JP2001153362A - Gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine combustor which is reduced in cost and increased in strength and combustion performance through the simplification of its configuration. SOLUTION: The gas turbine combustor is constituted in such a way that an inner tube is mounted on a substrate, with a plurality of main swirelers being arranged along the inner periphery of the tube, and a pilot swirler is provided at the central part surrounded by the main swirlers. Then a flame stabilizer is provided on the downstream side of the pilot swirler, and a combustion chamber and a transmission pipe are connected to each other on the downstream side of the inner tube. In the combustor, at least two of the main swirlers, substrate, pilot swirler, flame stabilizer, and transition pipe are integrally formed.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

The present invention relates to the structure of a gas turbine combustor.

[0002]

2. Description of the Related Art Conventionally, a gas turbine combustor generally has a structure shown in FIG.
Has a vertical view as shown in FIG. The combustion air a enters the inner cylinder 01 from the casing through an air passage 04 formed between the inner cylinder 01 and the outer cylinder 02, and the main fuel b1 supplied from the main fuel nozzle 05 and the main burner 06 Premix within.

A pilot fuel b2 supplied from a pilot fuel nozzle 07 provided at the center of the inner cylinder 01
The premixed gas is combusted in a combustion chamber 08 connected to the downstream side of the inner cylinder 01 by the diffusion flame.
The combustion gas generated by the combustion passes through a transition piece 09 connected to the downstream side of the combustion chamber 08 and is supplied to a turbine unit (not shown) connected to the transition piece 09.

FIG. 6 shows the structure of the main part of the conventional gas turbine combustor as described above. FIG. 6A is a schematic longitudinal sectional view, and FIG. 6B is a view taken in the direction of arrow DD in FIG.

In FIG. 6, a main swirler 010 is attached around each main fuel nozzle 05 to form an individual main burner 06, and a plurality of main burners 06 are arranged along the inner peripheral surface of the inner cylinder 01. Each main swirler 010 is held in alignment with the opening of the substrate 012, and the substrate 012 stops the air flow between the main swirlers.

A pilot fuel nozzle 07 having a pilot swirler 013 around it is provided in a central portion surrounded by the main burner 06, and a trumpet-shaped flame stabilizer 014 is provided downstream of the pilot swirler 013. .

The main fuel b1 supplied from the main fuel nozzle 05 and the air a supplied from the main swirler 010 are premixed by the main burner 06 and supplied outside the flame stabilizer 014. On the other hand, the pilot fuel b2 supplied from the pilot fuel nozzle 07 is supplied to the pilot swirler 01
While mixing with the air a supplied from 3, the flame is held at the front of the flame holder 014, and the premixed air from the main burner 06 is burned in the combustion chamber 08. Here, 015 is an air inflow portion,
Air for combustion a is introduced between the inner cylinder 01 and the outer cylinder 02,
It is a part that sends air a to each of the swirlers 010 and 013.

[0008]

In the conventional gas turbine combustor as described above, the swirlers 010 and 013, the flame stabilizer 014, the substrate 012, the combustion chamber 08, the transition piece 09 and the like are individually formed. Because it is a structure to assemble, the structure is complicated,
There was a disadvantage that the cost was high.

[0009] Further, there is a possibility that a combustion problem such as flashback occurs in the space between the flame stabilizer 014 and the main burner 06 due to its structural form.

SUMMARY OF THE INVENTION It is an object of the present invention to provide a gas turbine combustor in which the structure of the gas turbine combustor is simplified, cost is reduced, strength is improved, and combustion performance is improved.

[0011]

Means for Solving the Problems (1) The present invention has been made to solve the above-mentioned problems, and the first aspect thereof has been made.
As a means of, a plurality of main swirlers are arranged in the inner cylinder along the inner circumference of the inner cylinder and attached to the substrate, a pilot swirler is arranged in a central portion surrounded by the main swirler, and a downstream side of the pilot swirler is arranged. In a gas turbine combustor that includes a flame stabilizer and connects a combustion chamber and a transition piece downstream of the inner cylinder, the main swirler, the substrate, the pilot swirler,
An object of the present invention is to provide a gas turbine combustor characterized in that at least any two of a flame stabilizer, a combustion chamber, and a transition piece are formed integrally with each other.

According to the first means, the structure is simplified by integrating the structural parts of the gas turbine combustor, the strength is improved, and the cost is reduced.

(2) As a second means, there is provided the gas turbine combustor according to the first means, wherein the main swirler is formed integrally with the substrate. Things.

According to the second means, the features of the first means are provided particularly in the main swirler and the substrate.

(3) As a third means, there is provided a gas turbine combustor according to the first means, wherein the pilot swirler is formed integrally with the flame stabilizer. Things.

According to the third means, the features of the first means are provided especially in the pilot swirler and the flame stabilizer.

(4) As a fourth means, there is provided a gas turbine combustor according to the first means, wherein the combustion chamber is formed integrally with the transition piece. It is.

According to the fourth means, the features of the first means are provided particularly in the combustion chamber and the transition piece.

