JP2019105382A - Fuel combustion device and fuel combustion method - Google Patents

Abstract

To provide a fuel combustion device and a fuel combustion method, capable of improving flame stability and reducing the amount of nitrogen oxide to be discharged.SOLUTION: The fuel combustion device comprising a combustor comprising a combustion chamber to be supplied with an oxidizer, first fuel and second fuel, in which chamber the first fuel and the second fuel are combusted in a diffusion combustion mode, is characterized in that the combustor is provided with an oxidizer feed port for guiding the oxidizer to the combustion chamber, a first fuel feed port disposed inside of the oxidizer feed port to guide the first fuel to the combustion chamber, and a second fuel feed port disposed outside of the oxidizer feed port to feed the second fuel to the combustion chamber.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a fuel combustion apparatus and a combustion combustion method, and more particularly to a fuel combustion apparatus and a combustion combustion method for burning a fuel such as ammonia, which has a low flammable property as compared with a hydrocarbon fuel such as methane.

  The prospects for hydrogen carriers as media for storage and transport of renewable energy are increasing. The hydrogen carrier includes, for example, organic hydride, which is used by attaching and detaching hydrogen to an organic solvent, and ammonia which is synthesized from nitrogen and hydrogen. Ammonia does not contain carbon atoms, and substances mainly generated when ammonia is burned are water and nitrogen. That is, since ammonia does not generate carbon dioxide even when it is burned, the use of ammonia as a fuel can be expected to have an effect of reducing carbon dioxide emissions. However, when ammonia is burned, nitrogen oxides with high environmental impact may be produced. In addition, ammonia is less likely to be ignited than hydrocarbon fuels such as methane, and has a characteristic of low laminar burning velocity. For this reason, when using ammonia as fuel, unburned ammonia may be generated. Ammonia has a pungent odor and is designated as a deleterious substance. Nitrogen oxides and ammonia have emission regulations.

  Conventionally, a technology has been proposed in which ammonia and air are separately supplied to the combustion chamber of the combustor and the ammonia in the combustion chamber is diffused and burned (see, for example, Non-Patent Document 1). The technique of Non-Patent Document 1 stabilizes the flame formed in the combustion chamber by supplying ammonia, which is the fuel, to the combustion chamber of the combustor without mixing ammonia and air in advance before supplying the ammonia to the combustion chamber. It is Stabilization of the flame in the combustion chamber is important for practical use of a combustor that uses a fuel that is difficult to ignite and has a low combustion rate such as ammonia.

Osamu Kurata, Norihiko Iki, Takayuki Matsunuma, Takahiro Inoue, Takahiro Inoue, Taku Tsujimura, Hirohide Furutani, Hideaki Kobayashi, Akihiro Hayakawa, “Performances and emission characteristics of NH3-air and NH3-CH4-air combustion gas-turbine power generations” Proceedings of the Institute 36 (2017) 3351-3359.

  Since the technology of Non-Patent Document 1 mixes fuel and air in a combustor in diffusion combustion, it becomes possible to improve flame stability, and has led to the realization of a gas turbine power generation facility using ammonia as a fuel. However, the emissions of nitrogen oxides at the combustor outlet are extremely high and this reduction is sought.

  The present invention has been made in view of the problems in the above-mentioned prior art, and it is an object of the present invention to provide a fuel combustion apparatus and a fuel combustion method for forming a stable flame and suppressing the emission of nitrogen oxides. The purpose is.

  A fuel combustion apparatus according to the present invention includes a combustor having a combustion chamber to which an oxidant, a first fuel and a second fuel are supplied, and the first fuel and the second fuel diffuse and burn. And an oxidant supply port for introducing the oxidant into the combustion chamber, a first fuel supply port disposed inside the oxidant supply port and for introducing the first fuel into the combustion chamber, and an oxidant supply port. And a second fuel supply port disposed outside and supplying a second fuel to the combustion chamber.

  A fuel combustion method according to the present invention is a fuel combustion method in which an oxidant and fuel are supplied to a combustion chamber of a combustor to diffusely burn the fuel, and a first fuel supply method is performed from a position inside the oxidant supply position. The second fuel is supplied to the combustion chamber from a position outside the supply position of the oxidant while the second fuel is supplied to the combustion chamber.

