JP2604933Y2 - Gas turbine combustor - Google Patents

Description

[Detailed description of the invention]

[0001]

The present invention relates to a gas turbine combustor,
More particularly, the present invention relates to a gas turbine combustor which uses at least two types of fuels and reduces nitrogen oxides.

[0002]

2. Description of the Related Art Generally, a method of reducing nitrogen oxides (NOx) in exhaust gas generated from a gas turbine includes:
A) a method of suppressing the generation of NOx in the combustion process, and b) a method of post-treatment by a flue gas denitration apparatus. The former includes a) water or steam injection, b) lean diffusion combustion, c) pre-evaporation / premix combustion, d) two-stage combustion, and e) catalytic combustion.

However, in such various systems,
There are various practical problems, such as a decrease in thermal efficiency and a low NOx reduction rate, as well as poor flame stability, low mechanical strength and low reliability. Under such circumstances, the present inventor accommodates a combustion cylinder that forms a diffusion combustion area, a premixed combustion area, and a main combustion area inside the combustor body, and a pilot injection valve at the top of the combustion cylinder, Further, a plurality of premixing pipes are arranged at equal intervals in the circumferential direction, and an outlet of the premixing pipe is opened toward the premixed combustion region, and a fuel injection nozzle is inserted at an inlet side for a gas turbine combustion. Vessel has been proposed (Japanese Patent Application No. 3-118603).

[0004]

In the gas turbine combustor described above, liquid fuel such as heavy fuel oil A is atomized and injected from a fuel injection nozzle inserted at the inlet side of the premixer. In this case, low NOx combustion was possible by making the fuel concentration distribution uniform, but Dual Fuel could not be performed.

The present invention makes it possible to effectively use both a liquid fuel and a gaseous fuel in the same engine of a gas turbine, and in particular, to produce a liquid fuel corresponding to the operating conditions of a chemical plant or the like. And a gas turbine combustor that can use gaseous fuel. The present invention
Gas turbine combustion that can use two types of fuels, liquid fuel and gaseous fuel, without major modification of the conventional combustor, and enables low NOx combustion by making the concentration distribution of these fuels uniform. It is intended to provide a vessel.

In order to achieve the above object, a gas turbine combustor according to the present invention comprises a combustion cylinder 2 inside a combustion chamber main body 1.
Houses, a pilot injection valve 3 at the top of the combustion cylinder 2 is provided, the combustion tube 2 is configured to form a main combustion region D and the pre-mixture combustion region C the diffusion combustion region B, the combustion equidistantly disposed a plurality of premixing tubes 6 in the circumferential direction of the chamber body 1, in the combustor which is open towards this the premixed gas combustion region C the discharge port 6a of the premixing tubes 6, the premixed between the inner central portion the fuel injection nozzle 7 fuel injection nozzles 7 of <br/> come extended to the trachea 6 and the interior of the premixing tubes 6
A cylindrical air passage is formed, and the fuel injection nozzle 7 is
A first tube 8a, to the first tube 8a and concentrically with the second tube 8b which are distribution <br/> location outside forms a double pipe structure, the first tubular 8a tip Liquid from the opened first injection port 10a
A first fuel F ₁ is a fuel is injected into the premixing tubes 6, before the second injection port 10b on the side of the second tube 8b
The second injection is opened toward the inner surface of the premixed trachea 6.
A second combustion F ₂ is a gaseous fuel from a mouth 10b, the towards the inner wall of the premixing pipe 6 so as to intersect the air flow through the air passage to the injection, further, the second fuel F ₂
Mixed with in mixture formed by mixing with air, the first fuel F ₁ injected from the distal end of said first tube 8a
After the mixture is formed by evaporating the liquid fuel, the mixture is injected from the premixed air pipe 6 into the premixed gas combustion region C.

[0007] In the gas turbine combustor according to the present invention configured as described above, the gas turbine combustor is provided in the premixed pipe 6.
The first fuel which is a liquid fuel from the tip of the fuel injection nozzle 7
Injecting F ₁ nebulized further and the fuel injection nozzle 7 pre
Air flowing through a cylindrical air passage between the inner walls of the mixing pipe 6
The fuel is injected from the periphery of the fuel injection nozzle 7 so as to intersect the flow.
Inject and mix the second fuel F ₂ , which is a body fuel,
Mixing said first fuel F ₁ at the downstream side of the mixed gas
Liquid fuel diffuses into the gas mixture.
And evaporates effectively to become gaseous. And the first fuel
F ₁ and mixed gaseous fuel of the second fuel F ₂ is pre
Supplied to the premixed gas combustion region C from the outlet 6a of the mixed gas pipe
And is uniformly burned by the flame in the diffusion combustion zone C.
Combustion at low temperatures and low-temperature combustion that does not generate NOx
It is a function.

[0008]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, an embodiment of a gas turbine combustor according to the present invention will be described with reference to FIGS. FIG.
FIG. 2 is a sectional view of a main part of a combustor for a gas turbine, and FIG.
FIG. 3 is an enlarged cross-sectional view of a section A in FIG. 1. At the center of the bell-shaped combustor body 1 is a stepped cylindrical combustion cylinder 2.
Are provided concentrically, and a diffusion type combustor used in a conventional gas turbine, a pilot injection valve 3 and a swirler 4 are provided at the center of the top of the combustor 1. The combustion cylinder 2 has a portion forming a pilot flame, that is, a small diameter portion 2a forming a diffusion combustion region B, an intermediate conical portion 2b forming a premixed gas combustion region C, and a large diameter portion forming a main combustion region D. 2c.

