JPH04136603A - Burner and combustion equipment - Google Patents

Abstract

PURPOSE:To eliminate the attachment of the liquid fuel to the inner walls of a combustion chamber, atomize the liquid fuel, and reduce NOx by forming a straight flow in the periphery of the swirl flows and spraying liquid fuel in the form of a film to the boundary between the swirl flows and the straight flow. CONSTITUTION:The liquid fuel is preheated by a preheater 70 and goes through a fuel distributor 76, fuel supply pipe 47, and fuel reservoir 46, and is supplied to the inner circumferential face on the upstream side of an inner cylinder. The combustion air that flows into the inner cylinder 45 forms swirl flows in the inner cylinder 45 by a swirler 50 and presses the liquid fuel supplied to the inner circumferential face of the inner cylinder 45 on to the inner cicumferential face to form the fuel into a film. Since the diameter of the inner circumferential face of the inner cylinder 45 is extended as it goes to the downstream side, the thickness of the fuel in the film shape becomes thinner as it goes to the downstream. The liquid fuel that reaches the downstream end of the inner cylinder 45 is blown out to the boundary face between the swirl flow formed in the inner cylinder 45 and the straight flow formed between the inner cylinder 45 and the outer cylinder 41, and atomized by receiving the shearing force generated by the actions of the swirl flows and the straight flow.

Description

Detailed Description of the Invention 3.1 [Field of Industrial Application] The present invention provides a combustor that prevaporizes liquid fuel, premixes it with combustion air, and combusts it, a combustion equipment equipped with the same, and a combustion Regarding the method.

3.2 [Prior Art] 3.2.1 Premixing of Liquid Fuel In order to increase the load on the combustion gas turbine combustor, recently, liquid fuel has been vaporized (prevaporization) and mixed with air (premixing) in advance.
However, prevaporizing and premixed combustion in which fuel is ejected from the same nozzle is being used. The advantages of using premixed combustion are:
There are two main points: First, the use of premixed combustion can reduce the reaction area of combustion. In other words, the flame can be shortened and high-load combustion is possible.

Another is that NOx emissions are reduced by employing a lean fuel premix combustion method.

On the other hand, as a combustion method different from premix combustion, there is diffusion combustion in which air and fuel are ejected from different nozzles. In this combustion method, even if the fuel is burned under lean conditions, the ratio of the theoretical amount of air to the mixture of fuel and air (hereinafter referred to as the air ratio) is maintained during the mixing process of fuel and air in the combustion chamber. There is always a region where the value is close to 1. air ratio 1
The flame temperature in the vicinity is high, and therefore it is generally considered difficult to reduce NOx.

On the other hand, in premix combustion with a high air ratio, i.e., the premix combustion method in which excess air and fuel are mixed in advance and combusted,
Since fuel is burned under lean combustion conditions in all combustion regions, NOx can be easily reduced. Such a lean premix combustion method is being adopted in gas turbine combustors and the like (for example, Japanese Patent Publication No. 35016/1983).

Generally, in order to achieve premix combustion with liquid fuel, a premix combustion burner is provided that has an atomizer that atomizes the liquid fuel and an evaporation chamber that evaporates the atomized liquid fuel (gas Turbine Society Journal, Volume 16, No. 64, 4
(pages 7-55).

This premix combustion burner is required to form fine atomized particles to speed up the evaporation of fuel, and to mix the atomized particles with air to form a homogeneous pre-evaporation premixture.

Among the required conditions, as a premix combustion burner capable of forming at least fine atomized particles, for example, the 10th
There are things like the one shown in the figure (Progressive Energy Compassion Science; Prog, Energy C
ombust.

Sci, Vol. 6, pp. 233-261).

This is provided with an inner cylinder 2 on the inner circumferential surface of which liquid fuel is supplied in an air flow path 1, and a bottle 5 whose diameter increases toward the downstream side within the inner cylinder 2. Inner cylinder 2
On the inner periphery of the downstream side, a breaming surf ace 3 is formed whose diameter gradually increases toward the downstream.

The air that has gone straight through the inner cylinder 2 turns the liquid fuel into a film and guides it to the atomycin grip 4. The film-like liquid fuel that has reached the atomycin grip 4 is ejected from the atomycin grip 4 to the outer circumferential side by the air that has passed through the inner cylinder 2, and at the same time is sheared by the air that has gone straight through the outside of the inner cylinder 2. , is refined.

The atomization performance as well as the dispersion properties of the spray depend on the Vintol 5 shape. This means that the angle at which the liquid fuel is ejected relative to the air that has passed straight through the outside of the inner cylinder 2 is
This is because it is determined by the shape of .

3.2.2 Preheating liquid fuel Air is adiabatically compressed by a compressor and heated to approximately 270 to 350 degrees. In the evaporation chamber, the finely divided atomized particles are heated with combustion air and evaporated. At this time, for stable operation of the combustor, it is necessary to prevent spontaneous ignition of the spray particles. Therefore, the residence time of the sprayed particles in the evaporation chamber must be less than the spontaneous ignition time, and it is generally said that the residence time in the evaporation chamber under practical conditions is preferably about 4 m5ec or less.

On the other hand, if the residence time of the spray particles is simply made shorter than the self-ignition time, the spray particles will be supplied to the combustion chamber without being evaporated, making it impossible to reduce NOx.

Therefore, in order to evaporate the spray particles within a residence time that is less than the spontaneous ignition time, it is important to reduce the diameter of the spray particles. However, there is a limit to the reduction of eruption particle size. This limit is generally the sum of the ejected volumes divided by the sum of the spray surface areas, the so-called Sauter mean particle diameter of about 40 μm. Therefore, in order to speed up the evaporation of the eruption particles, in addition to atomizing the eruption particles, it is necessary to promote the evaporation of the eruption particles using other methods.

A possible method for this is to preheat the liquid fuel.

Liquid fuel preheating is commonly used in heavy oil fired boilers. However, this is to raise the temperature of low-grade heavy oil that has solidified at room temperature to about 80°C to fluidize it and make it possible to transport it through pipes. In other words, preheating liquid fuel in a heavy oil-fired boiler does not promote the evaporation of spray particles.

Regarding preheating to promote evaporation of seismic particles, for example, there is a method described in Japanese Patent Publication No. 14325/1983. In this method, the liquid fuel is preheated to a temperature higher than the boiling point in the ejection atmosphere, and then ejected into the evaporation chamber through the pores.

The fuel ejected from the pores causes a so-called reduced-pressure boiling phenomenon in the ejection atmosphere, becomes atomized due to volume expansion at this time, and evaporates.

3.2.3 Treatment of combustion intermediates Currently, NOx, Co
is subject to regulation as an environmental pollutant, and appropriate combustors and denitrification equipment are installed to meet the emission standards. However, for example, combustion intermediate products such as aldehydes are not subject to regulations and are currently not treated.

3.3 [Problems to be solved by the present invention] 3.3.1
Premixed Combustion of Liquid Fuel The atomizer as described above is used as an atomizer in a combustor that burns with a large amount of air, such as a gas turbine, because it atomizes the liquid with little pressure loss.

However, in order to supply atomized particles to a narrow space such as an evaporation chamber, it is necessary to supply fine jets mixed with air at a small spray angle. In order to obtain a small spray angle, it is necessary to reduce the spread angle of the bottle, but with a small spread angle, the shearing force caused by the contact between the air on the inner and outer sides is weakened, providing a good fine spray. I can't do it anymore.

