JP2005106305A - Nozzle for fuel combustion and fuel supplying method for gas turbine combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of solving a flame blown-off state by reignition even when the flame produced by the coaxial jet flow of fuel and air is partially blown off. <P>SOLUTION: A plurality of oxidant nozzles are arranged in the radial direction of a combustion chamber, and an injection hole outlet of at least one oxidant nozzle among the plurality of oxidant nozzles is located at a downstream side of the combustion chamber with respect to the injection hole outlet of at least one oxidant nozzle mounted at an inner peripheral side with respect to the oxidant nozzle. Whereby the flame is reignited even when the flame produced by the coaxial jet flow of fuel and air is partially blown off to solve the flame blown-off state. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

  The present invention relates to a fuel combustion nozzle and a gas supply method for a gas turbine combustor.

  In a combustor used for a gas turbine, it is necessary to reduce NOx emission from the standpoint of environmental conservation. One method of reducing NOx emissions is a lean premixed combustion method, in which combustion is performed in a state where fuel and oxidant are sufficiently mixed. However, with this combustion method, it was necessary to establish a method for preventing premixer burnout due to spontaneous ignition or flashback. As a prevention method, Patent Document 1 discloses a method in which a fuel and an oxidant are supplied to a combustion chamber as a plurality of coaxial jets and burned.

JP 2003-148734 A

  However, in the technique described in Patent Document 1, no particular reference is made to the arrangement of the ejection hole outlet with respect to the ejection hole outlet from which the coaxial jet of fuel and oxidant is ejected. For this reason, the outlets of the nozzle holes are all on the same plane with respect to the axial direction of the combustion chamber, and if a partial flame blowout occurs, it will not be easily reignited and the flame blown out state It will not be resolved.

  SUMMARY OF THE INVENTION Accordingly, an object of the present invention is to provide a gas turbine combustor capable of reigniting and eliminating a flame blow-off state even if a partial blow-off occurs in a flame generated by a coaxial jet of fuel and air. To do.

  In the present invention, a plurality of the oxidant nozzles are arranged in the radial direction of the combustion chamber, and at least one of the oxidant nozzles out of the plurality of oxidant nozzles has an outlet hole outlet disposed on the inner peripheral side of the oxidant nozzle. It is characterized by being arranged on the downstream side of the combustion chamber from the outlet hole of one oxidizer nozzle.

  According to the present invention, it is possible to provide a gas turbine combustor capable of reigniting and eliminating a flame blow-off state even if a partial blow-off occurs in a flame generated by a coaxial jet of fuel and air. .

  The configuration of the gas turbine in this embodiment will be described with reference to FIG. In this embodiment, the case where air is used as the oxidant supplied to the combustor will be described below.

The gas turbine includes a compressor 10 that compresses atmospheric air to generate compressed air, a combustor that generates combustion gas by mixing and burning compressed air and fuel, and a turbine 68 that rotationally drives a turbine shaft using the combustion gas. The 1 is a combustion chamber of the combustor, 4 is a combustion chamber outlet, and 5 is a transition piece. Further, 2 is an outer cylinder, 3 is a combustor liner that forms a part of the combustion chamber 1, 14 is a fuel nozzle, and 19 is an air hole. The injection hole of the fuel nozzle 14 for supplying fuel to the combustion chamber 1 and the injection hole of the air hole 19 provided for supplying air as the oxidant are arranged so as to be coaxial or close to the coaxial position. ing. In this embodiment, the air hole 19 corresponds to an oxidizer nozzle. And the air nozzle which supplies the air which is an oxidizing agent is arrange | positioned in the downstream of the fuel nozzle 14. FIG. In this way, by arranging the ejection holes of the fuel nozzle 14 and the ejection holes of the air nozzle coaxially, a generally coaxial jet is formed in which the combustion air that is an oxidant surrounds the outside of the fuel. The compressor 10 serves to supply compressed air 50 to the combustor. The turbine 68 is driven by the high-temperature combustion gas 15 generated in the combustion chamber 1. Here, as shown in FIG. 4, the ejection hole outlet surface 13 includes the ejection hole outlets of a plurality of air holes 19 that are air nozzles, and faces the combustion chamber 1.

