JP4854613B2 - Combustion apparatus and gas turbine combustor - Google Patents

Description

  The present invention relates to a combustion apparatus and a gas turbine combustor for supplying fuel and air as a plurality of coaxial jets to a combustion chamber for combustion, and promotes mixing of fuel and air to reduce nitrogen oxide (NOx) emissions. The present invention relates to a reducing combustion apparatus and a gas turbine combustor.

  In recent years, regulations on the emission of air pollutants have become stricter, and in a gas turbine combustor used as a combustion apparatus, particularly a power generation facility, nitrogen oxides contained in exhaust gas discharged from the gas turbine combustor Various combustion methods for reducing (NOx) emissions have been studied.

  Japanese Patent Application Laid-Open No. 2003-148734 discloses a technology related to a gas turbine combustor related to a coaxial jet combustion system in which fuel and air are supplied to a combustion chamber as a coaxial jet and burned. In comparison, it is possible to effectively promote the mixing of fuel and air at a very short distance, and to suppress the NOx emission amount to a low level.

JP 2003-148734 A

  In the coaxial jet type gas turbine combustor technology described in Japanese Patent Application Laid-Open No. 2003-148734, rapid mixing of fuel and air is possible, so that NOx emission can be kept low.

  However, environmental regulations for NOx emissions from gas turbine combustors are becoming stricter year by year from the viewpoint of the global environment, and further reduction of NOx emissions is desired in the future. .

  Here, the NOx generation amount greatly depends on the temperature of the flame formed in the combustion chamber of the gas turbine combustor, and the NOx emission amount increases exponentially as the flame temperature rises.

  For this reason, even if a coaxial jet method is used in which fuel and air are supplied to the combustion chamber as a coaxial jet and burned, if the fuel and air are not well mixed, a premixed mixture of fuel and air is used. A region having a high fuel concentration is formed locally.

  As a result, when the premixed gas in which the fuel concentration is locally formed is burned, the flame temperature is locally increased and the amount of NOx emission is increased. It has been difficult to further reduce NOx emissions.

  An object of the present invention is to provide a coaxial jet combustion system in which fuel and air are supplied to a combustion chamber as a coaxial jet and burned, and the fuel and air to be jetted coaxially are mixed uniformly so as to increase the degree of mixing between them. An object of the present invention is to provide a combustion apparatus and a gas turbine combustor which can be increased and greatly reduce NOx emissions.

A combustion apparatus according to the present invention includes a plurality of fuel injection nozzles that eject fuel and a plurality of mixture injections that are disposed downstream of the fuel injection nozzle and eject a first air-fuel mixture in which the fuel and primary air are mixed. A nozzle, an air hole plate provided downstream of the air-fuel mixture injection nozzle, and provided with a plurality of air holes for ejecting a second air-fuel mixture in which the first air-fuel mixture and secondary air are mixed; and the air A combustion chamber for combusting a mixture of fuel and air disposed on the downstream side of the air hole provided in the hole plate, and the center axis of the mixture injection nozzle is coaxial with the center axis of the fuel injection nozzle An air hole provided in the air hole plate is arranged so that the periphery of the jet of fuel ejected from the fuel injection nozzle is wrapped in primary air so as to be surrounded by the primary air. Same as the central axis of the injection nozzle A nozzle outer cylinder in which an air-fuel mixture header provided with the air-fuel mixture injection nozzle is disposed inside the first air-fuel mixture ejected from the air-fuel mixture injection nozzle; and the air-fuel mixture header; Is rapidly expanded in a flow path formed between the first air- fuel mixture and the air around the first air- fuel mixture so as to be surrounded by secondary air and introduced into the air holes of the air hole plate. It is characterized in that the second air-fuel mixture is jetted and burned.
Further, the combustion apparatus of the present invention includes a plurality of fuel injection nozzles for ejecting fuel, and a plurality of first fuel injectors that are disposed downstream of the fuel injection nozzle and eject a first air-fuel mixture in which the fuel and primary air are mixed. A plurality of air-fuel mixture headers provided with air holes, and a plurality of air-fuel mixture headers arranged on the downstream side of the first air holes provided in the air-fuel mixture header and ejecting a second air-fuel mixture mixed with the first air-fuel mixture and secondary air An air hole plate provided with a second air hole, and a combustion chamber disposed on the downstream side of the second air hole provided in the air hole plate and combusting a fuel / air mixture. The first air hole provided in the central axis of the fuel injection nozzle is arranged coaxially with the central axis of the fuel injection nozzle, and the mixing is performed so as to wrap around the fuel jet ejected from the fuel injection nozzle with primary air. This first air hole is introduced into the first air hole of the air header. The first air-fuel mixture ejected from the nozzle is abruptly passed through a flow path formed between the nozzle outer cylinder in which the air-fuel mixture header provided with the first air hole is installed and the air-fuel mixture header. Enlarge,
The second air hole provided in the air hole plate has a central axis coaxially arranged with the central axis of the first air hole, and the second air hole is disposed around the first air-fuel mixture ejected from the first air hole. It is configured to be introduced into the second air hole of the air hole plate so as to be enveloped by the secondary air, and to be burned by injecting the second air-fuel mixture from the second air hole into the combustion chamber. .
The combustion apparatus of the present invention includes a plurality of fuel injection nozzles for ejecting fuel, a plurality of first air holes arranged downstream of the fuel injection nozzle and into which the fuel and primary air flow and the first air. A gas mixture header provided with a premix header in which a chamber in which the fuel and primary air are mixed to form a first gas mixture is formed downstream of the hole, and the gas mixture header is formed in the gas mixture header. An air-fuel mixture injection nozzle that ejects the first air-fuel mixture from the premix header, and a second air-fuel mixture that is disposed downstream of the air-fuel mixture injection nozzle and in which the first air-fuel mixture and secondary air are mixed An air hole plate provided with a plurality of second air holes for ejecting gas, and a combustion chamber disposed downstream of the air holes provided in the air hole plate and combusting a fuel-air mixture. One air hole has a central axis coaxial with the central axis of the fuel injection nozzle. And surrounding the jet of fuel ejected from the fuel injection nozzle with the primary air so as to be introduced into the first air hole of the mixture header, and further through the first air hole, the premix header The fuel / primary air mixture flowing down into the premixing header is rapidly expanded to form a first mixture and ejected from the mixture injection nozzle. A second air hole provided in the air hole plate, which is rapidly expanded in a flow path formed between a nozzle outer cylinder having an air-fuel mixture header provided with the air-fuel mixture injection nozzle and the air-fuel mixture header. The air hole plate is arranged so that its central axis is coaxial with the central axis of the air-fuel mixture injection nozzle so as to wrap around the first air-fuel mixture ejected from the air-fuel mixture injection nozzle with secondary air And introduced into the second air hole of the Two to the air hole is ejected the second mixture in the combustion chamber, characterized by being configured to burn with.