  According to the present invention, since it has the above-mentioned configuration, it is possible to form a stable flame and to suppress the discharge amount of nitrogen oxides.

FIG. 2 is a schematic view of an injection gas supply system 100. FIG. 2 is a schematic configuration example of a combustor 40. FIG. 5 is a view schematically showing a supply surface portion 42 side of the combustor 40. FIG. 6 is a plan view of the supply surface 42 of the combustor 40. It is explanatory drawing of the flow of a fuel, and the flow of an oxidizing agent. The spiral flow of the gas in the combustor 40 and the flow of the gas in the combustor 40 into the central portion of the combustor 40 are shown. It is calculation area explanatory drawing of the three-dimensional calculation for detecting the effect of embodiment. FIG. 7 is an explanatory view of suppression of nitrogen oxides generated in each part of the combustor 40 by the configuration of the combustor 40. Even when the diffusion combustion system is adopted in the combustor 40, it is an explanatory view that the mixing of the fuel and the oxidant in the combustion chamber Rm is promoted. It is an explanatory view of the amount of emission of nitrogen oxides being controlled by the composition of burner 40.

Embodiment.
FIG. 1 is a schematic view of an injection gas supply system 100 according to the embodiment. The injection gas supply system 100 is a system that is applied to, for example, a gas turbine and the like and supplies the combustor 40 with an oxidant and fuel. Typical combustion methods of the combustor include "premixed combustion" in which the fuel and oxidant are mixed in advance and supplied to the combustor, and "diffusion combustion" in which the fuel and oxidant are separately supplied to the combustor There is. The embodiment adopts diffusion combustion. In the following description, the fuel and the oxidant are also referred to as gas.

<Configuration of Embodiment>
As shown in FIG. 1, the injection gas supply system 100 has a function of swirling the gas supplied into the combustor 40 to which the oxidant, the first fuel and the second fuel are supplied, and the gas supplied into the combustor 40. And a swirl flow former 20. The swirl flow forming device 20 includes a first swirler 20A for swirling an oxidant, a second swirler 20B for swirling a first fuel, and a third swirler 20C for swirling a second fuel. . Each of the first swirler 20A, the second swirler 20B, and the third swirler 20C has a plurality of vanes that change the flow of gas (the oxidant, the first fuel, and the second fuel). That is, the blades of each swirler have the function of bending the traveling direction of the gas passing through each swirler.

  Air and pure oxygen can be employed as the oxidant. In addition, as the oxidizing agent, a mixture of nitrogen and oxygen having an oxygen concentration higher than 21% can also be adopted. In the embodiment, the case where air is employed as the oxidant will be described. The first fuel and the second fuel may be used for ammonia, a mixture of ammonia and a hydrocarbon fuel, a mixture of ammonia and hydrogen, and the like. Moreover, although the 1st fuel and 2nd fuel are the same substances (ammonia) in embodiment, even if they are different, they may be used. In the embodiment, a case where ammonia is adopted as the first fuel and the second fuel will be described.

  FIG. 2 is a schematic diagram of the combustor 40. FIG. 3 is a view schematically showing the side of the supply surface 42 in the combustor 40. As shown in FIG. FIG. 4 is a plan view of the supply surface 42 of the combustor 40. In FIG. 2, the flow FL1 shows the flow of oxidant, the flow FL21 shows the flow of the first fuel, and the flow FL22 shows the flow of the second fuel. As shown in FIG. 2, the combustor 40 is provided on a cylindrical body 41, a disk-like supply surface 42 provided on one side of the body 41, and the other side of the body 41. And a tubular head 43. In the combustor 40, a combustion chamber Rm to which an oxidant, a first fuel, and a second fuel are supplied is formed. In the supply surface portion 42, an oxidant supply port Op1 for introducing an oxidant into the combustion chamber Rm and a first fuel supply port Op21 which is disposed inside the oxidant supply port Op1 for introducing a first fuel to the combustion chamber Rm. And a second fuel supply port Op22 which is disposed outside the oxidant supply port Op1 and supplies the second fuel to the combustion chamber Rm. Further, the head portion 43 is provided with an exhaust port Op3 for discharging the gas in the combustion chamber Rm.