If a fine spray cannot be supplied, the evaporation time of the spray particles in the evaporation chamber is proportional to the square of the spray particle diameter, so the time required for evaporation will increase, and the liquid fuel will not be able to achieve the pre-evaporation and premixing state. It ends up being supplied to the combustion space. If preevaporation and premix combustion cannot be achieved, low NOx combustion will inevitably also not be achieved.

Furthermore, when the spray angle is increased, the spray particles adhere to the inner wall of the evaporation chamber. Anything that adheres to the inner wall of the evaporation chamber is difficult to evaporate, and evaporation of the liquid fuel is inhibited. For this reason, low NO
Preevaporation and premix combustion suitable for x-combustion cannot be achieved.

Further, by increasing the spray angle, it is possible to make the spray particles finer, but it is very difficult to uniformly diffuse the liquid fuel, which has formed into a film and spread in a plane, in a three-dimensional space.

As described above, in the conventional technology, it is difficult to make the liquid fuel fine and further diffuse it uniformly into the evaporation chamber, and there is a problem in that it is not possible to sufficiently reduce NOx.

3゜3.2 Preheating of liquid fuel In general, boiling of liquid fuel in piping must be avoided to ensure a stable supply of fuel.

However, in the conventional fuel preheating method, since the liquid fuel is preheated to a temperature higher than the boiling point in the ejection atmosphere, the fuel boils in the liquid fuel piping, making it impossible to achieve stable premix combustion.

In particular, in devices such as the combustor of a gas turbine for power generation, where the load must be varied in response to electricity demand, the pressure in the liquid fuel pipe increases as the load fluctuates, that is, the amount of fuel supplied changes. There is a high possibility that the fuel will boil in the pipes.

Further, although the boiling point of a liquid fuel having a single composition can be clearly defined, the boiling point cannot be clearly defined for liquid fuels commonly used because they are a mixture of substances having multiple compositions. Therefore, for example, if the average value of each composition substance is taken as the boiling point of the liquid fuel, there is a high possibility that the composition substance having a boiling point temperature lower than this average value will boil in the pipe.

On the other hand, if the temperature of the liquid fuel is not raised to a certain degree, the particle size of the spray particles will increase and the temperature difference between the boiling point and the boiling point will be large, so the fuel will be supplied into the combustion chamber in an unevaporated state. Become.

Additionally, the type of fuel supplied to the combustor often changes. Generally, fuel is supplied from a tank.

When different types of fuel are added to a tank, the fuel is replaced with new fuel only after several hours or days. During this time,
Since the fuel properties, especially the boiling point, change, there is a risk of boiling inside the pipes if the fuel is operated at a constant temperature.

As described above, in order to evaporate the liquid fuel sprayed into the evaporation chamber within a residence time within the spontaneous ignition time, it is desirable to control the liquid fuel at an appropriate temperature.

On the other hand, it is desirable for a combustor to be able to burn a wide variety of fuels for cost and operational reasons.

However, conventional combustion equipment has a problem in that it cannot burn a wide variety of fuels because it can only heat fuel to a predetermined temperature.

3.3.3 Treatment of combustion intermediates As mentioned above, among the combustion emissions, NOx and C○ are
They are subject to environmental regulations, and various measures have been taken to address them, but unreacted intermediate substances other than NOx and C○ that are generated during the oxidation process of fuel are subject to regulations as trace products. The current situation is that no countermeasures have been taken so far.

However, even if the amount of the product is small, the impact on the environment cannot be underestimated. Combustion intermediates are a particular problem when burning alcohol-based fuels such as methanol. The combustion of alcohol-based fuel, that is, the oxidation reaction, changes into carbon oxides and water via intermediate products having carboxyl groups such as aldehydes. However, since intermediate products such as aldehydes can exist stably by themselves, if the combustion reaction is insufficiently performed, they are discharged from the combustor system.

There is a problem in that such intermediate products cannot be sufficiently treated with existing environmental equipment such as denitrification equipment installed downstream of the combustor.

3.3.4 Purpose of the Invention The present invention has been made by focusing on the above-mentioned conventional problems.

A first object of the present invention is to provide a combustor, gas turbine equipment, combustion equipment, combustion method, and liquid fuel preheating method that can reduce NOx while ensuring stable premix combustion even in liquid fuel. Our goal is to provide the following.

A second object of the present invention is to provide a combustion equipment and a preheating method that can heat various liquid fuels to a temperature that corresponds to the liquid fuel, and can combust various liquid fuels.

Furthermore, a third object of the present invention is to provide a combustion equipment and a method for processing combustion intermediates that emit less combustion intermediates that pollute the environment, such as aldehydes that are easily generated during the combustion process of alcohol-based fuels. It's about doing.

3.4 [Means for solving the problem] 3.4.1 Means for solving the first objective A combustor for solving the first objective ejects liquid fuel together with combustion air, In a combustor equipped with a premix combustion burner configured with an atomizer that erupts the liquid fuel, the atomizer moves almost straight downstream to an inner cylinder whose inner peripheral surface is supplied with the liquid fuel. an outer cylinder that forms a flow path for the combustion air between the inner cylinder and the outer circumferential surface of the inner cylinder; and a swirling flow guide plate that swirls the combustion air sent into the inner cylinder while directing it toward the downstream side. substantially downstream of the center of the swirling flow and near the outlet of the premix combustion burner, the cross-sectional area on the downstream side sharply decreases,
The present invention is characterized in that it includes a resistor that acts as a resistance to the premixed gas ejected from the premixed combustion burner.

Here, it is preferable that the diameter of the inner peripheral side of the inner cylinder of the atomizer increases toward the downstream side. moreover,
In the combustor, the inner peripheral surface and the outer peripheral surface of the inner cylinder of the atomizer are in contact with each other at an acute angle at the downstream end of the inner cylinder, and the opening area of the inner cylinder is It is preferable that the opening areas between the outer cylinder and the outer cylinder are substantially equal, and that the downstream end of the outer cylinder is located downstream of the downstream end of the inner cylinder.

Further, another combustor for achieving the first objective is a combustor equipped with a premix combustion burner having a space for mixing liquid fuel and combustion air, in which combustion air is provided in the space. a swirling flow forming means for forming a swirling flow, a straight flow forming means for forming a straight flow of combustion air flowing toward the downstream side around the swirling flow, and a boundary between the swirling flow and the straight flow. a liquid fuel supply means for supplying the liquid fuel; and a liquid fuel supply means for supplying the liquid fuel, and a gas generated by combustion of the premix gas ejected from the premix combustion burner near the outlet of the premix combustion burner on the downstream side of the center of the swirling flow. and circulating flow forming means for forming a circulating flow of combustion gas.

Here, the swirling flow forming means is specifically constituted by a vane, a nozzle, etc., arranged so that the combustion air can swirl. Further, the circulating flow forming means can be constituted by a resistor whose cross-sectional area on the downstream side becomes suddenly smaller.

Further, the combustion equipment for achieving the first objective includes a combustor that premixes combustion air and atomized liquid fuel in a premix combustion burner and combusts this in a combustion chamber. In the combustion equipment, when the boiling point temperature in the spray atmosphere of the constituent material having the lowest boiling point temperature among the constituent substances of the liquid fuel is T°C, before the liquid fuel is supplied to the premix combustion burner, The present invention is characterized in that it includes a heating means for heating the liquid fuel within a range not exceeding T'C.

