JPH06336902A - Turbine vane assembly method - Google Patents

Abstract

PURPOSE:To set a small gap size accurately and raise up the workability for assembling a turbine stationary blade by adhering melted metal to the joint surfaces of module blades so as to form small projections and grinding the small projections so as to set their projected heights and also putting together the joint surfaces of the module blades and filling melted soldering material in small gaps therebetween so as to integrate them. CONSTITUTION:Melted metal is stuck to plural places on the jointed surfaces of module blades 1 by spot welding or the like so as to form small projections 11 higher than a prescribed set size. Then, their parts are removed upto a chain line by means of a grinding process so as to get desired sizes. Small projections 11 are brought in tight contact with a pair of joint surfaces of each module blade 1 and the size of each small gap G is set by the projected height of each small projection 11. A spot welding is carried out while keeping the set size of the small gap G and plural module blades 1 are welded temporarily by spot welding part 5 so as to be set integrated its state to be and then it is integrated by soldering metal 12.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method of assembling a turbine vane, and in particular, the vane is modularized,
The present invention relates to a technique of assembling by brazing.

[0002]

2. Description of the Related Art One of the methods for efficiently manufacturing a turbine vane is to form a module vane in a state in which the vane is circumferentially divided and braze the joint surfaces of the plurality of module vanes. There is a method in which the blades are connected to each other in the circumferential direction to form a continuous blade, and these are further combined to form a stationary blade having the entire circumference integrated.

As shown in FIG. 2, for example, in the case of connecting four module blades 1 of the same type in the circumferential direction to form a continuous blade, between the outer peripheral ring member 2 and the inner peripheral ring member 3 in advance. The module blade 1 in which the blades 4 are integrally supported is formed in advance, and the four module blades 1 are combined,
The spot welding portion 5 in the temporary attachment state secures a state in which a small gap G is left on the joint surface, and the small gap G is filled with a brazing material in a molten state, whereby the assembled state is achieved. Then, the brazing material used for brazing is set corresponding to the constituent material of the module blade 1,
Generally, there are two types, a plate-like one and a powder-like one.

On the other hand, in turbine vanes for aircraft, etc., 1
In many cases, a material that can withstand a service temperature of 000 ° C. or higher is required, and a cobalt-based heat-resistant alloy, for example, is applied as the metal material for this purpose, but an optimal plate-shaped brazing material has not yet been developed. In combination, a powdery brazing material made into a paste with an organic solvent is applied, but the assembly accuracy of each module blade depends on the state of the small gap G on the joint surface.

FIG. 3 shows a state in which the shape of the module blade 1 is simplified, and shows a conventional example of a method of assembling while setting a small gap G on the joint surface. In this assembling method, the spot welding portion 5 is formed on the joint surface of the module blade 1 with the shim plate 6 set to a thickness of 0.1 mm, for example, in a tightly sandwiched state, and the connecting blade portion is temporarily attached. Is integrated, the shim plate 6 is pulled out to release the small gap G, and the small gap G is filled with the brazing material, as shown by the arrow and the chain line.

[0006]

However, in the above method, if the small gap G of the joint surface of the module blade 1 is to be set accurately, the joint surface and the shim plate 6 will be in close contact with each other. There are still problems to be solved, such as the drawability of the shim plate 6 is easily impaired, and the spot welded portion 5 and the shim plate 6 are welded.

The present invention has been made in view of these problems, and an object thereof is to improve the assembling accuracy by accurately setting the size of the small gap and to improve the workability at the time of setting the small gap.

[0008]

In order to solve these problems, in a method in which a plurality of module blades are brazed together and connected in the circumferential direction to assemble, molten metal is attached to the joint surface of the module blades. To form small protrusions, grind the small protrusions to set the protrusion height, and match the joint surfaces of the module blades and melt fill the small gap between them to integrate the module blades. The configuration having the steps of: In addition, a configuration using a paste-like brazing material is added to these means.

