JP6326205B2 - Fuel nozzle, combustor, and gas turbine - Google Patents

Description

  The present invention relates to a fuel nozzle, a combustor, and a gas turbine.

  The gas turbine includes a compressor, a combustor, and a turbine. In the combustor, when the combustion temperature increases, the amount of nitrogen oxide (NOx) generated increases. In order to suppress the amount of NOx generated, air and fuel are premixed (premixed) using a fuel nozzle of a combustor as disclosed in, for example, Patent Document 1 and Patent Document 2, and the premixing is performed. Premixed combustion is known in which an air-fuel mixture (premixed gas) generated by the above is combusted.

JP 2003-247425 A JP 2011-021875 A

  The premixed gas has flame propagation properties. Therefore, there is a possibility that a so-called flashback phenomenon occurs in which the flame generated by the combustion of the premixed gas enters the inside of the fuel nozzle. When the flashback phenomenon occurs, the fuel nozzle may be deteriorated. As a result, the performance of the fuel nozzle is reduced, and the performance of the combustor and the performance of the gas turbine may be reduced.

  An object of this invention is to provide the fuel nozzle, combustor, and gas turbine which can suppress the fall of performance.

  A fuel nozzle according to the present invention is disposed in a space around a predetermined axis so as to be orthogonal to an axis parallel to the predetermined axis, a space disposed on the first surface, and facing the first surface. A first supply port for supplying a first fluid, a second surface facing the space and disposed so as to surround the predetermined axis, and disposed on the second surface for supplying the second fluid to the space A second supply port, wherein one of the first fluid and the second fluid contains fuel, the other fluid is air, and the first supply port is a first parallel to the predetermined axis. The first fluid is supplied in a direction, the second supply port supplies the second fluid to be mixed with the first fluid in the space, and the first outlet is mixed in the space. Supply mixed fluid.

  According to the present invention, the first fluid is supplied from the first supply port, and the second fluid is supplied from the second supply port, so that the mixed fluid (premixed gas) of the first fluid and the second fluid in the space. ) Is generated. Since the first supply port supplies the first fluid in the first direction, the first fluid from the first supply port prevents the mixed fluid from staying in the space. The second surface is disposed so as to surround a predetermined axis. Therefore, the first fluid supplied to the space from the first supply port and the mixed fluid generated in the space are guided by the second surface, smoothly flow in the first direction, and are prevented from staying in the space. Therefore, combustion of the mixed fluid or the occurrence of a flashback phenomenon in the vicinity of the fuel nozzle is suppressed. Thereby, deterioration of a fuel nozzle is suppressed and the fall of the performance of a fuel nozzle is suppressed.

  In the fuel nozzle according to the present invention, the third surface facing the space and facing the second surface through a gap, and the second surface farthest from the first surface in a direction parallel to the predetermined axis. The first outflow port from which the mixed fluid of the first fluid and the second fluid generated in the space flows out between a second surface edge and a third surface edge of the third surface. May be. Accordingly, the first fluid supplied to the space from the first supply port and the mixed fluid generated in the space are guided by both the second surface and the third surface, and smoothly flow out from the first outlet. Therefore, the mixed fluid is suppressed from staying in the space, and the mixed fluid is prevented from burning in the vicinity of the fuel nozzle or the flashback phenomenon is suppressed from occurring.

  The fuel nozzle according to the present invention may include a third supply port that is arranged on the third surface and supplies a third fluid containing at least one of fuel and air to the space. Thereby, the mixed fluid is sufficiently generated by the first fluid from the first supply port, the second fluid from the second supply port, and the third fluid from the third supply port.

  In the fuel nozzle according to the present invention, one of the second surface and the third surface is disposed so as to face outward in a radial direction with respect to the predetermined axis around the predetermined axis, and the other surface is You may arrange | position so that it may face inward with respect to the radial direction with respect to the said predetermined axis around a predetermined axis. As a result, an annular (annular) space is formed in a plane perpendicular to the predetermined axis, and the mixed fluid is sufficiently generated in the space.

  In the fuel nozzle according to the present invention, the space between the second surface and the third surface may become narrower in the first direction. Thereby, since the flow velocity of the mixed fluid at the first outlet is increased, the retention of the mixed fluid at the first outlet is suppressed.

