JP2006189252A - Gas turbine combustor and method for operating gas turbine combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To improve stability of fire in a combustion chamber, low NOx and combustion stability by reducing NOx and promoting mixture of fuel and air, in gas turbine equipment. <P>SOLUTION: This gas turbine equipment is provided with the combustion chamber to which fuel and air are supplied. The gas turbine equipment is characterized by that the fuel and air are formed into a plurality of coaxial jet flows to be supplied to the combustion chamber; and, within a premixing flow passage, an air flow is formed on the outer peripheral side with a fuel flow as a center. <P>COPYRIGHT: (C)2006,JPO&NCIPI

Description

  The present invention relates to a gas turbine combustor and a method for operating a gas turbine combustor.

  In particular, the present invention relates to a low NOx type gas turbine combustor that emits less nitrogen oxides, and JP-A-5-172331 is cited as a prior art.

  In a gas turbine combustor, a diffusion combustion system in which fuel is directly injected into a combustion chamber has been widely employed in order to ensure a large turndown ratio from startup to a rated load condition and to ensure a wide range of combustion stability. There are also premixed combustion systems.

JP-A-5-172331

  In the conventional example, the diffusion combustion method has a problem of high level NOx. In the case of the premixed combustion method, there are problems of combustion stability such as flashback and flame stabilization at start-up and partial load. In actual operation, it is desirable to solve these problems simultaneously.

  An object of the present invention is to provide a gas turbine combustor having low NOx and excellent combustion stability and a method for operating the gas turbine combustor.

  The gas turbine combustor of the present invention includes a combustion chamber to which fuel and air are supplied, and is configured to supply the fuel and the air as a plurality of coaxial jets to the combustion chamber.

  Alternatively, the operating method of the gas turbine combustor according to the present invention is an operating method of a gas turbine combustor provided with a combustion chamber to which fuel and air are supplied, and a plurality of the fuel and air are supplied to the combustion chamber. It is characterized by being supplied as a coaxial jet.

  According to the present invention, it is possible to provide a gas turbine combustor having low NOx and excellent combustion stability and a method for operating the gas turbine combustor.

  First, two types of combustion methods in a gas turbine combustor will be described.

  (1) In the diffusion combustion system, as shown in FIG. 2, fuel is ejected outward near the outlet of the air swirler provided at the head of the combustor so as to intersect the swirling flow of air, and the central axis It aims to stabilize the diffusion flame by the circulation flow that can be made above.

  In FIG. 2, the air 50 sent from the compressor 10 passes between the outer cylinder 2 and the combustor liner 3, and a part of the combustion chamber 1 serves as cooling air 31 of the combustor liner and dilution air 32 that promotes mixing of the combustion gas. And part of the air flows into the combustion chamber 1 through the air swirler 12 as head swirling air 49. The gaseous fuel 16 is injected outward from the diffusion fuel nozzle 13 so as to intersect the swirling air flow, and forms a stable diffusion flame 4 together with the head swirling air 49 and the primary combustion air 33. The generated high-temperature combustion gas enters the turbine 18 and is exhausted with work.

  Although the diffusion combustion system shown here has high combustion stability, a flame is formed in a portion where the fuel and oxygen have a stoichiometric ratio, and the flame temperature becomes a high temperature close to the adiabatic flame temperature. Since the generation rate of nitrogen oxides increases exponentially with an increase in flame temperature, the diffusion concentration of nitrogen oxides is generally high in diffusion combustion, which is undesirable from the viewpoint of preventing air pollution.

  (2) On the other hand, the premixed combustion method is used for reducing NOx. FIG. 3 shows an example in which NOx is reduced by using diffusion combustion with excellent stability at the center and premixed combustion with excellent low NOx performance on the outer peripheral side. In FIG. 3, the air 50 sent from the compressor 10 passes between the outer cylinder 2 and the combustor liner 3, partly as the combustor liner cooling air 31 to the combustion chamber 1, and partly for premixed combustion. The air 48 flows into the premixer 23. The remainder flows into the combustion chamber 1 from the combustion air hole 14 and the cooling air hole 17 through a passage between the premixer flow path and the combustor end plate. The gaseous fuel 16 for diffusion combustion is injected from the diffusion fuel nozzle 13 into the combustion chamber 1 to form a stable diffusion flame 4. The premixed gaseous fuel 21 is ejected from the fuel nozzle 8 into the annular premixer 23 and mixed with air to form the premixed gas 22. The premixed gas 22 flows into the combustion chamber 1 to form a premixed flame 5. The generated high-temperature combustion gas enters the turbine 18 and is exhausted with work.

