JPH0478894B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION OBJECTS OF THE INVENTION (Industrial Field of Application) The present invention relates to an improvement in a gas turbine combustor, particularly in a gas turbine combustor in which the combustion chamber has a ceramic structure.

(Prior technology) Recently, the output of gas turbine equipment used for power generation has continued to increase, and in particular, improvements in the development of cooling blades have led to applications where the combustion gas temperature at the turbine inlet exceeds 1500°C. It's becoming possible. In gas turbine combustors that handle such extremely high-temperature combustion gas, a double-walled structure consisting of an inner cylinder and an outer cylinder is often adopted in consideration of the high heat load. That is, the inner cylinder that forms the combustion chamber is made of a heat-resistant material, such as a nickel-based alloy, and a passage is formed between the inner cylinder and the outer cylinder to guide part of the air discharged from the compressor. Air is used to dilute the temperature of the combustion gas inside the combustion chamber. Therefore, even though the combustion chamber is exposed to severe conditions, it maintains sufficient strength to withstand thermal shock or thermal stress.

(The problem that the invention attempts to solve) By the way, recently, the development power of ceramics has progressed,
The application of ceramics to gas turbine combustors is being considered. When applying ceramic parts to gas turbine combustors, they have good heat resistance, low cost, and are easy to mold, but on the other hand, they have very poor ductility. I have some concerns about its application. In other words, in a gas turbine combustor, an air inlet is attached to the inner cylinder because it is necessary to dilute the ultra-high temperature combustion gas with air. , a notch is previously formed to match the shape. For this reason, if the material is ceramic with a notch provided in the inner cylinder, the significant temperature difference between the ultra-high temperature combustion gas and the air will cause excessive damage to the attachment area (especially the notch in the inner cylinder). Stress concentration occurs, and the degree of damage is extremely high compared to conventional metal materials, often resulting in brittle fracture.

In order to solve this problem, attempts have been made to attach the air inlet by, for example, stacking the inner cylinder divided into ring sections one after the other and inserting it between the joint surfaces, but it is still not possible to install the air inlet permanently. No solution has been reached.

In view of the above points, the present invention aims to provide a gas turbine combustor that can sufficiently withstand thermal shock, etc., which causes stress concentration due to ultra-high temperature combustion gas, without making the structure particularly complicated. purpose.

[Structure of the invention]

(Means for Solving the Problems) In order to achieve the above object, the present invention stacks ceramic cylindrical segment pieces along the trunk axis, and crosses between the end edges of these segment pieces. A reinforcing piece made of ceramic and an air inlet made of metal are arranged around the inner combustion chamber to form an inner cylinder combustion chamber, while a protruding part provided on the reinforcing piece is attached to cover the edge of the segment piece, and The air inlet, which is inserted into the space formed by the piece and the reinforcing piece, is fixed to the outer sheath that covers the inner combustion chamber.

(Function) In the gas turbine combustor according to the present invention, cylindrical ceramic segment pieces are stacked,
A reinforcing piece made of ceramic and an air inlet made of metal are interposed across the edges of these segment pieces. In this case, the edge of the segment piece is covered with a protrusion provided on the reinforcing piece,
Further, an air inlet that is inserted into the space formed by the segment piece and the reinforcing piece is fixed by an outer cover that covers the inner cylinder combustion chamber. Therefore, since neither the segment piece nor the reinforcing piece is provided with a cutout portion, the unique characteristics of ceramic can be fully utilized. Therefore, there is no need to worry about ceramic damage due to stress concentration caused by superheated shock caused by ultra-high temperature combustion gas.

(Example) Hereinafter, an example of the present invention will be described with reference to the drawings.

In FIG. 1, reference numeral 1 generally indicates the entire combustor according to the present invention, and the combustor 1 has a cone portion 11 at the top, and a fuel injection valve 1 is attached to the cone portion 11.
0 is included. One end of this cone portion 11 is fixed to a jacket 9 made of a heat-resistant alloy.

Inside the jacket 9, as shown in FIG. 2, there is an inner combustion chamber 1a, which is a short circular cylinder and has ceramic segment pieces 2, 3, ... stacked along the body axis. , 1a, . . . are arranged.

In forming a continuously elongated combustion chamber using these inner cylinder combustion chambers 1a, 1a,...
First, one segment piece is set vertically, and the other end edge is covered with the reinforcing piece 7 shown in FIG. 3. That is, reinforcement piece 7
As can be seen in the same figure, there are hollow parts 11 on both sides.
It is formed in a T-shape having a and 11a, and the entire shape is formed into a curved surface shape with a relatively large curvature. One protrusion 11a of the reinforcing piece 7 having such a shape is attached to the edge of the segment piece and temporarily fixed with an adhesive or the like.
The temporarily fastened reinforcing piece 7 is arranged in an annular manner along the circumferential edge of the segment piece, leaving a space into which an air inlet, which will be described later, is inserted.