  As shown in FIGS. 3 and 4, the oxidant supply port Op1, the first fuel supply port Op21, and the second fuel supply port Op22 are annular openings, respectively. In the embodiment, the oxidant supply port Op1, the first fuel supply port Op21, and the second fuel supply port Op22 are formed in an annular shape.

<Operation of Embodiment>
FIG. 5 is an explanatory view of the flow of fuel and the flow of oxidant. FIG. 6 shows how the gas in the combustor 40 flows in a spiral and the gas in the combustor 40 flows into the center of the combustor 40. The oxidant flows into the combustion chamber Rm from the oxidant supply port Op1 of the combustor 40 as shown by the flow FL1 in FIG. 5, and as shown by the flow FL21 in FIG. The first fuel flows from the fuel supply port Op21 into the combustion chamber Rm, and the second fuel flows from the second fuel supply port Op22 of the combustor 40 into the combustion chamber Rm, as shown by the flow FL22 in FIG. At this time, the flow of the oxidant is sandwiched between the flow of the first fuel and the flow of the second fuel. In the combustion chamber Rm, the first fuel and the oxidant react and burn, and the second fuel and the oxidant react and burn. Further, before flowing into the combustion chamber Rm, a gas such as an oxidant passes through the swirling flow forming device 20 described in FIGS. 1 and 2. Therefore, as shown in FIG. 6, when the gas such as the oxidant flows into the combustion chamber Rm, it forms a swirling flow FLa. Here, the swirl flow FLa is a combined flow of the flow of the oxidant, the flow of the first fuel, and the flow of the second fuel. In addition, when the swirling flow FLa is formed in the combustion chamber Rm, the pressure is lowered at the central portion of the swirling flow FLa, so after flowing into the central portion of the swirling flow FLa, the head 43 side (see FIG. 2) ) To the supply surface 42 side is formed. That is, a flow FLb that flows backward is formed in the combustion chamber Rm. The formation of the flow FLb stabilizes the flame in the combustion chamber Rm.

  Here, the equivalence ratio will be described. The equivalence ratio is a numerical value representing the concentration of fuel. The equivalent ratio in the embodiment is an equivalent ratio of an oxidant (air) and a fuel (ammonia) obtained by combining the first fuel and the second fuel.

The equivalent ratio φ is expressed as the following equation (1-1).
φ = (fl1 / fl2) / (FLSO / FLSF) formula (1-1)
fl1 is the total flow rate of the first fuel flow actually supplied from the first fuel supply port Op21 and the second fuel flow actually supplied from the second fuel supply port Op22 . fl2 is a flow rate of the oxidant actually supplied from the oxidant supply port Op1.
FLSO is a theoretical value of the total flow rate obtained by combining the flow rate of the first fuel and the flow rate of the second fuel. FLSF is the theoretical value of the oxidant flow rate.

Here, the chemical reaction formula of ammonia and oxygen is as follows.
4NH ₃ + 3O ₂ = 6H ₂ O + 2N ₂
That is, ammonia and oxygen react at a ratio (molar ratio) of 4: 3. If all of the first and second fuels are ammonia and all of the oxidant is oxygen, then FLSO / FLSF = 4/3.

Therefore, the equivalent ratio φ is expressed as the following equation (1-2).
φ = (3/4) × (fl1 / fl2) formula (1-2)

  In the embodiment, the equivalent ratio φ is set to be larger than one. That is, the combined fuel of the first fuel and the second fuel is rich in oxidant. Preferably, the equivalence ratio φ is 1.2.

  In the embodiment, the volume of the first fuel supplied to the combustion chamber Rm per unit time (hereinafter also referred to as the first volume) is the second fuel supplied to the combustion chamber Rm per unit time. It is larger than the volume of fuel (hereinafter also referred to as a second volume). Also preferably, the ratio of the first volume to the second volume is 0.6: 0.4.

  Furthermore, in the embodiment, the pressure in the combustion chamber Rm is higher than the atmospheric pressure. For example, the pressure of the combustion chamber Rm can be adjusted by providing the injection gas supply system 100 with a pressure adjustment mechanism such as a valve.

