JP4861910B2 - Diffusion combustion type gas turbine combustor - Google Patents

Description

  The present invention relates to a diffusion combustion gas turbine combustor that burns at least one of gaseous fuel and liquid fuel.

  In general, the combustion system of a gas turbine combustor is roughly divided into diffusion combustion and premixed combustion. The former is a method in which fuel is directly injected into the combustion field and burns. Compared to premixed combustion, the fuel-rich region is more likely to be generated, and there is a problem that a large amount of thermal NOx is emitted due to the occurrence of a local high-temperature region. ing. On the other hand, the latter is a method in which fuel is previously mixed with air and then burned. In comparison with diffusion combustion, generation of a local high temperature region is suppressed and NOx emission is small. However, in the case of premixed combustion, a lean premixed flame is formed, so that the combustion state is likely to be unstable, and the flame may flow backward (flame return) to the mixer for generating the premixed gas, etc. There is a problem. Furthermore, since the combustor structure and the fuel system are complicated compared to diffusion combustion, the initial cost is increased.

  Therefore, in order to improve the combustion stability and ignition characteristics of the diffusion combustion type combustor, a swirler that provides swirl components to the combustion air is provided near the axial center of the upstream portion of the combustor, and liquid fuel is disposed in the vicinity of the swirler. In addition, there is a fuel nozzle that injects gaseous fuel (see Patent Document 1). In this technique, a cone-shaped member having a slit for introducing combustion air for forming a low flow rate circulation region of combustion gas is disposed on the outer peripheral side of the swirler.

JP 2005-226849 A

  In the gas turbine combustor, from the viewpoint of protecting the global environment in recent years, the emission amount of nitrogen oxides (hereinafter referred to as NOx) contained in exhaust gas is reduced, and the generation amount of dust generated when liquid fuel is burned is reduced. There is an urgent need. However, in the technique described in Patent Document 1, since the air flow ejected from the swirler is directed toward the center of the combustion field, the fuel ratio to the combustion air is increased at the position where the flame is formed, and is localized. Occurrence of NOx emissions and dust generation may not be sufficiently suppressed due to generation of a high temperature region.

  Accordingly, an object of the present invention is to provide a diffusion combustion type gas turbine combustor capable of reducing NOx emission when at least one of gaseous fuel and liquid fuel is burned.

In order to achieve the above object, a diffusion combustion type gas turbine combustor according to the present invention includes an inner cylinder that burns combustion air from a compressor mixed with fuel, and an upstream position on an axial center line of the inner cylinder. A liquid fuel nozzle that is provided and atomizes the liquid fuel and injects it into the inner cylinder, and an air flow path located on the outer peripheral side of the liquid fuel nozzle and imparts a swirl component to the combustion air that is injected into the inner cylinder A swirler, a plurality of gaseous fuel nozzles for injecting gaseous fuel toward the air flow path of the swirler, and a flow of combustion air that is provided on the outer peripheral side of the swirler and toward the center side of the inner cylinder A cone-shaped member that has a plurality of air introduction slits to be formed, and that forms a low-speed circulation flow region on the outer peripheral side of the swirler by an air flow ejected from the plurality of air introduction slits; gas fuel jetted into said inner cylinder And as the air-fuel mixture in the combustion air is mixed with combustion air to form the low-speed circulation flow region, the axial line of the air passage within the cylinder when viewed in cross section including the axial line of the inner tube Or inclined toward the outer peripheral side toward the downstream side with respect to the axial center line.

  ADVANTAGE OF THE INVENTION According to this invention, NOx emission amount at the time of combusting at least one of gaseous fuel and liquid fuel in a diffusion combustion type gas turbine combustor can be reduced.

  Embodiments of the present invention will be described below with reference to the drawings.

<First Embodiment>
FIG. 1 is a schematic configuration diagram of a gas turbine plant including a gas turbine combustor according to a first embodiment of the present invention. In the following description, the term “upstream / downstream” refers to upstream / downstream in the flow direction of the combustion gas.