  In the fuel nozzle according to the present invention, the first tip surface connected to the second surface edge and arranged to be orthogonal to the axis parallel to the predetermined axis, and the third surface edge is connected to the predetermined axis. A second tip surface disposed so as to be orthogonal to an axis parallel to the first tip surface, and a second outlet port disposed on at least one of the first tip surface and the second tip surface and through which air flows out. Good. Thereby, it is suppressed that the temperature of a fuel nozzle rises excessively by the air which flowed out from the 2nd outflow port. Therefore, deterioration of the fuel nozzle is suppressed.

  A combustor according to the present invention includes any one of the above fuel nozzles.

  According to the present invention, a decrease in performance is suppressed.

  The gas turbine which concerns on this invention is equipped with said combustor.

  According to the present invention, a decrease in performance is suppressed.

  According to the fuel nozzle according to the present invention, performance degradation is suppressed. Moreover, according to the combustor which concerns on this invention, the fall of a performance is suppressed. Moreover, according to the gas turbine which concerns on this invention, the fall of a performance is suppressed.

FIG. 1 is a diagram illustrating an example of a gas turbine according to the first embodiment. FIG. 2 is a side sectional view showing an example of a combustor according to the first embodiment. FIG. 3 is a cross-sectional view illustrating an example of a fuel nozzle according to the first embodiment. FIG. 4 is a perspective view showing an example of a fuel nozzle according to the second embodiment. FIG. 5 is a perspective view showing an example of a fuel nozzle according to the third embodiment. FIG. 6 is a perspective view showing an example of a fuel nozzle according to the fourth embodiment. FIG. 7 is a perspective view showing an example of a fuel nozzle according to the fourth embodiment. FIG. 8 is a perspective view showing an example of a fuel nozzle according to the fifth embodiment. FIG. 9 is a perspective view showing an example of a fuel nozzle according to the fifth embodiment.

  Hereinafter, embodiments according to the present invention will be described with reference to the drawings, but the present invention is not limited thereto. The requirements of the embodiments described below can be combined as appropriate. Some components may not be used.

  In the following description, an XYZ orthogonal coordinate system is set, and the positional relationship of each part will be described with reference to this XYZ orthogonal coordinate system. One direction in the predetermined plane is defined as the X-axis direction, the direction orthogonal to the X-axis direction in the predetermined plane is defined as the Y-axis direction, and the direction orthogonal to each of the X-axis direction and the Y-axis direction is defined as the Z-axis direction. Further, the rotation (inclination) directions around the X axis, Y axis, and Z axis are the θX, θY, and θZ directions, respectively. The X axis is orthogonal to the YZ plane. The Y axis is orthogonal to the XZ plane. The Z axis is orthogonal to the XY plane. The XY plane includes an X axis and a Y axis. The YZ plane includes a Y axis and a Z axis. The XZ plane includes an X axis and a Z axis.

<First Embodiment>
A first embodiment will be described. FIG. 1 is a diagram illustrating an example of a gas turbine 100 according to the present embodiment. In FIG. 1, the gas turbine 100 includes a compressor 1, a combustor 2, and a turbine 3. The gas turbine 100 includes a rotor shaft 4 connected to each of the compressor 1 and the turbine 3. The combustor 2 is disposed between the compressor 1 and the turbine 3.

  The compressor 1 compresses the introduced gas (air in this embodiment) to generate a high-pressure gas. In the present embodiment, the compressor 1 is an axial compressor. The compressor 1 has a moving blade that is a rotating blade and a stationary blade that is a non-rotating blade. The rotor blades give energy to the gas. The stationary blade decelerates the gas and increases the pressure of the gas. With respect to the axial direction of the compressor 1, the moving blades and the stationary blades are alternately arranged. A plurality (a plurality of stages) of a pair (one stage) of moving blades and stationary blades are arranged in the axial direction of the compressor 1. The gas flowing in the axial direction of the compressor 1 is gradually compressed by a plurality of stages of moving blades and stationary blades. The compressor 1 gradually increases the pressure of the gas while flowing the gas in the axial direction.

  The combustor 2 injects fuel into the high-pressure gas supplied from the compressor 1 to generate a high-temperature and high-pressure gas. Combustion is generated by mixing the high-pressure gas and fuel in the combustor 2, and high-temperature and high-pressure gas is generated. A plurality of combustors 2 are arranged around the rotor shaft 4. The high-pressure gas from the compressor 1 is supplied to each of the plurality of combustors 2.

