Combustion burner, combustor, and gas turbine having a swirl vane with opposite directed surfaces

Abstract

A combustion burner includes a nozzle and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle. The swirl vane includes a tip portion for swirling gas, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle, the root portion having a cutout on a side of a trailing edge. The radially-outer region and a radially-inner region of the axial flow path communicate with each other, at least in a range in the axial direction in which the swirl vane is disposed. The swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge.

Claims

1. A combustion burner comprising: a nozzle; and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle around the nozzle, wherein the swirl vane includes a tip portion for swirling gas in a swirl direction, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle as seen from the tip portion, the root portion having a cutout on a side of a trailing edge, wherein the radially-outer region and a radially-inner region of the axial flow path communicate with each other without being partitioned, at least in a range in the axial direction in which the swirl vane is disposed, wherein the swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge, wherein the trailing edge of the root portion of the swirl vane is formed by a downstream edge of the curved surface in the axial direction, the trailing edge of the root portion being disposed on an upstream side in the axial direction as compared to the trailing edge of the tip portion, wherein the pressure surface of the swirl vane at the tip portion has a curved surface curving in the swirl direction toward the trailing edge, and wherein the pressure surface of the swirl vane has a stepped portion between the curved surface of the tip portion and the curved surface of the root portion.

2. The combustion burner according to claim 1, wherein the trailing edge of the root portion of the swirl vane is disposed on an upstream side in the swirl direction, as compared to the trailing edge of the tip portion.

3. The combustion burner according to claim 2, wherein the trailing edge of the root portion of the swirl vane is disposed on a position same as that of a leading edge of the root portion, in a circumferential direction of the nozzle.

4. The combustion burner according to claim 1, wherein the airfoil of the root portion of the swirl vane has a line-symmetric shape with respect to a straight line parallel to the axial direction and passing through the trailing edge, at least on the side of the trailing edge.

5. The combustion burner according to claim 2, wherein the trailing edge of the root portion of the swirl vane is disposed on a side opposite to the trailing edge of the tip portion across a straight line parallel to the axial direction and passing through the leading edge, in the circumferential direction of the nozzle.

6. The combustion burner according to claim 1, wherein the curved surface at the root portion is configured to swirl gas in a direction opposite to the swirl direction, the gas flowing through the radially-inner region of the axial flow path.

7. The combustion burner according to claim 1, wherein a bisector of an angle formed by a tangent of the pressure surface passing through the trailing edge of the root portion and a tangent of a suction surface passing through the trailing edge of the root portion is oblique to the axial direction in a direction opposite to the swirl direction, at a downstream side of the trailing edge.

8. The combustion burner according to claim 1, wherein the leading edge of the swirl vane is oblique to the radial direction toward an upstream side in the axial direction as the leading edge gets closer to an outer side in the radial direction of the nozzle, at least on a side of the tip portion.

9. The combustion burner according to claim 1, wherein the tip portion includes a cutout-space forming surface disposed on a radially-outer side of a cutout space formed by the cutout, the cutout-space forming surface facing the cutout space, in a downstream region of the tip portion, and wherein the cutout-space forming surface has a shape such that a width of the cutout space in the radial direction increases toward a downstream side.

10. The combustion burner according to claim 9, wherein the cutout-space forming surface is a flat surface extending linearly and oblique to the axial direction so that the width of the cutout space in the radial direction increases toward the downstream side.

11. A combustor comprising: the combustion burner according to claim 1, and a combustor liner for forming a flow path for guiding combustion gas from the combustion burner.

12. A gas turbine comprising: a compressor for generating compressed air; the combustor according to claim 11 configured to combust fuel with the compressed air from the compressor to generate combustion gas; and a turbine configured to be driven by the combustion gas from the combustor.

13. A combustion burner comprising: a nozzle; and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle around the nozzle, wherein the swirl vane includes a tip portion for swirling gas in a swirl direction, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle as seen from the tip portion, the root portion having a cutout on a side of a trailing edge, wherein the radially-outer region and a radially-inner region of the axial flow path communicate with each other without being partitioned, at least in a range in the axial direction in which the swirl vane is disposed, wherein the swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge, wherein the pressure surface of the swirl vane at the tip portion has a curved surface curving in the swirl direction toward the trailing edge, wherein the pressure surface of the swirl vane has a stepped portion between the curved surface of the tip portion and the curved surface of the root portion, wherein an airfoil of the root portion has a shape same as that of an airfoil of the tip portion in an upstream region, and has a shape such that a portion corresponding to the cutout is cut out from the airfoil of the tip portion in the downstream region, and wherein the trailing edge of the root portion of the swirl vane is formed by a downstream edge of the pressure surface of the root portion including the curved surface so as to be disposed on a suction surface of the airfoil of the root portion having the same shape as the tip portion.

Description

BRIEF DESCRIPTION OF DRAWINGS

(1) FIG. 1 is a schematic configuration diagram of a gas turbine according to one embodiment.

(2) FIG. 2 is a cross-sectional view of a combustor according to one embodiment.

(3) FIG. 3 is a cross-sectional view of a part of a combustor according to one embodiment.

(4) FIG. 4 is a cross-sectional view of a combustion burner according to one embodiment.

(5) FIG. 5 is a view on arrow A of the combustion burner illustrated in FIG. 4.

(6) FIG. 6 is a side view of a nozzle and a swirler according to one embodiment.

(7) FIG. 7 is a planar view of a configuration example of a swirler.