  However, when such a premixed combustion method is adopted, an unstable element peculiar to premixed combustion is included, such as a so-called flashback phenomenon in which a flame enters the premixer and burns out the structure. .

  In the embodiment of the present invention, the fuel jet and the combustion air flow path are arranged coaxially so that the fuel flow is a coaxial jet that wraps the air flow, and further, the fuel jet and the combustion air flow path are configured to be dispersed in a large number. It is arranged on the combustion chamber wall surface as a perforated coaxial jet. On the other hand, a part or all of the coaxial jets are configured to flow at an appropriate swirl angle around the combustor axis. In addition, the fuel supply system is divided into a plurality of parts, and the fuel is supplied to only a part of the system when the gas turbine is started and partially loaded.

  By making the fuel into a coaxial jet that envelops the airflow, the fuel flows into the combustion chamber and then mixes with the surrounding coaxial airflow before actually in contact with the hot gas and starting combustion. It burns after it becomes a premixed gas mixture. For this reason, low NOx combustion equivalent to lean premixed combustion becomes possible. At this time, the portion corresponding to the premixing tube of the conventional premixing combustor is extremely short, and the fuel concentration is almost zero in the vicinity of the wall surface, so the potential for burnout due to flashback is extremely low.

  In addition, recirculation for stabilizing the flame at the same time while forming a flow form of a coaxial jet by configuring it so that a part or all of the coaxial jet flows with an appropriate swirl angle around the axis of the combustor. A flow can be formed.

  In addition, when starting up gas turbines and under partial load operation, by supplying fuel to only some systems, the fuel is locally over-concentrated, and diffusion combustion that uses oxygen in the surrounding air Combustion stability can be ensured by burning in a form close to.

A first embodiment of the present invention will be described below with reference to FIG. In FIG. 1, the air 50 sent from the compressor 10 passes between the outer cylinder 2 and the combustor liner 3. A part of the air 50 flows into the combustion chamber 1 as the cooling air 31 of the combustor liner 3. The remainder of the air 50 flows into the combustion chamber 1 through the air holes 52 as coaxial air 51.

  The fuel nozzle 55 and the fuel nozzle 56 are disposed so as to be coaxial or close to the same position as the injection hole of the combustion air hole 52, and the fuel 53 and the fuel 54 are substantially the same as the combustion air from the fuel nozzle 55 and the fuel nozzle 56. As a coaxial jet, it is ejected into the combustion chamber 1 to form a stable flame. The generated high-temperature combustion gas enters the turbine 18 to work and is exhausted.

  In the present embodiment, the fuel 53 and the fuel 54 are divided from a fuel supply system 80 having a control valve 80a. That is, here, the fuel supply system 80 is divided into two parts, a first fuel supply system 54b and a second fuel supply system 53b. The first fuel supply system 54b and the second fuel supply system 53b are respectively provided with a control valve 53a and a control valve 54a that can be individually controlled. The control valve 53a and the control valve 54a are configured such that each fuel flow rate is independently controlled by the load of the gas turbine. Here, the control valve 53a can control the flow rate of the fuel nozzle group 56, which is a central fuel nozzle group, and the control valve 54a can control the flow rate of the fuel nozzle 55 group, which is a surrounding fuel nozzle group. In the present embodiment, the fuel nozzle system is divided into a plurality of fuel nozzle groups in the central portion and the surrounding fuel nozzle groups, and a corresponding fuel supply system is provided, and the above-described control device capable of independently controlling the fuel flow rate is provided. .

  Next, details of the nozzle portion will be described with reference to FIG. In this embodiment, the fuel nozzle body is divided into a central fuel nozzle 56 and a surrounding fuel nozzle 55. Corresponding air holes 52 and air holes 57 are provided on the front side of the fuel nozzle 55 and the fuel nozzle 56 in the injection direction. A plurality of the air holes 52 and the air holes 57 are provided in a disk-like member with a small diameter. A plurality of air holes 52 and air holes 57 are provided so as to correspond to the plurality of fuel nozzles 55 and the fuel nozzles 56.