  The turbine 3 converts high-temperature and high-pressure gas energy supplied from the combustor 2 into power. In the present embodiment, the turbine 3 is an axial flow type. The turbine 3 includes a moving blade that is a rotating blade and a stationary blade that is a non-rotating blade. The rotor blades rotate by receiving high-temperature and high-pressure gas from the combustor 2. The moving blade converts the kinetic energy of the gas from the combustor 2 into rotational energy. The stationary blades regulate the gas flow. At least a part of the gas whose flow is adjusted by the stationary blade is blown onto the moving blade. With respect to the axial direction of the turbine 3, the moving blades and the stationary blades are alternately arranged. A plurality (a plurality of stages) of a pair (one stage) of moving blades and stationary blades are arranged in the axial direction of the turbine 3. The turbine 3 extracts rotational energy (rotational force) stepwise from the high-temperature and high-pressure gas by the plurality of stages of moving blades and stationary blades. As the rotor blades rotate, the rotor shaft 4 rotates.

  When the gas turbine 100 is used in a power generation system, the generator is operated by the rotational force of the turbine 3. A part of the rotational force of the turbine 3 is used for the rotation of the compressor 1.

  The combustor 2 has a combustion chamber 5 inside. The gas from the compressor 1 is supplied to the combustion chamber 5. At least a part of the combustor 2 is disposed inside the casing 9. The gas from the compressor 1 is supplied to a space (cabinet) 9 </ b> R inside the casing 9. The vehicle interior 9R is filled with high-pressure gas from the compressor 1. The gas in the passenger compartment 9 </ b> R is supplied to the combustion chamber 5 through the inlet 2 </ b> R provided in the combustor 2.

  The combustor 2 has a main fuel nozzle 7 and a pilot fuel nozzle 8. A plurality of main fuel nozzles 7 are arranged around the pilot fuel nozzle 8. The main fuel nozzle 7 supplies main fuel to the combustion chamber 5. The combustion chamber 5 is supplied with main fuel from the main fuel nozzle 7 and high-pressure gas from the compressor 1. In the combustion chamber 5, the main fuel supplied from the main fuel nozzle 7 and the high-pressure gas supplied from the compressor 1 are mixed and burned. High-temperature and high-pressure gas generated by combustion in the combustor 2 is supplied to the turbine 3 via the tail cylinder 6.

  The combustor 2 has swirl vanes (swirler vanes) 7 </ b> S disposed around the main fuel nozzle 7. The swirler vane 7S causes the gas to swirl. In other words, a swirl flow of gas is generated by the swirler vane 7S. The main fuel supplied from the main fuel nozzle 7 is mixed (premixed) with the flowing gas so as to be swirled by the swirler vane 7S, and then burned (premixed combustion) in the combustion chamber 5.

  Next, the pilot fuel nozzle 8 will be described. FIG. 2 is a side sectional view showing a part of the fuel nozzle 8 according to the present embodiment. FIG. 3 is a cross-sectional view showing a part of the fuel nozzle 8 according to the present embodiment. In the following description, the pilot fuel nozzle 8 is appropriately referred to as a fuel nozzle 8. The pilot fuel supplied to the pilot fuel nozzle 8 is appropriately referred to as fuel F. The gas supplied to the pilot fuel nozzle 8 is appropriately referred to as gas G. The fuel F is a fluid. The fuel F may be a gaseous fuel or a liquid fuel. The fuel F may be natural gas, for example, or may include oil as a liquid fuel. The gas G is air.

  The pilot fuel nozzle 8 improves the ignition performance and flame holding performance of the combustor 2. Combustion by the mixture of main fuel and gas supplied from the main fuel nozzle 7 is stabilized by the pilot fuel and gas supplied from the pilot fuel nozzle 8.

  2 and 3, the fuel nozzle 8 includes a first surface 11 disposed around the axis J, a second surface 12 disposed around the axis J and facing a different direction from the first surface 11, and the shaft. And a third surface 13 disposed around J and facing in a different direction from the first surface 11 and the second surface 12. In the present embodiment, the axis J is parallel to the X axis.

  The first surface 11 is disposed so as to be orthogonal to the X axis. The first surface 11 and the YZ plane are parallel. In the YZ plane, the first surface 11 is annular (annular). The second surface 12 is disposed so as to surround the axis J. The second surface 12 is disposed so as to be parallel to the axis J. The second surface 12 is arranged so as to face inward with respect to the radial direction with respect to the axis J. The third surface 13 is disposed so as to surround the axis J. The third surface 13 is disposed so as to be parallel to the axis J. The third surface 13 is arranged to face outward with respect to the radial direction with respect to the axis J. The 2nd surface 12 and the 3rd surface 13 oppose through a gap.