Next, the edges of the other segment pieces are attached to the other protrusion 11a of the reinforcing piece 7, and the segments are temporarily fastened with an adhesive or the like and stacked in the same manner as described above.

The stacking process is repeated several times in this way, until a single vertical combustion chamber is finally completed.

The combustion chamber thus completed is covered with an outer sheath 8 made of a heat-resistant alloy, with insulation materials 8, 8, . . . made of, for example, ceramic fiber interposed therebetween. In addition to the heat insulation materials 8, 8, ..., the insulation materials 8, 8, ...
This is to absorb sudden thermal shock caused by ultra-high temperature combustion gas.

On the other hand, in the combustion chamber covered with the outer sheath 8, an air inlet is provided toward a space provided in advance between reinforcing pieces 7, 7, . . . that cover the edges of the segment pieces 2, 3, . 6, 6, ... are inserted. As shown in FIG. 4, these air inlets 6, 6, ... are made of a heat-resistant alloy in which a base 6a and a rectangular tube 6b are integrally formed, and after being inserted into the space, is fixed to the outer cover 9 by screws, welding, or the like. In addition, air inlets 6, 6,
... is made by square tubes, segment pieces 2, 3,
. . . and the reinforcing pieces 7, 7, .

Thus, in the above configuration, the fuel injection valve 10
Fuel is injected from the fuel and air inlet 6,
The primary air from 6, .

However, the segment piece 2 on the side of the fuel injection valve 10 has one end restrained by the cone part 11, and the other end has the reinforcing pieces 7, 7, ..., the air inlets 6, 6,
Since it is restrained by ..., movement in the direction of the cylinder axis is prevented even if it receives a thermal shock from the ultra-high combustion gas flowing along the cylinder axis. Also, the other segment pieces 3, 4, ... also have reinforcing pieces 7, 7, ... at both ends.
Since the air inlets 6, 6, . Note that since the segment piece farthest from the fuel injection valve 10 is connected to and restrained by a transition piece of a gas turbine (not shown), there is no fear of movement in the axial direction of the cylinder.

On the other hand, reinforcing pieces 7, 7,... are attached to cover between the edges of segment pieces 2, 3, 4,...
are connected like a segmented arc ring wire, but both ends are restrained by coming into contact with the square tubes 6b, 6b, . . . of the air inlets 6, 6, . . . at given positions.
It won't fall off. Furthermore, reinforcing piece 7,
Since the surfaces of the parts 7, . . . are restrained by the jackets 9, 9, . . . with the insulation materials 8, 8, . Further, since the air inlets 6, 6, . . . are fixedly installed by the outer cover 9, 9, . . ., they do not move from their original positions.

As described above, in the ceramic member applied to the gas turbine combustor according to the present invention, the inner cylinder of the combustor is constructed without any notches, with sufficient consideration given to preventing the movement of ultra-high temperature combustion gas due to thermal shock. Because of this, the excellent unique properties of ceramic can be fully utilized.

〔Effect of the invention〕

As explained above, the gas turbine combustor according to the present invention includes ceramic segment pieces,
The inner combustion chamber is formed by using reinforcing pieces and the air inlet is made of metal, while the edges of the segment pieces are covered and engaged with the protruding parts of the reinforcing pieces, and the segment pieces are arranged transversely. Both ends of the segmented ring shape of the piece are restrained by the air inlet, and the air inlet is fixed by the outer cover, so there is no need to provide any notches in the segment piece or reinforcing piece. Therefore, even if ceramic members are used in a super-large combustor, the strength of the material will not decrease.
It is effective enough to be used industrially.

[Brief explanation of the drawing]

Fig. 1 is a schematic diagram showing an embodiment of a gas turbine combustor according to the present invention, Fig. 2 is a diagram showing an example of a segment piece, Fig. 3 is a diagram showing an example of a reinforcing piece, and Fig. 4 is a diagram showing an example of a segment piece. It is a figure showing an example of an introduction port. 1a... Inner cylinder combustion chamber, 1, 3, 4, 5... Segment piece, 6... Air inlet, 7... Reinforcement piece, 8
...insulation material, 9...outer covering.

Claims (1)

[Claims] 1 Ceramic cylindrical segment pieces are stacked along the body axis, and a ceramic reinforcing piece and a metal air inlet are provided around the edges of the segment pieces to form an inner cylinder combustion chamber. On the other hand, the protrusion provided on the reinforcing piece is attached to cover the edge of the segment piece, and the air inlet inserted into the space formed by the segment piece and the reinforcing piece is connected to the inner cylinder combustion chamber. A gas turbine combustor characterized in that it is fixedly installed in an outer covering covering the combustor.