(8) FIG. 8 is a side view of a nozzle and a swirler according to a comparison example.

(9) FIG. 9 is a graph showing a relationship between a mean axial-flow velocity and a radial distance at an outlet of an extension tube of the embodiment and the comparison example.

(10) FIG. 10 is a perspective view of a swirler according to one embodiment.

(11) FIG. 11 is a side view of a nozzle and a swirler according to another embodiment.

(12) FIG. 12 is a planar view of a configuration example of a swirl vane illustrated in FIG. 11.

(13) FIG. 13 is a planar view of another configuration example of a swirl vane illustrated in FIG. 11.

(14) FIG. 14 is a side view of a nozzle and a swirler according to another embodiment.

(15) FIG. 15 is a graph showing a relationship between a mean axial-flow velocity and a radial distance at an outlet of an extension tube of the embodiment and the comparison example.

(16) FIG. 16 is a side view of a nozzle and a swirler according to another embodiment.

DETAILED DESCRIPTION

(17) Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It is intended, however, that unless particularly specified, dimensions, materials, shapes, relative positions and the like of components described in the embodiments shall be interpreted as illustrative only and not intended to limit the scope of the present invention.

(18) First, with reference to FIG. 1, a gas turbine to which a combustion burner and a combustor according to the present invention are to be applied will be described. FIG. 1 is a schematic configuration diagram of a gas turbine 1 according to one embodiment.

(19) As illustrated in FIG. 1, the gas turbine 1 according to one embodiment includes a compressor 2 for producing compressed air that serves as an oxidant, a combustor 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be driven to rotate by the combustion gas. In the case of the gas turbine 1 for power generation, a generator (not illustrated) is connected to the turbine 6, so that rotational energy of the turbine 6 generates electric power.

(20) The configuration example of each component in the gas turbine 1 will be described specifically.

(21) The compressor 2 includes a compressor casing 10, an air inlet 12 for sucking in air, disposed on an inlet side of the compressor casing 10, a rotor 8 disposed so as to penetrate through both of the compressor casing 10 and the turbine casing 22 described below, and a variety of vanes disposed in the compressor casing 10. The variety of vanes includes an inlet guide vane 14 disposed adjacent to the air inlet 12, a plurality of stator vanes 16 fixed to the compressor casing 10, and a plurality of rotor vanes 18 implanted on the rotor 8 so as to be arranged alternately with the stator vanes 16. The compressor 2 may include other constituent elements not illustrated in the drawings, such as an extraction chamber. In the above compressor 2, the air sucked in from the air inlet 12 flows through the plurality of stator vanes 16 and the plurality of rotor vanes 18 to be compressed to turn into compressed air having a high temperature and a high pressure. The compressed air having a high temperature and a high pressure is sent to the combustor 4 of a latter stage from the compressor 2.

(22) The combustor 4 is disposed in a casing 20. As illustrated in FIG. 1, a plurality of combustors 4 may be disposed in an annular shape centered at the rotor 8 inside the casing 20. The combustor 4 is supplied with fuel and the compressed air produced in the compressor 2, and generates combustion gas that serves as a working fluid of the turbine 6 by combusting the fuel. The combustion gas is sent to the turbine 6 at a latter stage from the combustor 4. The configuration example of the combustor 4 will be described later in detail.

(23) The turbine 6 includes a turbine casing 22 and a variety of vanes disposed inside the turbine casing 22. The variety of vanes includes a plurality of stator vanes 24 fixed to the turbine casing 22 and a plurality of rotor vanes 26 implanted on the rotor 8 so as to be arranged alternately with the stator vanes 24. The turbine 6 may include other constituent elements not illustrated in the drawings, such as outlet guide vanes and the like. In the turbine 6, the rotor 8 is driven to rotate as the combustion gas passes through the plurality of stator vanes 24 and the plurality of rotor vanes 26. In this way, the generator connected to the rotor 8 is driven.

(24) An exhaust chamber 30 is connected to the downstream side of the turbine casing 22 via an exhaust casing 28. The combustion gas having driven the turbine 6 is discharged outside via the exhaust casing 28 and the exhaust chamber 30.

(25) Next, with reference to FIGS. 2 and 3, the specific configuration of the combustor 4 according to one embodiment will be described. FIG. 2 is a cross-sectional view of a combustor according to one embodiment. FIG. 3 is a cross-sectional view of a part of a combustor according to one embodiment.

(26) As illustrated in FIGS. 2 and 3, a plurality of combustors 4 according to one embodiment is disposed in an annular shape centered at the rotor 8 (see FIG. 1). Each combustor 4 includes a combustor liner 46 disposed in a combustor casing 40 defined by the casing 20, a pilot combustion burner 50 disposed in the combustor liner 46, and a plurality of premix combustion burners (main combustion burners) 60 disposed in the combustor liner 46. The combustor 4 may include other constituent elements such as a bypass line (not illustrated) for causing the combustion gas to bypass.

(27) For instance, the combustor liner 46 includes a combustor basket 46a disposed around the pilot combustion burner 50 and the plurality of premix combustion burners 60, and a transition piece 46b connected to a distal end of the combustor basket 46a.

(28) The pilot combustion burner 50 is disposed along the center axis of the combustor liner 46. The plurality of premix combustion burners 60 is arranged at a distance from one another so as to surround the pilot combustion burner 50.