  The air hole 52 and the air hole 57 have a small diameter, but when the fuel injected from the fuel nozzle 55 and the fuel nozzle 56 passes through the air hole 52 and the air hole 57, a fuel jet is generated along with surrounding air. It is desirable to have such a size that an annular flow of air enclosing it is formed. For example, it is desirable that the jet diameter from the fuel nozzle 55 and the fuel nozzle 56 be slightly larger.

  The air hole 52 and the air hole 57 are arranged so as to form a coaxial jet with the fuel nozzle 55 and the fuel nozzle 56, and a large number of coaxial jets in which the fuel jet is wrapped in an air annular flow are formed in the air hole 52 and the air. It ejects from the end face of the hole 57. In other words, the fuel nozzle holes of the fuel nozzle 55 and the fuel nozzle 56 are installed at the same position as the air hole 52 and the air hole 57 in a coaxial or near-coaxial position, and the fuel jet flows toward the vicinity of the inlet center of the air hole 52 and the air hole 57. The annular flow of the jet and fuel jet and the air enclosing it is a coaxial jet.

  Since fuel and air are configured as a large number of small-diameter coaxial jets, these fuel and air can be mixed in a short distance. Therefore, high combustion efficiency can be maintained without uneven distribution of fuel.

  Further, in the configuration of the present embodiment, partial mixing proceeds until the fuel is ejected from the end face of the air hole, and mixing of fuel and air at a shorter distance can be expected. Furthermore, by adjusting the flow path length of the air hole, it is possible to set from a state of hardly mixing in the flow path to a state of almost complete premixing.

  In this embodiment, an appropriate swirl angle is given to the center fuel nozzle 56 and the center air hole 57 so as to swirl around the combustion chamber axis. Thus, by providing the corresponding air hole 57 with a swivel angle that gives a swirl component around the combustion chamber axis, a stable recirculation region by swirl is formed in the mixed airflow including the central fuel, and the flame is stabilized. Can do.

  In this embodiment, a remarkable effect can be expected for various load conditions of the gas turbine. The fuel flow rate is adjusted using the control valve 53a and the control valve 54a shown in FIG. 1 to cope with various load conditions of the gas turbine.

  In other words, under conditions where the gas turbine load is small, the fuel flow rate with respect to the total air amount is small. In this case, only the central fuel 53 is supplied, and the fuel concentration in the central region exceeds the concentration at which the flame is stably formed. It can be operated to keep. Also, under conditions with a large gas turbine load, both the central fuel 53 and the surrounding fuel 54 can be supplied to perform lean low NOx combustion as a whole. In an intermediate load, the amount of fuel 53 in the center is set such that the equivalent ratio exceeds 1 with respect to the amount of air flowing from the air holes 57, and the operation is performed in a diffusion combustion manner using ambient air for combustion. It is also possible.

  Therefore, it can contribute to flame stabilization and low NOx combustion according to various gas turbine loads.

  In this way, by making the fuel jet into a coaxial jet that envelops the air flow, the fuel flows into the combustion chamber and then mixes with the surrounding coaxial air flow before actually contacting the hot gas and starting combustion. Then, after it becomes a premixed gas with an appropriate mixing ratio, it burns. For this reason, low NOx combustion equivalent to lean premixed combustion becomes possible. At this time, in this embodiment, the portion corresponding to the premixing tube of the conventional premixing combustor can be made extremely short.

  In addition, since the fuel concentration is almost zero near the wall surface, the potential for burnout due to flashback is extremely low.

  As described above, according to the present embodiment, it is possible to provide a gas turbine combustor and a gas turbine combustor operating method that have low NOx and excellent combustion stability.

  FIG. 5 shows details of the nozzle portion of the second embodiment. In this embodiment, there is one fuel system and it is not divided into the center and the periphery. Further, the swivel angle is not given to the nozzle and the combustion air hole near the center. In this embodiment, the nozzle structure can be simplified in operation or in a situation where combustion stability is not a significant problem due to the properties of the fuel.

  Example 3 is shown in FIG. In this embodiment, a single combustor is constituted by combining a plurality of nozzles of Embodiment 2 shown in FIG. That is, a single combustor is configured by combining a plurality of fuel nozzles and air holes as one module.