  The gas turbine plant shown in FIG. 1 mainly compresses air to produce high-pressure combustion air, and mixes combustion air 13 introduced from the compressor 1 and fuel to produce combustion gas 14. A diffusion combustion type gas turbine combustor (hereinafter simply referred to as a combustor) 3 to be generated and a turbine 2 into which a combustion gas 14 generated by the combustor 3 is introduced are provided. The shafts of the compressor 1 and the turbine 2 are connected.

  The combustor 3 forms a combustion chamber and mixes and burns combustion air 13 from the compressor with fuels 16 and 17 to generate combustion gas, and the combustion gas 14 generated by the inner cylinder 7 is supplied to the turbine 2. A transition piece 8 for guiding, a pressure spray type (one fluid spray type) liquid fuel nozzle 12 for atomizing the liquid fuel 17 by increasing the fuel supply pressure and injecting it into the inner cylinder 7, and a gaseous fuel for injecting the gaseous fuel 16 A nozzle 15, a swirler 11 that imparts a swirl component to the combustion air 13, an inner cylinder cap 10 having a slit (described later) for injecting the combustion air 13, and an ignition plug 9 for igniting the combustor 3 are externally provided. The cylinder 5 and the end cover 6 are hermetically sealed.

  The combustor 3 is a dual-type combustor capable of combusting both the gaseous fuel 16 and the liquid fuel 17. The combustor 3 operates by burning only the gaseous fuel 16, operates by burning only the liquid fuel 17, and both fuels. Any of the operations by burning 16 and 17 at the same time is possible.

  The combustion air 13 discharged from the compressor 1 passes through an annular air flow path defined by the outer cylinder 5, the inner cylinder 7, and the transition piece 8, and combustion holes (not shown) provided on the outer peripheral wall surface of the inner cylinder 7 The inner cylinder 7 includes a cooling hole, a slit hole provided in the inner cylinder cap 10 (a slit hole 23 described later in FIG. 2), a swirler air hole provided in the swirler 11 (air holes 19 and 20 described later in FIG. 2), and the like. It is introduced into the fuel and mixes with the fuels 16 and 17, and the air-fuel mixture of the combustion air 13 and the fuels 16 and 17 is ignited and burned in the inner cylinder 7 by the spark plug 9. The combustion gas 14 generated by the combustion is injected into the turbine 2 through the transition piece 8 to drive the turbine 2. The rotational power obtained by the turbine 2 is converted into electric energy by driving the generator 4 connected coaxially, and is also used as rotational power for the compressor 1.

  FIG. 2 is a side sectional view showing the configuration of the swirler 11 of the combustor 3 and its surroundings.

  As shown in FIG. 2, the liquid fuel nozzle 12 is disposed at an upstream position on the axis X of the inner cylinder 7 (that is, the left side in FIG. 2). The liquid fuel 17 injected from the liquid fuel nozzle 12 forms a conical fuel spray region 18.

  A plurality of combustion holes 24 for introducing the combustion air 13 from the annular flow path between the inner cylinder 7 and the outer cylinder 5 into the inner cylinder 7 are provided on the outer peripheral wall surface of the inner cylinder 7.

  The inner cylinder cap 10 is a cone-shaped member provided on the outer peripheral side of the swirler 11, and is a slit hole for air introduction that forms a flow of combustion air 13 toward the center side of the inner cylinder 7 along the inner wall surface thereof. A plurality of 23 are provided. A porous plate 21 for introducing combustion air 13 is installed on the upstream side of the inner cylinder cap 10, and the combustion air 13 that has passed through the porous plate 21 is ejected into the inner cylinder 7 from the slit hole 23 of the inner cylinder cap 10. To do. The air flow of the combustion air 13 ejected from the slit hole 23 of the inner cylinder cap 10 is circulated at a low speed in a region near the inner wall surface of the inner cylinder cap 10 in the region on the outer peripheral side of the swirler 11 and downstream of the inner cylinder cap 10. A stream 100 is formed.