Here, the heating means heats the liquid fuel at TXo, 8°C.
It is preferable to heat to a temperature higher than that.

Further, the combustion equipment for achieving the second objective includes a determining means for determining the type of liquid fuel, and a boiling point of a component having the lowest boiling point temperature among the components of the liquid fuel whose type has been determined. A boiling point calculating means for calculating the temperature, a heating temperature determining means for determining the heating temperature of the liquid fuel based on the calculated boiling point temperature, and a heating means for heating the liquid fuel to the determined heating temperature. It is characterized by this.

Here, the determining means may be configured to determine the type of the liquid fuel based on physical property values before and after the liquid fuel is heated.

Further, the combustion equipment for achieving the third objective is a combustion equipment equipped with a combustor that discharges combustible combustion intermediate products, and includes an absorption liquid that absorbs the combustion intermediate products and a combustion intermediate product that absorbs the combustion intermediate products. The combustor is characterized by comprising: an absorption device that reacts with the combustor intermediate product, and an absorption liquid injection ratio device that injects the absorption liquid that has absorbed the combustor intermediate product into the combustion chamber of the combustor. .

The combustor may include any type of combustor that premixes liquid fuel with combustion air and then combusts it, such as a combustor for a gas turbine, a boiler, a reactor in a chemical plant, an incinerator, etc. Contains.

(Left below) 3.5 [Operation 3.5.1 Premixed Combustion of Liquid Fuel The combustion air flowing into the inner cylinder forms a swirling flow inside the inner cylinder by the swirling flow guide vanes. The swirling combustion air presses the liquid fuel supplied to the inner peripheral surface of the inner cylinder onto the inner peripheral surface to form a film. At this time, if the diameter of the inner circumferential surface of the inner cylinder increases toward the downstream side, the film-like liquid fuel becomes thinner as it flows downstream, and the liquid fuel becomes finer. can be achieved.

The liquid fuel that has reached the downstream end of the inner cylinder is ejected at the boundary between the swirling flow formed inside the inner cylinder and the straight flow formed between the inner cylinder and the outer cylinder, where the swirling flow with different directions is formed. Due to the action of the straight flow and the shearing force, it is made fine. Preheating the liquid fuel is very effective in making the fuel finer. By heating the fuel to near its boiling point, its surface tension can be significantly reduced, and the diameter of the spray particles can be reduced to almost the limit for making the fuel finer. , it can be about 40 μm.

The straight flow prevents the liquid fuel ejected from the inner cylinder from adhering to the inner wall of the evaporation chamber. The swirling flow also pulls the spray particles toward the center of the swirl to prevent them from adhering to the walls of the evaporation chamber. When the liquid fuel adheres to the inner wall of the evaporation chamber, it becomes difficult to evaporate, and the unvaporized liquid fuel is sent into the combustion chamber, making it impossible to perform lean premix combustion. This is to prevent adhesion to the walls of the evaporation chamber.

In order to more effectively prevent the spray particles from adhering to the inner wall of the evaporation chamber, it is preferable that the downstream end of the outer cylinder be located downstream of the downstream end of the inner cylinder. This is because with this configuration, a straight flow can be ensured in the vicinity of the wall of the evaporation chamber.

In this way, by spraying a film of liquid fuel at the boundary between the swirling flow and the straight flow, which have different directions, it is possible to more effectively atomize the liquid fuel and prevent the fuel from adhering to the inner wall of the evaporation chamber. can be prevented.

As described above, the liquid fuel spray particles are attracted to the center of the swirl due to the swirling flow. By the way, the flow path area of the straight flow, that is, the opening area of the inner cylinder, and the flow path area of the swirling flow,
In other words, if the opening areas between the inner cylinder and the outer cylinder are equal, the air velocity distribution in the downstream direction within the evaporation chamber will be approximately equal. On the other hand, since the amount of fuel per unit volume is large at the center of the swirling flow, the amount of fuel per unit volume of air is also large. Looking at this from the viewpoint of air ratio, the air ratio is low at the center of the swirl and increases as it approaches the outside of the swirl, that is, near the evaporation chamber.

Conventionally, to reduce NOx with a premixed flame of liquid fuel,
Combustion with excess air is the mainstream technology, but as a result of extensive research, the inventors have discovered that they circulate high-temperature combustion gas in the center of a premixed gas jet of fuel spray vapor and combustion air, thereby reducing the It has been revealed that if combustion air or combustion gas is mixed with the premixed gas on the outer peripheral side before the gas is combusted, the flame can be stabilized and NOx can be reduced. The combustion gas introduced into the center of the premixed gas jet ignites the premixed gas by transferring heat therefrom, thereby stabilizing the flame. This flame propagates from the center of the jet toward the outside of the jet. On the outer peripheral side of the jet flow, a mixed gas of the premixed gas and the combustion gas or combustion air is formed, so the fuel density here is low and the generation of thermal NOx is suppressed.

Furthermore, in order to make this combustion method effective, at least the premixed gas that is ignited first must have no fuel droplets, and the fluctuating velocity of the premixed gas at the outlet of the premixed burner must be lower than the mainstream average velocity. It is important that it be at least 10% or less. When the premixed gas that is first ignited does not have fuel droplets, the unevaporated fuel droplets contained in the premixed gas will evaporate as the fuel mixture temperature rises due to radiation from the flame. Since lean premix combustion can be achieved, low NOx combustion can be achieved. Further, if the fluctuation in the injection speed of the fuel premixture is small, the premixed gas is less likely to flashback, and stable combustion can be achieved.

As one means to realize such a combustion method,
There is a flame holder. One of the simplest structures of flame stabilizers is a resistor whose cross-sectional area on the downstream side decreases rapidly. When the jet collides with this resistor, a circulation flow is formed downstream of the resistor, into which high-temperature combustion gas flows.
The effects described above can be obtained.

One way to promote mixing of combustion gas or combustion air from around the premixed gas jet is to use a combustor structure that ejects the premixed gas as a straight flow and allows the combustion gas to circulate around the premixed gas jet. Alternatively, there is a method of constructing a combustor in which the premixed gas jet is ejected as a straight flow and combustion air is ejected around the premixed gas jet.

Furthermore, in order to promote mixing of the premixed gas jet and the combustion gas or combustion air, it is preferable to eject the premixed gas jet and the combustion gas or combustion air with a speed difference between them.

Specifically, it is preferable to provide a combustion air flow path or a combustion air nozzle close to the premix combustion burner, and to make the ejection speed of the combustion air or combustion air smaller than the ejection speed of the premix gas.

According to the present invention, the above-mentioned resistor is provided almost downstream of the swirling flow formed in the evaporation chamber, so the air ratio of the mixed gas near the resistor is low, and the air ratio from the resistor to the resistor is low. As the distance increases, the air ratio of the gas mixture increases. In such a case, the air ratio at the center of the swirling flow, that is, near the resistor, may be as long as it can be ignited by high-temperature combustion gas, and the average air ratio of the premixed gas ejected from the premix combustion burner is: A stable flame can be formed even at high temperatures.

Therefore, a stable flame can be formed, and the average air ratio of the premixed gas can be increased, so that NOx can be reduced.