  In the present embodiment, the space MS is defined by the first surface 11, the second surface 12, and the third surface 13. In the YZ plane, the space MS is annular (annular). The first surface 11 faces the space MS. The second surface 12 faces the space MS. The third surface 13 faces the space MS.

  The fuel nozzle 8 includes a supply port 21 disposed on the first surface 11 and a supply port 22 disposed on the second surface 12. The supply port 21 supplies the first fluid to the space MS. The supply port 22 supplies the second fluid to the space MS. In the present embodiment, the first fluid is the fuel F. The second fluid is a gas (air) G. The supply port 21 supplies the fuel F to the space MS. The supply port 22 supplies the gas G to the space MS. The supply port 21 supplies (injects) the fuel F in the X-axis direction parallel to the axis J. The supply port 21 supplies the fuel F in the + X direction. The supply port 22 supplies (injects) the gas G in a direction that intersects the supply direction (X-axis direction) of the fuel F from the supply port 21. The supply port 22 may supply the gas G in a direction orthogonal to the supply direction (X-axis direction) of the fuel F from the supply port 21. In the present embodiment, the supply port 22 supplies the gas G in the radial direction with respect to the axis J. The supply port 22 supplies the gas G inward with respect to the radial direction with respect to the axis J.

  The supply port 21 supplies the fuel F so as to be mixed with the gas G in the space MS. The supply port 22 supplies the gas G so as to be mixed with the fuel F in the space MS. In the space MS, the fuel F supplied from the supply port 21 and the gas G supplied from the supply port 22 are mixed (premixed). By mixing the fuel F and the gas G, an air-fuel mixture (pre-air mixture) FG is generated. In the following description, the space MS is appropriately referred to as a mixed space MS.

  In the present embodiment, a plurality of supply ports 21 are arranged around the axis J. The plurality of supply ports 21 are arranged so as to surround the axis J with a space therebetween. A plurality of supply ports 22 are arranged around the axis J. The plurality of supply ports 22 are arranged so as to surround the axis J at intervals. In the present embodiment, the supply port 21 and the supply port 22 are each circular. One or the other of the supply port 21 and the supply port 22 may be a polygon or a slit.

  The supply port 21 may be arranged around the axis J. In other words, the supply port 21 may have an annular shape surrounding the axis J. The supply port 22 may be arranged around the axis J. That is, the supply port 22 may have an annular shape surrounding the axis J.

  Regarding the X-axis direction, between the second surface edge on the + X side of the second surface 12 farthest from the first surface 11 and the third surface edge on the + X side of the third surface 13 farthest from the first surface 11, An outlet 41 is provided through which an air-fuel mixture FG of the fuel F and gas G generated in the mixed space MS flows out. The supply port 21 and the outflow port 41 are arranged in the X-axis direction. The outlet 41 is disposed on the + X side of the supply port 21 and supplies the air-fuel mixture FG.

  The fuel nozzle 8 is connected to the + X side second surface edge of the second surface 12, and is connected to the tip surface 52 arranged to be orthogonal to the X axis and the + X side third surface edge of the third surface 13. And a distal end surface 51 disposed so as to be orthogonal to the X axis. The distal end surface 51 and the distal end surface 52 are each directed in the + X direction. The axis J passes through the tip surface 51. The tip surface 52 is disposed around the axis J. In the YZ plane, the tip surface 52 is annular (annular).

  The fuel nozzle 8 includes a flow path 31 through which the first fluid (fuel F) flows and a flow path 32 through which the second fluid (gas G) flows. Each of the flow path 31 and the flow path 32 is formed inside the fuel nozzle 8. The mixed space MS is a space outside the flow path 31 and the flow path 32. In the flow path 31, the fuel F flows in the + X direction. In the flow path 32, the gas G flows in the + X direction. The supply port 21 is connected to the flow path 31. The supply port 21 supplies at least a part of the fuel F in the flow path 31 to the mixing space MS. The supply port 22 is connected to the flow path 32. The supply port 22 supplies at least a part of the gas G in the flow path 32 to the mixing space MS.

  The flow path 32 is provided so as to surround the axis J. In the YZ plane, the flow path 32 is annular (annular). The channel 31 is disposed inside the channel 32. The flow path 31 includes an axis J.