  The swirler 11 has a plurality of outer peripheral air holes 19 arranged in an annular shape on the outer peripheral side of the liquid fuel nozzle 12, and the outer peripheral air holes 19 are substantially concentric between the plurality of outer air holes 19 and the liquid fuel nozzle 12. The plurality of inner peripheral air holes 20 are arranged in an annular shape. Since these two rows of air holes 19 and 20 are inclined to one side in the circumferential direction of the inner cylinder 7 toward the downstream side (that is, the right side in FIG. 2) when viewed from the axis X, the air holes A swirling component is imparted to the combustion air 13 that is jetted into the inner cylinder 7 from 19 and 20. The gaseous fuel nozzle 15 in the present embodiment has a plurality of fuel injection holes for injecting the gaseous fuel 16 toward the respective outer peripheral side air holes 19. The cross-sectional shape of the air holes 19 and 20 (cross section perpendicular to the axial center line of the holes) is substantially circular.

  At this time, the outer peripheral air hole 19 is an air hole that mainly forms an air flow that contributes to the diffusion of the gaseous fuel 16, and the combustion air 13 that is jetted into the inner cylinder 7 from the above-described circulation flow 100. Each of the inner cylinders 7 is parallel to the axis X when viewed in a cross section including the axis X of the inner cylinder 7 so as to be actively mixed with the combustion air 13 to be formed. On the other hand, each inner peripheral air hole 20 is an air hole that forms an air flow that mainly contributes to the diffusion of the liquid fuel 17, and similarly when viewed in a cross section including the axial line X of the inner cylinder 7, Each is inclined at an angle α toward the inner peripheral side (axial center line X side) of the inner cylinder 7 toward the downstream side with respect to the axial center line X.

  The swirler 11 has an air flow path located on the outer peripheral side of the liquid fuel nozzle 12, but this air flow path is not limited to the air holes 19, 20 as shown, and the liquid fuel nozzle 12 It can also replace with the annular air flow path located outside. A swirl vane is disposed in the annular air flow path, and a swirl component is imparted to the combustion air that circulates when the swirl vane is inclined in the circumferential direction. In the present embodiment, for example, when the air hole 19 on the outer peripheral side is replaced with such an air flow path with swirl vanes, when the air flow path is viewed in a cross section including the axial center line X of the inner cylinder 7, the axial center line is obtained. Form parallel to X. Or it can also be set as the structure which inclines to an outer peripheral side toward the downstream with respect to the axial center line X like subsequent embodiment (FIG. 5 etc.). On the other hand, when the inner circumferential air hole 20 is replaced with this type of air flow path, the inner circumferential side (axial center of the inner cylinder 7 toward the downstream side with respect to the axial center line X is the same as the inner circumferential air hole 20. Inclined to the line X side) at an angle α.

  Here, FIG. 3 is a side sectional view illustrating a comparative example. In FIG. 3, parts having the same functions as those in FIG.

  In the comparative example illustrated in FIG. 3, the swirler 11 and the gaseous fuel nozzle 15 of the gas turbine combustor 3 of the present embodiment are changed to a swirler 11 ′ and a gaseous fuel nozzle 26. The swirler 11 ′ is provided with a swirler air hole 25 inclined at an angle γ toward the axial center line X toward the downstream side, and a gaseous fuel nozzle 26 is connected to the side wall surface of the flow path.

  In the case of this comparative example, combustion air 13 is jetted into the inner cylinder 7 from the combustion hole 24 provided in the inner cylinder 7, the slit hole 23 provided in the inner cylinder cap 10, and the swirler air hole 25. The combustion air 13 ejected from the slit hole 23 of the inner cylinder cap 10 forms a low-speed circulation flow 100, and the combustion air 13 ejected from the swirler air hole 25 moves toward the axis X of the inner cylinder 7 and further swirls. Thus, a circulating flow 104 is formed. The fuels 16 and 17 ejected from the gaseous fuel nozzle 26 and the liquid fuel nozzle 12 are mixed and combusted with the combustion air 13 ejected from the swirler air hole 25, and the flame is held by the circulating flow 104. Circulating flow 100 stabilizes this flame.