One end of a premixed tube 6 is attached to the intermediate conical portion 2b constituting the combustion cylinder 2, and a plurality of the premixed tubes 6 are arranged at equal intervals in the circumferential direction of the combustor body 1. The discharge port 6a is open to the premixed gas combustion region C. A fuel injection nozzle 7 is inserted into the inlet side 6b of the premixed trachea 6. Fuel injection nozzle 7
The first tube 8a and the second tube 8 as shown in FIG.
b are arranged concentrically, and the inside of the first passage 9a and the second tube 8b formed in the first tube 8a and the first tube 8
The second passage 9b formed between the outside and the outside of a is formed concentrically. A first injection port 10a for injecting fuel in the longitudinal direction of the premixed trachea 6 is provided at the tip of the first pipe 8a, and a premixed pipe 6 is provided at a side wall of the second pipe 8b.
Plurality of second injection ports 10 for injecting fuel toward the inner wall of the vehicle
b are provided respectively.

The first pipe 9a is connected to the inlet 9a 'through, for example, A
Liquid fuel F _1, such as fuel oil high pressure (e.g. 100 to 200
kg / cm ² ), while the second pipe 9 b is supplied with an inlet 9 b ′, for example, a fuel F ₂ such as a gas such as hydrogen or methane. The fuel F ₁ supplied to the first pipe 9a is supplied from the first injection port 10a, and the fuel F ₂ supplied to the second pipe 9b is supplied from the second injection port 10b. is injected into the air G that flows through the inner fuel F ₂ at the tip of the second tube 8b is injected so as to surround the mist of the liquid fuel F _1, is a mixed flow G ', the outlet of the premixing pipe 6 6a, and is supplied to the premixed gas combustion region D.

[0011]

[0012]

[Effect of the invention] combustor for a gas turbine according to the present invention before
Since it is configured as described above, the central part of the premixed trachea 6
Second pipe 8 outside the fuel injection nozzle 7 located at
b, the second fuel F ₂ , which is a gaseous fuel,
Flow through the cylindrical space between the trachea 6 and the fuel injection nozzle 7
Is injected in a direction that intersects the combustion air
Therefore, gaseous fuel and air are mixed while the air is stirred.
Is done. Then, toward this mixed gas flow
Thus, the first liquid fuel from the tip of the fuel injection nozzle 7
Since the fuel F ₁ is injected, the is the body of gas fuel 2
The fuel F ₂ of the combustion air, further with the fuel F ₁ of the first
Flows through the premixed trachea 6 while being effectively mixed
In, mixed diffusion of the first fuel F ₁ is being accelerated evaporation
It is. Therefore, while using liquid fuel and gaseous fuel together
And burn these fuels for combustion.
Because it can be efficiently diffused and mixed in air,
The mixed gas is placed in the premixed gas combustion region C,
Premixed gas combustion can be performed efficiently
And stable combustion with low NOx emissions
It can be carried out.

Therefore, a liquid fuel and a gaseous fuel are used.
Not only is it possible to achieve low NOx combustion with so-called Dual Fuel ?
Ku, the switching of the liquid fuel and gas body fuel if necessary
Since it can be performed, it is possible to economically select and use the fuel , and the power generation cost can be reduced. Special
In addition, since a liquid fuel can be used, a gas turbine can also be used as a combined machine for emergency power generation. These advantages can expand the market for gas turbine engines.

[Brief description of the drawings]

FIG. 1 is a sectional view of a main part of a gas turbine combustor according to an embodiment of the present invention;

FIG. 2 is a sectional view taken along line XX of FIG.

FIG. 3 is an enlarged view of a portion A in FIG. 1;

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Combustor main body 2 Combustion cylinder 3 Pilot injection valve 4 Swirler 6 Premixed pipe 7 Fuel injection nozzle 8a First pipe 8b Second pipe 9a First passage 9b Second passage 10a First injection port 10b Second Injection port

──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Kazuo Ureshi 3-1-1, Tamano, Tamano-shi, Okayama Prefecture Mitsui Engineering & Shipbuilding Co., Ltd. Tamano Works (56) References JP-A-62-77520 (JP, A) 1-310232 (JP, A) Jikken 42-17048 (JP, Y1) (58) Fields investigated (Int. Cl. ⁷ , DB name) F23R 3/36 F02C 7/232 F23C 11/00 309 F23R 3/28

Claims (1)

(57) [Scope of request for utility model registration] 1. A combustion cylinder 2 is housed inside a combustion chamber main body 1 , and a pilot injection valve 3 is provided at the top of the combustion cylinder 2 .
The combustion tube 2 is configured to form a main combustion region D and the pre-mixture combustion region C the diffusion combustion region B, and a plurality of premixing tubes 6 at equal intervals in the circumferential direction of the combustion chamber body 1 placement and, in a combustor which is open towards this the premixed gas combustion region C the discharge port 6a of the premixing pipe 6, extending a fuel injection nozzle 7 inside the central portion of the premixed trachea 6
Internal length to the fuel injection nozzle 7 of the premixed trachea 6
Forming a cylindrical air passage between the fuel injection nozzle 7, a first tube 8a, to the first tube 8a and concentric
A first injection port 10 formed in a double pipe structure with a second pipe 8b disposed outside, and opened at the tip of the first pipe 8a.
a , a first fuel F ₁ , which is a liquid fuel, is injected into the premixed trachea 6, and a second injection port is provided beside the second pipe 8 b.
10b is opened toward the inner surface of the premixed trachea 6,
The second combustion F ₂ which is gaseous fuel from the second injection port 10b
Toward the inner wall of the premixed trachea 6 so as to intersect with the airflow flowing in the air passage.
Fuel F ₂ and in the gas mixture formed by mixing with air, the first fuel injected from the distal end of the first tube 8a of
By mixing F ₁ to form a mixture and evaporation of the liquid fuel
Thereafter, a gas turbine combustor configured to inject into the premixed gas combustion region C from the premixed gas pipe 6.