<Effect of the embodiment>
The following verification is performed to verify that the effects of the combustor 40 according to the embodiment can be obtained. For verification, an experimental method or a numerical calculation method can be considered. In addition, there are methods such as DNS (Direct Numerical Simulation), LES (Large Eddy Simulation), and RANS (Reynolds Averaged Navier Stokes equation) for numerical calculation. Here, the result verified by numerical calculation by LES is shown.

FIG. 7 is a diagram for explaining a calculation area of three-dimensional calculation for detecting the effect of the embodiment. FIG. 7A shows an overall view of the calculation area. FIG.7 (b) is a longitudinal cross-sectional view of the calculation area | region of Fig.7 (a). The verification of the effects of the embodiment by three-dimensional numerical calculation will be described with reference to FIG. Each calculation area adopts a structured grid, and although not shown in FIG. 6, the number of calculation areas is about 320 million, and the lattice width of each calculation area is about 0. The volume of each calculation area is about 0.25 mm ³ .

  As the numerical calculation code, Open source Field Operation And Manipulation (OpenFOAM) was used. Basic equations were mass conservation equation, momentum conservation equation (including LES filter), and chemical species transport equation. The WALE model was used for the subgrid scale model. The Pressure Implicit with Splitting of Operators (PISO) method was used as a pressure-velocity coupled method. In addition, the convergence judgment of the numerical calculation was based on the fact that the residual mass flow rate was sufficiently small, and that the mole fraction of chemical species in the specific cross section near the combustor outlet did not change with the calculation step.

  The calculation area utilizes POINTWISE, which is a mesh generator for fluid analysis. The calculation area is created by simulating the combustor 40 shown in FIG. The area 41 t corresponds to the body 41, the area 42 t corresponds to the supply surface 42, and the area 43 t corresponds to the head 43. Further, the region Op1t corresponds to the oxidant supply port Op1, the region Op21t corresponds to the first fuel supply port Op21, the region Op22t corresponds to the second fuel supply port Op22, and the region Op3t corresponds to the exhaust port Op3. doing. Further, the region Rmt corresponds to the combustion chamber Rm.

  As shown in FIGS. 7A and 7B, the diameter of the region 41t is 72 mm, and the total length of the region 41t is 150 mm. Moreover, as shown to Fig.7 (a), the internal diameter of area | region Op1t is 14 mm, and the outer diameter of area | region Op1t is 24 mm. The inner diameter of the region Op21t is 8 mm, and the outer diameter of the region Op21t is 13 mm. The inner diameter of the region Op22t is 25 mm, and the outer diameter of the region Op22t is 30 mm. Furthermore, the diameter of the region Op3t is 36 mm. The swirl angle in the region Opt1 is 40 degrees. The swirl angles in the region Op21t and the region Op22t are also 40 degrees. The swirl angle is an angle formed by the face of the swirler blade and the region 42t corresponding to the supply surface portion 42. The swirl angle is shown as an angle θ in FIG. 7 (b). Given the inside diameter, outside diameter and swirl angle of the swirler, the swirl number is derived. Specifically, at the aforementioned swirl angle, the swirl number of the region Opt1 is 0.68, the swirl number of the region Op21t is 0.69, and the swirl number of the region Op22t is 0.77. Also, the temperature of the fuel (first fuel and second fuel) and the temperature of the oxidant are 500 (K).

  FIG. 8 is an explanatory view that the configuration of the combustor 40 suppresses nitrogen oxides generated in various places of the combustor 40. Other parameters will be described based on FIGS. 8 (a) to 8 (e) described next. FIG. 8 (a) shows the result in the conventional combustor, and the embodiment of FIG. 8 (a) has a region corresponding to the first fuel supply port Op21, but corresponds to the second fuel supply port Op22. There is no area to In FIG. 8 (a), the equivalent ratio φ of the fuel to the oxidant is 1.2, the pressure in the combustor is 0.1 (MPa), and the initial velocity of air is 29.33 (m / s) The initial velocity of the fuel is 35.46 (m / s).