3.5.2 Preheating of liquid fuel It is desirable that the residence time in the evaporation chamber be constant from the viewpoint of fuel evaporation, but due to the operating characteristics of the gas turbine, the amount of combustion air increases and the residence time in the evaporation chamber increases. It may be shorter.

At this time, since the spray particles flow into the combustion chamber without completing their evaporation, lean premix combustion cannot be achieved and NOx cannot be reduced.

Conversely, the amount of combustion air may decrease and the residence time of the spray particles may become longer. If this residence time is too long, ignition will occur in the evaporation chamber, making it impossible to safely operate the combustor.

Therefore, in order to completely evaporate the spray particles before they spontaneously ignite, it is advisable to preheat the liquid fuel before spraying it.

The heating temperature range is defined as the boiling point temperature in the spray atmosphere of the constituent material with the lowest boiling point temperature among the constituent substances of the liquid fuel.
℃, X℃≧Temperature of the liquid fuel≧XX0.8℃.

By setting the upper limit of the heating temperature to X'C, even if the pressure in the liquid fuel pipe changes to change the amount of liquid fuel supplied, even the composition substance with the lowest boiling point temperature will still reach its boiling point in the pipe. The combustor can be operated stably with very little noise.

The atomized particles are heated to boiling point temperature from the time they are ejected from the atomizer into the evaporation chamber until they evaporate;
The time required is the sum of the evaporation time from when the boiling point temperature is reached until evaporation.

By setting the lower limit of the heating temperature to xxo, s°C, almost no heating time is required. Furthermore, since the surface tension of the liquid can be made very low, the spray particle size can be reduced almost to the limit. particle size 2
Since the power is proportional to the evaporation time, the evaporation time can also be made very short. Therefore, if you preheat like this,
Since the spray particles evaporate in a very short time, the residence time of the spray particles in the evaporation chamber can be set to be less than the spontaneous ignition time, and the spray particles can be evaporated within the residence time. If the seismic particles can be reliably evaporated in the evaporation chamber, the fuel will not burn in the form of atomized droplets, and therefore NOx can be reduced.

As mentioned above, it is desirable for combustors such as gas turbine combustors, boilers, and incinerators to be able to burn a wide variety of fuels for cost and operational reasons, but each type of fuel has different flow characteristics. Due to the changes, operation management is difficult and cannot be realized.

Therefore, in the present invention, a means for determining the type of liquid fuel is provided, and a heating means is provided for heating the fuel according to the determined type.

By heating according to the type of liquid fuel, even if the type of liquid fuel is different, the flow characteristics etc. can be kept almost constant, and stable operation can always be performed.

In order to determine the type of liquid fuel, the relationship between density, vapor partial pressure, surface tension, optical refractive index, etc., and temperature must be verified for each type of liquid fuel in advance. This can be determined by actually measuring these values for the fuel in question and comparing them with the verified values.

In order to make a more accurate determination, it is recommended to refer to measurements taken at two locations: upstream and downstream of the preheater. Further, different physical properties such as density and surface tension may be measured at two locations.

Since liquid fuel is generally composed of multiple substances, its boiling point cannot be clearly determined.

Therefore, it is preferable to determine the heating temperature based on the boiling point temperature of the assembled acid substance having the lowest boiling point temperature among the constituent substances. This is because boiling can be prevented at locations where boiling is undesirable, such as inside piping.

3.5.3 Treatment of Combustion Intermediates For example, when alcohol-based fuel is burned, combustion intermediates such as aldehydes are produced. Although this substance pollutes the air, it is not subject to regulation and is currently largely untreated.

Therefore, combustion intermediate products can be removed from the exhaust gas by providing an absorption device in the exhaust gas line that injects an absorption liquid that absorbs these substances.

The combustion intermediate product is injected into the combustion chamber together with the absorption liquid by an absorption liquid injection ratio device. The combustion intermediates come into contact with the high temperature combustion gas in the combustion chamber and are thermally decomposed into, for example, H2O and CO2.

On the other hand, the flame is cooled by the absorbing liquid and thermal NOx is reduced.

In this way, by absorbing combustion intermediate products with the absorption liquid and spraying this into the combustor, thermal NOx can be reduced and the combustion intermediate products can be treated.

If the combustor that generates combustion intermediates is for a gas turbine, the atomized particle size of the absorption liquid should be as small as possible, and the flow rate should be such that the absorption liquid can be completely evaporated in the combustor. Preferably limited. This is because if all evaporation is not completed within the combustion chamber, not only will it not be possible to sufficiently reduce the temperature within the combustor chamber due to evaporation, but also unevaporated droplets will collide with the turbine blades and generate two lotions. be.

(The following is a blank space.) 3.6 [Example 3.6.1 First Example Hereinafter, a first example of the present invention will be described using FIGS. 1 to 7.

The combustor of this embodiment is a combustor for a gas turbine, and as shown in FIG. 1 and FIG.
A pilot burner 2o is installed in the center of the combustion tube 10 on the upstream side of the combustion chamber 10, and a plurality of premix combustion burners 30, 30.・・・
-, a liquid fuel preheater 70, and a casing 15 that houses them.

The inside of the combustion tube 10 is a combustion chamber 11, and the annular flow path formed between the combustion tube 10 and the casing 15 is a wind box 16.

The premix combustion burner 30 includes an atomizer 40 that atomizes liquid fuel, and an evaporation chamber 31 that evaporates the atomized liquid fuel and premixes it with combustion air.

The atomizer 40 is provided on the upstream side of the evaporation chamber 31, and includes an outer cylinder 41, an inner cylinder 45 attached concentrically to the outer cylinder 41, and a swirling flow of combustion air within the inner cylinder 45. The structure includes a swirler 50 that is provided to

As shown in FIG. 3, the downstream inner circumferential surface of the inner cylinder 45 is
The diameter increases toward the downstream side, and the downstream end 49 that contacts the outer circumferential surface of the inner cylinder 45 has a nerf edge cross section, and the inner circumferential surface and the outer circumferential surface of the inner cylinder 45 contact at an acute angle. ing. A fuel reservoir 4 is provided on the inner periphery of the upstream side of the inner cylinder 45.
6 is formed. The fuel reservoir 46 includes a fuel distributor 7.
6 is connected to the fuel supply pipe 47.

Furthermore, a wind box 1 is provided on the upstream side of the inner cylinder 45.
Air inflow hole 4 for guiding the combustion air of No. 6 into the inner cylinder 45
8 is provided.

The swirler 50 provided inside the inner cylinder 45
Support 51 is provided in the center of 5 and has a cylindrical shape.
and a plurality of swirling flow guide vanes 52 provided radially thereon.

An air inflow hole 42 is provided on the upstream side of the outer cylinder 41 to guide combustion air from the wind box 16 into an air flow path formed between the inner cylinder 45 and the outer cylinder 41. The air inflow hole 42 has a bell mouth shape to reduce resistance when air flows in. Downstream end 4 of outer cylinder 41
3 is located downstream of the downstream end 49 of the inner cylinder 45.

The air flow path area in the inner cylinder 45 and the inner cylinder 45 and outer cylinder 4
The air flow path areas between the two air flow paths are approximately equal so that the flow rates of combustion air flowing through the respective air flow paths are equal.