  However, in this comparative example, the spread of the flame is suppressed by the combustion air 13 injected inward in the radial direction from the swirler air hole 25, and the fuel ratio to the combustion air 13 is increased at the position where the flame is formed. Therefore, a local high temperature region may occur, and there may be a case where the amount of NOx emission and the amount of dust generated during liquid fuel combustion cannot be sufficiently suppressed.

  On the other hand, in the case of the present embodiment, the combustion air 13 is jetted into the inner cylinder 7 from the combustion hole 24 provided in the inner cylinder 7, the slit hole 23 of the inner cylinder cap 10, and the swirler air holes 19 and 20. The combustion air 13 ejected from the inner cylinder cap 10 forms a low-speed circulation flow 100 and stabilizes the flame. The combustion air 13 ejected from the inner peripheral air hole 20 for liquid fuel is ejected toward the axial center line X of the inner cylinder 7 and then forms a circulation flow 102 by the swirling action. Further, the combustion air 13 ejected from the outer peripheral side air hole 19 for the gaseous fuel expands toward the downstream side due to the swirling action to form a circulating flow 101.

  Thus, according to the present embodiment, the gaseous fuel 16 injected from the gaseous fuel nozzle 15 toward the outer peripheral air hole 19 of the swirler 11 is mixed with the combustion air 13 inside the outer peripheral air hole 19. It spouts into the inner cylinder 7 while fitting. The mixture of the gaseous fuel 16 and the combustion air 13 ejected from the outer peripheral side air hole 19 receives a centrifugal force due to the swirling action, expands the diameter toward the downstream side, and swirls in the vicinity of the inner cylinder cap 10. And is further mixed with the combustion air 13 forming the circulating flow 100. Therefore, as compared with the comparative example of FIG. 3, the ratio of the fuel to the combustion air 13 at the flame forming position is reduced, and the mixing of the gaseous fuel 16 and the combustion air 13 is promoted, thereby suppressing the occurrence of a local high temperature region. Therefore, the NOx emission amount can be reduced.

  Further, the liquid fuel 17 droplets on the outer peripheral side of the fuel spray region 18 injected from the liquid fuel nozzle 12 also accompany the circulating flow 101 from the outer peripheral air hole 19, thereby circulating the liquid from the inner cylinder cap 10. Toward 100, the fuel droplets are further atomized and mixing with the combustion air 13 is promoted. Thereby, the discharge amount of NOx / dust can be reduced. Furthermore, since the circulating flow 102 ejected from the inner peripheral air hole 20 for liquid fuel provided in the swirler 11 is directed to the inside of the fuel spray region 18, the combustion air 13 is positively introduced into the fuel spray region 18. As a result, the fuel spray region 18 can be mixed with a larger amount of the combustion air 13, which also reduces the NOx emission due to the dilution of the fuel and the dust emission due to the atomization of the fuel and the promotion of the oxidation reaction. The effect of reducing the amount is obtained.

  Thus, according to the gas turbine combustor of the present embodiment, the fuels 16 and 17 injected from the gaseous fuel nozzle 15 and the liquid fuel nozzle 12 circulate the combustion air 13 ejected from the swirler air holes 19 and 20. Since it is first mixed with the streams 101 and 102 and then further mixed with the circulating flow 100 of the combustion air 13 ejected from the inner cylinder cap 10 and burned, the generation of the fuel rich region is suppressed, and the local high temperature Since the generation of the region is suppressed, the NOx emission amount / dust generation amount can be reduced.

  Furthermore, the combustor 3 according to the present embodiment adopting the diffusion combustion method as compared with the case where the premixed combustion method is adopted has a great merit in that the structure is simple, easy to manufacture, and inexpensive. Furthermore, since the pressure injection type liquid fuel nozzle 12 is used, it operates in comparison with the case where an air spray type (two-fluid spray type) liquid fuel nozzle that shears with an air flow to atomize the liquid fuel is employed. The amount of compressed air consumed for applications other than fluids is reduced, contributing to improved efficiency of the gas turbine plant.