A general operation process of the gas turbine in the present embodiment will be described with reference to FIG. The atmospheric air taken in from the outside is compressed by the compressor 10 to generate compressed air 50. The generated compressed air 50 passes between the outer cylinder 2 in the combustor and the combustor liner 3, and a part thereof is used to cool the combustor liner 3 as cooling air 52. The compressed air 50 other than the cooling air 52 becomes combustion air 51 and is used as an oxidant. In addition, since the combustor generally uses air as an oxidant, air is also used as an oxidant in this embodiment. The fuel 16 is ejected from the fuel nozzle 14 into the air hole 19. In the air hole 19, a coaxial jet 20 is formed in which the combustion air 51 surrounds the outside of the fuel 16, and the fuel 16 and the combustion air 51 are premixed. Then, the coaxial jet 20 flows into the combustion chamber 1. In FIG. 4, the fuel nozzle 14 has entered the inside of the air hole 19. By changing the length of the fuel nozzle 14, the state in which the fuel nozzle 14 hardly mixes in the air hole 19 flow path is almost completely mixed. It is possible to set up to. In addition, when the fuel nozzle 14 protrudes to the outlet of the air hole 19, the fuel 16 and the combustion air 51 are mixed for the first time in the combustion chamber 1, and a combustor with little risk of flashback can be obtained. . After the coaxial jet 20 flows into the combustion chamber 1 as described above, a flame is formed in the combustion chamber 1 and the combustion gas 15 is generated. The combustion gas 15 passes through the transition piece 5 and enters the turbine 68. And after converting a part of kinetic energy of the combustion gas 15 into the rotational energy of a turbine, it is exhausted.

  A first embodiment is shown in FIGS. These figures are views of a portion including the fuel nozzle, air holes, and ejection hole outlet surfaces shown in FIG. 4, FIG. 1 is a longitudinal side view, and FIG. 2 is a view seen from the combustion chamber 1 side. . On the ejection hole exit surface 73, outlets (ejection hole exits) of a plurality of air holes 19 are arranged in the radial direction of the combustion chamber. Note that an outlet (ejection hole outlet) located near the combustor liner 3 is called an outer peripheral outlet 45, and an outlet (ejection hole outlet) located inside the outer peripheral outlet 45 and far from the combustor liner 3. ) Will be referred to as the inner peripheral outlet 46. The upstream side of the fuel supply is the upstream side of the combustion chamber. In the present embodiment, the outer peripheral side outlet 45 is located on the downstream side of the combustion chamber with respect to the inner peripheral side outlet 46. Therefore, the vertical side surface of the ejection hole outlet surface 73 is not flat but has a fan shape extending from the center in the radial direction of the combustion chamber to the downstream side of the combustion chamber, as shown in the vertical side view of FIG. Further, the ejection hole outlet surface 73 is inclined with respect to the central axis of the combustion chamber. In addition, about the air hole 19 and the fuel nozzle 14, those numbers, arrangement | positioning, the shape of a cross section, and a dimension are not limited only to what was shown in FIG. 1, FIG. 2, the air hole 19 and the fuel nozzle 14 are circular in cross section, and are arranged concentrically. However, for example, as shown in FIG. 6, the air holes 19 and the fuel nozzles 14 may be rectangular in cross section and arranged in a lattice shape. The air holes may have a cylindrical shape as shown in FIG.

  Next, in order to explain the operation and effect of the present embodiment, the case where the ejection hole outlet surface of the combustor is a plane will be described.

  FIG. 5 shows a region in the vicinity of the outlet of the air hole 19 when the ejection positions (ejection hole outlets) of the plurality of air nozzles (air holes) in the combustor are located on the same plane perpendicular to the central axis of the combustion chamber. It is an enlarged view. A recirculation flow region 25 is formed by the coaxial jet 20 ejected from the air hole 19. A flame holding point 26 is formed at the apex of the recirculation flow region 25, and a flame surface 30 is formed in a fan shape from the flame holding point 26. The area inside the flame surface 30 is a combustion gas area 31, which represents an area where the generated combustion gas exists. Further, in the combustion gas region 31, a region located near the combustor liner 3 is located in the outer burned region 32, and a burned region located far from the combustor liner 3 is defined as the inner burned region 33. To do.

  Next, a method for generating the flame shown in FIG. 5 will be described. In order for a stable flame to be maintained, the flame holding point 26 in the recirculation flow region 25 must be constantly supplied with a hot fluid mass (hereinafter referred to as the hot fluid mass). . In FIG. 5, if there is a hot fluid mass at the flame holding point 26, the hot fluid mass rides on the circulating flow in the recirculation flow region 25 and returns to the flame holding point 26 again. Therefore, since a high-temperature fluid mass is constantly supplied to the flame holding point 26, a stable flame is formed.