[0009]

The small protrusion formed by adhering the molten metal to the joint surface of the module blade is ground to set the protrusion height to a size corresponding to the desired small gap. When the height of the required number of small protrusions is set and the joint surfaces are matched, a uniform small gap is formed between the joint surfaces. When the brazing material is melt-filled in the small gaps of the plurality of module blades while maintaining the small gaps, the plurality of module blades are integrated and connected in the circumferential direction after the brazing material is solidified. If the brazing material is in paste form, the molten brazing material flows into the small gap by applying it inside the small gap or in the opening, and the bonding surface is maintained while maintaining the size of the small gap. To be in a joined state.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a method for assembling a turbine vane according to the present invention will be described in the order of steps based on FIG.
This embodiment is applied to the case where the module blade 1 is made of a cobalt-base heat-resistant alloy, and FIG. 1 shows the shape in a simplified state as in the example of FIG.

[Formation of Small Protrusions] As shown in FIG. 1 (a), a desired set dimension (for example, 0 .. Small protrusion 1 higher than 1 mm)
1 is attached and formed in an arbitrary number. The small protrusions 11 are formed on one of the joint surfaces that form a pair to be joined.

[Setting of Height of Small Protrusion] The portion of the small protrusion 11 is removed by grinding up to the portion shown by the chain line in FIG. 1 (a), and the desired setting is made as shown in FIG. 1 (b). Aligned to dimensions.

[Temporary Fixing of Module Wing] Module Wing 1
The small protrusions 11 are brought into close contact with the pair of joint surfaces, and the size of the small gap G is set by the protrusion height of the small protrusions 11. While maintaining the set size of this small gap G,
As shown in (c), temporary attachment by spot welding is performed, and the plurality of module blades 1 are integrated by forming spot welds 5. The small gap G in this state is the spot weld 5
The opening is formed along the edge of the joint surface by releasing almost the entire portion except the forming portion.

[Brazing] As the brazing material, a powder (for example, having a melting point of 1100 ° C.) made of a brazing compatible material for a cobalt-based heat resistant alloy is prepared by pasting with an organic solvent as described above, It is applied and attached to the entire circumference of the opening of the small gap G and the like. When the module blade 1 to which the brazing material is attached is housed in a heating furnace and melted by heating,
The molten brazing filler metal flows into and fills the small gap G. In this case, the facing dimension of the small gap G is set to the spot welding portion 5
And, the small projections 11 lead to a joined state while holding the same. After the brazing material is solidified, as shown in FIG. 1D, the plurality of module blades 1 are integrated by the brazing metal 12 and are connected in the circumferential direction to form a continuous blade.

[Other Embodiments] In the present invention, the following technique can be adopted instead of one embodiment. a) The number of connecting blades and the number of brazing of the module blade 1 are arbitrary plural. b) Applicable to brazing materials such as plates.

[0016]

The method of assembling a turbine vane according to the present invention has the following excellent effects. (1) A step of adhering molten metal to the joint surface of the module blade to form a small protrusion, a step of grinding the small protrusion to set the protrusion height, and a brazing material in a small gap between the joint surfaces. By adopting a configuration including a step of melting and filling the module blades to integrate the module blades, it is possible to accurately set the size of the small gap based on the height of the small protrusion and improve the assembling accuracy. (2) When a plurality of module blades are joined, the workability at the time of joining can be improved by inevitably setting a small gap based on the small protrusions.

[Brief description of drawings]

FIG. 1 is a process explanatory diagram of an embodiment of a method for assembling a turbine vane according to the present invention.

FIG. 2 is a perspective view showing an example of making a continuous blade by a module blade.

FIG. 3 is a perspective view showing a conventional example of a brazing method for making a module blade into a continuous blade.

[Explanation of symbols]

 1 Module Blade 2 Outer Ring Member 3 Inner Ring Member 4 Blade 5 Point Weld 6 Shim Plate 11 Small Protrusion 12 Brazing Metal G Small Gap

Claims (2)

[Claims] 1. A method of assembling a plurality of module blades by connecting them in the circumferential direction by brazing, the method comprising: adhering molten metal to a joint surface of the module blades to form small protrusions; A turbine comprising: a step of grinding a protrusion to set a protrusion height thereof; and a step of aligning the joint surfaces of the module blades and melting and filling a small gap between them with a brazing filler metal to integrate the module blades. How to assemble the stationary blade. 2. The method of assembling a turbine vane according to claim 1, wherein a paste-like brazing material is used.