(29) The pilot combustion burner 50 includes a pilot nozzle (nozzle) 54 connected to a fuel port 52, a pilot cone 56 disposed so as to surround the pilot nozzle 54, and a swirler 58 disposed on the outer circumference of the pilot nozzle 54.

(30) The premix combustion burner 60 includes a main nozzle (nozzle) 64 connected to a fuel port 62, a burner cylinder 66 disposed so as to surround the nozzle 64, an extension tube 65 for connecting the burner cylinder 66 and the combustor liner 46 (e.g. combustor basket 46a), and a swirler 70 disposed on the outer circumference of the nozzle 64. The specific configuration of the premix combustion burner 60 will be described later.

(31) As illustrated in FIG. 3, the extension tube 65 extends from an upstream end surface connected to the burner cylinder 66 to a downstream end surface (extension-tube outlet 65a). Further, FIG. 3 illustrates a flow-path center axis O passing through the center position of the extension-tube outlet 65a.

(32) In the combustor 4 having the above configuration, the compressed air having a high temperature and a high pressure produced in the compressor 2 is supplied into the combustor casing 40 from a casing inlet 42, and then flows into the burner cylinder 66 from the combustor casing 40. The compressed air and fuel supplied from the fuel port 62 are premixed in the burner cylinder 66. At this time, the premixed air mainly forms a swirl flow by the swirler 70, and flows into the combustor liner 46. Further, the compressed air and fuel injected from the pilot combustion burner 50 via the fuel port 52 are mixed in the combustor liner 46, and ignited by a pilot light (not illustrated) to be combusted, thereby generating combustion gas. At this time, a part of the combustion gas diffuses to the surroundings with flames, which ignites the premixed air flowing into the combustor liner 46 from each premix combustion burner 60 to cause combustion. Specifically, the pilot flame due to the pilot fuel injected from the pilot combustion burner 50 makes it possible to secure flames for performing stable combustion of premixed air (premixed fuel) from the premix combustion burners 60. At this time, a combustion region is formed, for instance, in the combustor basket 46a.

(33) Now, the configuration of the combustion burner according to the present embodiment will be described in detail referring to the above described premix combustion burner 60 as an example.

(34) The combustion burner according to the present embodiment is not limited to the premix combustion burner 60, and the configuration of the present embodiment can be applied to a combustion burner of any type as long as the combustion burner includes a swirler (swirl vane) in an axial flow path around a nozzle. For instance, the combustion burner may be a combustion burner which mainly performs diffusive combustion like the pilot combustion burner 50 disposed in the combustors 4 of the gas turbine 1, or may be a combustion burner disposed in a device other than the gas turbine 1.

(35) FIGS. 4 and 5 illustrate the schematic configuration of the combustion burner (premix combustion burner) 60 according to one embodiment. FIG. 4 is a cross-sectional view along the axial direction of the nozzle of the combustion burner 60 according to one embodiment, and FIG. 5 is a view on arrow A of the combustion burner illustrated in FIG. 4.

(36) The combustion burner 60 according to one embodiment includes a nozzle (fuel nozzle) 64, a burner cylinder 66, and a swirler 70.

(37) The nozzle 64 is connected to the fuel port 62 (see FIGS. 2 and 3) as described above, and fuel is supplied from the fuel port 62. The fuel may be gas or liquid, and the type is not particularly limited. Further, the pilot nozzle 54 and the nozzle 64 may be supplied with different types of fuel. For instance, the pilot nozzle 54 may be supplied with oil fuel while the nozzle 64 is supplied with gas fuel such as natural gas fuel.

(38) The burner cylinder 66 is disposed concentrically with the nozzle 64 and so as to surround the nozzle 64. Specifically, the axis of the burner cylinder 66 substantially coincides with the axis O of the nozzle 64, and the diameter of the burner cylinder 66 is larger than the diameter of the nozzle 64.

(39) An axial flow path 68 of an annular shape is formed along the axial direction of the nozzle 64 between the outer circumferential surface of the nozzle 64 and the inner circumferential surface of the burner cylinder 66. Gas G such as compressed air flows through the axial flow path 68 from the upstream side (left side in FIG. 4) toward the downstream side (right side in FIG. 4).

(40) The swirler 70 is configured to swirl gas flowing through the axial flow path 68, and includes at least one swirl vane 72. In an example illustrated in FIGS. 4 and 5, the swirler 70 includes six swirl vanes 72 disposed radially from the nozzle 64 at the center. In FIG. 4, as a matter of convenience, the drawings illustrate only two swirl vanes 72 disposed at the positions of 0 and 180 angular degrees along the circumferential direction (in the situation illustrated in FIG. 4, four swirl vanes 72 in total could be seen in reality).

(41) The swirl vanes 72 are disposed around the nozzle 64 in the axial flow path 68 extending in the axial direction (direction of the axis O) of the nozzle 64, and configured to apply a swirl force to the gas flowing through the axial flow path 68. Each swirl vane 72 has a pressure surface 81, a suction surface 82, a leading edge 83 being an upstream edge in the flow direction of the gas (the axial direction of the nozzle 64), and a trailing edge 84 being a downstream edge in the flow direction of the gas (the axial direction of the nozzle 64).