  Here, let us consider a case where a part of the flame is blown off for some reason in the outer burned region 32. In order to form a stable flame again, the high temperature fluid mass needs to be supplied to the flame holding point 26 again. Although the flow in the combustion chamber is considered to be in a turbulent flow state, the position of the flame holding point 26 varies with time mainly in the direction indicated by the arrow 84 due to the flow fluctuation caused by the turbulent flow. Due to the temporal variation in the position of the flame holding point 26, if the flame holding point 26 enters the inner burned region 33 where the flame exists, and if a high-temperature fluid mass can be obtained therefrom, it is ignited again. As described above, since the high-temperature fluid mass is constantly supplied to the flame holding point 26 by the circulating flow in the recirculation flow region 25, the blow-off of the flame can be eliminated.

However, when the outlet surface 13 of the ejection hole is flat and the outlet (ejection hole outlet) of the air hole 19 that is an air nozzle is arranged as shown in FIG. Since it cannot move, the flame holding point 26 of the outer burned region 32 cannot move to the point A that reaches the inner burned region 33. Therefore, even if the position of the flame holding point 26 varies with time, the flame holding point 26 cannot enter the inner burned region 33. Therefore, the flame holding point 26 cannot acquire a high-temperature fluid mass, and the flame of the outer burned region 32 is blown off. Thus, since the coaxial jet ejected from the air hole 19 is premixed combustion, if a part of the flame formed in the combustion chamber 1 is blown off, the following problems occur. First, if the other part of the flame is blown out without the partial blow-off of the flame being eliminated, there is a risk that the entire flame will eventually blow out. In order to increase the operating margin of the gas turbine combustor, it is necessary to make it difficult to cause such overall flame blowout. Secondly, the fuel does not burn completely where the flame is blown out, which increases the amount of CO and unburned hydrocarbon emissions. Third, since a burned area and an unburned area are formed in the combustion chamber 1 due to partial blowout of the flame, a large temperature deviation occurs, and this temperature deviation may cause damage to the turbine blades. Therefore, there is a need for a combustor capable of reigniting and eliminating the flame blow-out state even if a partial flame blow-off occurs in the combustion chamber 1.

Therefore, in this embodiment, the longitudinal side surface of the outlet surface of the outlet hole where the outlet hole for ejecting the coaxial jet of fuel and air is arranged in a fan shape extending from the center in the radial direction of the combustion chamber to the downstream side of the combustion chamber. The outlet of the air hole 19 (ejection hole outlet) is arranged in a shape. FIG. 8 is an enlarged view of the ejection hole outlet surface 73 of the combustor in the present embodiment. As shown in the drawing, the outer peripheral recirculation flow region 35 is located closer to the combustor liner 3 than the inner peripheral recirculation flow region 55. Further, an outer peripheral side flame holding point 36 and an inner peripheral side flame holding point 56 are provided at the apexes of the outer peripheral side recirculation flow region 35 and the inner peripheral side recirculation flow region 55. In FIG. 8, the names of the parts other than the above are the same as those in FIG.

  Comparing FIG. 8 and FIG. 5, the shape of the burned area including the flame surface and the combustion gas area is different. This is because the positional relationship between the outlets of the air holes 19 (ejection hole outlets) is different. In FIG. 8, the outlet hole outlet of the air hole forming the outer peripheral side recirculation flow region 35 is located on the downstream side of the combustion chamber 1 with respect to the outlet hole outlet of the air hole forming the inner peripheral side recirculation flow region 55. The combustor liner is configured such that the coaxial jet is ejected on the downstream side of the combustion chamber rather than the coaxial jet ejected from the inner peripheral side of the combustion chamber. Therefore, the outer flame side flame holding point 36 is also located on the downstream side of the combustion chamber 1 with respect to the inner circumferential flame holding point 56. Therefore, also in the burned area formed with the flame holding point as the starting point, the outer burned area 32 is located on the downstream side of the combustion chamber 1 with respect to the inner burned area 33, and therefore the burned area having the shape shown in FIG. A region is formed.