At the downstream end of the evaporation chamber 31, that is, approximately at the center near the outlet of the premix combustion burner 30, a conical resistor 35 with its apex facing upstream is provided. This resistor 35 is connected to the evaporation chamber 3
It is supported by a resistor support 36 provided on the inner peripheral surface of 1.

An air nozzle 60 is provided around the premix combustion burner 30 to blow out combustion air. The air nozzle 60 communicates with the wind box 16, and an air flow control valve 61 for regulating the flow rate of combustion air is provided at this communication location.

As shown in FIG. 2, the pilot burner 20 has a pilot fuel nozzle 21 at its center that spouts pilot fuel 26 in the form of a conical film. An atomization air nozzle 22 is provided around the pilot fuel nozzle 21 to eject air 27 for atomizing the film-like pilot fuel 26 into fine fuel droplets. Furthermore, an air nozzle 23 is provided around the nozzle 23 for ejecting air for combustion of pilot fuel. A swirler 24 is provided inside the air nozzle 23 in order to swirl the combustion air jetted out.
is provided.

The preheater 70 is provided in the wind box to heat the liquid fuel using the heat of the heated combustion air.

The preheater 70 is connected at its upstream side to a fuel tank (not shown), and has a measuring device 71 that measures the density and temperature of the liquid fuel and a fuel flow rate that adjusts the flow rate of the liquid fuel supplied to the preheater 70. A control valve 72 is provided. On the other hand, the downstream side of the preheater 70 is connected to a fuel distributor 76 for supplying equal amounts of liquid fuel to the respective premix combustion burners 30, 30, . The fuel distributor 7 is provided with a measuring device 73 for measuring the density and temperature of the liquid fuel between the fuel distributor 76 and the preheater 70.
6 is provided with a fuel return valve 75 for returning fuel to the fuel tank.

A measuring device 71 is installed in the fuel flow rate control valve 72 and the return valve 75.
．． A control device 74 is connected which controls these valves 72, 75 based on signals from 73. This control device 7
4 includes a function to determine the type of liquid fuel based on the measurement results of the measuring instruments 71 and 73, and a function to calculate the boiling point temperature in the fuel injection atmosphere of the composition substance with the lowest boiling point among the determined composition substances of the liquid fuel. It has a function of determining the heating temperature of the fuel based on the calculated boiling point temperature and controlling the valve opening degree of each valve 72 and 75.

Next, the operation of this embodiment will be explained.

First, the operation of the pilot burner 20 will be explained.

The pilot fuel 26 is injected from the pilot fuel nozzle 21 into the combustion chamber 11 in the form of a conical film.

The atomizing air 27 is ejected from the atomizing air nozzle 22 toward the pilot fuel 26 ejected in a conical film shape at a speed of about 100 to 200 m/s. The atomization air 27 applies a strong shearing force to the liquid film, and the pilot fuel 26 is atomized.

The micronized pilot fuel 26 is combusted by combustion air jetted from the air nozzle 23. At this time, the combustion air forms a swirling flow by the swirler 24 provided in the air nozzle 23, so a flow toward the upstream side is formed downstream of the pilot fuel nozzle 21, which is the center of swirling. Ru. Therefore, high-temperature combustion gas flows therein, and the finely divided pilot fuel 26 is heated and ignited.

The flame from the pilot burner 20 is transmitted through a separate nozzle 21
．． Combustion air and pilot fuel 26 ejected from 23
This is a so-called diffusion flame formed by For this reason, the pilot flame is stably formed even if the amount of fuel supplied is changed. However, in a diffusion flame, a high-temperature area is always formed where combustion occurs at the stoichiometric air ratio, so a large amount of NO
x occurs. To prevent this, the pilot burner 20 is mainly used when the load is low, such as when starting the combustor, and the premix combustion burner 3o is mainly used when the load is high.

Next, combustion in the premix burner 30 and preheating of the liquid fuel supplied to the premix burner 3o will be explained.

Premix combustion burner 30 from a fuel tank (not shown)
,30. The liquid fuel supplied to... is preheated by the preheater 70.

This preheating method will be explained in detail.

The density and temperature of the liquid fuel are measured by measuring devices 71, 73. The relationship between density and temperature of various liquid fuels has been verified in advance, and based on this relationship and the measured results, the control device 74 determines the type of liquid fuel and selects the composition with the lowest boiling point among the constituent materials of the liquid fuel. Calculate the boiling point temperature of the substance in the fuel ejection atmosphere. Then, the heating temperature of the liquid fuel is determined based on this calculated boiling point temperature.

In this way, since the heating temperature is determined by determining the type of liquid fuel, even if the type of liquid fuel changes, the heating temperature corresponding to the fuel can be determined. Measuring device 7
1.73 are provided on the upstream and downstream sides of the preheater 70 in order to accurately grasp the physical properties of the liquid fuel and accurately determine the type of liquid fuel. Although the type of liquid fuel is determined based on the density of the liquid fuel in this embodiment, it may be determined based on various physical property values such as surface tension, vapor partial pressure, and refractive index of light. .

The heating temperature is set within the temperature range of X°C≧heating temperature°C≧XX0.8°C, where the calculated boiling point temperature is X°C.

By setting the upper limit of the heating temperature to X'C, even if the pressure in the liquid fuel pipe changes to change the amount of liquid fuel supplied, even the composition substance with the lowest boiling point temperature will still reach its boiling point in the pipe. There are very few.

The lower limit of the heating temperature is determined through tests as a value that allows efficient atomization of the liquid fuel.

The relationship between the atomization of liquid fuel and temperature will be described later.

The preheated liquid fuel is supplied to the premix combustion nozzle 30. There, liquid fuel is atomized by an atomizer 40, evaporated and premixed in a combustion chamber 31, and combusted at a burner outlet.

Hereinafter, the atomization process, evaporation premixing process, and combustion process will be explained in this order.

The preheated liquid fuel passes through the fuel distributor 76, the fuel supply pipe 47, and the fuel reservoir 46, and is supplied to the upstream inner peripheral surface of the inner cylinder.

The combustion air flowing into the inner cylinder 45 forms a swirling flow within the inner cylinder 45 by the swirler 50 .

The swirling combustion air presses the liquid fuel supplied to the inner peripheral surface of the inner cylinder 45 onto the inner peripheral surface to form a film. Since the diameter of the inner circumferential surface of the inner cylinder 45 increases toward the downstream side, the film-like liquid fuel becomes thinner as it flows downstream.

The liquid fuel that has reached the downstream end of the inner cylinder 45 is ejected onto the interface between the swirling flow formed within the inner cylinder 45 and the straight flow formed between the inner cylinder 45 and the outer cylinder 41, where Due to the action of swirling flow and straight flow, it is subjected to shearing force and becomes fine. Preheating liquid fuel is very effective in making fuel fine.
As mentioned above, by heating the fuel to near its boiling point, its surface tension is significantly reduced, forming particles with a diameter of about 40 μm, which is almost the limit of miniaturization.

The flow rates of the air forming the swirling flow and the straight flow are approximately equal because the respective air flow path areas are equal.

Therefore, the respective flow velocities in the downstream direction become equal, so there is little turbulence in the flow, and the straight flow and swirling flow can be maintained relatively downstream.