  FIG. 8 (b) shows the result in the combustor 40 according to the embodiment. In FIG. 8B, the equivalence ratio φ between the fuel and the oxidant is 1.2, the pressure in the region Rmt corresponding to the combustion chamber Rm is 0.1 MPa, and the initial velocity of air is 29.33 (m / m s), the initial velocity of the first fuel is 23.73 (m / s), and the initial velocity of the second combustion is 4.53 (m / s). Further, in the embodiment of FIG. 8 (b), the volume of the first fuel supplied to the area corresponding to the combustion chamber Rm per unit time, and the volume supplied to the area corresponding to the combustion chamber Rm per unit time The ratio of the volume of fuel to 2 is 0.67: 0.33.

  FIG. 8C also shows the result in the combustor 40 according to the embodiment. In FIG. 8C, the equivalence ratio φ between the fuel and the oxidant is 1.2, the pressure in the region Rmt corresponding to the combustion chamber Rm is 0.1 MPa, and the initial velocity of air is 29.33 (m / m s). In these respects, the embodiment of FIG. 8 (c) is similar to the embodiment of FIG. 8 (b). On the other hand, in FIG. 8C, the initial speed of the first fuel is 21.36 (m / s), and the initial speed of the second combustion is 5.47 (m / s). Further, in the embodiment of FIG. 8C, the volume of the first fuel supplied to the region Rmt corresponding to the combustion chamber Rm per unit time and the region Rmt corresponding to the combustion chamber Rm per unit time are supplied. The ratio to the volume of the second fuel is 0.60: 0.40.

  FIG. 8D also shows the result in the combustor 40 according to the embodiment. In FIG. 8D, the equivalence ratio φ between the fuel and the oxidant is 1.2, the pressure in the region Rmt corresponding to the combustion chamber Rm is 0.1 MPa, and the initial velocity of air is 29.33 (m / m s). In these respects, the embodiment of FIG. 8 (d) is similar to the embodiment of FIGS. 8 (b) and 8 (c). On the other hand, in FIG. 8D, the initial speed of the first fuel is 19.60 (m / s), and the initial speed of the second combustion is 6.10 (m / s). Further, in the embodiment of FIG. 8D, the volume of the first fuel supplied to the region Rmt corresponding to the combustion chamber Rm per unit time and the region Rmt corresponding to the combustion chamber Rm per unit time are supplied. The ratio to the volume of the second fuel is 0.55: 0.45.

  FIG. 8E also shows the result of the combustor 40 according to the embodiment. Since the parameters other than the pressure of the region Rmt corresponding to the combustion chamber Rm are the same as those of the embodiment of FIG. In FIG. 8 (e), the pressure in the region Rmt corresponding to the combustion chamber Rm is 0.5 MPa.

  A region Rg1 and a region Rg2 shown in FIG. 8 indicate regions of the region Rmt corresponding to the combustion chamber Rm in which the generation amount of nitrogen oxides is increased. The generation amount of nitrogen oxides in the region Rg1 is increased to about 8000 (ppm) or more, and the generation amount of nitrogen oxides in the region Rg2 is increased to about 2000 to 6000 (ppm). As shown in the result of the conventional combustor shown in FIG. 8A, although the formation of nitrogen oxides in the central region of the region Rmt of the combustor is suppressed, the region Rg1 in FIG. As shown in and the region Rg2, the formation of nitrogen oxides can not be suppressed in a wide range of the region Rmt corresponding to the combustion chamber Rm near the inner peripheral portion of the combustor. As a result, the production amount of nitrogen oxide is as high as 1148 (ppm). On the other hand, as shown in the result of FIG. 8B, in the aspect of the combustor 40 according to the embodiment, the generation of nitrogen oxides in the central portion of the region Rmt corresponding to the combustion chamber Rm is suppressed. Instead, in comparison with FIG. 8A, the formation of nitrogen oxides in the region near the inner circumferential portion of the combustor in the region Rmt corresponding to the combustion chamber Rm is also suppressed. The production amount of nitrogen oxide is 1066 (ppm), and the aspect of the combustor 40 according to the embodiment produces the nitrogen oxide when compared with the result of the conventional combustor of FIG. 8 (a). It turns out that it is excellent in controlling.