In the gas turbine of the present invention, a plurality of fuel injection nozzles for ejecting fuel and primary air that is a part of high-pressure air that is disposed downstream of the fuel injection nozzle and compressed by the compressor are mixed. A plurality of air-fuel mixture injection nozzles for ejecting the first air-fuel mixture; and a part of high-pressure air that is disposed downstream of the air-fuel mixture injection nozzle and compressed by the first air-fuel mixture and the compressor An air hole plate provided with a plurality of air holes for ejecting the second air-fuel mixture mixed with the secondary air, and disposed on the downstream side of the air holes provided in the air hole plate to burn the fuel / air mixture A combustion chamber, and the air-fuel mixture injection nozzle has a central axis disposed coaxially with the central axis of the fuel injection nozzle so as to wrap around the fuel jet ejected from the fuel injection nozzle with primary air. Introduced into the lever The air hole provided in the air hole plate has a central axis coaxially arranged with the central axis of the air-fuel mixture injection nozzle, and the first air-fuel mixture ejected from the air-fuel mixture injection nozzle is disposed inside the air hole. The nozzle outer cylinder having the gas mixture header provided with the gas mixture injection nozzle is rapidly expanded in a flow path formed between the gas mixture header and the secondary air around the first gas mixture The second air-fuel mixture is introduced into the air holes of the air hole plate so as to be encased, and the second air-fuel mixture is ejected from the air holes into the combustion chamber for combustion.
Further, the gas turbine according to the present invention mixes a plurality of fuel injection nozzles for ejecting fuel, and primary air that is disposed at a downstream portion of the fuel injection nozzle and is a part of high-pressure air compressed by the compressor. An air-fuel mixture header provided with a plurality of first air holes for ejecting the first air-fuel mixture, and the first air-fuel mixture and the compression disposed on the downstream side of the first air hole provided in the air-fuel mixture header An air hole plate provided with a plurality of second air holes for ejecting a second air-fuel mixture mixed with secondary air that is part of the high-pressure air compressed by the machine, and second air provided on the air hole plate A combustion chamber disposed on the downstream side of the hole and combusting a mixture of fuel and air, and the first air hole provided in the mixture header has a central axis coaxial with the central axis of the fuel injection nozzle Around the jet of fuel ejected from the fuel injection nozzle An air-fuel mixture header is provided in which the first air-fuel mixture is introduced into the first air hole so as to be enveloped by the secondary air, and the first air-hole is further ejected from the first air hole. The second air hole provided in the air hole plate has a central axis that is the central axis of the first air hole. The second air hole is arranged on the same axis and introduced into the second air hole of the air hole plate so as to surround the first air-fuel mixture ejected from the first air hole with secondary air. The second air-fuel mixture is jetted into the combustion chamber and burned .

According to the present invention, fuel and in the air that the coaxial injection flow combustion method for burning is supplied to the combustion chamber as a coaxial jet, both degree of mixing uniformly mixed fuel and air jetting coaxially And a combustion apparatus and a gas turbine combustor that can significantly reduce NOx emissions can be realized .

  A case where the present invention is applied to a gas turbine combustor as a combustion apparatus according to an embodiment of the present invention will be described below with reference to the drawings.

  As a combustion apparatus according to an embodiment of the present invention, an embodiment applied to a gas turbine combustor will be described with reference to FIG.

  FIG. 1 is an overall schematic view of a gas turbine power generator equipped with a gas turbine combustor which is an embodiment of the present invention to which a coaxial jet combustion system of fuel and air is applied.

  In FIG. 1, as main equipment constituting the gas turbine power generation apparatus, a compressor 110 that compresses air, and a high-pressure air compressed by the compressor 110 and fuel are supplied as a coaxial jet to a combustion chamber and burned. A combustor 1, a turbine 200 driven by high-temperature combustion gas generated by combustion in the gas turbine combustor 1, and a generator 210 that rotates and generates electric power by driving the turbine 200 are provided.

  The air compressor 110 compresses the atmosphere to generate high-pressure air 120, and the high-pressure air 120 is introduced into the passenger compartment 140 via the diffuser 130.

  The high-pressure air 120 further passes through a flow path formed between the transition piece 150 and the transition piece flow sleeve 151 installed on the outer periphery of the transition piece 150, and the liner 160 constituting the gas turbine combustor 1. It flows into the flow path formed between the outer cylinder 161 concentrically arranged on the outer periphery of the liner 160.

  The high-pressure air 120 reverses the flow direction downstream of the flow path and is introduced into the combustion chamber 190 from the air holes 30 provided in the air hole plate 31.

  On the other hand, the fuel system 180 that supplies the fuel 40 to the gas turbine combustor 1 is provided with a fuel pump 181 and a flow rate control valve 182, and the pressure is increased by the fuel pump 181 and the flow rate is adjusted by the flow rate control valve 182. The fuel 40 is ejected from a fuel injection nozzle 10 installed inside the gas turbine combustor 1.

  The structure in the vicinity of the fuel injection nozzle 10 and the air hole 30 will be described with reference to FIG.

  The air-fuel mixture ejected from the air hole 30 is supplied from the air hole 17230 into the combustion chamber 190 of the gas turbine combustor 1 formed inside the liner 160 and burns, and forms a flame in the combustion chamber 190 to form a high temperature and high pressure. The combustion gas 191 is generated.

  The high-temperature and high-pressure combustion gas 191 generated in the combustion chamber 190 of the gas turbine combustor 1 flows down through the tail cylinder 150 and is introduced into the turbine 200 as a driving fluid.

  In the turbine 200, the electric power is obtained by driving the generator 210 by converting the work generated when the high-temperature and high-pressure combustion gas 191 adiabatically expands into the shaft rotational force.

  The compressor 110 and the generator 210 have a single-shaft structure connected to each other by a single rotor shaft common to the turbine 200.

  However, the structure may be a two-axis structure in which the rotor shaft that connects the compressor 110 and the turbine 200 and the rotor shaft that connects the turbine 200 and the generator 210 are separate axes.

  Further, although shown as one system in the fuel system 180 shown in FIG. 1, the multi-burner having a configuration in which the fuel system 180 is divided into a plurality of systems and is supplied to a plurality of fuel headers provided in the gas turbine combustor. A gas turbine combustor having a structure may be used.

  In general, a gas turbine power generator widely used in a thermal power plant or the like has a structure in which a plurality of gas turbine combustors are radially arranged around a rotor shaft.

  Next, a partial structure of the gas turbine combustor 1 which is an embodiment of the present invention applied to the gas turbine power generator shown in FIG. 1 will be described with reference to FIG.

  FIG. 2A is a partial cross-sectional view in which the peripheral portions of the fuel injection nozzle 10, the mixture injection nozzle 20 and the air hole 30 installed in the gas turbine combustor 1 are enlarged, and FIG. It is an arrow view of the AA direction of (a).

  A fuel header 11 having a plurality of fuel injection nozzles 10 for injecting fuel 40 inside the nozzle outer cylinder 2 inside the gas turbine combustor 1 shown in FIGS. 2 (a) and 2 (b). And an air-fuel mixture header provided with a plurality of air-fuel mixture injection nozzles 20 that are installed on the downstream side of the fuel header 11 and inject the fuel 40 injected from the fuel injection nozzle 10 and the primary air 41 coaxially. 21.

  Further, the air hole plate 31 is provided on the downstream side of the air-fuel mixture header 21 and includes a plurality of air holes 30 and is disposed facing the combustion chamber 190, and the air hole plate 31 is injected from the air holes 30. And a cylindrical liner 160 that forms a combustion chamber 190 for burning an air-fuel mixture of fuel and air.

