaft body in the radial direction and having a plurality of blades provided at intervals in the circumferential direction of the shaft body and having fuel ejection holes formed on the surface thereof.
First cylindrical portion surrounding only the main outer surface in the outer peripheral side, and gradually reduced toward the front side of the axial direction together with continuously in said first cylindrical portion surrounds only the reduced diameter outer peripheral surface from the outer periphery A flow path forming cylinder having a second cylinder having a diameter,
Combustor nozzle with. The swivel blade has a support portion located on the inner peripheral side of the flow path forming cylinder and a swirling blade main body located on the outer peripheral side of the flow path forming cylinder.
The combustor nozzle according to claim 1, wherein the fuel ejection hole is formed only in the swivel blade main body. The combustor nozzle according to claim 2, wherein the support portion extends from the rear side to the front side in the axial direction and has a blade cross-sectional shape having the axis as a symmetric axis. The combustor nozzle according to claim 2 or 3, wherein the rear edge of the support portion and the rear edge of the swivel blade body are flush with each other. Any one of claims 2 to 4, wherein the swivel blade main body has a curved tip portion located on the outer side in the radial direction and a root portion located on the inner side in the radial direction and having a notch on the front side. Combustor nozzle described in. The angle between the tangent line in contact with the average warp line of the swivel blade body at the front edge of the swivel blade body and the axis is 0 to 10 degrees inside the front edge of the swivel blade body in the radial direction. The method according to any one of claims 2 to 5, wherein the angle on the outer side in the radial direction of the front edge of the swivel blade main body is larger than the angle on the radial inner side of the front edge of the swivel blade main body. Combustor nozzle. The portion of the first tubular portion including the rear edge in the axial direction is according to any one of claims 1 to 6, wherein the radial dimension is gradually reduced from the front side to the rear side. Combustor nozzle. Any one of claims 1 to 7, wherein the flow path forming cylinder is connected to the end of the first cylinder portion on the rear side in the axial direction and has an introduction portion having an inner diameter dimension larger than that of the first cylinder portion. Combustor nozzle as described in the section. The edge of the second cylinder portion on the front side in the axial direction is any of claims 1 to 8 in which the radial dimension is gradually reduced from the rear side to the front side in a cross-sectional view including the axis. The combustor nozzle according to one item. Assuming that the diameter of the shaft body is D and the inner diameter of the first cylinder portion is B, the ratio D / B of the diameter D and the inner diameter B is 0.5 ≦ D / B ≦ 0.8. The combustor nozzle according to any one of the above. The combustor nozzle according to any one of claims 1 to 10.
A cylinder that covers the combustor nozzle from the outer peripheral side,
Combustor equipped with. A compressor that produces high-pressure air,
The combustor according to claim 11, wherein the high-pressure air and fuel are mixed and burned to generate combustion gas.
The turbine driven by the combustion gas and
A gas turbine equipped with.

Images