  By adopting such a configuration, as described in the first embodiment, it is possible to flexibly cope with a change in the load of the gas turbine by using a plurality of fuel systems and to increase / decrease the number of nozzles per can of the combustor. Those having different capacities can be provided relatively easily.

Example 4 is shown in FIG. The present embodiment is basically the same as the second embodiment except that the coaxial jet itself is provided with a swirl component by the air swirler 58.

  With this configuration, mixing of individual coaxial jets is promoted, and more uniform low NOx combustion is possible. A structure in which a swirl component is given to the fuel jet in the fuel nozzle is also effective for promoting mixing.

  FIG. 8 shows a fifth embodiment. This embodiment is different from the third embodiment in that the nozzle installed on the central axis of the third embodiment is a conventional diffusion burner 61 having an air swirler 63 and a fuel injection hole 62 intersecting with the air swirler 63.

  Such a configuration is considered advantageous when starting stability is emphasized by using a conventional diffusion combustion burner at start-up / acceleration and partial load.

  FIG. 9 shows a sixth embodiment. In this embodiment, the liquid fuel nozzle 68 and the spray air nozzle 69 are installed in the diffusion burner 61 of the embodiment shown in FIG. 8, and the liquid fuel 66 is atomized with the spray air 65 to cope with the combustion of the liquid fuel. It is something that can be done. Although many cannot be expected in terms of reducing NOx, it is intended to provide a combustor that can flexibly cope with fuel supply conditions.

  FIG. 10 shows a seventh embodiment. This embodiment is an example in which an auxiliary fuel supply system 71, a header 72, and a nozzle 73 are added to the downstream side of the combustor in the first embodiment shown in FIGS. The fuel ejected from the nozzle 73 flows into the combustion chamber as a coaxial jet through the air hole 74, and the combustion reaction proceeds by the high-temperature gas flowing from the upstream side.

  By adopting such a configuration, the structure is complicated, but a low NOx combustor that is flexible in load handling can be provided.

  FIG. 11 shows an eighth embodiment. In this embodiment, the individual fuel nozzles of the embodiment shown in FIG. 5 are made into a double structure so that the liquid fuel 66 is supplied to the inner liquid fuel nozzle 68 and the atomized air 65 is supplied to the outer nozzle 81. By supplying the liquid fuel 66, even when the liquid fuel 66 is used, a large number of coaxial jets can be formed to realize low NOx combustion with a very low backfire potential.

  In addition, by stopping the supply of liquid fuel and supplying gaseous fuel instead of atomizing air, it is possible to operate as a low-NOx combustor of gaseous fuel, and combustion corresponding to both liquid and gaseous fuel It can also have features that make it possible to provide vessels.

  As described above, a part or all of the fuel nozzles have a double structure so that the spraying of the liquid fuel and the gaseous fuel can be switched or used in combination, so that both liquid and gaseous fuels can be used.

  As described above, according to the above-described embodiment, the fuel is flowed into the combustion chamber by making many coaxial jets that wrap the fuel in the air flow, and then actually comes into contact with the hot gas and starts combustion. Before mixing, it is mixed with the surrounding coaxial air flow, and after it becomes a premixed gas with an appropriate mixing ratio, it burns. For this reason, low NOx combustion equivalent to lean premixed combustion becomes possible. At this time, the part corresponding to the premixing tube of the conventional premixing combustor is extremely short, and the fuel concentration is almost zero near the wall surface. it can.

  FIG. 12 shows a partial cross-sectional view in which the fuel nozzle 55 and the combustion air hole 52 are arranged substantially coaxially. A combustion air hole 52 is provided on the fuel ejection downstream side of the fuel nozzle 55. That is, a premixing channel is formed on the fuel jet downstream side of the fuel nozzle 55. The size (flow path area) of the combustion air hole 52 is preferably larger than the fuel ejection hole area of the fuel nozzle 55. In the present embodiment, the diameter of the combustion air hole 52 (the premixed channel diameter area) is formed larger than the diameter (area) of the fuel injection hole of the fuel nozzle 55. The fuel is ejected from the fuel nozzle 55 through this premixing flow path, and the fuel and air are coaxially jetted. At this time, it is desirable that the fuel from the fuel nozzle 55 be ejected toward substantially the center of the inlet portion of the combustion air hole 52 to form a good coaxial jet. In the case of the present embodiment, the fuel concentration distribution downstream of the air outlet has a symmetrical shape around the axis of the coaxial flow as shown in the figure, and rapidly mixes and becomes uniform as it goes downstream. As a result, compared with the conventional premixed combustion method, the same low NOx performance can be realized with a short premix distance.