  In addition, the pressure spray type liquid fuel nozzle that does not use a secondary medium such as air for atomizing the fuel imparts a powerful swirl to the liquid fuel, so that large droplets of fuel droplets are placed on the outer periphery of the fuel spray region. Easy to concentrate. In addition, the particle size of the fuel droplets tends to be larger than that of an air spray type liquid fuel nozzle that atomizes the liquid fuel by shearing with a secondary medium.

  The pressure spray type liquid fuel nozzle has such characteristics. In the case of the present embodiment, even if the pressure spray type liquid fuel nozzle is adopted, the fuel droplets having large particle diameters tend to concentrate. The portion on the outer peripheral side of the spray region 18 is further atomized by the circulating flow 101 ejected from the outer peripheral air hole 19 and the circulating flow 100 from the inner cylinder cap 10 to promote mixing with the combustion air. The reaction can be promoted, and the NOx / dust reduction effect becomes even more prominent as compared to the case of using an air spray type liquid fuel nozzle.

  FIG. 4 shows the state of the flame when the combustor is ignited. FIG. 4A is a side sectional view of the gas turbine combustor of the present embodiment, and FIG. 4B is a comparative example of FIG. It is a sectional side view of the gas turbine combustor.

  The combustor 3 is ignited by the spark of the spark plug 9 inserted from the outer peripheral wall surface of the inner cylinder 7. When a plurality of combustors 3 are installed around the compressor 1, the inner cylinder 7 a of the combustor 3 in which the ignition plug 9 is installed and the inner cylinder 7 b of the adjacent combustor 3 in which the ignition plug 9 is not installed are provided. An ignition operation of the combustor 3 having no ignition plug 9 is performed by flame propagation that is communicated by the flame propagation tube 29 and ignited by the exchange of the combustion gas 14. The flame propagation means that the combustor 3 in which the ignition plug 9 is installed is ignited by the ignition plug 9, and the flame propagation tube 29 is moved from the ignited combustor 3 by the pressure difference generated between the adjacent unignited combustors. The combustion gas 14 is caused to flow into the adjacent unignited combustor, and the unignited combustor is ignited by the introduced combustion gas 14. In order to improve the ignition characteristics of such an ignition operation, it is important that a combustible air-fuel mixture exists in the vicinity of the flame propagation hole 27 and the spark plug 9 of the inner cylinder 7b to which the flame propagation tube 29 is connected.

  In the case of the comparative example of FIG. 4B, the combustion air 13 from the swirler 11 ′ is ejected toward the axial center line X of the inner cylinder 7a, so that the fuel / air mixture and the flame 28 are radially outward. It does not spread and tends to concentrate in the vicinity of the combustor shaft center X. On the other hand, in the case of the present embodiment, due to the effect that the combustion air 13 from the outer peripheral side air hole 19 is ejected toward the inner wall surface side of the inner cylinder 7a, as shown in FIG. The air-fuel mixture and the flame 28 can be spread radially outward, and the air-fuel mixture and the flame 28 come close to the flame propagation hole 27 and the spark plug 9, so that the ignition characteristics can be improved as compared with FIG.

<Second Embodiment>
FIG. 5 is a side cross-sectional view showing a configuration of a swirler of a gas turbine combustor according to the second embodiment of the present invention and its surroundings. Parts that are the same as those in the first embodiment and parts that play the same role are denoted by the same reference numerals and description thereof is omitted.

  In the present embodiment, the shaft of the inner cylinder 7 is arranged so that the combustion air 13 ejected into the inner cylinder 7 from the outer peripheral air hole 30 provided in the swirler 11 can be easily mixed with the combustion air 13 forming the circulation flow 100. When viewed in a cross section including the core X, the outer peripheral air hole 30 is inclined toward the outer peripheral side at an angle β toward the downstream side with respect to the axial center line of the inner cylinder 7. Other configurations are the same as those of the first embodiment.