The straight flow suppresses the liquid fuel ejected from the atomizer 40 from adhering to the inner wall of the evaporation chamber 31 . When the liquid fuel adheres to the inner wall of the evaporation chamber 31, it becomes difficult to evaporate, and the liquid fuel that is not vaporized is sent into the combustion chamber 11. When liquid fuel that has not been vaporized is combusted, a large amount of NOx is generated, similar to diffusion combustion. In order to prevent this, it is significant that a straight flow is formed along the inner wall of the evaporation chamber 31.

On the other hand, the swirling flow draws the liquid fuel jet particles to the center of the swirl. Therefore, the concentration of spray particles in the evaporation chamber 31 is high near the center axis of the atomizer 40 and decreases toward the inner wall of the evaporation chamber 31. By the way, as described above, since the air velocity distribution within the evaporation chamber 31 is approximately uniform, the ratio of the spray particle flow rate to the unit air flow rate decreases from the central axis of the atomizer toward the outer circumference. Considering the atomized particle concentration from the viewpoint of air ratio, the air ratio increases from the center of the evaporation chamber 31 toward the inner peripheral wall of the evaporation chamber.

Note that the swirl flow also contributes to preventing the spray particles from adhering to the evaporation chamber 31 by gathering the spray particles toward the center of the swirl.

In the process of the eruption particles flowing downstream of the evaporation chamber 31,
It is heated by the combustion air heated to about 350° C., evaporates, and mixes with the combustion air to form a premixed gas.

The atomized particles require a total time of time to be heated to the boiling point (heating time) and time to evaporate after reaching the boiling point (evaporation time) from the time they are ejected from the atomizer 4o until they evaporate. By the way, since the liquid fuel is heated to near the boiling point temperature by the preheater 7o, the heating time is hardly required. Further, since the evaporation time is proportional to the square of the particle size, the evaporation time of spray particles reduced to near the limit of the particle size is extremely short.

Therefore, the eruption particles evaporate in a very short time,
The residence time of the spray particles in the evaporation chamber can be set to be less than the spontaneous ignition time, and the spray particles can be evaporated within the residence time.

A test regarding the air ratio distribution at the outlet of the evaporation chamber was conducted, and this test will be explained below.

The test conditions were: inner diameter of the evaporation chamber 80 mm, wind tower speed of the evaporation chamber 70 m/s, length of the evaporation chamber 0.3 m, and an air jet velocity of 140 m for downstream swirling flow and straight flow at the atomizer outlet. /s, an angle of 30'' with respect to the central axis of the swirl flow guide vane.

The test results under these conditions are shown in FIG. In addition, in the same figure,
The vertical axis shows the air ratio, and the horizontal axis shows the value obtained by dividing the distance from the center of the evaporation chamber to the air ratio measurement position by the radius of the evaporation chamber.

In this test, the air ratio near the center of the evaporation chamber was 1°2, the air ratio near the wall of the evaporation chamber was 1.6, and the average air ratio was 1.4.
Therefore, the air ratio near the inner wall of the evaporation chamber was approximately 30% higher than the air ratio near the center of the evaporation chamber.

The premixed gas having such an air ratio distribution is ejected from the premix combustion burner 30 and combusted.

The premix combustion process will be explained based on FIG. 4.

The premixed gas 90 ejected from the premixed combustion burner 30 collides with the resistor 35 and creates a circulating flow region 91 on the downstream side thereof.
form. In the circulating flow region 91, the center side of the resistor 35 flows toward the upstream side, and the peripheral side of the resistor 35 flows toward the downstream side.

Furthermore, a lean premix region 93 of premix gas 90 and combustion air 92 is formed at the boundary between premix combustion burner 30 and air nozzle 60 .

Combustion gas 94 generated by combustion of the premixed gas 90 flows into the circulating flow region 91, and the circulating flow region 91 becomes high in temperature.

Due to the high temperature combustion gas 94 in the circulating flow region 91, the premixed gas 90 reaches the ignition temperature and is ignited, forming a combustion region 95 on the downstream side around the resistor 35.

Here, when paying attention to the air ratio distribution within the combustion chamber 11, the air ratio increases as the distance from the resistor 31 increases.

This means that the premixed gas 90 with a low air ratio is present near the resistor 31.
is ejected from the premix combustion burner 30, and an air nozzle 60 provided around the premix combustion burner 30
This is because the combustion air 92 is blown out from.

As mentioned above, the premixed gas 9o first passes through the resistor 35.
It ignites in contact with the high temperature combustion gas 94 on the downstream side of the flame, forming a stable premixed flame. and.

The flame propagates toward the outer periphery, where the air ratio is high and stable combustion is difficult, thereby stabilizing the combustion of the lean premixed gas. By the way, since the generated NOx decreases as the air ratio increases, the concentration of NOx generated by combustion of the premixed gas in the outer peripheral area at a high air ratio becomes extremely low.

Generally, in order to reduce NOx, the air ratio distribution of premixed gas is made uniform, but in this embodiment, the air ratio in the center of the premix combustion burner 30 is intentionally made low, and the The premixed gas 90 with a low ratio is introduced near the resistor 35 to stabilize combustion.

Note that, in order to stabilize combustion, it is also necessary to reduce speed fluctuations of the premixed gas 90 at the outlet of the premixed combustion burner 30. This is because when the speed fluctuation is large and the speed momentarily decreases, the flame flows back into the evaporation chamber 31.6 According to various experimental results, the value obtained by dividing the fluctuating speed by the average speed is If it is about 10% or less, stable combustion can be achieved. For example, if combustion air is supplied from the middle of the evaporation chamber 31 to increase the turbulence intensity and increase the homogeneity of the main gas mixture, the speed fluctuation at the outlet of the premix combustion burner 30 will increase, making combustion unstable. Therefore, backfire to the evaporation chamber 31 is likely to occur.

Further, in this embodiment, if only the premixed gas in the center of the premixed combustion burner 30 has an air ratio that can be ignited by the high-temperature circulating flow formed downstream of the resistor 35, the flame Therefore, it is not necessary to bring the entire premixed gas 90 ejected from the premixed combustion burner 30 to an ignitable air ratio. Therefore, the premixed gas 9
The overall average air ratio can be increased, and NOx can be reduced.

The effect of the air nozzle 60 provided around the premix combustion burner 30 was tested and will now be described.

As shown in FIG. 6, the combustor used in this test has a combustion chamber 80 with an inner diameter of 50 mm located at the upstream center of a combustion chamber 80 with an inner diameter of 200 mm.
mm premix combustion burner 81 is provided, and this burner 81
A disk-shaped resistor 82 with an outer diameter of 36 mrn is provided on the downstream side of the burner 81, and an air nozzle 83 having an annular shape with an inner diameter of 68 mm and an outer diameter of 78 mm is provided around the burner 81.

This test was conducted in two cases: a case in which premixed gas is ejected from the premix combustion burner 81 and combustion air is ejected from the air nozzle 83; The NOx concentration at the combustor outlet was measured in the case where no air was blown out.

The measurement results are shown in FIG. In the figure, the vertical axis is NO at the combustor outlet corrected so that the oxygen concentration at the combustor outlet is 0%.
x concentration, and the horizontal axis shows the air ratio of the premix combustion burner 81. In addition, the black circles are cases in which premixed gas is ejected from the premix combustion burner 81 and combustion air is ejected from the air nozzle 83, and the white circles are cases in which premixed gas is ejected only from the premix combustion burner 81 and combustion air is ejected from the air nozzle 83. This shows a case where no air is blown out.