(42) A plurality of injection apertures 74, 77 is formed on the swirl vanes 72. In the present embodiment, as an example, two injection apertures 74, 75 are formed on the pressure surface 81 of the swirl vane 72, and two injection apertures 76, 77 are formed on the suction surface 82 of the swirl vane 72. The plurality of injection apertures 74 to 77 may be disposed on the side of the leading edge 83 of the swirl vane 72. Further, two injection apertures 74 and 75, or two injection apertures 76 and 77, that open on the same surface, may be disposed offset from each other with respect to the axial direction or the radial direction of the nozzle 64. The injection apertures 74 to 77 communicate with each other inside the swirl vane 72, and also to a fuel path in the nozzle 64. Fuel injected from the injection apertures 74 to 77 is mixed with gas (e.g. compressed air serving as an oxidant) to become premixed gas (fuel gas), and is sent to the combustor liner 46 to be combusted.

(43) Further, a cutout 90 is formed on the trailing edge 84 of each swirl vane 72, in a region 68b at the radially inner side within the axial flow path 68 (hereinafter, referred to as a radially-inner flow path region). Specifically, the swirl vanes 72 are configured to form mainly a swirl flow in a region at the radially outer side within the axial flow path 68 (hereinafter, referred to as a radially-outer flow path region), and form mainly an axial flow in the radially-inner flow path region 68b by the cutouts 90. The specific configuration of the cutouts 90 will be described later.

(44) With reference to FIGS. 6 to 17, the configuration example of the swirl vanes 72 will be described specifically, except FIG. 8 illustrates a swirl vane of a comparative example. In FIGS. 6 to 17, the same component is indicated by the same reference numeral.

(45) The swirl vanes 72a to 72d illustrated in FIGS. 6 to 17 include a tip portion 85 for swirling gas that flows through the radially-outer flow path region 68a (see FIG. 4) in a swirl direction, and a root portion 86 disposed on the inner side in the radial direction of the nozzle 64 as seen from the tip portion 85, i.e., disposed in the radially-inner flow path region 68b (see FIG. 4), the trailing edge 93 of the root portion 86 being defined by cutouts 90a to 90d.

(46) On the pressure surface 81 of the tip portion 85 of the swirl vanes 72a to 72d, a curved surface 91 curving from the upstream side toward the downstream side is formed so as to apply a swirling force mainly to the gas flowing through the axial flow path 68. Specifically, the pressure surface 81 of the tip portion 85 of the swirl vanes 72a to 72d is configured such that the angle formed between a camber line C (see FIG. 7) of the pressure surface 81 and the flow direction of the gas (i.e. the axial direction of the nozzle 64) gradually increases from the upstream side toward the downstream side. The angle formed between the camber line C and the flow direction of the fluid may be within a range of from 20 to 30 in a downstream region of the tip portion 85 of the swirl vanes 72a to 72d. Due to the curved surface 91 of the pressure surface 81 of the tip portion 85 configured as described above, the gas flowing through the radially-outer flow path region 68a forms into a swirl flow D swirling in a swirl direction.

(47) On the other hand, a downstream region of the pressure surface 81 of the root portion 86 of the swirl vanes 72a to 72d is defined by the cutouts 90a to 90d as curved surfaces 92a to 92d which curve opposite to a swirl direction toward the trailing edge 93 of the root portion 86. That is, the downstream region of the root portion 86 is curved in a direction opposite to the tip portion 85. The curved surfaces 92a to 92d of the pressure surface 81 of the root portion 86 configured as described above form gas flows E, F in the radially inner region.

(48) The trailing edge 93 of the root portion 86 of the swirl vanes 72a to 72d may be disposed on the upstream side in the axial direction and on the upstream side in the swirl direction as compared to the trailing edge of the tip portion 85.

(49) Further, at least in a range in the axial direction in which the swirl vanes 72a to 72d are provided, the radially-outer flow path region 68a and the radially-inner flow path region 68b of the axial flow path 68 are communicating with each other without being partitioned. The range in the axial direction refers to the range along the axis O of the nozzle 64.

(50) That is, as illustrated in the above described FIG. 5, a plurality of axial flow paths 68 is formed in a radial fashion radially outside the nozzle 64 centered at the axis O, and between adjacent swirl vanes 72 (72a to 72d) as seen from the tip end of the nozzle 64. In each of the axial flow paths 68, the radially-outer flow path region 68a and the radially-inner flow path region 68b are in communication so that a single space is formed in the radial direction of the nozzle 64. The axial flow path 68 may include no portion between the radially-outer flow path region 68a and the radially-inner flow path region 68b, the radially-outer flow path region 68a and the radially-inside flow path region 68b communicating with each other (as illustrated in the drawings), or may include another portion (not illustrated) between the radially-outer flow path region 68a and the radially-inside flow path region 68b, the radially-outer flow path region 68a and the radially-inside flow path region 68b partially communicating with each other.

(51) With the above configuration, at the tip portion 85 of the swirl vanes 72a to 72d, the gas flowing through the radially-outer flow path region 68a of the axial flow path 68 is swirled, which makes it possible to promote premix of the gas and the fuel supplied to the axial flow path 68 by the swirl flow D formed by the tip portion 85. On the other hand, the cutouts 90a to 90d are formed on the downstream side of the root portions 86 of the swirl vanes 72a to 72d, and the cutouts 90a to 90d form the curved surfaces 92a to 92d curving in a direction opposite to the swirl direction toward the trailing edge 93 of the root portions 86 in the downstream region of the pressure surface 81 of the root portions 86. Thus, in the radially-inner flow path region 68b of the axial flow path 68, the gas is attracted toward the curved surfaces 92a to 92d by the Coanda effect to be rectified in a direction opposite to the swirl direction. As a result, the swirl component applied to the gas in the upstream region of the pressure surface 81 of the root portion 86 weakens in the downstream region of the pressure surface 81 of the root portion 86, which increases the mean axial-flow velocity in the radially-inner flow path region 68b to improve the flashback-resistant property. The gas further flows along the curved surfaces 92a to 92d in the downstream region of the pressure surface 81 of the root portion 86, which makes it possible to suppress occurrence of turbulence due to separation of the flow at the downstream side of the cutouts 90a to 90d, and to prevent the axial-flow velocity from becoming unstable due to a negative fluctuation component caused by such turbulence. Thus, it is possible to suppress a fluctuation in the axial-flow velocity in the radially-inner flow path region 68b and to improve the flashback-resistant property effectively.