  According to the present embodiment having such a configuration, the combustion air 13 ejected from the outer peripheral air hole 30 is more easily expanded to the outer peripheral side as compared with the first embodiment, and the combustion ejected from the inner cylinder cap 10. Further promotion of mixing of the air 13 and the fuels 16, 17 can be expected, and as a result, a further reduction effect of NOx and dust emission can be expected. Further, since a further diameter expansion effect of the air-fuel mixture and flame of the fuels 16 and 17 and the combustion air 13 can be expected as compared with the first embodiment, further improvement of the ignition characteristics of the combustor 3 is expected.

<Third Embodiment>
FIG. 6 is a side sectional view showing a swirler of a gas turbine combustor according to the third embodiment of the present invention and the surrounding configuration. Parts that are the same as those in the first embodiment and parts that play the same role are denoted by the same reference numerals and description thereof is omitted.

  In the present embodiment, in addition to the gaseous fuel nozzle 15, the inner circumferential air hole 20 is provided so that the gaseous fuel 16 is injected into both the inner circumferential air hole 20 and the outer circumferential air hole 19 of the swirler 11. A plurality of gaseous fuel nozzles 31 for ejecting the gaseous fuel 16 toward each of them are added. The fuel supply system of the outer peripheral side gas fuel nozzle 15 and the inner peripheral side gas fuel nozzle 31 is shared, but may be a separate system. The outer peripheral side air hole 19 may be inclined outward as in the second embodiment. Other configurations are the same as those of the first embodiment.

  According to this embodiment having such a configuration, in addition to the same effects as those of the first embodiment, the gas fuel 16 is dispersed by adding the inner peripheral side gas fuel nozzle 31 and increasing the number of fuel injection holes. Can be made. Further, the gas mixture of the gaseous fuel 16 and the combustion air 13 is ejected from both the outer peripheral side air hole 19 and the inner peripheral side air hole 20, so that the gaseous fuel 16 is further diluted as compared with the above-described embodiment. As a result, it is possible to expect further reduction effect of the NOx emission amount of the gaseous fuel burning.

<Fourth embodiment>
FIG. 7 is a configuration diagram of a gas turbine combustor according to a fourth embodiment of the present invention. FIG. 7A is a side sectional view showing a configuration of a swirler and its surroundings, and FIG. FIG. 7A is a cross-sectional view taken along line AA in FIG. 7A, and FIG. 7C is a cross-sectional view taken along line BB in FIG. In these drawings, the same parts as those in the first embodiment and the parts having the same functions are denoted by the same reference numerals and the description thereof is omitted.

  The fuel injection hole of the gaseous fuel nozzle 32 in the present embodiment is arranged on the outer peripheral side so that the gaseous fuel 16 is ejected in a direction substantially coaxial with the combustion air 13 ejected from the outer peripheral side air hole 19 of the swirler 11 into the inner cylinder 7. The air holes 19 are formed so as to be inclined in accordance with the direction in which the air holes 19 are formed. That is, as shown in FIG. 7C, the gaseous fuel nozzle 32 is roughly the same as the combustion air 13 in which the gaseous fuel 16 injected toward the outer peripheral air hole 19 of the swirler 11 is ejected from the outer air hole 19. The axial center line of the fuel injection hole is substantially coincident with the axial center line Y of the outer peripheral air hole 19 so as to be a coaxial jet. The cross-sectional shape (cross section perpendicular to the axial center line of the hole) of the fuel injection hole and the air holes 19 and 20 of the gaseous fuel nozzle 32 is substantially circular. Other configurations are the same as those of the first embodiment.