  The central axes of the fuel injection nozzle 10, the air-fuel mixture injection nozzle 20, and the air hole 30 are arranged so as to be positioned on the same axis.

  The fuel 40 is injected from the fuel injection nozzles 10 installed in the fuel header 11 as fuel jets in the same direction toward the center of the holes of the mixture injection nozzles 20 installed in the same manner.

  The jets of the fuel 40 respectively injected from the plurality of fuel injection nozzles 10, together with the primary air 41 supplied to the holes of the mixture injection nozzle 20 so as to wrap around the fuel 40, are holes in the mixture injection nozzle 20. Is formed into a coaxial jet of fuel and air, so that a coaxial jet mixture in which fuel and air are mixed is formed inside the hole of the mixture injection nozzle 20.

  An air-fuel mixture of a coaxial jet formed by mixing fuel and air formed inside the hole of the air-fuel mixture injection nozzle 20 is ejected downstream from the hole of the air-fuel mixture injection nozzle 20.

  When the air-fuel mixture is ejected from the outlet of the air-fuel mixture injection nozzle 20 to the downstream side, the flow of the air-fuel mixture in the coaxial jet rapidly expands, so that the turbulence occurs in the air-fuel mixture, and the fuel 40, the primary air 41, Is promoted.

  Further, the mixture of the fuel 40 and the primary air 41 ejected toward the center of the air hole 30 provided in the air hole plate 31 together with the secondary air 42 supplied so as to wrap the mixture from the surroundings. It is introduced into the air hole 30 to form a coaxial jet of the air-fuel mixture and the secondary air 42.

  Within the air hole 30, the air-fuel mixture of the fuel 40 and the primary air 41 is further mixed by the secondary air 42 to become a lean air-fuel mixture.

  The further mixed lean air-fuel mixture is ejected from the outlet of the air hole 30 into the combustion chamber 190 on the downstream side.

  When the lean air-fuel mixture is ejected into the combustion chamber 190, the flow rapidly expands, so that the flow of the lean air-fuel mixture is disturbed.

  As a result, the mixture of the lean air-fuel mixture and the secondary air 42 is further promoted to form a lean and uniform air-fuel mixture.

  The lean and uniform premixed gas of the coaxial jet introduced into the combustion chamber 190 burns in the combustion chamber 190.

  Since this lean and uniform premixed gas suppresses the generation of a region where the fuel concentration is locally high, it is excellent in the combustion chamber 190 even when it is burned without generating a local high temperature field. A uniform high temperature and pressure combustion gas 191 can be generated by forming a flame.

  FIG. 8 shows the result of measuring the degree of mixing of the coaxial jet mixture in the combustion apparatus of this example by a visualization test.

  In the visualization test of the coaxial jet mixing degree in the combustion apparatus shown in FIG. 8, the axial center of the fuel injection nozzle 10 that injects the fuel 40 and the central axis of the air hole 30 through which air flows are arranged coaxially. Thus, the coaxial jet flow is a combination of the case where the jet of the fuel 40 is supplied from the fuel injection nozzle 10 to the air hole 30 to form a mixture of the coaxial jet in which the fuel and air are mixed inside the air hole 30. It is a test result of the fuel concentration of an air-fuel mixture.

  In FIG. 8, the numerical value on the horizontal axis of the graph is obtained by dividing the distance from the air hole inlet of the air hole 30 toward the downstream side of the air hole outlet (hereinafter referred to as X) by the inner diameter of the air hole 30 (hereinafter referred to as φD). The vertical axis represents the standardized maximum fuel concentration value indicating the degree of mixture of the mixture of fuel and air in each cross section of the air hole 30 from the air hole inlet to the air hole outlet. Is.

  Here, the maximum fuel concentration value shown in FIG. 8 indicates that the lower the value on the vertical axis, the better the fuel and air are mixed.

  From the result of the visualization test of the coaxial jet mixing degree shown in FIG. 8, the mixing of the fuel and the air starts near X / φD = 0.5 immediately after the fuel and the air are introduced into the air hole, and the air hole outlet The mixing of fuel and air is promoted toward

  In other words, in the case shown in FIG. 8, the jet of the fuel 40 injected from the fuel injection nozzle 10 is supplied to the hole of the air hole 30 together with the air supplied so as to wrap around the fuel 40 and the fuel. Since a coaxial jet with air is formed, an air-fuel mixture of a coaxial jet in which fuel and air are mixed is formed inside the air hole 30.

  Further, the air-fuel mixture of the coaxial jet is ejected to the downstream side from the air hole outlet of the air hole 30, and when the air-fuel mixture is ejected, the flow of the air-fuel mixture of the coaxial jet rapidly expands downstream of the air hole outlet. Disturbance occurs in the flow of the fuel, and the mixing of fuel and air is further promoted.

  That is, by arranging the fuel injection nozzle 10 and the axial center of the air hole 30 coaxially to form a coaxial jet, the fuel jet has the effect of promoting the mixing of the coaxial jet of fuel and air inside the air hole. Two effects of the mixing promotion effect by the rapid expansion of the flow of the air-fuel mixture when the air-fuel mixture is ejected from the air hole outlet are obtained.

  The result of the visualization test of the mixing degree of the coaxial jet mixture shown in FIG. 8 is extrapolated, and the fuel based on the structure of the gas turbine combustor which is the combustion apparatus according to the embodiment of the present invention shown in FIG. The result of predicting the degree of air mixing is shown in FIG.

  9 is a graph showing the mixing degree of the coaxial jet mixture predicted based on the graph of the visualization test of the mixing degree of the coaxial jet mixture in FIG.

  The numerical value on the horizontal axis of the graph is the distance X from the air hole inlet of the air-fuel mixture injection nozzle 20 toward the downstream direction of the air hole outlet, and the horizontal axis on the left side of the graph represents X as the inner diameter (φDn) of the air-fuel mixture injection nozzle 20 The horizontal axis on the right side of the graph is a value obtained by dividing X by the inner diameter (φD) of the air hole 30 of the air hole plate 31.

  As shown in the prediction result of the degree of mixing of fuel and air shown in FIG. 9, in the structure of the gas turbine combustor according to the embodiment of the present invention shown in FIG. The jet of the injected fuel 40 is supplied to the hole of the air-fuel mixture injection nozzle 20 together with the primary air 41 supplied so as to wrap around the periphery of the fuel 40, and a coaxial jet of the fuel 40 and the primary air 41 is formed. As a result, an air-fuel mixture of a coaxial jet in which the fuel 40 and the primary air 41 are mixed is formed inside the hole of the air-fuel mixture injection nozzle 20.

  Furthermore, the jet of the air-fuel mixture ejected from the air-fuel mixture injection nozzle 20 and the secondary air 42 supplied so as to wrap around the air-fuel mixture are air holes installed on the downstream side of the air-fuel mixture injection nozzle 20. Since it is supplied to the hole of the air hole 30 of the plate 31 to form a coaxial jet of the air-fuel mixture and the secondary air 42, the coaxial air-fuel mixture and the secondary air 42 are mixed inside the hole of the air hole 30. A jet mixture is formed.