  As described above, when the outlet surface of the injection hole is not flat as in the present embodiment (FIG. 8), even if the flame blows off in the outer burned region 32 that has been premixed and burned by the coaxial jet of fuel and air, the outer side flame holding When the hot fluid mass is supplied again to the point 36, the flame is re-ignited and the flame blow-off is eliminated. The position of the outer flame holding point 36 varies with time mainly in the direction indicated by the arrow 84 due to flow fluctuations. Since the distance from the outer flame holding point 36 to the inner burned region 33 is short, the outer flame holding point 36 enters the inner burned region 33 due to the change in position, and the inner burned region 33 A hot fluid mass can be easily obtained from the flame. That is, the coaxial jet is ejected from the exit surface of the ejection hole so that a part of the inner burned region overlaps within the action range of the flame holding point indicated by the arrow. Therefore, even if the flame blows off in the outer burned area 32, the blow-off of the flame is eliminated. Since it becomes possible to eliminate the blow-off of the flame, it becomes possible to expand the operating margin of the gas turbine combustor. In addition, the amount of CO and unburned hydrocarbon emissions generated from the location where the flame has blown off is reduced, and the turbine blade is prevented from being damaged due to temperature deviation in the combustion chamber.

  In this embodiment, the longitudinal side surface of the outlet surface of the ejection hole is formed in a fan shape extending from the center in the radial direction of the combustion chamber to the downstream side of the combustion chamber. A similar effect can be obtained by shifting the positional relationship in the combustion chamber axial direction. That is, the outlet hole outlet of at least one air hole among the plurality of air holes (oxidant nozzles) is located downstream of the outlet hole outlet of at least one air hole arranged on the inner peripheral side of the air hole. The same effect can be obtained by using the arrangement.

  Next, the degree of unevenness on the outlet surface of the ejection hole will be described with reference to FIG. FIG. 18 is a longitudinal side view of a portion including a fuel nozzle, an air hole, and an ejection hole outlet surface of the combustor. The distance between the air hole outlet (ejection hole outlet) closest to the combustor outlet and the air hole outlet (ejection hole outlet) farthest from the combustor outlet in the combustion chamber central axis direction is D1, and the radial direction of the combustion chamber The distance between adjacent air hole outlets (ejection hole outlets) is D2. In this case, D1 needs to be about one-tenth of the maximum value in the dimension of all air hole outlets (ejection hole outlets). For example, when the cross-sectional shape of all the air holes is circular, about 1/10 of the maximum value of the diameter of all air holes is required. Moreover, it is necessary to make D2 larger than the maximum value in the dimension of all air hole outlets (ejection hole outlets). If this is not done, the air holes may overlap. Next, D2 needs to be smaller than about 5 times the maximum value in the size of all air hole outlets (ejection hole outlets). If D2 is smaller than about five times the maximum value in the size of all air hole outlets (outlet hole outlets), air and fuel are mixed. Conversely, if D2 is larger than this value, air and fuel hardly mix. It is. Accordingly, it is desirable that D2 is set to be larger than the maximum value in the all air hole outlet (ejection hole outlet) size and further smaller than about five times the maximum value in the all air hole outlet (ejection hole outlet) size. For this reason, in this embodiment, the ejection hole outlet surface that does not correspond to the above conditions D1 and D2 is a flat surface.

  A second embodiment is shown in FIGS. FIG. 9 is a longitudinal side view of a portion including the fuel nozzle 14, the air hole 19, and the ejection hole outlet surface in the second embodiment. Moreover, FIG. 10 represents the figure which looked at the ejection hole exit surface from the combustion chamber 1 side. In the second embodiment, the central axis of each air hole 19 is the central axis of the combustion chamber so that the coaxial jet 20 ejected from the outer peripheral side outlet 75 and the inner peripheral side outlet 76 faces the central axis of the combustion chamber 1. Is tilted at an angle to The angle formed by the central axis of the air hole 19 and the central axis of the combustion chamber 1 may be different for each air hole 19. In FIG. 9, the fuel nozzle 14 has entered a position slightly inserted from the inlet of the air hole 19, but the length of the fuel nozzle 14 enters can be changed to change the fuel 16 in the air hole 19 flow path and the combustion nozzle. Various mixing states with the air 51 can be set.