  According to the present embodiment having such a configuration, the gaseous fuel 16 ejected from the gaseous fuel nozzle 32 inside the outer peripheral air hole 19 is uniformly surrounded by the combustion air 13, and the outer peripheral air hole 19 of the swirler 11. Mixing of the gaseous fuel 16 and the combustion air 13 can be promoted by the fine vortex generated along with the rapid expansion of the flow path at the time of jetting from. Thereby, in addition to the effect similar to 1st Embodiment, the effect of the further reduction of NOx discharge | emission amount is anticipated.

  In the present embodiment, the gaseous fuel nozzle 32 is installed so as to inject the gaseous fuel 16 only into the outer peripheral side air hole 19 of the swirler 11, but as in the third embodiment (FIG. 6). If a gas fuel nozzle for injecting the gaseous fuel 16 to the inner peripheral side air hole 20 is added to the inner circumferential side air hole 20, dilution of the gaseous fuel 16 and mixing of the gaseous fuel 16 and the combustion air 13 are promoted, and further NOx reduction effect is expected. it can. Further, as in the second embodiment (FIG. 5), the outer peripheral air hole 19 may be inclined outward.

  Further, by making the cross section of the swirler air holes 19 and 20 substantially circular as in the present embodiment, for example, the manufacturing cost of the swirler 11 can be reduced as compared with an air hole having a rectangular cross section. There are also advantages.

  Since the gas turbine combustor 3 according to the first to fourth embodiments described above has a simple configuration, for example, when there is an existing facility having a configuration such as the comparative example of FIG. It is also a great advantage that the fuel nozzle can be manufactured by simple modification of only the fuel injection hole portion.

It is a schematic block diagram of the gas turbine plant provided with the gas turbine combustor which concerns on the 1st Embodiment of this invention. It is a sectional side view showing the structure of the swirler of the gas turbine combustor which concerns on the 1st Embodiment of this invention, and its periphery. It is the sectional side view which illustrated the comparative example. It is the figure which compared and showed the state of the flame at the time of the combustor ignition of the gas turbine combustor which concerns on the 1st Embodiment of this invention, and the comparative example of FIG. It is a sectional side view showing the swirler of the gas turbine combustor which concerns on the 2nd Embodiment of this invention, and the structure of the circumference | surroundings. It is a sectional side view showing the swirler of the gas turbine combustor which concerns on the 3rd Embodiment of this invention, and the structure of the circumference | surroundings. It is a block diagram of the gas turbine combustor which concerns on the 4th Embodiment of this invention.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Compressor 3 Gas turbine combustor 7 Inner cylinder 10 Inner cylinder cap 11 Swivel machine 12 Liquid fuel nozzle 13 Combustion air 15 Gas fuel nozzle 16 Gas fuel 17 Liquid fuel 19 Outer peripheral side air hole 20 Inner peripheral side air hole 23 Slit hole 30 Outer peripheral side air hole 31 Inner peripheral side gas fuel nozzle 32 Gaseous fuel nozzle 100 Circulating flow 101 Circulating flow 102 Circulating flow X axis center line Y axis center line

Claims (6)