  When the jet of air from the outlet of the air hole 30 is jetted into the combustion chamber 190 on the downstream side, the flow of the air-fuel mixture of the coaxial jet mixed with the secondary air 42 rapidly expands, so that the flow of the air-fuel mixture is disturbed. In addition, the mixing of fuel and air is further promoted.

  That is, the fuel injection nozzle 10, the mixture injection nozzle 20, and the axial centers of the air holes 30 are arranged coaxially to form a coaxial jet of fuel, primary air, and secondary air. The jet is a mixture-promoting effect of the coaxial jet of fuel and air inside the air-fuel mixture injection nozzle 20 and the air hole 30, and the air-fuel mixture from the outlet of the air-fuel mixture injection nozzle 20 and the air hole 30. As a result, two effects of the mixing promotion effect due to the rapid expansion of the flow of the air-fuel mixture when jetted to the downstream side are obtained.

  Then, the fuel 40 injected from the fuel injection nozzle 10 is mixed in the primary air 41 and the mixture injection nozzle 20, and the mixing promotion effect when the fuel 40 is injected from the outlet of the mixture injection nozzle 20 as the mixture is mixed. Combustion on the downstream side of the air hole 30 due to the mixing promotion effect when the gas is mixed inside the air hole 30 installed on the downstream side of the air-fuel mixture injection nozzle 20 and ejected as an air-fuel mixture from the outlet of the air hole 30 It is considered that the fuel and air are mixed very well inside the chamber 190 to form an air-fuel mixture having a uniform concentration.

  As a result of obtaining the above-described two mixing promotion effects, in the gas turbine combustor according to the embodiment of the present invention shown in FIG. It becomes possible.

  And it can suppress that the high temperature field where a flame temperature rises locally generate | occur | produces in the combustion gas produced | generated when this air-fuel mixture of a uniform density | concentration burns, and NOx discharge amount discharged | emitted from a gas turbine combustor A significant reduction can be achieved.

  In the gas turbine combustor according to the embodiment of the present invention shown in FIG. 2, the air hole plate 31 has a plurality of air holes 30 arranged in three rows in an annular shape as shown in FIG. 2 (b). Is formed.

  Since the air-fuel mixture ejected from the air holes 30 is well mixed in a uniform concentration as described above, the combustion chamber 190 is also burned when the air-fuel mixture ejected from the air holes 30 to the combustion chamber 190 is combusted. It can suppress that a local flame temperature rise arises inside.

  Therefore, the number of the air holes 30 formed in the air hole plate 31 can be set to the optimum air hole arrangement and quantity according to the flame holding form.

  In addition, the fuel injection nozzle 10, the mixture injection nozzle 20, and the air hole 30 installed in the gas turbine combustor gradually increase the amount of fuel and air fluid flowing inside as the load of the gas turbine increases. However, in order to prevent an increase in pressure loss due to an increase in the flow velocity in the pipe, it is desirable to form the holes so that the inner diameters of the nozzle and air holes gradually increase from the inlet side to the outlet side.

  Further, from the result of the coaxial jet mixing degree visualization test shown in FIG. 8, the mixing degree of fuel and air is X / φD = 4, that is, the mixing degree is around the distance that is twice the air hole diameter from the air hole outlet. The value is asymptotic to a constant value.

  Therefore, the axial gap between the outlet of the mixture injection nozzle 20 and the inlet of the air hole 30 in the gas turbine combustor of the embodiment of the present invention shown in FIG. 9 is relative to the inner diameter Dn of the mixture injection nozzle 20. It is desirable to set the interval at least twice as long.

  According to the above-described embodiment of the present invention, in the coaxial jet combustion system in which fuel and air are supplied to the combustion chamber as a coaxial jet and burned, the fuel and air to be jetted coaxially are mixed uniformly. A combustion apparatus and a gas turbine combustor that can increase the degree of mixing of both and greatly reduce NOx emissions can be realized.

  Next, a partial structure of a gas turbine combustor according to another embodiment of the present invention will be described with reference to FIG.

  3A is a partial cross-sectional view in which the peripheral portions of the fuel injection nozzle 10, the first air hole 22, and the air hole 30 installed in the gas turbine combustor 1 are enlarged as in FIG. FIG. 3B is an arrow view in the BB direction of FIG.

  The configuration of the gas turbine combustor 1 of this embodiment shown in FIG. 3 is the same as the configuration of the gas turbine combustor 1 of the previous embodiment shown in FIGS. In the example, the description of the configuration common to both is omitted, and only the configuration that is different will be described below.

  In the gas turbine combustor 1 of the present embodiment shown in FIG. 3, the first air hole 22 is provided in the mixture header 21 in place of the mixture injection nozzle, which is the previous implementation shown in FIG. This is different from the structure of the example gas turbine combustor 1.

  In the gas turbine combustor 1 of this embodiment shown in FIG. 3, the fuel 40 flows from the fuel injection nozzles 10 installed in the fuel header 11 to the first air holes 22 installed in the mixture header 21. It is injected as a fuel jet in the coaxial direction toward the center of the hole.

  The jets of the fuel 40 injected from these fuel injection nozzles 10 are encased in the holes of the first air holes 22 together with the primary air 41 supplied to the holes of the first air holes 22 so as to wrap around the fuel 40. Since it is supplied to form a coaxial jet of fuel and air, an air-fuel mixture of coaxial jet in which fuel and air are mixed is formed inside the hole of the first air hole 22.

  An air-fuel mixture of a coaxial jet formed by mixing fuel and air formed inside the first air hole 22 is ejected downstream from the hole of the first air hole 22. When the air-fuel mixture is ejected from the outlet 22 to the downstream side, the flow of the air-fuel mixture of the coaxial jet rapidly expands, so that the flow of the air-fuel mixture is disturbed, and the mixing of the fuel 40 and the primary air 41 is promoted.

  Further, the air-fuel mixture of the fuel 40 and the primary air 41 ejected toward the center of the air hole 30 serving as the second air hole provided in the air hole plate 31 is supplied so as to wrap the air-fuel mixture from the surroundings. The secondary air 42 and the secondary air 42 are introduced into the air holes 30 to form a coaxial jet of the air-fuel mixture and the secondary air 42. Therefore, the fuel 40 and the primary air are formed in the air holes 30. The air-fuel mixture with 41 is further mixed by the secondary air 42 to become a lean air-fuel mixture.

  Further, the further mixed lean air-fuel mixture is ejected from the outlet of the air hole 30 into the combustion chamber 190 on the downstream side.

  When the air-fuel mixture is ejected into the combustion chamber 190, the flow rapidly expands, so that the flow of the lean air-fuel mixture is disturbed, and the mixing of the air-fuel mixture and the secondary air 42 is further promoted. A lean and uniform mixture is formed.

  The lean and uniform premixed gas of the coaxial jet introduced into the combustion chamber 190 burns in the combustion chamber 190.

  In this lean and uniform premixed gas, the generation of a region where the fuel concentration is locally high is suppressed. Therefore, even when the premixed gas is burned, it is burned without generating a local high temperature field. A good flame can be formed in the chamber 190 and a uniform high-temperature and high-pressure combustion gas 191 can be generated.

  The mixing form of the fuel 40 and the primary air 41 and the secondary air 42 in the gas turbine combustor 1 of this embodiment shown in FIG. 3 is substantially the same as that of the gas turbine combustor 1 of the previous embodiment shown in FIG. is there.