  Further, as shown in the results of FIGS. 8C and 8D, the aspect of the combustor 40 according to the embodiment is adopted, and the ratio of the first volume to the second volume is 0. 0. The formation of nitrogen oxides can be further suppressed by setting 6: 0.4 (the embodiment of FIG. 8 (c)) or 0.55: 0.45 (the embodiment of FIG. 8 (d)) I understand. The generation amount of nitrogen oxides is suppressed to 608 (ppm) in the embodiment of FIG. 8 (c), and is suppressed to 637 (ppm) in the embodiment of FIG. 8 (d).

  Furthermore, as shown in the result of FIG. 8E, the aspect of the combustor 40 according to the embodiment is adopted, and the ratio of the first volume to the second volume is 0.6: 0.4. Further, by raising the pressure in the region Rmt corresponding to the combustion chamber Rm to 0.5 (Mpa), the formation of nitrogen oxides can be further suppressed even in comparison with FIG. 8 (c). I understand that. By raising the pressure in the region Rmt corresponding to the combustion chamber Rm, it is known that the generation of OH radicals in the combustion chamber Rm can be suppressed, and as a result, in FIG. Control has been made.

  FIG. 9 is an explanatory view that the mixing of the fuel and the oxidant in the combustion chamber Rm is promoted even when the diffusion combustion method is adopted in the configuration of the combustor 40. FIG. 9 shows the distribution of the mixed state of the fuel and the oxidant in the region Rmt corresponding to the combustion chamber Rm. Further, Z shown in FIG. 9 is called a mixing fraction, and indicates a mixing state of the fuel and the oxidant. Z = 1 corresponds to fuel only, Z = 0 corresponds to oxidant only, and Z = 0.142 corresponds to stoichiometry. The conditions of various parameters of the result shown in FIG. 9A are the same as those of the result shown in FIG. Further, conditions of various parameters in the result shown in FIG. 9B are the same as those in the result shown in FIG. As shown in FIGS. 9A and 9B, the aspect of the combustor 40 according to the embodiment is adopted, and the ratio of the first volume to the second volume is 0.6: 0. By setting it as 4, it is understood that Z is uniform, ie, without bias, throughout the combustor, and the fuel (the first fuel and the second fuel) mixes with the oxidant. In particular, in the result of FIG. 9A, it can be seen that in the region Rg10 of the central portion of the combustor, the mixing is stagnant from the inflow side to the outflow side of the gas of the combustor. As a result, it can be seen that in the region Rg11 of the central portion of the combustor, the mixing proceeds from the inflow side to the outflow side of the gas of the combustor. Thus, the configuration of the combustor 40 according to the embodiment can mix fuel (first fuel and second fuel) and an oxidant without bias, and as a result, the flame stability in the combustion chamber Rm And the formation of nitrogen oxides are suppressed.

  FIG. 10 is an explanatory view that the emission amount of nitrogen oxide is suppressed by the configuration of the combustor 40. FIG. 10 shows the results of FIG. 8 as a bar graph. 8 (a) corresponds to FIG. 10 (a), FIG. 8 (b) corresponds to FIG. 10 (b), FIG. 8 (c) corresponds to FIG. 10 (c), and FIG. 8 (d) Corresponds to FIG. 10 (d), and FIG. 8 (e) corresponds to FIG. 10 (e). As shown to FIG.10 (b)-(e), it turns out that the quantity of the nitrogen oxide produced | generated by combustion chamber Rm can be suppressed by employ | adopting the combustor 40 demonstrated by embodiment. As a result, the emission amount of nitrogen oxide of the combustor 40 can be suppressed. Further, the combustor 40 described in the embodiment performs diffusion combustion. Further, as shown in FIG. 10 (e), the pressure of the combustion chamber Rm is made higher than the atmospheric pressure (for example, 0.5 (MPa)), so that the amount of nitrogen oxides generated in the combustion chamber Rm can be reduced. It turns out that it can suppress further. As a result, the emission amount of nitrogen oxide of the combustor 40 can be further suppressed.