(52) Further, at least in a range in the axial direction in which the swirl vanes 72a to 72d are provided, the radially-outer flow path region 68a and the radially-inner flow path region 68b of the axial flow path 68 of the combustion burner 60 are communicating with each other without being partitioned. In this way, the mixing of the gas flowing through the radially-outer flow path region 68a and the gas flowing through the radially-inner flow path region 68b is promoted. Thus, the concentration distribution of the fuel supplied to the axial flow path 68 is equalized in the radial direction of the combustion burner 60.

(53) Now, with reference to FIG. 9, the flashback-resistant property of the combustion burner of the present embodiment will be compared to that of the comparison example. FIG. 9 is a graph showing a relationship between a mean axial-flow velocity and a radial distance at an outlet of an extension tube of the embodiment and the comparison example. In the drawing, the combustion burner of the embodiment includes the nozzle 64 and the swirler 70a illustrated FIGS. 6 and 7, and the combustion burner of the comparison example includes the nozzle 120 and the swirler 102 illustrated in FIG. 8, and the mean axial-flow velocity of each case is shown.

(54) In the comparison example illustrated in FIG. 8, the swirler 102 includes a plurality of swirler vanes 104 disposed in a radial fashion around the nozzle 120. Each swirl vane 104 includes a tip portion 116 at the radially outer side and a root portion 118 at the radially inner side. Further, the swirl vane 104 includes a pressure surface 106, a suction surface 108, a leading edge 110, and a trailing edge 112. In the above configuration (e.g. the number and arrangement of the swirl vanes), the comparison example is substantially the same as the configuration of the present embodiment. Further, the swirl vane 104 includes a cutout 115 having a configuration different from that of the present embodiment. The cutout 115 is formed on a downstream region of the root portion 118 of the swirl vane 104, and the cutout 115 defines the trailing edge 114 of the root portion 118 in a planar shape orthogonal to the axis O of the nozzle 120. That is, the trailing edge 114 of the root portion 118 is formed by an end surface orthogonal to the axis O of the nozzle 120 between the pressure surface 106 and the suction surface 108 of the root portion 118.

(55) As described above, according to the findings of the present inventors, flashback that may occur in a combustion burner (vortex-core flashback, in particular) is likely to occur when the mean axial-flow velocity of the combustion burner decreases extremely in the radially-inner flow path region 68b. Thus, for each of the combustion burner in the present embodiment and the combustion burner in the comparison example, computational fluid dynamics (CFD) is used to calculate the mean axial-flow velocity with respect to the radial distance of the nozzles 64, 120. The mean axial-flow velocity mentioned here is the axial-flow velocity at the outlet of the extension tube at the downstream side of the nozzles 64, 120 averaged over a predetermined period.

(56) As a result, in the combustion burner of the comparison example, the mean axial-flow velocity decreases more considerably in the radially-inner flow path region than in the radially-outer flow path region, and the mean axial-flow velocity at the center axis O of the flow path decreases in the mean axial-flow velocity distribution (dotted line in FIG. 9) at the outlet of the extension tube. The reason is that the trailing edge 114 of the root portion 118 of the swirl vane 104 in the comparison example is formed by an end surface that intersects orthogonally with the axis O of the nozzle 120, and thus the gas having flown along the upstream region of the root portion 118 separates from the root portion 118 at the trailing edge 114, and turbulence occurs at the downstream side of the cutout 115.

(57) On the other hand, in the combustion burner in the present embodiment, the mean axial-flow velocity in the radially-inner flow path region 68b is higher than that in the comparison example, and thus a decrease in the mean axial-flow velocity at the center axis O of the flow path is suppressed in the mean axial-flow velocity distribution (solid line in FIG. 9) at the outlet 65a of the extension tube. Specifically, according to the present embodiment, the mean axial-flow velocity distribution at the outlet 65a of the extension tube is uniform as compared to that in the comparison example. This is because, as described above, the gas is rectified to a direction opposite from the swirl direction by the cutout 90a in the radially-inner flow path region 68b, so that the swirl component applied to the gas in the upstream region of the pressure surface 81 of the root portion 86 weakens in the downstream region of the pressure surface 81 of the root portion 86, which increases the mean axial-flow velocity in the radially-inner flow path region 68b.

(58) As described above, according to the present embodiment, it is possible to suppress a fluctuation in the axial-flow velocity in the radially-inner flow path region 68b and to improve the flashback-resistant property.

(59) In addition to the basic configuration of the combustion burner according to the present embodiment described above, the combustion burner of the present embodiment may further include any one of the following configurations. Further, it will be understood that two or more of the configurations illustrated in different drawings may be combined in one embodiment.

(60) FIG. 6 is a side view of the nozzle 64 and the swirler 70a according to one embodiment. FIG. 7 is a planar view of a configuration example of the swirler 70a.