  In the gas turbine combustor 1 of the embodiment of FIG. 3, the structure of the gas turbine combustor is simplified by providing the first air hole 22 instead of the mixture injection nozzle 20, thereby reducing the manufacturing cost. It becomes possible.

  Specifically, in the case of the gas turbine combustor 1 of the present embodiment shown in FIG. 3, a plurality of first axes coaxial with the fuel injection nozzle 10 are simply formed by drilling the mixture header 21 with a drill or the like. The air hole 22 can be easily provided.

  Even in the case of the gas turbine combustor 1 of the present embodiment shown in FIG. 3, the air-fuel mixture ejected from the air holes 30 is well mixed in a uniform concentration as described above. Even when the air-fuel mixture jetted into the chamber 190 is combusted, it is possible to suppress a local increase in flame temperature in the combustion chamber 190.

  Therefore, it is not necessary to install a large number of air holes 30 formed in the air hole plate 31, and an optimum air hole arrangement and quantity corresponding to the flame holding form can be obtained.

  Further, the fuel injection nozzle 10, the first air hole 22, and the air hole 30 serving as the second air hole installed in the gas turbine combustor according to the present embodiment include fuel flowing in the interior in response to an increase in the load of the gas turbine, and The amount of air fluid gradually increases.

  In order to prevent an increase in pressure loss due to an increase in flow velocity in the pipe, it is desirable to form the holes so that the inner diameters of the nozzle and air holes gradually increase from the inlet side to the outlet side.

  Further, from the result of the coaxial jet mixing degree visualization test shown in FIG. 8, the mixing degree of fuel and air is X / φD = 4, that is, the mixing degree is around the distance that is twice the air hole diameter from the air hole outlet. The value is asymptotic to a constant value.

  Therefore, the axial gap between the outlet of the first air hole 22 and the inlet of the air hole 30 of the second air hole in the gas turbine combustor of the present embodiment shown in FIG. It is desirable to set the interval at least twice as long as Dn.

  According to the above-described embodiment of the present invention, in the coaxial jet combustion type in which fuel and air are supplied to the combustion chamber as a coaxial jet and burned, the fuel and air to be jetted coaxially are mixed uniformly. A combustion apparatus and a gas turbine combustor that can increase the degree of mixing of both and greatly reduce NOx emissions can be realized.

  Next, a partial structure of a gas turbine combustor which is still another embodiment of the present invention will be described with reference to FIG.

  4A is a partial cross-sectional view in which the peripheral portions of the fuel injection nozzle 10, the first air hole 22, and the air hole 30 installed in the gas turbine combustor 1 are enlarged as in FIG. FIG. 4B is an arrow view in the CC direction of FIG.

  The configuration of the gas turbine combustor 1 of the present embodiment shown in FIG. 4 is the same as the configuration of the gas turbine combustor 1 of the previous embodiment shown in FIGS. In the example, the description of the configuration common to both is omitted, and only the configuration that is different will be described below.

  In the gas turbine combustor 1 of this embodiment shown in FIG. 4, a first air hole 22 is provided in the air-fuel mixture header 21 in place of the air-fuel mixture injection nozzle, and further, premixing is performed downstream of the first air hole 22. The difference between the header 23 and the structure of the gas turbine combustor 1 of the previous embodiment shown in FIG. 2 is that the mixture in the premix header 23 is injected through the mixture injection nozzle 20. is doing.

  In the gas turbine combustor 1 of the present embodiment, the fuel injection nozzle 10, the hole of the first air hole 22, the air-fuel mixture injection nozzle 20, and the air hole 30 serving as the second air hole provided in the air hole plate 31. Are arranged so as to be coaxial with each other.

  In the gas turbine combustor 1 of the present embodiment shown in FIG. 4, the fuel 40 flows from the fuel injection nozzles 10 installed in the fuel header 11 to the first air holes 22 installed in the mixture header 21. It is injected as a fuel jet in the coaxial direction toward the center of the hole.

  The jets of the fuel 40 injected from these fuel injection nozzles 10 are encased in the holes of the first air holes 22 together with the primary air 41 supplied to the holes of the first air holes 22 so as to wrap around the fuel 40. Since it is supplied to form a coaxial jet of fuel and air, an air-fuel mixture of coaxial jet in which fuel and air are mixed is formed inside the hole of the first air hole 22.

  An air-fuel mixture of a coaxial jet formed by mixing fuel and air formed inside the first air hole 22 is ejected downstream from the hole of the first air hole 22.

  Since the premixing header 23 is provided on the downstream side of the first air hole 22, the flow of the mixture of the coaxial jets jetted into the premixing header 23 from the outlet of the first air hole 22 rapidly expands. Thus, the flow of the air-fuel mixture is disturbed, and the mixing of the fuel 40 and the primary air 41 is promoted.

  In addition, by providing the premixing header 23 on the downstream side of the first air hole 22, the air-fuel mixture immediately after being ejected from the first air hole 22 is pre-mixed without being surrounded by the secondary air 42. Since the flow of the air-fuel mixture is greatly expanded in the header 23, the mixing of the fuel 40 and the primary air 41 forming the air-fuel mixture is further promoted.

  Further, since the fuel 40 and the primary air 41 are retained in the premixing header 23, the mixing time becomes longer, and it is possible to further promote the mixing of the fuel 40 and the primary air 41 forming the mixture. Become.

  Furthermore, the mixture of the fuel 40 and the primary air 41 ejected from the premixing header 23 through the mixture injection nozzle 20 toward the center of the air hole 30 serving as the second air hole provided in the air hole plate 31 is: The air-fuel mixture is introduced into the air holes 30 as the second air holes together with the secondary air 42 supplied so as to wrap around the air-fuel mixture to form a coaxial jet of the air-fuel mixture and the secondary air 42.

  In the air hole 30, the air-fuel mixture of the fuel 40 and the primary air 41 is further mixed by the secondary air 42 to become a lean air-fuel mixture.

  The further mixed lean air-fuel mixture is ejected from the outlet of the air hole 30 into the combustion chamber 190 on the downstream side.

  When the air-fuel mixture is ejected into the combustion chamber 190, the flow rapidly expands, so that the flow of the lean air-fuel mixture is disturbed, and the mixing of the lean air-fuel mixture and the secondary air 42 is further promoted. A lean and uniform mixture is formed.

  The lean and uniform premixed gas of the coaxial jet introduced into the combustion chamber 190 burns in the combustion chamber 190.

  In this lean and uniform premixed gas, the generation of a region where the fuel concentration is locally high is suppressed. Therefore, even when the premixed gas is burned, the combustion chamber does not generate a local high temperature field. A good flame can be formed in 190, and uniform high-temperature and high-pressure combustion gas 191 can be generated.

  Even in the case of the gas turbine combustor 1 of this embodiment shown in FIG. 4, the air-fuel mixture ejected from the air holes 30 is well mixed in a uniform concentration as described above. Even when the air-fuel mixture jetted into the chamber 190 is combusted, it is possible to suppress a local increase in flame temperature in the combustion chamber 190.

  Therefore, it is not necessary to install a large number of air holes 30 formed in the air hole plate 31, and an optimum air hole arrangement and quantity corresponding to the flame holding form can be obtained.