  FIGS. 13A and 13B are examples in which the axis of the combustion air hole 52 is inclined with respect to the fuel jet axis of the fuel nozzle 55 by an angle θ °. In the vicinity of the entrance of the combustion air hole 52, the combustion air hole 52 is inclined with respect to the flow direction in a coaxial arrangement. In this arrangement, the fuel concentration distribution downstream of the air outlet is asymmetric with respect to the air jet axis as shown in the figure. As it goes downstream, it is mixed and uniformed, but the asymmetry with respect to the axis is not completely eliminated, and it is considered that a concentration deviation remains. Then, for example, as shown in FIG. 13B, such a misalignment between the fuel jet axis and the air hole axis is positively utilized for the coaxial nozzle hole near the center of the burner formed by the coaxial jet assembly. It is possible. That is, in this embodiment, the above-described inclination of the combustion air hole 52 is provided around the flame holding region and near the center of the burner, and the combustion air hole 52 on the opposite side is not inclined (θ = 0 °). The fuel concentration in the flame holding region can be kept relatively high, and the flame stability can be enhanced. In this embodiment, while adopting a straight fuel injection hole with no turning angle or inward / outward angle in the fuel injection hole, only the air hole has an angle not parallel to the axis of the burner, such as the turning angle, It is excellent in that the premixed gas can be swirled and inward and outward angles can be given with a relatively simple structure, and the premixed gas flow can be set with a relatively simple structure according to the burner configuration and purpose. ing.

  Next, FIG. 14 is an example in which the axial direction of the coaxial arrangement of the fuel injection hole and the air hole is the same and the positional deviation d is set intentionally. Due to this deviation, as shown in the figure, the concentration deviation is asymmetrically distributed with respect to the air jet axis, and the concentration deviation of the fuel can be positively generated, and combustion characteristics such as combustion stability can be improved. Can do.

  In this embodiment, the fuel from the fuel nozzle 55 flows almost along the center of the premixing channel in the premixing channel. In addition, air is configured to flow from the outer peripheral side of the fuel nozzle 55 along the outer peripheral side of the flow channel in the premixed flow channel. Therefore, in the premix channel, air flows along the fuel flow on the outer peripheral side of the fuel flow, and both flows are substantially coaxial. By providing a plurality of such nozzle forms, mixing can be promoted and stable combustion can be realized with a simple structure.

  15A and 15B show examples of the length of the premixing length L. Mixing due to rapid expansion after exiting the air hole is dominant, and the influence of the premixing length L on the uniformity of mixing and the low NOx performance is considered to be not so large. As shown in FIG. 15A, it is considered that the low NOx performance can be sufficiently ensured even if the member for forming the air hole is made thin and the premixing distance L is shortened. On the other hand, it is possible to expect savings in the material of the member forming the air holes and the processing cost of the hole processing of the air holes, and the cost reduction is advantageous. FIG. 15B shows an example where the premix length L is sufficiently long. Fuel and air can be expected to be sufficiently mixed in this flow path, and a combustor with even lower NOx properties can be provided. Furthermore, it is advantageous that L is about several times the diameter of the air hole in order to give a function such as giving a swirl component by giving an oblique angle to the air hole or giving an inward / outward deflection angle. is there.

  FIGS. 15C and 15D show examples in which the axial distance G between the fuel nozzle tip and the air hole inlet is different. FIG. 15C is an example in which G is large. A substantial premixing distance can be taken, and it is considered advantageous for uniform mixing and low NOx properties. Further, since the length of the fuel nozzle can be shortened, the manufacturability of the fuel nozzle is improved and the cost can be reduced. On the other hand, FIG. 15 (d) shows an arrangement in which a premixing channel is formed relatively downstream of the fuel nozzle 55, the axial distance G is negative, and the fuel injection hole protrudes into the air hole. With such an arrangement, the potential of flashback is further reduced, and it is considered effective when, for example, ignitable fuel such as dimethyl ether (DME) is burned with low NOx.