(61) As illustrated in FIGS. 6 and 7, in each swirl vane 72a, the airfoil (a cross-sectional shape taken along a plane orthogonal to the radial direction of the nozzle 64; the same apply hereinafter) of the root portion 86 has the same airfoil as that of the tip portion 85 in the upstream region, while having such a shape that a portion corresponding to the cutout 90a is cut out from the airfoil of the tip portion 85 in the downstream region. This configuration can be suitably used in a two-dimensional airfoil.

(62) In this way, formed is a blade member having a substantially constant airfoil over the entire length of the blade height of the swirl vane 72a, with the cutout 90a disposed in the downstream region of the root portion 86 of the blade member. As a result, it is possible to produce the swirl vane 72a having a curved surface curving in a direction opposite to the swirl direction at the root portion 86.

(63) As illustrated in FIG. 7, the trailing edge 93 of the root portion 86 of the swirl vane 72a may be disposed at the same position as the leading edge 83 of the root portion 86, in the circumferential direction of the nozzle 64. In other words, the trailing edge 93 of the root portion 86 is disposed on a straight line L.sub.1 that extends along the axis O of the nozzle 64 and passes through the leading edge 83 of the swirl vane 72a.

(64) According to the above embodiment, the trailing edge 93 of the root portion 86 of the swirl vane 72a returns to the same position as that of the leading edge 83 in the circumferential direction due to the curve curving in a direction opposite to the swirl direction. Thus, as compared to a case in which the trailing edge 93 of the root portion 86 of the swirl vane 72a is offset toward the downstream side in the swirl direction from the leading edge 83, it is possible to mitigate the swirl component of the flow in the radially-inner flow path region 68b sufficiently and increase the mean axial-flow velocity securely.

(65) Further, the airfoil of the root portion 86 of the swirl vane 72a may have a shape that is line-symmetric with respect to the straight line L.sub.1 passing through the trailing edge 93 and parallel to the axial direction, at least at the side of the trailing edge 93. For instance, the airfoil of the root portion 86 of the swirl vane 72a may have an ellipse shape, a teardrop shape, an oval shape, or the like. In addition to the above configuration, the airfoil of the root portion 86 may have a line-symmetric shape with respect to a straight line orthogonal to the axial direction at the sides of the leading edge 83 and the trailing edge 93 (e.g. an ellipse shape or an oval shape).

(66) In this way, it is possible to increase the mean axial-flow velocity in the radially-inner flow path region 68b and to simplify the cross-sectional shape of the root portion 86. In this case, it is possible to improve the manufacturability of the swirl vane 72a.

(67) FIG. 10 is a perspective view of a swirler according to one embodiment. As illustrated in FIG. 10, in one embodiment, the pressure surface 81 of the tip portion 85 of the swirl vane 72a has the curved surface 91 curving in the swirl direction toward the trailing edge 84, and the pressure surface 81 of the swirl vane 72a has a stepped portion 95 between the curved surface 91 of the tip portion 85 and the curved surface 92a of the root portion 86.

(68) According to the above embodiment, at the stepped portion 95 formed on the pressure surface 81 of the swirl vane 72a, a shear layer is formed between a flow D in the swirl direction along the curved surface 91 of the tip portion 85 and a flow E opposite to the swirl direction along the curved surface 92a of the root portion 86. A swirl is generated at the shear layer, and the mixing of the gas flowing through the radially-outer flow path region 68a and the gas flowing through the radially-inner flow path region 68b is promoted. In this way, in a case where fuel is supplied at the upstream of the swirl vane 72a, it is possible to further equalize the distribution of the fuel concentration in the radial direction of the combustion burner 60.

(69) FIG. 11 is a side view of a nozzle and a swirler according to another embodiment. FIG. 12 is a planar view of a configuration example of a swirl vane illustrated in FIG. 11. FIG. 13 is a planar view of another configuration example of a swirl vane illustrated in FIG. 11.

(70) As illustrated in FIG. 11, in the swirler 70b of another embodiment, the curved surface 92b of the root portion 86 may be configured to swirl gas that flows through the radially-inner flow path region 68b of the axial flow path in a direction opposite to the swirl direction. In this way, the gas swirls in the radially-inner flow path region 68b in a direction opposite to the swirl direction of the radially-outer flow path region 68a, which makes it possible to mitigate the swirl component in the radially-inner flow path region 68b even more effectively.

(71) As illustrated in FIGS. 11 and 12, in another embodiment, the trailing edge 93 of the root portion 86 of the swirl vane 72b may be disposed opposite to the trailing edge 84 of the tip portion 85 across a straight line L.sub.2 that passes through the leading edge 83 and extends parallel to the axial direction, in the circumferential direction of the nozzle 64. In this way, the trailing edge 93 of the root portion 86 is positioned at the upstream side of the leading edge 83 in the swirl direction, which makes it possible to orient the flow in the radially-inner flow path region 68b (see FIG. 5) securely in a direction opposite to the swirl direction, and to reduce the swirl component in the radially-inner flow path region 68b even more effectively. As a result, it is possible to increase the mean axial-flow velocity in the radially-inner flow path region 68b securely.

(72) As illustrated in FIGS. 11 and 13, in another embodiment, the bisector L.sub.5 of an angle formed by a tangent L.sub.3 of the suction surface 82 passing through the trailing edge 93 of the root portion 86 of the swirl vane 72b and a tangent L.sub.4 of the pressure surface 81 passing through the trailing edge 93 of the root portion 86 may be oblique to the axial direction in a direction opposite to the swirl direction at the downstream side of the trailing edge 93 of the root portion 86.