  Further, the fuel injection nozzle 10, the first air hole 22, the air-fuel mixture injection nozzle 20, and the air hole 30 serving as the second air hole installed in the gas turbine combustor of the present embodiment correspond to the increase in the load of the gas turbine. As a result, the amount of fuel and air flowing through the inside gradually increases.

  In order to prevent an increase in pressure loss due to an increase in flow velocity in the pipe, it is desirable to form the holes so that the inner diameters of the nozzle and air holes gradually increase from the inlet side to the outlet side.

  Further, from the result of the coaxial jet mixing degree visualization test shown in FIG. 8, the mixing degree of fuel and air is X / φD = 4, that is, the mixing degree is around the distance that is twice the air hole diameter from the air hole outlet. The value is asymptotic to a constant value.

  Therefore, the axial gap between the outlet of the mixture injection nozzle 20 and the inlet of the air hole 30 serving as the second air hole in the gas turbine combustor of this embodiment shown in FIG. It is desirable to set the interval at least twice as long as the inner diameter Dn.

  According to the above-described embodiment of the present invention, in the coaxial jet combustion system in which fuel and air are supplied to the combustion chamber as a coaxial jet and burned, the fuel and air to be jetted coaxially are mixed uniformly. A combustion apparatus and a gas turbine combustor that can increase the degree of mixing of both and greatly reduce NOx emissions can be realized.

  Next, the partial structure of the gas turbine combustor which is another Example of this invention is demonstrated using FIG.

  FIG. 5A is an enlarged partial cross-sectional view of the peripheral portion of the fuel nozzle 10, the first air hole 22, and the air hole 30 installed in the gas turbine combustor 1 as in FIG. ) Is an arrow view in the DD direction of FIG.

  The configuration of the gas turbine combustor 1 of this embodiment shown in FIG. 5 is the same as the configuration of the gas turbine combustor 1 of the previous embodiment shown in FIG. Description of the common configuration is omitted, and only the different configuration will be described below.

  In the gas turbine combustor 1 of the present embodiment shown in FIG. 5, a premix header 23 is disposed on the downstream side of the first air hole 22 provided in the mixture header 21.

  A plurality of the mixture injection nozzles 20 for injecting the mixture from the premix header 23 are installed on the premix header 23 so that the number of the mixture injection nozzles 20 is larger than the number of the fuel injection nozzles 10. The difference between the structure of the gas turbine combustor 1 of the previous embodiment shown in FIG.

  In the gas turbine combustor 1 of the present embodiment, the central axes of the fuel injection nozzle 10 and the first air hole 22 are arranged so as to be coaxial, and the air-fuel mixture injection nozzle 20 and the air The central axis with the hole of the air hole 30 used as the 2nd air hole provided in the hole plate 31 is arrange | positioned so that it may be located coaxially.

  However, the center axis | shaft of the hole of the said 1st air hole 22 and the air-fuel | gaseous mixture injection nozzle 20 is arrange | positioned so that it may be located on a different axis line.

  The injection state of the fuel 40, primary air 41, secondary air 42, and air-fuel mixture in the gas turbine combustor 1 of this embodiment shown in FIG. 5 is the same as that of the gas turbine combustor 1 of this embodiment shown in FIG. Since it is the same as that of the case, description of those injection situations is omitted here.

  By the way, in the gas turbine combustor 1 of the previous embodiment shown in FIG. 4, since the fuel injection nozzle 10, the premixing header 23, and the second air hole 30 are respectively paired, the numbers thereof are equal. ing.

  From the viewpoint of promoting the mixing of the fuel 40 and the primary air 41 in the premixed header 23 by the expansion of the mixture, the size of the premix header 23 needs to be increased so that the mixture can be sufficiently expanded. Naturally, as shown in FIG. 4B, the number of air holes 30 serving as the second air holes is reduced.

  For this reason, when the mixture of the air-fuel mixture injected from the second air holes 30 into the combustion chamber 190 is made uniform over the entire area of the combustion chamber 190, the number of air holes 30 serving as the second air holes is reduced. There can be some constraints.

  For this reason, there is a possibility that a spatial bias occurs in the flame generated by burning the air-fuel mixture injected from the air hole 30 in the combustion chamber 190.

  Therefore, the gas turbine combustor 1 of the present embodiment shown in FIG. 5 has a configuration in which a plurality of mixture injection nozzles 20 are arranged in one premixing header 23 as described above.

  Then, while maintaining the effect of promoting the mixing by the expanded flow of the mixture of the fuel 40 and the primary air 41 in the premixing header 23, the air holes 30 serving as the second air holes arranged with increasing numbers are provided. The air-fuel mixture and the secondary air 42 are mixed, and the mixed air-fuel mixture is injected from the air hole 30 into the combustion chamber 190.

  Therefore, it is possible to suppress the occurrence of a spatial bias in the flame generated by burning the air-fuel mixture in the combustion chamber 190.

  In addition, since the number of the fuel injection nozzles 10 and the first air holes 22 can be reduced as compared with the air holes 30 serving as the second air holes, the manufacturing cost of the combustion apparatus can be reduced. Is possible.

  According to the above-described embodiment of the present invention, in the coaxial jet combustion system in which fuel and air are supplied to the combustion chamber as a coaxial jet and burned, the fuel and air to be jetted coaxially are mixed uniformly. A combustion apparatus and a gas turbine combustor that can increase the degree of mixing of both and greatly reduce NOx emissions can be realized.

  Next, a partial structure of a gas turbine combustor which is still another embodiment of the present invention will be described with reference to FIG.

  FIG. 6A is a partial cross-sectional view in which the peripheral portions of the fuel nozzle 10 and the first air holes 22 and the air holes 30 installed in the gas turbine combustor 1 are enlarged as in FIG. ) Is an arrow view in the EE direction of FIG.

  The configuration of the gas turbine combustor 1 of the present embodiment shown in FIG. 6 is the same as the configuration of the gas turbine combustor 1 of the previous embodiment shown in FIG. Description of the common configuration is omitted, and only the different configuration will be described below.

  In the gas turbine combustor 1 according to the present embodiment shown in FIG. 6, the mixture header 21 on the downstream side of the fuel injection nozzle 10 is first connected to the number of the fuel injection nozzles 10 installed in the fuel header 11. Air holes 22 are arranged respectively.

  A premix header 23 is disposed on the mixture header 21 on the downstream side of the first air hole 22.

  The number of the premixing headers 23 is set such that one premixing header 23 can be arranged for each of the plurality of first air holes 22, for example, for every two, so that the mixture injection is more than the number of the fuel injection nozzles 10. The point that the number of nozzles 20 is small is different from the structure of the gas turbine combustor 1 of the previous embodiment shown in FIG.

  In the gas turbine combustor 1 of the present embodiment, the central axes of the fuel injection nozzle 10 and the first air hole 22 are arranged so as to be coaxial, and the air-fuel mixture injection nozzle 20 and the air The central axis with the hole of the air hole 30 used as the 2nd air hole provided in the hole plate 31 is arrange | positioned so that it may be located coaxially.

  However, the center axis | shaft of the hole of the said 1st air hole 22 and the air-fuel | gaseous mixture injection nozzle 20 is arrange | positioned so that it may be located on a different axis line.