  FIGS. 15E and 15F show an example in which the diameter D of the air hole is small and large. In the case of FIG. 15 (e) in which the diameter D of the air hole is small and the number thereof is increased, the fuel and air are finely dispersed from the burner, so that they are uniformly mixed well in a short distance, and are lower. Suitable when NOx performance is important. When the air hole diameter D is increased and the number of air holes is reduced as shown in FIG. 15 (f), a long mixing distance is required and the uniformity is somewhat impaired, so the low NOx performance is slightly inferior. It is possible to reduce the number of manufacturing steps and to make the required manufacturing accuracy relatively rough, which is advantageous when emphasizing cost reduction.

FIG. 16A shows another embodiment. In the embodiment described so far, the arrangement of the coaxial air holes in the burner surface has been shown as being concentrically distributed, but the basic characteristics are not lost even in a lattice arrangement or a staggered arrangement. Absent. FIG. 16 (a) shows an example of such arrangement. When arranged in this manner, although depending on the average flow velocity in the combustor liner, the axial position in which the flame is formed becomes a substantially lifted flame within the liner cross section. It may be simple to produce but may not be sufficient in terms of flame stabilization. FIG.
In such a case, (b) is low in a part of the burner surface by providing a region having a small air hole area or a region having no air hole or a large pitch even though the air hole pitch is the same. In this example, a flow velocity portion and a circulation flow region are formed, and the flame is stabilized at this portion. Such a configuration can provide a combustor having a low flashback potential and having both low NOx properties and combustion stability.

  FIG. 17 shows an example of an experimental result regarding the relationship between the premix distance L and the NOx emission amount of the present invention. Complete premix combustion, in which fuel and air are completely mixed and then combusted, requires a mixing device having a sufficiently long mixing distance or a large pressure loss, but the NOx discharged is very low. (Point A in the figure) On the other hand, in a practical premixer structure formed by arranging a plurality of fuel nozzles in an annular premixing flow path, NOx increases approximately in inverse proportion to the premixing distance L. An example of a premixer, NOx, is shown at point B in the figure.

  On the other hand, in the present invention, the relationship between the premix distance and the NOx emission amount in one embodiment of the present invention in which fuel and air are arranged as a large number of coaxial jets is as shown at point C in the figure. However, it has been shown that the NOx performance equivalent to that of the conventional premixer is exhibited at a premixing distance of 1/20 or less that of the conventional structure.

BRIEF DESCRIPTION OF THE DRAWINGS Explanatory drawing including the whole sectional drawing of Example 1 of this invention. Explanatory drawing of a diffusion combustion system. Explanatory drawing of a premix combustion method. The nozzle part detailed explanatory drawing of Example 1 of this invention. The nozzle part detailed explanatory drawing of Example 2 of this invention. The nozzle part detailed explanatory drawing of Example 3 of this invention. The nozzle part detailed explanatory drawing of Example 4 of this invention. The nozzle part detailed explanatory drawing of Example 5 of this invention. The nozzle part detailed explanatory drawing of Example 6 of this invention. The nozzle part detailed explanatory drawing of Example 7 of this invention. The nozzle part detailed explanatory drawing of Example 8 of this invention. The nozzle part detailed explanatory drawing of Example 9 of this invention. The other nozzle part detailed explanatory drawing of Example 9 of this invention. The other nozzle part detailed explanatory drawing of Example 9 of this invention. The figure which shows the various nozzle form of this invention. The nozzle part detailed explanatory drawing of Example 10 of this invention. The figure which shows the relationship between a premixing distance and NOx discharge | emission amount.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 ... Combustion chamber, 2 ... Outer cylinder, 3 ... Combustor liner, 4 ... Diffusion flame, 5 ... Premix flame, 8, 55, 56 ... Fuel nozzle, 10 ... Compressor, 12, 63 ... Air swirler, 13 DESCRIPTION OF SYMBOLS ... Diffusion fuel nozzle, 14 ... Combustion air hole, 16 ... Gas fuel, 17 ... Cooling air hole, 18 ... Turbine, 21 ... Premixed gas fuel, 22 ... Premixed gas, 23 ... Premixer, 31 ... Cooling air 32 ... dilution air, 33 ... primary combustion air, 49 ... head swirling air, 50 ... air, 51 ... coaxial air, 52, 57,
74: Air hole, 53, 54 ... Fuel, 61 ... Diffusion burner, 62 ... Fuel injection hole, 65 ... Spraying air, 66 ... Liquid fuel, 68 ... Liquid fuel nozzle, 69 ... Spraying air nozzle, 71, 80 ... Fuel supply System, 72 ... header, 73 ... nozzle.