  In the present embodiment, the fuel nozzle 8 includes a nozzle member 61 that is at least partially disposed around the axis J, and a nozzle member 62 that is disposed at least partially around the nozzle member 61. The nozzle member 62 is disposed around the axis J. The first surface 11, the third surface 13, and the tip surface 51 are disposed on the nozzle member 61. The second surface 12 and the tip surface 52 are disposed on the nozzle member 62. The flow path 31 and the supply port 21 are disposed in the nozzle member 61. The flow path 32 and the supply port 22 are disposed in the nozzle member 62.

  In the present embodiment, the fuel nozzle 8 has a convex portion 17 protruding in the + X direction and a peripheral wall portion 18 disposed around the convex portion 17. The convex portion 17 includes the axis J. The peripheral wall portion 18 is disposed so as to surround the axis J. The convex portion 17 is provided on the nozzle member 61. The peripheral wall 18 is provided in the nozzle member 62. The third surface 13 includes the outer surface (outer peripheral surface) of the convex portion 17. The second surface 12 includes the inner surface (inner peripheral surface) of the peripheral wall portion 18. The distal end surface 51 includes the distal end surface of the convex portion 17 facing the + X direction. The front end surface 52 includes the front end surface of the peripheral wall portion 18 facing the + X direction.

  Next, an example of the operation of the fuel nozzle 8 according to this embodiment will be described. When the fuel F is supplied to the flow path 31, at least a part of the fuel F is supplied from the supply port 21 to the mixing space MS. When the gas G is supplied to the flow path 32, at least a part of the gas G is supplied from the supply port 22 to the mixing space MS. The supply port 21 supplies the fuel F in the + X direction parallel to the axis J. The supply port 22 supplies the gas G inward with respect to the radial direction with respect to the axis J. As a result, the fuel F and the gas G are mixed (premixed) in the mixed space MS, and a mixed gas (premixed gas) FG is generated. At least a part of the air-fuel mixture FG generated in the mixing space MS flows out of the mixing space MS from the outlet 41. The air-fuel mixture FG that has flowed out of the mixed space MS through the outlet 41 flows in the + X direction (downstream direction) and burns (premixed combustion) in the combustion space FS on the + X side of the mixed space MS.

  In the present embodiment, since the supply port 21 supplies (injects) the fuel F in the + X direction, the mixture FG in the mixture space MS defined by the first surface 11, the second surface 12, and the third surface 13. Occurrence of stagnation is suppressed. In the present embodiment, the outflow port 41 is disposed on the + X side with respect to the supply port 21, and the supply port 21 supplies the fuel F in the + X direction. Due to the flow of fuel F supplied (injected) from the supply port 21, the air-fuel mixture FG in the mixed space MS is quickly discharged from the mixed space MS via the outlet 41. As a result, the occurrence of stagnation of the air-fuel mixture FG in the mixed space MS is suppressed. By suppressing the occurrence (stagnation) of the mixture FG in the mixture space MS, the mixture FG burns in the fuel space FS away from the fuel nozzle 8. That is, the combustion of the air-fuel mixture FG in the mixed space MS is suppressed. Thereby, the contact of the flame with respect to the fuel nozzle 8 and the occurrence of the flashback phenomenon are suppressed.

  As described above, according to the present embodiment, since the fuel F is supplied from the first supply port 15 in the + X direction, the occurrence of stagnation of the mixture FG in the mixture space MS is suppressed. . Therefore, the contact of the flame with the fuel nozzle 8 and the occurrence of the flashback phenomenon are suppressed. Therefore, the deterioration of the fuel nozzle 8 is suppressed, and the deterioration of the performance of the fuel nozzle 8 is suppressed. In addition, a decrease in the performance of the combustor 2 including the fuel nozzle 8 and a decrease in the performance of the gas turbine 100 are suppressed.

  In the present embodiment, the gas G may be supplied from the supply port 21 and the fuel F may be supplied from the supply port 22.

Second Embodiment
A second embodiment will be described. In the following description, the same or equivalent components as those in the above-described embodiment are denoted by the same reference numerals, and the description thereof is simplified or omitted.

  FIG. 4 is a side sectional view showing an example of the fuel nozzle 8B according to the present embodiment. In FIG. 4, the fuel nozzle 8B is disposed on the first surface 11 and is disposed on the second surface 12 for supplying the fuel F in the + X direction toward the mixing space MS, and toward the mixing space MS. A supply port 22 that supplies gas G to the inside in the radial direction with respect to the axis J and a supply port 23 that is disposed on the third surface 13 and can supply the third fluid to the mixed space MS are provided.