  The injection state of the fuel 40, primary air 41, secondary air 42, and air-fuel mixture in the gas turbine combustor 1 of this embodiment shown in FIG. 6 is the same as that of the gas turbine combustor 1 of this embodiment shown in FIG. Since it is the same as that of the case, description of those injection situations is omitted here.

  In the gas turbine combustor 1 of the present embodiment shown in FIG. 6, as described above, a plurality of first air holes 22 are arranged in one premixing header 23, and the fuel 40 and the premixing header 23 are arranged. The air-fuel mixture of the primary air 41 is introduced, and the number of the air-fuel mixture injection nozzles 20 for injecting the air-fuel mixture from the premixing header 23 is less than the number of the fuel injection nozzles 10.

  Therefore, the gas turbine combustor 1 of the present embodiment shown in FIG. 6 has a configuration in which one mixture injection nozzle 20 is arranged in one premix header 23 as described above.

  While maintaining the effect of promoting the mixing by the expanded flow of the mixture of the fuel 40 and the primary air 41 in the premixing header 23, the mixture and the secondary air 42 are supplied to the air holes 30 serving as the second air holes. Since the mixed air-fuel mixture is injected into the combustion chamber 190 from the air hole 30, a spatial bias occurs in the flame generated by the combustion of the air-fuel mixture in the combustion chamber 190. Can be suppressed.

  As described above, in the gas turbine combustor 1 of this embodiment shown in FIG. 6, the capacity of the premixing header 23 can be increased, and the arrangement of the mixture injection nozzles 20 provided in the downstream portion of the premixing header 23 is arranged. A large degree of freedom can be taken.

  From the viewpoint of flame holding, the number and positions of the air holes 30 serving as the second air holes can be optimally arranged to improve the fuel stability.

  Moreover, since the number of the air-fuel mixture injection nozzles 20 and the air holes 30 serving as the second air holes can be reduced, it is possible to reduce the manufacturing cost of the gas turbine combustor.

  According to the above-described embodiment of the present invention, in the coaxial jet combustion system in which fuel and air are supplied to the combustion chamber as a coaxial jet and burned, the fuel and air to be jetted coaxially are mixed uniformly. A combustion apparatus and a gas turbine combustor that can increase the degree of mixing of both and greatly reduce NOx emissions can be realized.

  Next, a partial structure of a gas turbine combustor according to another embodiment of the present invention will be described with reference to FIG.

  FIG. 7A is a partial cross-sectional view showing a peripheral portion of the fuel nozzle 10, the mixture injection nozzle 20 and the air hole 30 installed in the gas turbine combustor 1, and FIG. It is an arrow view of the EE direction of).

  The configuration of the gas turbine combustor 1 of this embodiment shown in FIG. 7 includes a fuel header 11 having a fuel injection nozzle 10 and an air-fuel mixture injection nozzle 20 in the gas turbine combustor 1 of the embodiment shown in FIG. As shown in FIG. 7B, a plurality of burners having a structure having an air-fuel mixture header 21 are combined as shown in FIG. 7B, one at the center and six at the outer peripheral side. Are arranged on the upstream side of the air hole plate 31 having the air holes 30, and a common air hole plate 31 having the air holes 30 or the second air holes is provided on the downstream side of these modules. Constitutes one gas turbine combustor 1.

  A fuel system 180 having a fuel flow rate adjusting valve 182 for supplying fuel to the plurality of burners is also branched according to the number of the burners, and the number of burners for burning fuel according to the load of the gas turbine. By controlling the above, it is possible to continue the combustion of the gas turbine combustor stably from the start condition of the gas turbine where the fuel flow rate greatly changes to the 100% load condition.

  Further, by adopting a burner in which the number of fuel nozzles installed in the burner is increased or decreased, it is possible to provide a gas turbine combustor having a different capacity per can of the gas turbine combustor relatively easily. .

  Further, the gas turbine combustor 1 of the present embodiment has a structure adopting the burner structure of the module shown in FIG. 2, but in addition to this, the modules of the burner structures shown in FIGS. 3 to 6 are used. Can be adopted.

  According to the above-described embodiment of the present invention, in the coaxial jet combustion system in which fuel and air are supplied to the combustion chamber as a coaxial jet and burned, the fuel and air to be jetted coaxially are mixed uniformly. A combustion apparatus and a gas turbine combustor that can increase the degree of mixing of both and greatly reduce NOx emissions can be realized.

  The present invention can be applied not only to a gas turbine combustor but also to combust gas fuel such as methane, such as a fuel reforming combustor, a boiler combustor, a hot air heater and an incinerator mounted on a fuel cell. It can also be applied to devices.

BRIEF DESCRIPTION OF THE DRAWINGS Schematic which shows the structure of the gas turbine power generator to which the gas turbine combustor which is a combustion apparatus of one Example of this invention was applied. The fragmentary sectional view which shows the detailed structure of the gas turbine combustor which is a combustion apparatus of one Example of this invention. The fragmentary sectional view which shows the detailed structure of the gas turbine combustor which is a combustion apparatus of the other Example of this invention. The fragmentary sectional view which shows the detailed structure of the gas turbine combustor which is a combustion apparatus of the further another Example of this invention. The fragmentary sectional view which shows the detailed structure of the gas turbine combustor which is a combustion apparatus of another Example of this invention. The fragmentary sectional view which shows the detailed structure of the gas turbine combustor which is a combustion apparatus of another Example of this invention. The fragmentary sectional view which shows the detailed structure of the gas turbine combustor which is a combustion apparatus of one Example of this invention. FIG. 4 is a fuel concentration measurement diagram showing the results of a visualization test of the degree of mixing of fuel and air in the combustion apparatus according to the embodiment of the present invention. The figure which shows the result of having estimated the mixing degree of the fuel and air in the combustion apparatus of the Example of this invention shown in FIG.

Explanation of symbols

  10: Fuel injection nozzle, 11: Fuel header, 20: Mixture injection nozzle, 22: First air hole, 23: Premix header, 30: (Second) air hole, 31: Air hole plate, 50: Partition wall, 110: air compressor, 120: high pressure air flow, 130: diffuser, 140: passenger compartment, 150: tail cylinder, 151: tail cylinder flow sleeve, 160: liner, 161: outer cylinder, 180: fuel system, 181: fuel Pump, 182: Fuel flow control valve, 190: Combustion chamber, 191: Combustion gas flow, 200: Turbine, 210: Generator.