(73) In the present embodiment, while the gas is swirling in the swirl direction in the radially-outer flow path region 68a (see FIG. 5), the gas flows in a direction opposite to the swirl direction in the radially-inner flow path region 68b (see FIG. 5). In this way, it is possible to mitigate the swirl component in the radially-inner flow path region 68b even more effectively.

(74) FIG. 14 is a side view of a nozzle and a swirler according to another embodiment. As illustrated in FIG. 14, in another embodiment, the tip portion 85 of the swirl vane 72c is disposed on the outer side, in the radial direction, of a cutout space formed by the cutout 90c in the downstream region of the tip portion 85, so as to have a cutout-space forming surface 96 that faces the cutout space. The cutout-space forming surface 96 has a shape such that a width of the cutout space increases in the radial direction toward the downstream side. Specifically, with regard to the width of the cutout space in the radial direction, i.e., a distance between the cutout-space forming surface 96 and the outer circumferential surface of the nozzle 64, the distance H.sub.2 at the downstream side (e.g. at the position of the trailing edge 84 of the tip portion 85 in the axial direction) is greater than the distance H.sub.1 at the upstream side of the cutout 90c (e.g. at the position of the trailing edge 93 of the root portion 86 in the axial direction). Further, the cutout-space forming surface 96 may be formed so as to gradually increase from the distance H.sub.1 at the upstream side toward the distance H.sub.2 at the downstream side. Alternatively, the cutout-space forming surface 96 may be a flat surface that extends linearly and oblique to the axial direction so that the width of the cutout space in the radial direction increases toward the downstream side. Further, from the distance H.sub.1 at the upstream side toward the distance H.sub.2 at the downstream side, the distance may be from 3 to 20% of the height H of the swirl vane 72c in the radial direction. For instance, the distance H.sub.1 at the upstream side being a lower limit is 3% or more and the distance H.sub.2 at the downstream side being an upper limit is 20% or less.

(75) According to the above embodiment, it is possible to secure a large width where the flow mainly including the swirl flow in the radially-outer flow path region 68a and the flow mainly including the axial flow passing through the cutout 90c in the radially-inner flow path region 68b are to be mixed with each other, which makes it possible to equalize the flow-velocity distribution at the downstream side of the axial flow path 68. The more uniform the flow-velocity distribution at the flame-holding position is, the closer the shape of the flame surface gets to a flat shape, and the smaller a baroclinic torque that causes the flame surface to flow backward to the upstream side becomes. Thus, with the flow-velocity distribution at the downstream side of the axial flow path 68 being uniform, it is possible to improve the flashback-resistant property in the radially-inner flow path region 68b effectively.

(76) In the swirler 70c in another embodiment illustrated in FIG. 14, the trailing edge 93 of the root portion 86 of the swirl vane 72c includes a curved surface 92c. However, the trailing edge 93 of the root portion 86 may not include the curved surface 92c. That is, the swirl vane 72c is configured such that the cutout-space forming surface 96 has a shape such that a width of the cutout space in the radial direction increases toward the downstream side, and the trailing edge 93 of the root portion 86 has a flat shape similarly to the trailing edge 114 of the comparison example. Specifically, the swirl vane 72c includes the tip portion 85 for swirling gas flowing through the radially-outer flow path region 68a of the axial flow path 68 in the swirl direction, and the root portion 86 disposed on the inner side, in the radial direction, of the nozzle 64 as seen from the tip portion 85 and having the cutout 90c at the side of the trailing edge. Further, at least in a range in the axial direction in which the swirl vane 72c is provided, the radially-outer flow path region 68a and the radially-inner flow path region 68b of the axial flow path 68 are communicating with each other without being partitioned. Moreover, the tip portion 85 includes, in the downstream region of the tip portion 85, a cutout-space forming surface 96 disposed on the outer side, in the radial direction, of a cutout space formed by the cutout 90c so as to face the cutout space, the cutout-space forming surface 96 having a shape such that the width, in the radial direction, of the cutout space increases toward the downstream side.

(77) Now, with reference to FIG. 15, the flashback-resistant property of the combustion burner of the present embodiment will be compared to that of the comparison example. FIG. 15 is a graph showing a relationship between a mean axial-flow velocity and a radial distance at an outlet of an extension tube of the embodiment and the comparison example. In the drawing, the combustion burner in the embodiment includes the nozzle 64 and the swirler 70c illustrated FIG. 14, and the combustion burner in the comparison example includes the nozzle and the swirler illustrated in FIG. 8, and the mean axial-flow velocity of each case is shown.

(78) In FIG. 14, the trailing edge 93 of the root portion 86 includes a curved surface 92c. However, in the following analysis, a swirl vane with the trailing edge 93 of the root portion 86 not having the curved surface 92c is used. That is, in the combustion burner of the present embodiment, the cutout-space forming surface 96 has a shape such that a width of the cutout space increases in the radial direction toward the downstream side, and the trailing edge 93 of the root portion 86 is formed in a flat shape similarly to the comparison example.

(79) In each of the combustion burner in the present embodiment and the combustion burner in the comparison example, computational fluid dynamics (CFD) is used to calculate the mean axial-flow velocity with respect to the radial distance of the nozzles 64, 120.