(5) As a fifth means, in the gas turbine combustor of the first means, the main swirler is formed integrally with the substrate, and the pilot swirler is formed integrally with the flame stabilizer. A gas turbine combustor characterized in that a combustion chamber is formed integrally with the transition piece.

According to the fifth means, since all the main parts of the gas turbine combustor have the features of the first means, the effect is great.

(6) As a sixth means, in the gas turbine combustor according to any one of the first means to the fifth means, the downstream end of the main swirler is extended to near the outer peripheral surface of the flame stabilizer. A gas turbine combustor characterized by being provided.

According to the sixth means, in addition to the features of any of the first to fifth means, the downstream end of the main burner is extended to the vicinity of the back surface (outer peripheral surface) of the flame stabilizer. Therefore, there is no backfire between the flame stabilizer and the main burner.

[0023]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A gas turbine combustor according to an embodiment of the present invention will be described with reference to FIGS. FIG. 1 shows a structure of a main part of a gas turbine combustor according to the present embodiment. FIG. 1A is a schematic longitudinal sectional view, and FIG. FIG.

FIG. 2 shows the pilot swirler 13 shown in FIG.
FIGS. 4A and 4B are explanatory views of the flame stabilizer 14, wherein FIG. 4A is a longitudinal sectional view showing positions in the outer cylinder 2, and FIG. FIG. 3 shows the main swirler 10 and the substrate 12 shown in FIG.
5A is a vertical cross-sectional view showing positions in the outer cylinder 2 together, and FIG. 5B is a view taken along the line CC in FIG. FIG.
FIG. 2 is an explanatory view of a combustion chamber 8 in FIG. 1, and is a longitudinal sectional view also showing a position of an outer cylinder 2 with respect to an inner cylinder 1.

In the gas turbine combustor shown in FIG. 1, a plurality of main swirlers 10 are arranged inside the inner cylinder 1 along the inner circumference of the inner cylinder 1 and attached to the substrate 12, and the main swirler 1
A pilot swirler 13 is disposed at a central portion surrounded by a circle 0, and a trumpet-shaped flame stabilizer 14 extending downstream is provided downstream of the pilot swirler, and a combustion chamber 8 and a combustion chamber 8 of the combustion chamber 8 are provided downstream of the inner cylinder 1. The transition piece is connected to the downstream side.

As shown in FIG. 2, the pilot swirler 1
3 and the flame stabilizer 14 are integrally formed, and the pilot fuel nozzle 7 is provided at the center of the pilot swirler 13.

As shown in FIG. 3, the plurality of main swirlers 10 and the substrate 12 are formed integrally.
The main fuel nozzle 5 is attached to the center of each main swirler 10, and the downstream part of the main swirler 10 constitutes the main burner 6.

The substrate 12 has a so-called trumpet shape which is wide toward the downstream side, and has an opening 12a on the slope of the substrate 12 in alignment with the downstream end of the main swirler. It has an opening 12b.
The opening 12a is a downstream end of the main burner.

The flame stabilizer 14 is wrapped around the opening of the main burner 6 at a position downstream of the opening 12a of the substrate 12 when the flame stabilizer 14 is inserted through the substrate 12. It has a notch 14a at the periphery of the shape.

The downstream end of the main burner 6 (ie, the downstream end of the main swirler 10) is
When penetrated into the substrate 12, it extends so as to be located near the back surface (outer peripheral surface) of the flame stabilizer 14, that is, near the notch portion 14 a. In the present embodiment, since the substrate 12 is integrated so as to be aligned with the downstream end of the main swirler 10, the substrate 12 also extends along the back surface (outer peripheral surface) of the flame stabilizer 14. Although it is a trumpet type,
The main burner 6 is not necessarily limited to this.
It is important that the downstream end (i.e., the downstream end of the main swirler 10) extends to the vicinity of the back surface (outer peripheral surface) of the flame stabilizer 14.

As shown in FIG. 3, the combustion chamber 8 is connected to the downstream side of the inner cylinder 1.
Are integrally formed so as to also serve as a transition piece connected to the turbine section. That is, it has an integral structure which also serves as the combustion chamber 08 and the transition piece 09 of the conventional apparatus of FIG.

In the gas turbine combustor according to the present embodiment as described above, the main swirler 10 and the substrate 12, and the pilot swirler 13 and the flame stabilizer 14 are integrated, so that the structure is simplified and the strength is improved. Cost reduction is achieved.

Further, since the combustion chamber 8 which is a high temperature part and the transition piece are integrated, the cost can be reduced.

Further, the main swirler 10 and the substrate 12 are integrated, and the downstream end of the main burner 6 (downstream end of the main swirler 10) extends to the vicinity of the back surface (outer peripheral surface) of the flame stabilizer 14. There is no possibility of backfire between the flame stabilizer 14 and the main burner 6. Also, substrate 1
2 is a trumpet along the flame stabilizer 14
The air passing through the back surface (outer peripheral surface) of the substrate 4 also has the effect of film cooling the downstream surface of the substrate between the main swirlers 10.

Although one embodiment of the present invention has been described above, the present invention is not limited to the above-described embodiment, and various changes may be made to the specific structure within the scope of the present invention. Needless to say.