Claims (9)

A plurality of fuel injection nozzles for injecting fuel; a plurality of mixture injection nozzles disposed downstream of the fuel injection nozzle for discharging a first air-fuel mixture in which the fuel and primary air are mixed; and the air-fuel mixture injection An air hole plate disposed on the downstream side of the nozzle and provided with a plurality of air holes for ejecting a second air-fuel mixture in which the first air-fuel mixture and secondary air are mixed, and air holes provided in the air hole plate A combustion chamber for combusting a fuel / air mixture, and the fuel injection nozzle is arranged such that its central axis is coaxial with the central axis of the fuel injection nozzle. An air hole provided in the air hole plate has a central axis coaxial with the central axis of the air-fuel mixture injection nozzle. be placed above,該混Said first air-fuel mixture injected from the gas injection nozzle, and the nozzle outer cylinder was installed mixture header having the mixture injection nozzle on the inside, flow path formed between the air-fuel mixture header The air mixture is rapidly expanded, and the air around the first air- fuel mixture is introduced into the air holes of the air hole plate so as to be surrounded by secondary air, and the second air-fuel mixture is ejected from the air holes into the combustion chamber. A combustion apparatus configured to burn. An air-fuel mixture header provided with a plurality of fuel injection nozzles for injecting fuel, and a plurality of first air holes arranged downstream of the fuel injection nozzle and for injecting a first air-fuel mixture in which the fuel and primary air are mixed And a plurality of second air holes that are arranged downstream of the first air holes provided in the air-fuel mixture header and eject a second air-fuel mixture in which the first air-fuel mixture and secondary air are mixed. An air hole plate, and a combustion chamber disposed on the downstream side of the second air hole provided in the air hole plate and combusting a mixture of fuel and air, and the first air hole provided in the air- fuel mixture header includes: its central axis is arranged on the central axis coaxial of the fuel injection nozzle, surrounding the jet of fuel ejected from the fuel injection nozzle so as to wrap around the primary air to the first air hole of the air-fuel mixture header It is introduced, the first to be ejected from the first air holes The Aiki, and nozzle outer cylinder mixture headers provided with said first air hole on the inside is installed, rapid growth is in flow is formed passage between the gas mixture header, to the air hole plate The second air hole provided is arranged so that its central axis is coaxial with the central axis of the first air hole so as to wrap around the first air-fuel mixture ejected from the first air hole with secondary air. The combustion apparatus is configured to be introduced into the second air hole of the air hole plate and to inject and burn the second air-fuel mixture from the second air hole into the combustion chamber. A plurality of fuel injection nozzles for injecting fuel, a plurality of first air holes arranged downstream of the fuel injection nozzle and into which the fuel and primary air flow, and the fuel on the downstream side of the first air holes A mixture header provided with a premix header that forms a chamber in which primary air is mixed to form a first mixture, and the first mixture header formed in the mixture header from the first An air-fuel mixture injection nozzle for injecting the air-fuel mixture, and a plurality of second airs arranged on the downstream side of the air-fuel mixture injection nozzle to eject a second air-fuel mixture in which the first air-fuel mixture and secondary air are mixed An air hole plate provided with holes, and a combustion chamber disposed on the downstream side of the air holes provided in the air hole plate and combusting a mixture of fuel and air, the first air hole having a central axis The fuel injection nozzle is arranged coaxially with the central axis of the fuel injection nozzle. Around the jet of fuel ejected by the enveloping the primary air is introduced into the first air holes of the air-fuel mixture headers from the further fuel flowing down into the pre-mix header via the first air hole A mixture of primary air is rapidly expanded in the premixing header to form a first mixture and ejected from the mixture injection nozzle, and the first mixture is injected inside the mixture injection nozzle. a nozzle outer cylinder the air-fuel mixture header was installed with a rapid expansion is in flow is formed passage between the gas mixture header, a second air hole provided in the air hole plate the mixture is its center axis Arranged coaxially with the central axis of the air injection nozzle and introduced into the second air hole of the air hole plate so as to wrap around the first air mixture ejected from the air mixture injection nozzle with secondary air From the second air hole to the combustion chamber Combustion apparatus characterized by being configured to burn by ejecting a second gas mixture.   4. The combustion apparatus according to claim 3, wherein a plurality of air-fuel mixture injection nozzles for ejecting the first air-fuel mixture from the pre-mixing header are arranged with respect to the pre-mixing header, and the number of the fuel injection nozzles is larger than the number of the fuel injection nozzles. A combustion apparatus characterized in that a large number of mixture injection nozzles are arranged.   4. The combustion apparatus according to claim 3, wherein a plurality of the first air holes through which fuel and primary air flow into the premixing header are disposed with respect to the premixing header, and the number of the fuel injection nozzles is greater than the number of the fuel injection nozzles. A combustion apparatus characterized in that a small number of mixture injection nozzles are arranged.   The combustion apparatus according to any one of claims 3 to 5, wherein the fuel apparatus is used in a gas turbine combustor.   6. The combustion apparatus according to claim 1, wherein an assembly having a structure from the fuel injection nozzle to the air-fuel mixture injection nozzle or the first air hole is formed as one module, and these modules are combined. A combustion apparatus comprising a gas turbine combustor comprising a plurality of air holes or a common air hole plate having air holes or second air holes on the downstream side of these modules. A plurality of fuel injection nozzles for injecting fuel, and a first air-fuel mixture that is disposed downstream of the fuel injection nozzle and mixed with the primary air that is a part of high-pressure air compressed by the compressor A plurality of air-fuel mixture injection nozzles, and a second air that is disposed downstream of the air-fuel mixture injection nozzles and mixed with secondary air that is part of the high-pressure air compressed by the compressor An air hole plate provided with a plurality of air holes for jetting the air-fuel mixture, and a combustion chamber disposed downstream of the air holes provided in the air hole plate and combusting the fuel-air mixture. The air-fuel mixture injection nozzle has a central axis coaxially arranged with the central axis of the fuel injection nozzle, and encloses the periphery of the fuel jet ejected from the fuel injection nozzle with primary air. Let the air hole plate Only air holes arranged on its central axis the mixture center axis of the injection nozzle and coaxial, the first air-fuel mixture to be ejected from the mixture injection nozzle, the mixture injection nozzle on the inside The air that is rapidly expanded in a flow path formed between the nozzle outer cylinder provided with the air-fuel mixture header and the air-fuel mixture header so as to wrap around the first air- fuel mixture with secondary air. A gas turbine combustor configured to be introduced into an air hole of a hole plate and to inject and burn the second air-fuel mixture from the air hole into a combustion chamber. A plurality of fuel injection nozzles for injecting fuel, and a first air-fuel mixture that is disposed downstream of the fuel injection nozzle and mixed with the primary air that is a part of high-pressure air compressed by the compressor An air-fuel mixture header provided with a plurality of first air holes, and a high-pressure air that is disposed downstream of the first air holes provided in the air-fuel mixture header and compressed by the first air-fuel mixture and the compressor. An air hole plate provided with a plurality of second air holes for ejecting a second air-fuel mixture mixed with a portion of the secondary air, and disposed downstream of the second air holes provided in the air hole plate. A combustion chamber for burning a mixture of fuel and air, and the first air hole provided in the mixture header has a central axis coaxial with the central axis of the fuel injection nozzle, and the fuel injection nozzle So that the air around the jet of fuel Is introduced into the first air hole and further the first air-fuel mixture to be ejected from the first air holes, the nozzle outer cylinder mixture headers are installed provided with the first air holes inside thereof, The second air hole provided in the air hole plate is rapidly enlarged in a flow path formed between the air-fuel mixture header and the central axis thereof is arranged coaxially with the central axis of the first air hole. The periphery of the first air-fuel mixture ejected from the first air hole is introduced into the second air hole of the air hole plate so as to be wrapped with secondary air, and the second air hole is introduced into the combustion chamber from the second air hole. A gas turbine combustor configured to jet and combust an air-fuel mixture.

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