JP2524002Y2 - Fuel supply pipe in gas turbine combustor - Google Patents

Description

[Detailed description of the invention]

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a fuel supply pipe in a gas turbine combustor, and more particularly, to a fuel supply pipe in a gas turbine combustor using a liquid fuel, such as liquid butane, which is easily vaporized. It is.

[0002]

2. Description of the Related Art Generally, when fuel is burned in a combustion chamber of a gas turbine combustor, fuel is sprayed from a fuel injection nozzle into the combustion chamber. For example, in a gas turbine combustor, FIG.
As shown in FIG. 4 which is an enlarged view, a plurality of nozzle bodies 2 having premixed air tubes 7 are arranged in the combustor body 1, and fuel is supplied from a fuel pipe 3 connected to the nozzle body 2 via a fuel supply path 4. The fuel F1 is injected into the premixed gas pipe 7 to form a premixed gas C, and is injected from the premixed gas injection hole 5 into the combustion chamber 6, where it is mixed with the combustion air A and burned. I have. The injection hole 8 is formed to have a very small diameter in consideration of the good mixing of the fuel and the combustion air, and the fuel pressurized to a high pressure is injected. Further, the fuel F1 supplied to each nozzle body 2 is controlled by the load of the gas turbine.

Further , Japanese Patent Application Laid-Open No. 61-90211 discloses
Therefore, the fuel injection nozzle is formed in a double pipe,
Air to the annular space between the inner and outer tubes.
Gas turbine fuel nozzles have been proposed
I have. However, this fuel injection nozzle is
Or carbon adheres to the tip of the nozzle
A small air flow around the fuel injection holes to prevent
It is designed to be distributed and supplied. Therefore, this
In the invention, the fuel is cooled by an air flow to
Proposed a fuel injection nozzle to prevent fuel vapor lock
Not.

[0004]

[Problems to be solved by the invention ]
Nozzle body 2 has a high temperature in a gas turbine combustor
Since the fuel F1 is provided in the atmosphere, for example, a liquid
If a liquid fuel that easily vaporizes, such as butane, is used,
If the supply pressure is low, vapor lock occurs in the fuel supply pipe 4,
As a result, a gas-liquid multi-phase flow
As a result, the gas-liquid multi-phase flow
When it occurs, the fuel supply can be precisely controlled
Will not be. Therefore, to prevent this gas-liquid multiphase flow
It is necessary to increase the supply pressure at
When the force is set to, for example, 100 kg / cm ² or more ,
Even if phase flow can be prevented, fuel supply equipment such as fuel control valves
Since the pressure limit is exceeded, there are problems such as fuel leakage.
Was. The present invention solves the above-mentioned problems of the prior art, and
-Accurate fuel injection without locking
To provide fuel supply pipe in gas turbine combustor
The purpose is to do so.

[0005]

[MEANS FOR SOLVING THE PROBLEMS] To achieve the above object
Fuel supply in the gas turbine combustor according to the present invention
The tube is used for gas turbine fuel that uses liquid fuel that is easy to vaporize.
In the kiln, the tip of the nozzle main body 26 is connected to the combustor main body 2.
3 and protrude inside.
A cooling air guide tube 27 is provided so as to surround the outer
In addition, the nozzle body 26 and the cooling air guide tube 27
The lower end is inserted into the upper opening of the premixed trachea 28,
The nozzle body 26 has a fuel supply passage 24 at the center thereof.
Surrounding the fuel supply passage 24, and the fuel supply passage 2
The plurality of first cooling air passages 25 are arranged in parallel to
The first cooling air passage 25 is disposed in a distributed manner.
Opening in the cooling air guide tube 27, the first cooling
The cooling air ejected from the air passage 25 is supplied to the fuel injection nozzle.
A second cooling air passage between the surroundings and the cooling air guide tube 27;
And flows outside the premixed trachea 28
The fuel injected from the injection holes 33 together with the incoming combustion air
And flows into the premixed trachea 28 while mixing.
It is characterized by doing.

[0006]

The fuel supply passage 24 is formed at the center of the nozzle body 26.
A plurality of first fuel supply passages so as to surround the fuel supply passage 24.
Cooling air passage 25 as if it were a lotus root
Place and effectively cool the fuel with cooling air while the combustion chamber
Is discharged into the cooling air guide pipe 27 provided therein, and the combustion air
And an injection hole 33 provided at an end of the fuel supply passage 24.
Mixing the cooling air with the injected fuel
The fuel can be premixed in
Gas-liquid mixed phase flow in the feed passage 24
It is possible to accurately control the injection amount without
Furthermore, there is no need to make the fuel ultra high pressure,
A vessel of normal pressure can be used.

[0007]

BRIEF DESCRIPTION OF THE DRAWINGS FIG.
An embodiment of a fuel supply pipe in a combustor will be described. Figure 1
FIG. 2 is a sectional view of the fuel supply pipe, and FIG.
And the upper part (lid part) of the gas turbine combustor main body 23
The tip of the nozzle body 26 has a high temperature atmosphere in the body 23.
It is fixed so as to protrude from the surrounding H portion. This nozzle book
The body 23 has a fuel supply passage 24 at the center thereof.
A plurality of first cooling air passages 25 are provided around the
It is arranged like a hole in a container.

An injection hole 33 is provided at the tip of the fuel supply passage 24.
Is provided, and the tip of the nozzle body 26 is provided.
Cooling air fixed to the lid of the combustor body 23 so as to surround the end
A second cooling air passage 29 is formed by providing an air guide tube 27.
And the tip of the cooling air guide tube 27 surrounding the nozzle.
The end is inserted and provided in the premixed trachea 28. Nozzle book
At the upper end of the body 26, a mounting member 32 is provided.
A fuel hole communicating with the fuel supply passage 24 opened at the center is
The feed line 30 is connected and the second
1 Cooling air supply line
Terminal 31 is connected.