An inner cylinder that burns combustion air from the compressor mixed with fuel; and
A liquid fuel nozzle that is provided at an upstream position on the axial line of the inner cylinder and atomizes the liquid fuel and injects it into the inner cylinder;
A swirler having an air flow path located on the outer peripheral side of the liquid fuel nozzle and imparting a swirl component to the combustion air ejected into the inner cylinder;
A plurality of gaseous fuel nozzles for injecting gaseous fuel toward the air flow path of the swirler;
The swirler includes a plurality of air introduction slits that are provided on an outer peripheral side of the swirler and that form a flow of combustion air toward the center side of the inner cylinder, and the swirl is performed by the air flow ejected from the plurality of air introduction slits. A cone-shaped member that forms a low-speed circulating flow region on the outer peripheral side of the vessel,
When viewed in a cross-section including the axial center line of the inner cylinder so that a mixture of gaseous fuel and combustion air ejected from the swirler into the inner cylinder mixes with the combustion air forming the low-speed circulation flow region The diffusion combustion type gas turbine combustor is characterized in that the air flow path is parallel to the axial center line of the inner cylinder or inclined toward the outer peripheral side toward the downstream side with respect to the axial center line. An inner cylinder that burns combustion air from the compressor mixed with fuel; and
A liquid fuel nozzle that is provided at an upstream position on the axial line of the inner cylinder and atomizes the liquid fuel and injects it into the inner cylinder;
A swirler having a plurality of air holes arranged annularly on the outer peripheral side of the liquid fuel nozzle, and imparting a swirl component to the combustion air ejected into the inner cylinder from the plurality of air holes;
A plurality of gaseous fuel nozzles for injecting gaseous fuel toward the plurality of air holes of the swirler;
The swirler includes a plurality of air introduction slits that are provided on an outer peripheral side of the swirler and that form a flow of combustion air toward the center side of the inner cylinder, and the swirl is performed by the air flow ejected from the plurality of air introduction slits. A cone-shaped member that forms a low-speed circulating flow region on the outer peripheral side of the vessel,
When viewed in a cross-section including the axial center line of the inner cylinder so that a mixture of gaseous fuel and combustion air ejected from the air hole into the inner cylinder mixes with the combustion air forming the low-speed circulation flow region A diffusion combustion type gas turbine combustor characterized in that the air hole is parallel to the axial center line of the inner cylinder or inclined toward the outer peripheral side toward the downstream side with respect to the axial center line. The diffusion combustion gas turbine combustor according to claim 2,
The swirler is annularly arranged between the plurality of air holes and the liquid fuel nozzle, and is downstream of the axis of the inner cylinder when viewed in a cross section including the axis of the inner cylinder. A diffusion combustion type gas turbine combustor comprising a plurality of inner peripheral side air holes inclined toward the inner peripheral side. The diffusion combustion gas turbine combustor according to claim 3,
A diffusion combustion type gas turbine combustor comprising a plurality of inner peripheral side gas fuel nozzles for injecting gaseous fuel toward the plurality of inner peripheral side air holes. In the diffusion combustion type gas turbine combustor according to any one of claims 2 to 4,
The fuel injection hole of the gaseous fuel nozzle is provided with an inclination in accordance with the direction of the air hole so that the gaseous fuel is ejected in a direction substantially coaxial with the combustion air ejected from the air hole into the inner cylinder. A diffusion combustion type gas turbine combustor characterized in that: An inner cylinder that burns combustion air from the compressor mixed with fuel; and
A pressure spray type liquid fuel nozzle which is provided at an upstream position on the axial line of the inner cylinder and which atomizes the liquid fuel by increasing the fuel supply pressure and injects it into the inner cylinder;
A plurality of outer peripheral air holes disposed annularly on the outer peripheral side of the liquid fuel nozzle; and a plurality of inner peripheral air holes disposed annularly between the plurality of outer peripheral air holes and the liquid fuel nozzle. A swirler for imparting a swirl component to the combustion air ejected into the inner cylinder from the plurality of outer peripheral air holes and inner peripheral air holes;
A plurality of gaseous fuel nozzles for injecting gaseous fuel toward the plurality of outer peripheral air holes of the swirler;
The swirler includes a plurality of air introduction slits that are provided on an outer peripheral side of the swirler and that form a flow of combustion air toward the center side of the inner cylinder, and the swirl is performed by the air flow ejected from the plurality of air introduction slits. A cone-shaped member that forms a low-speed circulating flow region on the outer peripheral side of the vessel,
As seen in a cross section including the axial center line of the inner cylinder so that the mixture of gaseous fuel and combustion air ejected from the outer peripheral side air hole into the inner cylinder mixes with the combustion air forming the low-speed circulation flow region. The outer peripheral air holes are parallel to the axial center line of the inner cylinder or are inclined toward the outer peripheral side toward the downstream side with respect to the axial center line, while the plurality of inner peripheral air holes are shafts of the inner cylinder A diffusion combustion type gas turbine combustor which is inclined toward the inner peripheral side toward the downstream side with respect to the core wire.

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