  Next, the operation and effect of the present embodiment will be described. FIG. 11 is an enlarged view of the ejection hole outlet surface 73 of the combustor in the present embodiment. A coaxial jet 20 of fuel and air is jetted into the combustion chamber 1 along the direction of the central axis of the air hole 19. Therefore, the recirculation flow region, the flame holding point, and the burned gas region formed in the combustion chamber 1 are as shown in FIG. Here, 85 and 95 are an outer periphery side recirculation flow region and an inner periphery side recirculation flow region, respectively, and 86 and 96 are an outer periphery side flame holding point and an inner periphery side flame holding point, respectively. In this embodiment, since the distance from the outer flame holding point 86 to the inner burned region 33 is further shorter than in the first embodiment, the outer flame holding point 86 is caused by a variation in its temporal position. The high-temperature fluid mass can be acquired from the inner burned region 33 more easily. Therefore, in the second embodiment, even if the flame burns out in the outer burned area 32, the outer flame holding point 86 can easily acquire the high-temperature fluid mass from the inner burned area 33 and reignite it. Therefore, it has a further effect on eliminating the blaze.

  FIG. 12 shows the third embodiment. In the first and second embodiments described above, for example, in FIG. 8 of the first embodiment, countermeasures are taken against the blow-off of the flame in the outer burned area, but no measures are taken for the inner burned area. Therefore, in this embodiment, measures are also taken against the blow-off of the flame in the inner burned area.

In order to stabilize the flame, it is effective to create a recirculation flow region and perform diffusion combustion. Therefore, in this embodiment, the fuel nozzle installed at the center in the radial direction of the combustion chamber is replaced with the pilot burner 18, which is downstream of the ejection portion of the pilot burner 18 and on the outer periphery of the pilot burner 18. The air hole 48 which ejects a coaxial jet is the characteristic. In the pilot burner 18, when the combustion air 51 passes through the outlet of the pilot burner 18, a swirl component is given to the air flow by the swirler 12. Accordingly, a swirling flow of air is ejected from the central air hole outlet 47, which is the outlet of the air hole 48, toward the combustion chamber 1. As a result, a recirculation flow region accompanying the swirling flow of air is formed downstream of the pilot burner 18. The fuel nozzle 43 constituting the pilot burner 18 protrudes to the position of the center air hole outlet 47, and diffuses and burns fuel and air downstream of the pilot burner 18. In this way, fuel and air are diffused and burned on the central axis of the combustion chamber to create a recirculation flow that accompanies the swirling flow of air, so that it is possible to prevent the inner burned area from being blown out. is there. Further, the fuel supply system of the fuel nozzle 43 in the pilot burner 18 and the fuel supply system of the fuel supplied to the other fuel nozzles 44 are divided. Therefore, the fuel supply to the fuel nozzles 43 and 44 is separated from the fuels 42 and 41, respectively.

  In order to stably operate the gas turbine combustor from the start to the rated condition and to achieve low NOx under the rated condition, premixed combustion is effective instead of diffusion combustion. Therefore, a fuel and air supply method in the present embodiment will be described. First, when starting the gas turbine, only the fuel 42 is supplied, and the pilot burner 18 performs diffusion combustion. Then, when increasing the load, the supply amount of the fuel 41 is increased while gradually decreasing the supply amount of the fuel 42, and the premixed combustion in which the fuel 41 and the air are sufficiently mixed by the air holes 48 is performed. Eventually, only the premixed combustion is performed in the combustion chamber 1, and the rated condition of the gas turbine is derived. Note that, under rated conditions, the pilot burner 18 also needs to stabilize the flame, so a part of the total fuel to be supplied is supplied as the fuel 42. In the third embodiment, since the fuel supply system is divided in this way, the gas turbine combustor can be stably started and guided to the rated condition.

  Next, a fourth embodiment will be described. FIG. 13 shows a longitudinal side view of a portion including the fuel nozzle 14, the air hole 19, and the ejection hole outlet surface 113 in the present embodiment. In the ejection hole outlets 61, 62, 63, 64 that are the ejection parts of the air holes, the ejection hole outlet 61 is located closest to the combustor liner 3. As for the jet hole outlets 61 and 62 near the combustor liner 3, the jet hole outlet 61 closer to the combustor liner 3 is arranged downstream of the jet hole outlet 62 in the central direction of the combustion chamber. Therefore, at the downstream of the outlet hole 61, even if the flame blows off, it can be reignited to eliminate the blowout. On the other hand, the jet hole outlets 63 and 64 located at the center in the radial direction of the combustion chamber are substantially the same position in the central axis direction of the combustion chamber, and the jet hole outlet surface 113 near the jet hole outlets 63 and 64 is substantially flat. It has become. Also in this embodiment, since the fuel supply system is divided, it is possible to stably start the gas turbine combustor and adjust the fuel supply amount so as to lead to the rated condition.