  The third fluid is at least one of fuel F and gas G. That is, the fuel F may be supplied from the supply port 23 or the gas G may be supplied. In the present embodiment, the supply port 21 is connected to the flow path 31. The supply port 23 supplies the fuel F to the mixing space MS.

  The supply port 23 supplies (injects) the third fluid in a direction that intersects the supply direction (X-axis direction) of the fuel F from the supply port 21. The supply port 23 may supply (inject) the third fluid in a direction orthogonal to the supply direction of the fuel F from the supply port 21. In the present embodiment, the supply port 23 supplies the fuel F toward the outside in the radial direction with respect to the axis J.

  A plurality of supply ports 23 are arranged around the axis J. The plurality of supply ports 23 are arranged so as to surround the axis J at intervals. The supply port 23 is circular. The supply port 23 may be a polygon or a slit.

  The supply port 23 may be disposed so as to face the supply port 22. The supply port 23 may supply the fuel F to the mixing space MS so as to collide with the gas G supplied from the supply port 22.

  The supply port 23 may be arranged around the axis J. That is, the supply port 23 may have an annular shape surrounding the axis J.

  As described above, according to the present embodiment, the fuel F is supplied from the supply port 21, the gas G is supplied from the supply port 22, and the fuel F is supplied from the supply port 23 to the mixing space MS. . Also in the present embodiment, the occurrence of stagnation (stagnation) of the mixture FG in the mixed space MS and the occurrence of a flashback phenomenon are suppressed.

<Third Embodiment>
A third embodiment will be described. In the following description, the same or equivalent components as those in the above-described embodiment are denoted by the same reference numerals, and the description thereof is simplified or omitted.

  FIG. 5 is a side sectional view showing an example of the fuel nozzle 8C according to the present embodiment. In FIG. 5, the fuel nozzle 8C is disposed on the first surface 11 and is disposed on the second surface 12 and the supply port 21 for supplying the fuel F in the + X direction toward the mixing space MS, and toward the mixing space MS. A supply port 22 for supplying the gas G inward with respect to the radial direction with respect to the axis J; a supply port 23 arranged on the third surface 13 for supplying the fuel F outward with respect to the radial direction with respect to the axis J toward the mixing space MS; It has.

  In the present embodiment, the mixed space MS between the second surface 12 and the third surface 13 becomes narrower in the + X direction. Thereby, the flow velocity of the air-fuel mixture FG at the outlet 41 is increased. That is, the flow rate of the mixture FG flowing out from the outlet 41 is increased by the so-called nozzle effect. Therefore, the occurrence of stagnation of the air-fuel mixture FG at the outlet 41 and the occurrence of a flashback phenomenon are suppressed.

  In the second and third embodiments, the gas G may be supplied from the supply port 21 and the supply port 23, and the fuel F may be supplied from the supply port 22.

  In the first, second, and third embodiments described above, the nozzle member 61 and the nozzle member 62 may be integrated. In other words, the combustion nozzle 8 may be a single member.

<Fourth embodiment>
A fourth embodiment will be described. In the following description, the same or equivalent components as those in the above-described embodiment are denoted by the same reference numerals, and the description thereof is simplified or omitted.

  FIG. 6 is a side sectional view showing an example of the fuel nozzle 8D according to the present embodiment. In FIG. 6, the fuel nozzle 8D is disposed on the first surface 11 and is disposed on the second surface 12 to supply the first fluid in the + X direction toward the mixing space MS, and toward the mixing space MS. A supply port 22 for supplying the second fluid inward in the radial direction with respect to the axis J, and a supply port for supplying the third fluid outwardly in the radial direction with respect to the axis J toward the mixing space MS. 23.

  The fuel F is supplied from at least one of the supply port 21, the supply port 22, and the supply port 23, and the gas G is supplied from at least one of the supply port 21, the supply port 22, and the supply port 23. In the present embodiment, the fuel F is supplied from the supply port 21, the gas G is supplied from the supply port 22, and the fuel F is supplied from the supply port 23.

  In the present embodiment, the fuel nozzle 8 </ b> D includes a flow path 31 </ b> D connected to the supply port 21, a flow path 32 </ b> D connected to the supply port 22, and a flow path 33 </ b> D connected to the supply port 23. The flow path 31D, the flow path 32D, and the flow path 33D are separate flow paths. The fuel F flows through the flow path 31D, the gas G flows through the flow path 32D, and the fuel F flows through the flow path 33D. The fuel F supplied from the supply port 21 (the fuel F flowing through the flow path 31D) and the fuel F supplied from the supply port 23 (the fuel F flowing through the flow path 33D) may be the same type of fuel or different. Any type of fuel may be used.