In this test, it was confirmed that by separately supplying combustion air from the outer peripheral side of the premix combustion burner 81, NOx can be reduced even at the same air ratio compared to the case where combustion air is not separately supplied.

Therefore, similarly to this test, in this example, NOx can be reduced by supplying combustion air from the air nozzle 60 around the premixed gas to form a lean premixed gas.

3.6.2 Second Embodiment A second embodiment of the present invention will be described below with reference to FIGS. 8 and 9.

The gas turbine combined cycle equipment of this embodiment includes a combustor 100
and a gas turbine 111 connected to the combustor 100
, a denitrification device, an exhaust heat recovery boiler 112 , an absorption tower 113 , and a chimney 115 , which are shown in the figure and are sequentially installed on the downstream side of the gas turbine 100 .

A spray nozzle 114 that sprays water downward is provided in the upper part of the absorption tower 113. At the bottom of the absorption tower 113, the water accumulated in the lower part of the tower is transferred again to the spray nozzle 114.
A circulation pipe 116 for supplying the fuel to the combustor 100 and a supply pipe 117 for supplying the fuel into the combustor 100 are connected. A supply pump 118 is provided in the supply pipe 117 .

As shown in FIG. 9, the combustor 100 includes a combustion tube 102 forming a combustion chamber 101, a pilot burner 103 and a premix combustion burner 104 provided upstream of the combustion tube 102.
, 104. ... and a transducer 105 provided on the downstream side of the inner cylinder 102.

An orifice 1 having an opening inward of the combustion chamber 101 at a position 2/3 from the upstream side to the downstream side of the combustion tube 102
06, 106, 106 are provided. A supply pipe 117 from an absorption tower 113 is connected to this orifice 106 .

The orifice 106 is designed to use water supply pressure to spray water. Also, orifice 10
The opening diameter of No. 6 is set so that the flow rate can be limited to such that the water ejected from the orifice 106 evaporates before reaching the center of the combustion tube 102 . The reason why the spray flow rate is restricted by the orifice 106 is to prevent water from being supplied to the gas turbine 111 without being evaporated.

Next, the operation of this embodiment will be explained.

In this embodiment, alcohol is used as the fuel for the combustor 100.

When alcohol is combusted, aldehyde, which is a combustion intermediate, is produced and is supplied to the gas turbine 111 together with other exhaust gases. After passing through the gas turbine 111, the exhaust gas containing aldehyde is transferred to a denitrification device as shown in the figure.
It passes through the exhaust heat recovery boiler 112 and is sent to the lower part of the absorption tower 113.

In the absorption tower 113, water is sprayed downward from the spray nozzle 114, comes into contact with the exhaust gas rising upward, and the aldehyde in the exhaust gas is absorbed by the water. The water that has absorbed the aldehyde accumulates at the bottom of the tower 113, and part of it passes through the circulation pipe 116 and is again supplied to the spray nozzle 1146.The other part passes through the supply pipe 117 and is added by the supply pump 118. Pressured, orifice 106°106
is sprayed into the combustion chamber 101 from there.

The sprayed water comes into contact with high-temperature gas of 1400° C. or higher in the combustion chamber 101. The sprayed water lowers the temperature of the high-temperature gas through vaporization heat transmission. As the temperature decreases, nitrogen in the air becomes less likely to be oxidized, and the amount of NOx produced decreases. Furthermore, aldehydes absorbed in water are hot gases,
It is thermally decomposed into H, O, CO2, etc., and is discharged from the combustor 100 together with the exhaust gas.

In this way, by absorbing aldehyde, which is a combustion intermediate product, into water and spraying it into the combustor 100, it is possible to treat aldehyde, which is an environmental pollutant, and also to reduce NOx.

Note that in this embodiment, the orifice 106 was provided at a position of 2/3 from the upstream side to the downstream side of the inner cylinder 102;
This is because water containing aldehyde is sprayed near the tip of the flame, and if the position of the tip of the flame differs due to the structure of the combustor, it is preferable to change the position of the orifice accordingly.

Furthermore, in this embodiment, an alcohol-based fuel that produces aldehyde is used as the combustion intermediate, but any fuel may be used as long as it produces a combustion intermediate that is absorbed by water.

3.7 [Effects of the Invention] According to the present invention, a straight flow is formed around the swirl flow and a film of liquid fuel is sprayed at the boundary thereof, so that the liquid fuel does not adhere to the combustion chamber wall. By making liquid fuel finer,
It is possible to reduce NOx. Furthermore, by providing a resistor almost downstream of the center of the swirling flow, a stable flame can be formed and the average air ratio of the premixed gas can be made higher, which reduces NOx. be able to.

In addition, by heating the liquid fuel to a temperature close to the boiling point of the component with the lowest boiling point among these constituent materials, it is possible to set the residence time of the eruption particles in the evaporation chamber to be less than the spontaneous ignition time, and also to be within the residence time. The spray particles can then be evaporated. Therefore, spontaneous combustion can be prevented and stable combustion can be performed, and lean premix combustion can be reliably realized, and NOx can be reduced.

Furthermore, by changing the heating temperature depending on the type of liquid fuel, stable operation can always be achieved regardless of the type of liquid fuel.

Further, by absorbing combustion intermediate products with an absorbing liquid and injecting them into the combustor, thermal NOx can be reduced and the combustion intermediate products can be treated.

[Brief explanation of the drawing]

Figures 1 to 7 show the first embodiment, where Figure 1 is a sectional view of the main part of the combustor, Figure 2 is a sectional view taken along the line ■-■ in Figure 1, and Figure 3 is a sectional view of the main part of the combustor. Overall sectional view of the mixed combustion burner, No. 4
The figure is an explanatory diagram to explain the combustion state, Figure 5 is a graph showing the air ratio distribution in the evaporation chamber, Figure 6 is a cross-sectional view of the test combustor, and Figure 7 is the relationship between air ratio and NOx concentration. Graph showing. 8 and 9 show a second embodiment, and FIG.
The figure is a system diagram of a gas turbine combined power generation facility, FIG. 9 is a sectional view of a combustor, and FIG. 10 is a sectional view of a conventional atomizer. 10... Combustion tube, 20... Pilot burner, 30...
... Premix combustion burner, 31 ... Evaporation chamber, 35 ... Resistor, 40 ... Atomizer, 41 ... Outer cylinder, 45 ...
... Inner cylinder, 50 ... Swirler, 52 ... Swirling flow guide vane, 60 ... Air nozzle, 70 ... Preheater, 71
．． 73...Measuring device, 72...Fuel flow rate control valve, 74...
...control device, 75...fuel return valve, 100...combustor, 101...combustion chamber, 106...orifice,
113・Absorption tower. 117... Supply piping, 118... Supply pump.