  Note that, in the vicinity of the ejection hole outlets 63 and 64, there may be a case where the ejection hole outlet 63 is located downstream of the ejection hole outlet 64 in the central axis direction of the combustion chamber due to manufacturing errors or the like. However, if the positions of the outlet holes 63 and 64 in the direction of the central axis of the combustion chamber are within a range of about one-tenth or less of the sectional dimension of the outlet hole outlet (for example, the diameter in the case of a circular cross section). For example, there is no particular problem with flame stability.

  A fifth embodiment is shown in FIG. FIG. 14 is a view of the ejection hole outlet surface in the combustor as viewed from the combustion chamber side. In this embodiment, in order to generate a swirling flow in the flow ejected from the entire ejection hole outlet surface into the combustion chamber 1, the central axis of the air hole having the ejection hole outlet 63 is shown in FIG. Tilt to. By constructing the air hole outlet which is the ejection hole as in this embodiment, the ejection hole outlet 63, 64 portion of the fourth embodiment (FIG. 13) is provided with a mechanism for strengthening flame holding. As a result, it is possible to reinforce the flame holding downstream of the ejection hole outlets 63 and 64 by the circulation flow accompanying the swirling flow ejected from the ejection hole outlets 63 and 64.

The fuel nozzle 14 and air hole 19 shown in the first embodiment (FIGS. 1 and 2) are used as one module, and a plurality of the modules are combined to form one combustor. FIG. FIG. 15 is a view of a combustor in which a plurality of modules each having a circular outlet surface is viewed from the combustion chamber 1 side. In the figure, reference numeral 77 represents the module. In the combustor of the present embodiment, even if a partial flame blowout occurs in each module 77, it can be reignited to eliminate the flame blowout. The number of modules 77 and their arrangement are not limited to those shown in FIG. For example, it may be as shown in FIGS. FIG. 16 is a longitudinal side view of the air hole outlet surface in a combustor in which a plurality of modules are combined, and FIG. 17 is a view of FIG. 16 viewed from the combustion chamber 1 side. Further, when a plurality of modules 78 having fan-shaped exit surfaces are combined, the space between the modules 78 can be reduced. Therefore, it is possible to reduce the deviation of the arrangement of the ejection holes and supply the fuel. Therefore, it is possible to supply combustion gas with no spatial bias to the turbine. In addition, the ejection hole exit surface shown in 2nd Example, 3rd Example, 4th Example, 5th Example can also be used as a module.

The longitudinal section side view of the gas turbine combustor in the 1st example. The figure which looked at the gas turbine combustor in the 1st example from the combustion chamber side. The enlarged view of the air hole exit surface of the gas turbine combustor in 1st Example. The longitudinal section of a gas turbine combustor, and the lineblock diagram of a gas turbine. The figure showing the state of the burned area | region etc. in a combustion chamber when all the air hole exits are arrange | positioned on the same plane. The figure showing the case where the air hole and fuel nozzle cross section of a gas turbine combustor are rectangular in 1st Example. The figure showing the case where the air hole of a gas turbine combustor is cylindrical in the 1st example. The figure showing the mode of the burned area | region etc. in the combustion chamber in 1st Example. The longitudinal section side view of a gas turbine combustor in case the central axis of an air hole has turned to the central axis of a combustion chamber. The figure which looked at the gas turbine combustor when the central axis of an air hole has faced the central axis of a combustion chamber from the combustion chamber side. The figure showing the state of the burned area | region etc. in a combustion chamber when the central axis of an air hole has faced the central axis of a combustion chamber. The longitudinal side view of the gas turbine combustor when the pilot burner is installed at the axial center of the combustion chamber. The longitudinal section side view of the gas turbine combustor which supplies fuel with two or more systems. The figure which looked at the gas turbine combustor at the time of inclining the central axis of an air hole exit with respect to a combustion chamber central axis from the combustion chamber side. The figure which looked at the gas turbine combustor whose ejection hole exit surface is a circular module from the combustion chamber side. FIG. 3 is a longitudinal side view of a gas turbine combustor having a fan-shaped module whose outlet surface is an ejection hole. The figure which the ejection hole exit surface saw from the combustion chamber side of the gas turbine combustor of a fan-shaped module. The figure showing the degree of the unevenness | corrugation in an ejection hole exit surface.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 ... Combustion chamber, 2 ... Outer cylinder, 3 ... Combustor liner, 4 ... Combustion chamber exit, 5 ... Transition piece, 10 ... Compressor, 12 ... Swivel, 13, 73, 83, 93, 103, 113 ... Jet Hole exit surface, 14, 43, 44 ... Fuel nozzle, 15 ... Combustion gas, 16, 41, 42 ... Fuel, 18 ... Pilot burner, 19 ... Air hole, 20 ... Coaxial jet, 25 ... Recirculation flow region, 26 ... Flame holding point, 30 ... flame surface, 31 ... combustion gas region, 32 ... outside burned region, 33 ... inside burned region,
35, 85 ... outer recirculation flow area, 36, 86 outer flame holding point, 45, 75 outer outlet, 46, 76 inner outlet, 47 central air hole outlet, 48 air hole 50 ... Compressed air, 51 ... Combustion air, 52 ... Cooling air, 55, 95 ... Inner circumference recirculation flow region, 56, 96 ... Inner circumference flame holding point, 61, 62, 63, 64 ... Ejection Hole outlet, 68... Turbine, 77, 78... Module, 84.

