JPS6245904A - Gas turbine stationary blade - Google Patents

Abstract

PURPOSE:To preferably maintain the property of a ceramic part and ensure a sealing effect with a high reliability by means of a metal part, by providing grooves at each adjacent end part of inner and outer shrouds made of metal. CONSTITUTION:In case of a gas turbine stationary blade, for example, the outside part thereof is constituted in such a way that the outside shroud 8, 8' made of ceramic and the outside shroud 5 made of metal are integrally assembled through cushioning materials 12, 12'. With regard to this constitution, a seal plate 13 is inserted to a groove (a) provided on the end surface of the outside shroud 5 and a pin 15 is inserted to the outside shroud 5 and the seal plate 13. The pin is fixed to the outside shroud 5 by welding so as to prevent the seal plate 13 from being fallen out and thereafter the seal plate 13 is inserted to the groove (a) of the end surface of the outside shroud 5' adjacent to said outside shroud 5. Therefore, it is possible to preferably maintain the property of ceramic material and ensure a sealing effect by means of a metal part to the leak of liquid out of the shroud.

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a gas turbine stator blade having a ceramic component.

[Conventional technology]

The invention previously filed by the inventors of this invention will be explained.

In FIG. 4, the metal parts include a mandrel 2. which is fillet welded to the inner shroud 1 over the entire circumference at section f. and an outer shroud 5, which will be described later, and a T-shaped groove e is provided in the top of the mandrel 2, and a root i of the same shape of the stopper 8 is inserted into the groove e. By fitting the threaded portion 3a into the top hole of the outer shroud 5 from above and tightening the nut 4 into the threaded portion 3a, the mandrel 2 and the outer shroud 5 are integrated. The ceramic part is composed of a wing inner shroud 6, a wing section 7, and a wing outer shroud 8, which may be integrally molded, or the wing inner and outer shrouds 6.8 may be bonded to the wing section 7. May be molded.

The wing portion 7 of the ceramic part is attached to the core 2 of the metal part.
When the outer shroud 5 is further inserted and the nut 4 is fastened to the stopper 3, the ceramic portion is fixed between the inner and outer shrouds 1 and 5.

A gas turbine stationary blade will be formed.

Further, to explain in detail, buffers (211 and 1
2 are inserted into each other, and therefore, it has the effect of removing the external force accompanied by the thermal stress of the ceramic member and the vibration transmitted from the metal part, so it is extremely reliable W.
E+7) A gas turbine stationary blade using ceramics can be obtained. The code 9 is the stator blade inner mounting bracket.

10 is a washer.

[[, Invention solves 1. [Problems] One stator vane stage of a gas turbine is constructed by arranging dozens of the gas turbine stator blades in the circumferential direction, but in this case, the adjacent inner and outer shrouds If there is a gap, the working gas in the gas passage may flow out or cooling air may flow into the gas passage through the gap, and the former causes a decrease in gas turbine thermal efficiency.

The latter has a problem in that it causes a decrease in the strength of high-temperature parts due to a lack of cooling air. Therefore, it is necessary to seal between adjacent shrouds.

Performing sea / l / in the second part of Shurarador Ceramic is due to the fact that the fracture toughness of the ceramic material is low and lacks ductility.9 The strength of the parts is uneven and the mechanical strength is dominated by minute defects. undesirable for this reason.

[Means for solving problems]

Accordingly, the present invention provides a seal between metal shrouds, in which a gas passage is formed by a ceramic wing portion and an inner and outer shroud, and each gas turbine station is configured with a metal core and an inner and outer shroud. g
2) When arranging a plurality of shrouds in the circular n direction, concave grooves are provided on adjacent surfaces of the inner and outer metal shrouds in the circumferential direction, and metal seal plates are placed in a pair of adjacent grooves. It is designed to be inserted and worn again.

Therefore, the groove and seal plate mentioned above are made of metal.

Guaranteed ductility and material uniformity, high reliability. In this way, structural design methods suitable for ceramics can be utilized.

〔Example〕

Below, an example of the production of a gas turbine stationary blade to which the ceramic material according to the present invention is applied is shown in Figures 1 to 3.
This will be explained using figures.

FIG. 1 is an external view of an example of a single tool to which the present invention is applied. The same reference numerals in the figure as those in FIG. 4 indicating the conventional example have almost the same structure.

The actions and effects are also almost the same, so explanations will be omitted.

The shaded area in the figure is the surface corresponding to the adjacent stationary blade.

A groove a is provided on this surface.

FIG. 2 shows the seal structure on the outer shroud of the two stator vanes, and FIG. 3 shows the seal structure on the inner shroud. In both figures, parts with the same reference numerals and dashes indicate adjacent parts.

In FIG. 2, the seal plate 13 is inserted into the groove a on the end face of the metal outer shroud 5, the pin 15 is inserted into the outer shroud 5 and the seal plate 13, and then the pin 15 is welded to the outer shroud 5 and the seal plate is After stopping the removal of the seal plates 13, the seal plates 13 are inserted into the grooves a in the end faces of the adjacent metal outer shrouds 5'.

Figure 3 shows the inner shroud sealing device.
It is no different from the outer shroud. Therefore, 14 is a seal plate, and 16 is a pin.

In addition, in order to prevent stress due to thermal expansion, the seal plate 14 is
There is a gap C between the groove a and the groove a.

〔Effect of the invention〕

As detailed above, according to the present invention, ceramics are used in the high-temperature gas passages constituting the gas turbine stationary blades,
Taking advantage of the high temperature strength, creep properties, and high temperature oxidation resistance of ceramics, we have achieved a highly reliable sealing effect by sealing with a metal part that does not have the disadvantages of ceramics against fluid leakage from the shroud. Since gas turbine performance can be greatly increased, its industrial utility value is great.

[Brief explanation of drawings]

1 is a partially cutaway side view of a main part showing a first embodiment of the present invention, FIG. 2 is an enlarged sectional view of a section taken along the line Il-■ in FIG. FIG. 1 is an enlarged sectional view taken in the direction of the arrows ■ to ■ in FIG. 1; FIG. 4 is a partially cutaway side view of main parts showing a conventional example. 1... Inner shroud, 2... Core metal, 3... Stopper, 4... Oak l-, 5, 5'... Outer shroud, 6゜6'... Wing inner shroud , 7... Wing section, 8.8'... Wing outer shroud, 11.1.2
...Cushioning material, 1.8.14...Seal plate, 8...
・Groove, 1)...hole, C...gap with groove, 15
．． 16...pin. Tori 1 Prisoner 2nd Flash Il, t'nman+m

Claims (1)

[Claims] When arranging a plurality of gas turbine stationary blades in the circumferential direction, which are constructed by integrally combining ceramic inner and outer shrouds and blade parts, metal inner and outer shrouds, and core metal, adjacent metal inner and outer shrouds are A gas turbine stationary blade characterized in that a concave groove is provided in each end face of a shroud, and a seal plate is inserted and fixed into a pair of adjacent grooves.