  In the present embodiment, the fuel nozzle 8D includes a nozzle member 63D having a flow path 33D, at least a portion disposed around the nozzle member 63D, and a nozzle member 61D having a flow path 31D, and at least a portion of the nozzle member 61D. , And a nozzle member 62D having a flow path 32D.

  In this embodiment, the convex part 17 is arrange | positioned at the nozzle member 63D. The peripheral wall portion 18 is disposed on the nozzle member 62D. The first surface 11 is disposed on the nozzle member 61D. The second surface 12 is disposed on the nozzle member 62D. The third surface 13 is disposed on the nozzle member 63D.

  As described above, in the present embodiment, the flow path 31D connected to the supply port 21, the flow path 32D connected to the supply port 22, and the flow path 33D connected to the supply port 23 are different. It is a flow path. Therefore, the supply amount of the first fluid supplied from the supply port 21, the supply amount of the second fluid supplied from the supply port 22, and the supply amount of the third fluid supplied from the supply port 23 are individually controlled. Is possible. For example, even if the supply amount of the first fluid supplied from the supply port 21 is larger than the supply amount of the second fluid supplied from the supply port 22 and the supply amount of the third fluid supplied from the supply port 23. Good. By doing so, the occurrence of stagnation of the gas mixture MS in the mixed space MS and the occurrence of a flashback phenomenon are suppressed.

  FIG. 7 is a modification of the combustion nozzle 8D described with reference to FIG. In the combustion nozzle 8E shown in FIG. 7, the mixing space MS between the second surface 12 and the third surface 13 becomes narrower in the + X direction. Thereby, the flow velocity of the air-fuel mixture FG at the outlet 41 is increased.

  In the present embodiment, the gas G may be supplied from the supply port 21, the fuel F may be supplied from the supply port 22, and the fuel F may be supplied from the supply port 23. The fuel F may be supplied from the supply port 21, the fuel F may be supplied from the supply port 22, and the gas G may be supplied from the supply port 23.

  The gas G may be supplied from the supply port 21, the gas G may be supplied from the supply port 22, and the fuel F may be supplied from the supply port 23. The gas G may be supplied from the supply port 21, the gas F may be supplied from the supply port 22, and the fuel G may be supplied from the supply port 23. The fuel F may be supplied from the supply port 21, the fuel G may be supplied from the supply port 22, and the gas G may be supplied from the supply port 23.

<Fifth Embodiment>
A fifth embodiment will be described. In the following description, the same or equivalent components as those in the above-described embodiment are denoted by the same reference numerals, and the description thereof is simplified or omitted.

  FIG. 8 is a side sectional view showing an example of the fuel nozzle 8F according to the present embodiment. In FIG. 8, the fuel nozzle 8F is disposed on the first surface 11 and is disposed on the second surface 12 for supplying the first fluid in the + X direction toward the mixing space MS, and toward the mixing space MS. A supply port 22 for supplying the second fluid inward in the radial direction with respect to the axis J, and a supply port for supplying the third fluid outwardly in the radial direction with respect to the axis J toward the mixing space MS. 23.

  The fuel F is supplied from at least one of the supply port 21, the supply port 22, and the supply port 23, and the gas G is supplied from at least one of the supply port 21, the supply port 22, and the supply port 23.

  In the present embodiment, the combustion nozzle 8 </ b> F is disposed on the front end surface 51 of the convex portion 17, and includes an outlet 42 through which gas (air) G flows out. The outlet 42 is smaller than the outlet 41. The outlet 42 is smaller than the supply port 21, the supply port 22, and the supply port 23.

  In the present embodiment, at least a part of the combustion nozzle 8 </ b> F including the tip surface 51 is cooled by the gas G flowing out from the outlet 42 of the tip surface 51. When the air flows out from the outlet 42 arranged on the front end surface 51, the temperature of the combustion nozzle 8F including the front end surface 51 is prevented from excessively increasing. Moreover, the occurrence of the flashback phenomenon is suppressed by cooling at least a part of the combustion nozzle 8F including the tip surface 51. Therefore, deterioration of the fuel nozzle 8F is suppressed.