A first fuel supply passage 24 is disposed around the fuel supply passage 24.
The cooling air supplied to the cooling air passage 25 is close to the nozzle.
The second cooling air in the cooling air guide pipe 27 from the side surface
Spouts into passage 29, passing around nozzle and premixed trachea
28. The fuel supply having the above configuration
In the feed pipe, a liquid that is easily vaporized, such as liquid butane
The body fuel F1 is supplied from the fuel supply line 30 to the fuel supply passage 24.
Through the injection hole 33 at the tip of the nozzle and into the premixed trachea 28
Injected to.

On the other hand, the cooling air F2 is supplied by a cooling air supply line.
A first cooling air passage 25 and a second air cooling passage
It flows through the channel 29 and is ejected from the ejection port 34 into the premixed trachea 28
I do. In this process, the liquid fuel F1 is supplied to the first cooling air
Efficient cooling by cooling air F2 flowing in the air passage 25
Not ze generate a gas-liquid multiphase flow is, therefore issued a vapor lock
Injects the liquid fuel F1 at a controlled flow rate without producing
Premixed gas is injected from the injection hole 33 into the premixed trachea 28
Can be formed. The premixed trachea 28
With the combustion air flowing through the outside of the
The air is mixed with the cooling air F2 and injected from the injection holes 33.
It mixes with the incoming fuel spray to form a premix.

As described above, the center of the cross section of the nozzle body 26 is
And a fuel supply passage 24 disposed around the fuel supply passage 24.
Opened like a lotus root in parallel with the supply passage 24
The fuel supply passage is provided by the plurality of first cooling air passages 25.
Although the liquid fuel F1 flowing in the passage 24 is not effectively cooled,
From the injection hole 33, the temperature of the liquid fuel F1 is increased.
Temperature can rise abnormally to create a gas-liquid multiphase flow.
And the liquid state can be maintained up to the injection hole 33.
Fuel, such as liquid butane, which is easy to vaporize,
Can be sprayed.

[0012]

[Effect of the Invention] The gas turbine combustor according to the present invention has
The fuel supply pipe is a gas that uses liquid fuel that is easy to vaporize.
In the turbine combustor, the tip of the nozzle body 26 is
When fixed so as to protrude inside the combustor body 23,
The cooling air guide so as to surround the
The nozzle body 26 and the cooling air
Insert the lower end of the guide tube 27 into the upper opening of the premixed trachea 28.
The nozzle body 26 has a fuel supply passage in the center.
Surrounding the fuel supply passage 24 and the fuel supply passage 24.
A plurality of first cooling air so as to be parallel to the material supply passage 24.
The air passages 25 are distributed and arranged, and the first cooling air passage
25 outlets are opened in the cooling air guide tube 27,
The cooling air ejected from the first cooling air passage 25 is
Between the periphery of the injection nozzle and the cooling air guide tube 27
2 through the cooling air passage 29,
With the combustion air flowing in and flowing outside, the injection holes 33
Surrounding the fuel to be injected and premixing while mixing
It is configured to flow into the trachea 28.

Therefore, the liquid flowing in the fuel supply passage 24
The fuel F1 is injected from the injection hole 33 while being effectively cooled.
Therefore, the temperature of the liquid fuel F1 generates a gas-liquid multiphase flow.
It does not rise abnormally. Also this injection
Since the liquid state can be maintained up to the hole 33,
Inject liquid and stable fuel such as liquid butane easily and stably
Can be. Further, a nozzle body projecting into the high-temperature atmosphere H
The tip of 26 is protected by a cooling air guide tube 27,
The cooling air is blown out inside to cool down.
The nozzles with the injection holes 33 opened at the tip are all cooled air.
To cool the nozzle and protect it from abnormally high temperatures
can do.

[Brief description of the drawings]

FIG. 1 shows the fuel in a gas turbine combustor according to the present invention .
It is sectional drawing which shows the Example of a feed pipe.

FIG. 2 is a sectional view showing a portion A in FIG . 1;

FIG. 3 shows a schematic structure of a conventional gas turbine combustor.
It is sectional drawing.

FIG. 4 is an enlarged sectional view of a portion B in FIG . 3;

[Description of Signs] 24 Fuel supply passage 25 First cooling air passage 26
Nozzle body 27 Cooling air guide tube 28 Premixed air tube 29
Second cooling air passage 30 Fuel supply line 31 Cooling air supply line 3
3 Injection hole 34 Injection port

Claims (1)

(57) [Scope of request for utility model registration] In a gas turbine combustor using a liquid fuel which is easy to vaporize , a tip end of a nozzle body (26) is provided.
When fixed so as to protrude inside the combustor body (23)
In both cases, the cooling air
An id tube (27), and further with the nozzle body (26).
Connect the lower end of the cooling air guide pipe (27) to the premixed
8), and the nozzle body (26) has a fuel supply passage (2) at the center.
4) surrounding the periphery of the fuel supply passage (24);
A plurality of first fuel cells are arranged in parallel with the fuel supply passage (24).
The cooling air passages (25) are distributed and arranged, and the first cooling
The outlet of the cooling air passage (25) is connected to the cooling air guide pipe.
(27) an opening in the first cooling air passage (25);
The cooling air that has been blown out is around the fuel injection nozzle and the cooling air.
The second cooling air passage (2) between the air guide pipe (27)
9) flow inside and outside the premixed trachea (28)
Inject from the injection hole (33) together with the inflowing combustion air
Surrounding the fuel, and mixing the premixed trachea (2
8) A fuel supply pipe in a gas turbine combustor, wherein the fuel supply pipe flows into the combustor.