(80) As a result, in the combustion burner in the comparison example, the mean axial-flow velocity decreases more considerably in the radially-inner flow path region than in the radially-outer flow path region, and the mean axial-flow velocity at the center axis O of the flow path decreases in the mean axial-flow velocity distribution (dotted line in FIG. 15) at the outlet of the extension tube.

(81) On the other hand, in the combustion burner in the present embodiment, the mean axial-flow velocity in the radially-inner flow path region 68b is higher than that in the comparison example, and thus a decrease in the mean axial-flow velocity at the center axis O of the flow path is suppressed in the mean axial-flow velocity distribution (solid line in FIG. 15) at the outlet 65a of the extension tube. Specifically, according to the present embodiment, the mean axial-flow velocity distribution at the outlet 65a of the extension tube is uniform as compared to that in the comparison example. As described above, it is possible to secure a large width where the flow mainly including the swirl flow in the radially-outer flow path region 68a and the flow mainly including the axial flow passing through the cutout 90c in the radially-inner flow path region 68b are to be mixed with each other, which makes it possible to equalize the flow-velocity distribution at the downstream side of the axial flow path 68.

(82) According to the present embodiment, with the flow-velocity distribution at the downstream side of the axial flow path 68 being uniform, it is possible to improve the flashback-resistant property in the radially-inner flow path region 68b effectively.

(83) FIG. 16 is a side view of a nozzle and a swirler according to another embodiment.

(84) As illustrated in FIG. 16, the leading edge 83 of the swirl vane 72d is oblique to the radial direction so as to be oriented toward the upstream side in the axial direction toward the outer side in the radial direction of the nozzle 64, at least on the side of the tip portion 85. The leading edge 83 may be oblique over the entire region of the leading edge 83 of the swirl vane 72d in the radial direction or the nozzle 64. Alternatively, the leading edge 83 may be oblique in at least a partial region of the leading edge 83 in the radial direction of the nozzle 64, especially at the radially-outer side (a part corresponding to the radially-outer flow path region 68a) in the radial direction of the nozzle 64.

(85) In this way, the flow of the gas gets closer to the radially-inner flow path region 68b (see FIG. 5) along the pressure gradient in the radial direction on the blade surface of the swirl vane 72d, and thus the flow rate in the radially-inner flow path region 68b increases relatively. As a result, the mean axial-flow velocity in the radially-inner flow path region 68b increases.

(86) In the swirler 70d of another embodiment illustrated in FIG. 16, the swirl vane 72d includes a cutout 90d formed on the downstream side of the root portion 86. However, the cutout 90d may not be formed. Further, as described above with reference to the embodiment illustrated in FIG. 14, the swirl vane 72d in the other embodiment illustrated in FIG. 16 may include a cutout having a cutout-space forming surface such that the width of the cutout space in the radial direction increases toward the downstream side.

(87) Embodiments of the present invention were described in detail above, but the present invention is not limited thereto, and various amendments and modifications may be implemented.

(88) For instance, a combustion burner of a premix combustion type is described as an example in the above embodiment. The combustion burner of a premix combustion type is capable of suppressing a local increase in the combustion temperature and thus effective in restricting generation of NOx. However, the embodiment of the present invention can be applied to the combustion burner of a diffusive combustion type. In this case, an embodiment in which the swirl vanes do not have the fuel injection holes and there is nearly no fuel in the axial flow path is also included.

(89) Further, while a two-dimensional airfoil is illustrated in the above embodiment, the embodiment of the present invention can be applied to a three-dimensional airfoil

(90) For instance, an expression of relative or absolute arrangement such as in a direction, along a direction, parallel, orthogonal, centered, concentric and coaxial shall not be construed as indicating only the arrangement in a strict literal sense, but also includes a state where the arrangement is relatively displaced by a tolerance, or by an angle or a distance whereby it is possible to achieve the same function.

(91) For instance, an expression of an equal state such as same equal and uniform shall not be construed as indicating only the state in which the feature is strictly equal, but also includes a state in which there is a tolerance or a difference that can still achieve the same function.

(92) Further, for instance, an expression of a shape such as a rectangular shape or a cylindrical shape shall not be construed as only the geometrically strict shape, but also includes a shape with unevenness or chamfered corners within the range in which the same effect can be achieved.

(93) On the other hand, an expression such as comprise, include, have, contain and constitute are not intended to be exclusive of other components.

DESCRIPTION OF REFERENCE NUMERALS

(94) 1 Gas turbine 2 Compressor 4 Combustor 6 Turbine 8 Rotor 10 Compressor casing 22 Turbine casing 28 Exhaust casing 40 Combustor casing 46 Combustor liner 46a Combustor basket 46b Transition piece 50 Combustion burner (pilot combustion burner) 52 Fuel port 54 Nozzle (pilot nozzle) 56 Pilot cone 58 Swirler 60 Combustion burner (premix combustion burner) 62 Fuel port 64 Nozzle (main nozzle) 65 Extension tube 65a Extension tube outlet 66 Burner cylinder 68 Axial flow path 68a Radially-outer flow path region 68b Radially-inner flow path region 70, 70a to 70d Swirler 72, 72a to 72d Swirl vane 74 to 77 Injection aperture 81 Pressure surface 82 Suction surface 83, 83 Leading edge 84 Trailing edge 85 Tip portion 86 Root portion 86a Radially-outer flow path region 86b Radially-inner flow path region 90, 90a to 90b Cutout 91 Curved surface 92a to 92d Curved surface 93 Trailing edge 95 Stepped portion 96 Cutout-space forming surface