  The fuel nozzle 8 </ b> F includes a flow path 31 </ b> F connected to the supply port 21, a flow path 32 </ b> F connected to the supply port 22, and a flow path 33 </ b> F connected to the supply port 23. In the present embodiment, the outlet 42 is connected to the flow path 33F. The gas G flows through the flow path 33F. The outflow port 42 flows out at least a part of the gas G in the flow path 33F. The fuel nozzle 8F may have a different flow path from the flow path 31F, the flow path 32F, and the flow path 33F. The outlet 42 may be connected to the other flow path. The outflow port 42 may flow out the gas G flowing through the other flow path. In that case, the gas G may flow into the flow path 33F, or the fuel F may flow.

  In the example shown in FIG. 8, the fuel F flows through the flow path 31F and the gas G flows through the flow path 32F. The gas G may flow through the flow path 31F, and the fuel F may flow through the flow path 32F.

  In addition, the outflow port 42 which flows out the gas G may be provided in the front end surface 52 of the surrounding wall part 18. Also by the gas G flowing out from the outlet 42 provided on the front end surface 52, the temperature rise of the combustion nozzle 8F is suppressed, and the occurrence of the flashback phenomenon is suppressed. The outlet 42 provided in the distal end surface 52 may be connected to the flow path 32F, or may be connected to a flow path different from the flow path 31F, the flow path 32F, and the flow path 33F.

  In each of the embodiments described above, a supply port for supplying the first fluid is provided on the first surface 11, a supply port for supplying the third fluid is provided on the third surface 13, and a supply port is provided on the second surface 12. The mouth may not be provided. Even in that case, the fuel F is supplied from one of the supply port provided in the first surface 11 and the supply port provided in the third surface 13, and the gas G is supplied from the other supply port. Thus, the mixture FG can be generated in the mixture space MS.

  FIG. 9 is a modification of the combustion nozzle 8F described with reference to FIG. In the combustion nozzle 8G shown in FIG. 9, the mixing space MS between the second surface 12 and the third surface 13 becomes narrower in the + X direction. Thereby, the flow velocity of the air-fuel mixture FG at the outlet 41 is increased.

1 Compressor 2 Combustor 3 Turbine 8 Pilot fuel nozzle (fuel nozzle)
11 First surface 12 Second surface 13 Third surface 21 Supply port 22 Supply port 23 Supply port 31 Channel 32 Channel 33 Channel 41 Outlet 42 Outlet 51 Tip surface 52 Tip surface 100 Gas turbine F Fuel FG Mixture (Mixed fluid)
G gas (air)
J axis

Claims (7)

A first surface having a ring shape in a plane perpendicular to the predetermined axis, arranged to be orthogonal to an axis parallel to the predetermined axis around the predetermined axis;
A second surface arranged to surround the predetermined axis;
A third surface facing the second surface via a gap;
A first supply port that is disposed on the first surface facing a space defined by the first surface, the second surface, and the third surface, and that supplies a first fluid to the space;
A second supply port disposed on the second surface facing the space and supplying a second fluid to the space;
The first surface generated between the second surface edge of the second surface farthest from the first surface and the third surface edge of the third surface with respect to a direction parallel to the predetermined axis and generated in the space. A first outlet from which a fluid mixture of the fluid and the second fluid flows out ;
With
One fluid of the first fluid and the second fluid contains fuel, and the other fluid is air,
The first supply port supplies the first fluid in a first direction parallel to the predetermined axis,
The second supply port supplies the second fluid to be mixed with the first fluid in the space;
Fuel nozzle.   The fuel nozzle according to claim 1, further comprising a third supply port that is disposed on the third surface and supplies a third fluid containing at least one of fuel and air to the space.   One surface of the second surface and the third surface is arranged to face outward with respect to the radial direction with respect to the predetermined axis around the predetermined axis, and the other surface is the predetermined axis around the predetermined axis. The fuel nozzle according to claim 1, wherein the fuel nozzle is disposed so as to face inward with respect to a radial direction with respect to.   4. The fuel nozzle according to claim 1, wherein the space between the second surface and the third surface becomes narrower in the first direction. 5. A first tip surface connected to the second surface edge and arranged to be orthogonal to an axis parallel to the predetermined axis;
A second tip surface connected to the third surface edge and arranged to be orthogonal to an axis parallel to the predetermined axis;
The fuel nozzle according to any one of claims 1 to 4, further comprising: a second outlet port that is arranged on at least one of the first tip surface and the second tip surface and through which air flows out.   A combustor comprising the fuel nozzle according to any one of claims 1 to 5.   A gas turbine comprising the combustor according to claim 6.

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