JPS6016868Y2 - Gas turbine combustor transition piece - Google Patents

Description

[Detailed explanation of the idea] The present invention relates to an improvement of a gas turbine combustor transition piece.

In a conventional gas turbine combustor, as shown in Figure 1,
Air compressed by the compressor 101 is supplied into the casing 103 through the diffuser 102, and then flows into the combustor inner cylinder 104, where it becomes combustion gas and is transferred to the combustor tail cylinder 105.
The configuration is such that the air is guided to the turbine 106 through the.

FIG. 2 is a perspective view of this combustor inner cylinder 104 and transition piece.

FIG. 3 is a view of the transition piece viewed from the outlet.

Transition tube lower surface 203 and upper surface 20 shown in these drawings
4. Further, the side surface 301 from the combustor inner cylinder is cooled by the air exiting the diffuser, but the transition tube outlet side surface 382 is arranged in contact with the adjacent transition tube side wall as shown in FIG. Therefore, this wall surface is not cooled by air, and since high-temperature combustion gas flows inside at a high flow rate, it is heated to near the combustion gas temperature.

For this reason, there is no practical problem if the combustion gas temperature is about 800 to 900C, but it becomes a problem when the combustion gas temperature increases to 1300 to 15006C as gas turbines become more efficient.

The present invention has been made to solve this drawback.According to the present invention, the side wall of the transition tube outlet of a cannular type combustor is removed, and the earth wall and lower wall are replaced by a similar transition tube outlet adjacent to the earth wall and the lower wall. In addition to being connected to the earthen wall and lower wall of the section,
A gas turbine combustor transition piece is characterized in that a small hole is provided at the connecting portion of the side walls of the transition piece.

The present invention will now be described in detail with reference to preferred embodiments illustrated in the accompanying drawings.

In one embodiment of the present invention shown in FIGS. 3 to 6,
The inner cylinder 4G1, 402 is the same as that of the conventional example shown in FIGS. 1 and 2.

However, the transition tube 4 connected to these inner tubes 401 and 402
G3,404 has no sidewall at its exit portion 405.

That is, the side wall 302 of the conventional example is omitted.

As best shown in FIG. 6, outwardly extending flanges 503 and 504 are provided at the exit portion of the transition tube and are connected to flanges of adjacent transition tubes.

Therefore, an upper wall 601 and a lower wall 602 are present at the transition tube outlet, and these are connected to each other in a ring shape by flanges 503 and 504.

Therefore, the air coming out of the compressor is transferred to the adjacent transition pipe 403.40.
The combustor inner cylinder 40 passes through the space 505 formed between the
1,402.

A small hole 607 is provided in the transition tube connecting portion 606, so that cooling can be performed by air introduced through the small hole 607.

With the above configuration, the entire surface of the transition piece of the present invention is cooled by convection or film by the air discharged from the compressor.

Since the side wall of the exit part of the transition tube, which is difficult to cool, is omitted, even if the combustion gas temperature becomes as high as 1300°C to 1500°C, the temperature of the transition piece wall can be suppressed to about 800°C or less.

In addition, in order to prevent eddies from occurring at the transition tube connection, a small hole is provided to blow air out of the hole, so there is no risk of burnout.

Furthermore, an annular-type transition piece is heavy and difficult to attach to the gas turbine body, whereas the present invention uses a cannular-type transition piece, which makes it easy to assemble to the gas turbine body. be.

Although the preferred embodiment of the present invention has been described in detail above, the present invention is not limited to this specific embodiment.

In particular, the present invention can be directly applied to jet engines.

[Brief explanation of the drawing]

Fig. 1 is a partial longitudinal sectional view of a conventional combustor, Fig. 2 is a perspective view of its inner cylinder and transition piece, Fig. 3 is a partial perspective view of the transition piece as seen from the exit of the transition piece, and Fig. 4 5 is a perspective view of the inner tube and transition tube in a preferred embodiment of the present invention, FIG. 5 is a plan view of the transition tube outlet, and FIG. 6 is an enlarged perspective view of the transition tube outlet. 101... Compressor, 102... Diffuser, 103... Casing, 104...
... Inner tube, 105... Tail tube, 106...
...Turbine, 203...Bottom surface, 204...
...Top surface, 301...Side surface, 302...
... Tail tube outlet side, 401, 402... Inner tube, 403.404... Tail tube, 405...
・Exit part, 503.504...Flange, 50
5... Space, 601... Earth wall, 602
...Lower wall, 606...Temporary tube connection part, 6
07...Small hole.

Claims (1)

[Scope of utility model registration request] The side wall of the transition tube outlet of the cannular type combustor is removed, the earth wall and the lower wall are connected to the earth wall and the lower wall of the similar adjacent transition tube outlet, and the transition tube side walls are connected to each other. A gas turbine combustor transition piece characterized by having a small hole in the part.