Claims (1)

[Scope of Claims] 1. In a combustor equipped with a premix combustion burner configured with an atomizer that injects liquid fuel together with combustion air and atomizes the liquid fuel, the atomizer has an internal an inner cylinder to which the liquid fuel is supplied to the peripheral surface, an outer cylinder that forms a flow path for the combustion air that travels substantially straight downstream to the downstream side between the outer peripheral surface of the inner cylinder; a swirling flow guide plate that swirls the combustion air while directing it toward the downstream side; A combustor characterized in that it is equipped with a resistor whose cross-sectional area is rapidly reduced and acts as a resistance to the premixed gas ejected from the premixed combustion burner. 2. In a combustor equipped with a premix combustion burner having a space for mixing liquid fuel and combustion air, a swirling flow forming means for forming a swirling flow of combustion air in the space; a straight flow forming means for forming a straight flow of combustion air flowing downstream toward the surroundings thereof; a liquid fuel supply means for supplying the liquid fuel to a boundary between the swirling flow and the straight flow; and the swirling flow. Circulating flow forming means for forming a circulating flow of combustion gas generated by combustion of the premixed gas ejected from the premixed combustion burner, substantially downstream of the center of the flow and near the outlet of the premixed combustion burner. A combustor characterized by comprising: 3. In a combustor equipped with a premix combustion burner having a space for mixing liquid fuel and combustion air, an air ratio distribution uneven distribution means for lowering the air ratio distribution in the space only at a specific location; A circulating flow forming means for forming a circulating flow of combustion gas generated by combustion of the liquid fuel and the combustion air is provided in the vicinity of the outlet of the premix combustion burner on the substantially downstream side of the location. Characteristic combustor. 4. The combustor according to claim 1, wherein the diameter of the inner peripheral side of the inner cylinder of the atomizer increases toward the downstream side. 5. The combustor according to claim 1 or 4, wherein the inner circumferential surface and outer circumferential surface of the inner cylinder of the atomizer are in contact at an acute angle at a downstream end of the inner cylinder. 6. Claim 1, wherein the opening area of the inner cylinder and the opening area between the inner cylinder and the outer cylinder are approximately equal.
The combustor according to 4 or 5. 7. The combustor according to claim 1, 4, 5 or 6, wherein the downstream end of the outer cylinder is located downstream of the downstream end of the inner cylinder. 8. Combustion according to claim 1, 4, 5, 6 or 7, comprising one or more of the premix combustion burners in which the resistor is provided near the outlet, and a diffusion combustion burner. vessel. 9. A claim characterized in that a plurality of the premix combustion burners each having the resistor provided near the outlet are provided on the same circumference, and a diffusion combustion burner is provided approximately at the center of the circumference. The combustor according to item 1, 4, 5, 6 or 7. 10. Claim 1, 2, 3, 4, 5, 6, 7, 8 or 9, further comprising a combustion air nozzle that blows out combustion air from around the outlet of the premix combustion burner.
Combustor as described. 11. The combustor according to claim 1, 2, 3, 4, 5, 6, 7, 8, 9 or 10, and a gas turbine driven by exhaust gas discharged from the combustor. Characteristic gas turbine equipment. 12. In a combustion method in which liquid fuel and combustion air are mixed in advance and then combusted, a swirling flow of the combustion air is formed while swirling toward the downstream side, and a swirling flow is formed around the swirling flow on the downstream side. forming a straight flow of the combustion air flowing toward the flow, supplying the liquid fuel in the form of a film to the boundary between the swirling flow and the straight flow, and premixing the liquid fuel and the combustion air. The premixed liquid fuel and the combustion air are ejected from the burner outlet and combusted, and the combustion gas generated by the combustion is
A combustion method characterized in that the swirling flow is temporarily circulated in the vicinity of the outlet of the burner substantially downstream of the swirling center of the swirling flow. 13. The combustion method according to claim 12, characterized in that heating is performed within a range that does not exceed the boiling point temperature in the spray atmosphere of a constituent material having the lowest boiling point temperature among the constituent substances of the liquid fuel. 14. Among the constituent substances of the liquid fuel, when the boiling point temperature in the spray atmosphere of the constituent substance having the lowest boiling point temperature is T°C, before the liquid fuel is supplied to the premix combustion burner, the liquid fuel of. 13. The combustion method according to claim 12, wherein the heating is performed within a temperature range of T°C≧temperature of the liquid fuel≧T×0.8°C. 15. In a combustion equipment equipped with a combustor that premixes combustion air and atomized liquid fuel in a premix combustion burner and combusts this in a combustion chamber, the boiling point of the constituent substances of the liquid fuel is 1. Combustion equipment characterized in that it is equipped with a heating means for heating within a range that does not exceed the boiling point temperature in the spray atmosphere of the composition substance having the lowest temperature. 16. In a combustion equipment equipped with a combustor that premixes combustion air and atomized liquid fuel in a premix combustion burner and combusts this in a combustion chamber, the boiling point of the constituent substances of the liquid fuel is When the boiling point temperature in the spray atmosphere of the constituent material having the lowest temperature is T°C, before the liquid fuel is supplied to the premix combustion burner, the temperature of the liquid fuel is T°C≧Temperature of the liquid fuel≧ T×0
．． A combustion equipment characterized in that it is equipped with a heating means for heating within a temperature range of 8°C. 17. The combustor according to claim 15 or 16, wherein the heat source in the heating means is combustion air. 18. A determining means for determining the type of the liquid fuel, and a boiling point calculating means for calculating the boiling point temperature of a constituent material having the lowest boiling point temperature among the constituent materials of the liquid fuel whose type has been determined, Claim 1, wherein the means heats the liquid fuel based on the calculated boiling point temperature.
The combustion equipment according to 5, 16 or 17. 19. A combustion equipment equipped with a combustor that burns liquid fuel, comprising: a determination means for determining the type of liquid fuel; and a heating means for heating the liquid fuel according to the determined type of liquid fuel. Combustion equipment characterized by: 20. Boiling point calculation means for calculating the boiling point temperature of a composition material having the lowest boiling point temperature among the composition materials of the liquid fuel whose types have been determined; and determining the heating temperature of the liquid fuel based on the calculated boiling point temperature. 20. The combustion equipment according to claim 19, further comprising: heating temperature determining means, wherein the heating means heats to the determined heating temperature. 21. The combustion equipment according to claim 18, 19 or 20, wherein the determining means determines the type of the liquid fuel based on physical property values before and after the liquid fuel is heated. 22. In a method for preheating a liquid fuel to be sprayed into a premix combustion burner, when the boiling point temperature in the spray atmosphere of a constituent material having the lowest boiling point temperature among the constituent substances of the liquid fuel is T°C, the liquid fuel is Before being supplied to the premix combustion burner, the liquid fuel is heated such that T°C≧temperature of the liquid fuel≧T×0
．． A method for preheating liquid fuel, characterized by heating within a temperature range of 8°C. 23. In a combustion equipment equipped with a combustor that discharges combustible combustion intermediate products, an absorption device that causes an absorption liquid that absorbs the combustion intermediate products to react with the combustion intermediate products; A combustion equipment comprising: an absorption liquid injection device that injects the absorption liquid that has absorbed generated substances into a combustion chamber of the combustor. 24. The combustion equipment according to claim 23, wherein the absorption liquid ejecting device includes an absorption liquid amount limiting means for limiting the flow rate of the ejected absorption liquid to a flow rate that can completely evaporate within the combustion chamber. 25. Claim 23 or 2, characterized in that the absorption liquid injection ratio device is equipped with a jet port for spouting the absorption liquid near the tip of a flame formed in the combustion chamber.
The combustion equipment described in 4. 26. A method for treating combustible combustion intermediate products discharged from a combustion chamber of a combustor, the method comprising: absorbing the combustion intermediate products with an absorption liquid that absorbs the combustion intermediate products; A method for treating combustion intermediates, the method comprising: spraying the absorption liquid that has absorbed into the combustion chamber.