[0036]

(1) According to the first aspect of the present invention, the gas turbine combustor is mounted on the board by disposing a plurality of main swirlers in the inner cylinder along the inner periphery of the inner cylinder. In a gas turbine combustor in which a pilot swirler is provided in a central portion surrounded by a swirler, a flame stabilizer is provided downstream of the pilot swirler, and a combustion chamber and a transition piece are connected downstream of the inner cylinder, the main swirler is provided. , The substrate, the pilot swirler, the flame stabilizer, the combustion chamber, and the transition piece are configured so as to be formed integrally with each other, so that the structure is obtained by integrating the structural parts of the gas turbine combustor. Can be simplified, the strength can be improved, and the cost can be reduced.

(2) According to the second aspect of the invention, in the gas turbine combustor according to the first aspect, the main swirler is formed integrally with the substrate. The effect of the first invention is exhibited particularly in the main swirler and the substrate.

(3) According to the invention of claim 3, claim 1
In the gas turbine combustor according to the above, the pilot swirler is formed integrally with the flame stabilizer, so that the effect of the invention of claim 1 is exhibited particularly in the pilot swirler and the flame stabilizer. Becomes

(4) According to the invention of claim 4, claim 1
In the gas turbine combustor according to the above, since the combustion chamber is formed integrally with the transition piece, the effect of the invention of claim 1 is exhibited particularly in the combustion chamber and the transition piece, Since the combustion chamber, which is a high-temperature component, and the transition piece are integrated, the effect of cost reduction is great.

(5) According to the invention of claim 5, claim 1
In the gas turbine combustor according to the above, the main swirler is formed integrally with the substrate, the pilot swirler is formed integrally with the flame stabilizer, and the combustion chamber is formed integrally with the transition piece. Therefore, the effect of the invention of claim 1 is achieved in all the main parts of the gas turbine combustor, and the effect is large.

(6) According to the invention of claim 6, according to claim 1,
In the gas turbine combustor according to any one of claims 1 to 5, the downstream end of the main swirler is configured to extend to near the outer peripheral surface of the flame stabilizer. In addition to the effect of the invention of any one of item 5, there is an effect that there is no backfire between the flame stabilizer and the main burner.

[Brief description of the drawings]

FIG. 1 is an explanatory view of a main part of a gas turbine combustor according to an embodiment of the present invention, where (a) is a schematic longitudinal sectional view, and (b) is a view taken along the line AA in (a). FIG.

FIGS. 2A and 2B are explanatory diagrams of a pilot swirler and a flame stabilizer in FIG. 1, wherein FIG. 2A is a longitudinal sectional view, and FIG.

3A and 3B are explanatory views of a main swirler and a substrate in FIG. 1, wherein FIG. 3A is a longitudinal sectional view and FIG. 3B is a view taken along the line CC in FIG.

FIG. 4 is an explanatory view of a combustion chamber in FIG. 1 and is a longitudinal sectional view.

FIG. 5 is a longitudinal sectional view showing a general configuration of a conventional gas turbine combustor.

6A and 6B are explanatory views of a main part of a conventional gas turbine combustor, wherein FIG. 6A is a schematic longitudinal sectional view, and FIG.
It is an arrow D view.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Inner cylinder 2 Outer cylinder 5 Main fuel nozzle 6 Main burner 7 Pilot fuel nozzle 8 Combustion chamber 10 Main swirler 12 Substrate 13 Pilot swirler 14 Flame stabilizer

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Koichi Nishida 2-1-1 Shinama, Araimachi, Takasago City, Hyogo Prefecture Inside Takasago Works, Mitsubishi Heavy Industries, Ltd. No. 1 Inside Mitsubishi Heavy Industries, Ltd. Takasago Factory

Claims (6)

[Claims] A plurality of main swirlers are arranged in an inner cylinder along the inner circumference of the inner cylinder and attached to a substrate, and a pilot swirler is arranged in a central portion surrounded by the main swirler, and is disposed downstream of the pilot swirler. A gas turbine combustor comprising a flame stabilizer on the side and connecting a combustion chamber and a transition piece downstream of the inner cylinder, wherein the main swirler, the substrate, the pilot swirler,
A gas turbine combustor, wherein at least any two of a flame stabilizer, a combustion chamber, and a transition piece are formed integrally with each other. 2. The gas turbine combustor according to claim 1, wherein said main swirler is formed integrally with said substrate. 3. The gas turbine combustor according to claim 1, wherein the pilot swirler is formed integrally with the flame stabilizer. 4. The gas turbine combustor according to claim 1, wherein the combustion chamber is formed integrally with the transition piece. 5. The gas turbine combustor according to claim 1, wherein said main swirler is integrally formed with said substrate, said pilot swirler is integrally formed with said flame stabilizer, and said combustion chamber is said transition piece. A gas turbine combustor characterized by being formed integrally with a gas turbine combustor. 6. The gas turbine combustor according to claim 1, wherein a downstream end of the main swirler is extended to near an outer peripheral surface of the flame stabilizer. And gas turbine combustor.