Claims (14)

  A gas turbine combustor comprising a combustion chamber to which fuel and air are supplied and configured to supply the fuel and air to the combustion chamber as a plurality of coaxial jets.   A fuel nozzle for injecting fuel into the combustion chamber; and an air hole for injecting air into the combustion chamber; and the fuel nozzle and the air so that the fuel and the air are injected into the combustion chamber as a plurality of coaxial jets. A gas turbine combustor comprising air holes.   A gas turbine combustor having a fuel nozzle, an air hole, and a combustion chamber, wherein the fuel and air are jetted into the combustion chamber as a plurality of small-diameter coaxial jets. The gas turbine combustor according to claim 3.
The fuel nozzle hole of the fuel nozzle is installed at a position that is coaxial or nearly coaxial with the air hole, the fuel jet is jetted toward the vicinity of the center of the inlet of the air hole, and the fuel jet and the annular flow of the air surrounding it are coaxial A gas turbine combustor which is jetted from the outlet of the air hole to the combustion chamber as a jet. The gas turbine combustor according to claim 4.
A gas turbine combustor comprising a control device that divides a large number of fuel nozzles into a plurality of fuel supply systems and independently controls each fuel flow rate according to a load of the gas turbine.   6. The gas turbine combustor according to claim 5, wherein some or all of the fuel nozzles and a swirl angle that gives a corresponding air hole a component swirling around the combustor axis. A gas turbine combustor characterized in that The gas turbine combustor of claim 5.
The fuel nozzle hole of the fuel nozzle is installed at a position that is coaxial or nearly coaxial with the air hole, the fuel jet is jetted toward the vicinity of the center of the inlet of the air hole, and the annular flow of the fuel jet and the air that wraps it is a coaxial jet Configured to be ejected from the air hole outlet to the combustion chamber;
A gas turbine combustor characterized in that a plurality of these fuel nozzles and air holes are combined into one module to constitute one combustor. The gas turbine combustor according to any one of claims 3 to 7,
A gas turbine combustor comprising a mechanism for imparting a swirl component around each axis to each air hole or fuel nozzle. The gas turbine combustor according to claim 3.
A gas turbine combustor characterized in that a part or all of the fuel nozzle has a double structure so that spraying of liquid fuel and gaseous fuel can be switched or used together. A method for operating a gas turbine combustor having a combustion chamber to which fuel and air are supplied,
An operation method of a gas turbine combustor, wherein the fuel and the air are supplied to the combustion chamber as a plurality of coaxial jets. A method for operating a gas turbine combustor having a combustion chamber to which fuel and air are supplied,
A plurality of fuel nozzles for injecting the fuel are provided, the fuel nozzles are divided into a plurality of fuel supply systems, each fuel flow rate is controlled independently by a gas turbine load, and the fuel and the air are supplied to a plurality of coaxial jets. An operation method of a gas turbine combustor, characterized by being supplied as A gas turbine combustor having a combustion chamber to which fuel and air are supplied,
A plurality of fuel nozzles for ejecting the fuel are provided,
A premixing channel located on the fuel jet downstream side of the fuel nozzle and having a channel area larger than the fuel jet hole area of the fuel nozzle;
A gas turbine combustor configured to eject fuel from the fuel nozzle through the premixing flow path. A gas turbine combustor having a combustion chamber to which fuel and air are supplied,
A plurality of fuel nozzles for ejecting the fuel are provided,
A premixing channel located on the fuel ejection downstream side of the fuel nozzle and having a channel diameter area larger than the fuel ejection hole diameter area of the fuel nozzle;
The fuel from the fuel nozzle flows substantially along the center of the flow path in the premix flow path, and the air from the outer peripheral side of the fuel nozzle flows along the flow path outer periphery side in the premix flow path. A gas turbine combustor configured as described above. A combustion chamber to which fuel and air are supplied, a plurality of fuel nozzles for ejecting the fuel,
A premixing channel having a channel diameter area larger than the fuel injection hole diameter of the fuel nozzle,
A gas turbine combustor configured to eject the fuel from the fuel nozzle toward a substantially center of an inlet portion of the premixing channel.

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