JPH08170501A - Gas turbine cooled moving blade - Google Patents

Abstract

PURPOSE: To form cooling air channels through which moving blade parts and platforms can be sufficiently cooled. CONSTITUTION: Holes 2A, 2B, 2C through which cooling air is led to flow into serpentine channels for cooling a blade part, are opened in a gas turbine cooled moving blade. The terminals of the serpentine channels serve as platform 3 parts, and reservoirs 4 are formed thereon. Holes 6 for cooling convection, which are communicated with the reservoirs 4, are opened in the platforms 3 so as to cool the platforms 3. Further, holes through which the cooling air is led to flow from the holes 6 for cooling the convection onto the upper surfaces of the platforms 3, are also opened.

Description

Detailed Description of the Invention

[0001]

FIELD OF THE INVENTION The present invention relates to a gas turbine cooling blade configured to supply cooling air to blades and platforms.

[0002]

2. Description of the Related Art Various structures have been announced so far for supplying cooling air to a gas turbine cooling blade platform. For example, as shown in FIG. 3, a small hole 13 from the middle of the serpentine channel 11 for cooling the moving blade to the upper surface of the platform 12 is provided, and cooling air for the platform is blown from the small hole 13 to the upper surface of the platform 12. There is something.

Alternatively, as shown in FIG. 4, the shank portion 14
A cooling air reservoir 16 is provided at a portion avoiding the profile of the blades 15 of the above, and cooling air is stored in this reservoir 16 separately from the blade cooling air, and a hole 17 that communicates this reservoir 16 with the upper surface of the platform 12 is provided. There is also a structure in which cooling air is blown out from the holes 17.

Further, as shown in FIG. 5, the platform 1
2, a plurality of seal air flow passage holes 18 are provided in the radial direction, and a shape film blow-out port 19 is provided on the upper surface (top surface of the platform) of each of the air flow passage holes 18.
Is provided to blow the sealing air onto the upper surface of the platform 12.

[0005]

As the temperature of the gas turbine rises, it is required to improve the cooling capacity of the turbine section. In particular, cooling measures are required for the platform of the gas turbine cooling blade. Regarding the platform, as mentioned above, several platforms with cooling structure have been announced at present, but none of them has advantages and disadvantages and there is no solid one.

The present invention has been made to solve this problem, and provides a gas turbine cooling blade in which a cooling air passage is formed so as to sufficiently cool the moving blade portions and the platform. That is the issue.

[0007]

In order to solve the above-mentioned problems in a gas turbine cooling blade, the present invention provides an end point of a serpentine flow path of the gas turbine cooling blade on the platform side and a reservoir at the end point. Form. The platform is provided with a convection cooling hole communicating with the reservoir at the end of the serpentine channel.

[0008] A plurality of holes for convection cooling communicating with the platform and the reservoir are arranged and drilled so as to enhance the optimum cooling effect for the platform. As described above, it is preferable that the platform is provided with a hole for convection cooling, and a hole communicating with the hole is also provided on the upper surface of the platform.

[0009]

In the gas turbine cooling moving blade according to the present invention, the cooling structure of the moving blade and the platform has the above-mentioned structure, so that the cooling air used for cooling the blade is heated to a certain extent by heat exchange. However, since a large amount of cooling air is collected in the reservoir formed at the end portion of the serpentine channel and supplied to the convection cooling holes formed in the platform, the cooling effect of the platform is further enhanced. As described above, in the gas turbine cooling blade of the present invention, the platform is sufficiently cooled together with the blade portions.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A gas turbine cooling blade according to the present invention will be specifically described below based on an embodiment shown in FIGS. In the gas turbine blade shown in FIGS. 1 and 2, reference numeral 1 denotes a shank portion, and the shank portion 1 has holes 2A, 2B, 2 for allowing blade cooling air to flow into a serpentine channel in the blade.
C is formed.

The serpentine flow path connected to the holes 2A and 2B ends at the platform 3 and reservoirs 4 and 4 are formed at the end points thereof. From each reservoir 4, a plurality of cooling air holes 6 for convective cooling are provided in the platform 3, as best shown in FIG.
Is growing.

Therefore, the blade cooling air flows in from the holes 2A to 2C of the shank portion 1 and partially flows out to the surface of the moving blade through each serpentine flow path to cool the blade from the inner and outer surfaces. The cooling air that has flowed into the serpentine flow path connected to the holes 2A and 2B is finally collected in the reservoir 4 formed in the platform 3.

The cooling air accumulated in the reservoir 4 cools the platform 3 in the process of passing through the cooling air holes 6 formed in the platform 3 from the side surface of the reservoir 4. The cooling air hole 6 formed in the platform 3 may be formed so as to have an optimum effect on cooling, and is not limited to the structure shown in FIG.

A hole 7 communicating with the cooling air hole 6 is also formed on the upper surface of the platform 3. By adopting this structure, a large amount of cooling air used for blade cooling flowing through the serpentine flow channel flows out from the holes 6 and 7 formed in the platform 3, so that the cooling effect on the gas turbine cooling blade is improved. To be done.

[0015]

As described in detail above, according to the gas turbine cooling blade of the present invention, the end point of the serpentine flow path is provided on the platform side, and the reservoir is formed at the end point, and the reservoir is formed from there. Since the cooling air is supplied to the formed convection cooling holes, a large amount of cooling air can be supplied to the platform without causing a shortage of the blade cooling air.

That is, the cooling air after cooling the blade portion in the serpentine channel is stored in the reservoir to maintain sufficient storage and pressure, and the platform is cooled by the air flowing from the reservoir. Therefore, if the total amount of cooling air is adjusted at the beginning, the subsequent adjustment of the amount of cooling air becomes unnecessary, and it will be one step closer to dealing with the high temperature of the gas turbine.

[Brief description of drawings]

FIG. 1 is a vertical cross-sectional view of a gas turbine cooling blade according to an embodiment of the present invention.

FIG. 2 is a cross-sectional view of the gas turbine cooling blade shown in FIG.

FIG. 3 is a vertical sectional view of a conventional gas turbine cooling blade.

FIG. 4 is a vertical cross-sectional view of another conventional gas turbine cooling blade.

FIG. 5 is a partial perspective view of still another conventional gas turbine cooling blade.

[Explanation of symbols]

 1 shank part 2A, 2B, 2C hole 3 platform 4 reservoir 6,7 cooling air hole

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Eisaku Ito 1-1-1, Niihama, Arai-cho, Takasago-shi, Hyogo Mitsubishi Heavy Industries Ltd. Takasago Laboratory

Claims (1)

[Claims] 1. An end point of a serpentine passage of a gas turbine cooling blade is provided on a platform side, a reservoir is formed at the end portion, and a convection cooling hole communicating with the reservoir at the end point of the serpentine passage is formed in the platform. A gas turbine cooling moving blade characterized by being provided.