  The configuration and the like of the present embodiment can be applied to, for example, a fuel combustion apparatus applied to a gas turbine or the like.

  In the present embodiment, based on the above-described verification, the principle, configuration, and the like of suppressing the emissions of nitrogen oxides and ammonia by two-stage combustion are clarified. If this principle, configuration, and the like are applied to a fuel combustion apparatus such as a gas turbine or the like which provides a high temperature and high pressure environment, the effects described in the present embodiment can be obtained.

  Reference Signs List 20 swirl flow former, 20 A first swirler, 20 B second swirler, 20 C third swirler, 40 combustor, 41 barrel, 41 t area, 42 supply surface, 42 t area, 43 head, 43 t area, 100 Injection gas supply system, FLa swirling flow, Op1 oxidant supply port, Op1t area, Op21 first fuel supply port, Op21t area, Op22 second fuel supply port, Op22t area, Op3t exhaust port, Op3t area, Opt1 area Rm Combustion chamber, Rmt region, θ angle, φ equivalence ratio.

The present invention relates to a fuel combustion system and combustion method, for example, it relates to a fuel combustion system and combustion method flammability compared to the hydrocarbon-based fuel burning fuel such low ammonia such as methane.

Claims (14)

The combustor includes a combustion chamber supplied with an oxidant, a first fuel, and a second fuel, and in which the first fuel and the second fuel diffuse and burn.
In the combustor, an oxidant supply port for introducing the oxidant into the combustion chamber, and a first fuel supply port disposed inside the oxidant supply port for introducing the first fuel to the combustion chamber And a second fuel supply port disposed outside the oxidant supply port and configured to supply the second fuel to the combustion chamber. The volume of the first fuel supplied to the combustion chamber per unit time is larger than the volume of the second fuel supplied to the combustion chamber per unit time. The fuel combustion apparatus according to The fuel combustion apparatus according to claim 1 or 2, further comprising: a swirl flow former for spirally swirling the oxidant, the first fuel, and the second fuel in the combustion chamber. . The fuel according to any one of claims 1 to 3, wherein the oxidant supply port, the first fuel supply port, and the second fuel supply port are respectively provided in an annular shape. Combustion equipment. The fuel combustion apparatus according to any one of claims 1 to 4, wherein an equivalent ratio of a fuel composed of the first fuel and the second fuel to the oxidant is larger than one. The pressure of the said combustion chamber is higher than atmospheric pressure. The fuel combustion apparatus as described in any one of the Claims 1-5 characterized by the above-mentioned. The fuel combustion apparatus according to any one of claims 1 to 6, wherein the first fuel and the second fuel are ammonia. A fuel combustion method for supplying an oxidant and a fuel to a combustion chamber of a combustor and diffusing and burning the fuel,
The first fuel is supplied to the combustion chamber from a position inside the supply position of the oxidant, and the second fuel is supplied to the combustion chamber from a position outside the supply position of the oxidant. Characteristic fuel combustion method. A fuel combustion method for supplying an oxidant and a fuel to a combustion chamber of a combustor and diffusing and burning the fuel,
The oxidant is supplied to the combustion chamber from an annular oxidant supply port provided in the combustor.
The first fuel is supplied to the combustion chamber from an annular first fuel supply port provided in the combustor and disposed inside the oxidant supply port;
The second fuel is supplied to the combustion chamber from an annular second fuel supply port provided in the combustor and disposed outside the oxidant supply port. How to burn. The volume of the first fuel supplied to the combustion chamber per unit time is larger than the volume of the second fuel supplied to the combustion chamber per unit time. The fuel combustion method according to claim 8 or 9. The fuel combustion method according to any one of claims 8 to 10, wherein the oxidant, the first fuel and the second fuel are spirally swirled in the combustion chamber. . The fuel according to any one of claims 8 to 11, wherein an equivalent ratio of a fuel comprising the first fuel and the second fuel to the oxidant is set to be larger than 1. How to burn. The pressure of the said combustion chamber is made higher than atmospheric pressure. The combustion method of the fuel as described in any one of Claims 8-12 characterized by the above-mentioned. The method according to any one of claims 8 to 13, wherein the first fuel and the second fuel are ammonia.

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