Claims (6)

A fuel nozzle for supplying fuel to the combustion chamber; and an oxidant nozzle for supplying an oxidant located downstream of the fuel nozzle. The fuel nozzle and the oxidant nozzle are coaxially arranged. A fuel combustion nozzle arranged in a shape,
Arranging a plurality of the oxidizer nozzles in the radial direction of the combustion chamber;
Outlet outlets of at least one oxidant nozzle among the plurality of oxidant nozzles are arranged downstream of the combustion chamber from the outlet holes of at least one oxidant nozzle arranged on the inner peripheral side of the oxidant nozzle. Fuel combustion nozzle. A fuel nozzle for supplying fuel to the combustion chamber; and an oxidant nozzle for supplying an oxidant located downstream of the fuel nozzle. The fuel nozzle and the oxidant nozzle are coaxially arranged. A fuel combustion nozzle arranged in a shape,
A pilot burner that performs diffusive combustion of fuel and oxidant is disposed at the center in the radial direction of the combustion chamber, and is located downstream of the ejection portion of the pilot burner and in the outer periphery of the pilot burner. A fuel combustion nozzle, characterized in that an agent nozzle is disposed. A fuel nozzle for supplying fuel to the combustion chamber; and an oxidant nozzle for supplying an oxidant located downstream of the fuel nozzle. The fuel nozzle and the oxidant nozzle are coaxially arranged. A fuel combustion nozzle arranged in a shape,
A plurality of ejection hole outlets of the oxidizer nozzle are arranged in the radial direction of the combustion chamber on the ejection hole outlet surface facing the combustion chamber, and the ejection hole outlet surface is inclined with respect to the central axis of the combustion chamber. A fuel combustion nozzle. A fuel supply method for a gas turbine combustor, wherein a coaxial jet of fuel supplied from a fuel nozzle to a combustion chamber and an oxidant supplied from an oxidant nozzle downstream of the fuel nozzle is jetted into the combustion chamber. ,
A plurality of the coaxial jets of fuel and oxidant are ejected in the radial direction of the combustion chamber;
Out of the plurality of coaxial jets ejected from the outlet of the oxidant nozzle, at least one coaxial jet is ejected from the at least one coaxial jet disposed on the inner peripheral side of the coaxial jet. A fuel supply method for a gas turbine combustor, characterized by being formed so as to be ejected from an outlet. A fuel supply method for a gas turbine combustor according to claim 4,
A fuel supply method for a gas turbine combustor, characterized in that a coaxial jet is ejected from the oxidizer nozzle so as to face the central axis of the combustion chamber. A fuel supply method for a gas turbine combustor, wherein a coaxial jet of fuel supplied from a fuel nozzle to a combustion chamber and an oxidant supplied from an oxidant nozzle downstream of the fuel nozzle is jetted into the combustion chamber. ,
A plurality of the coaxial jets of fuel and oxidant are ejected in the radial direction of the combustion chamber;
One burned region formed by at least one coaxial jet disposed on the inner peripheral side of the coaxial jet within an action range of a flame holding point formed by at least one coaxial jet among the plurality of coaxial jets. The fuel supply method for a gas turbine combustor, wherein the plurality of coaxial jets are ejected so that the portions overlap each other.

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