JPS5924243B2 - Method for manufacturing hollow blades for gas turbines - Google Patents

Description

[Detailed Description of the Invention] The pursuit of higher output and higher performance of aviation gas turbines is being constantly pursued, and it is currently believed that achieving these demands by increasing the turbine operating temperature is likely. Therefore, various techniques for cooling turbine blades have been researched and developed as a way to maintain long life at high operating temperatures.

Figure 1 shows an example of a hollow wing formed by a conventional manufacturing method, in which a is the outer blade plate, ba c is the inner blade plate, d,
e indicates holes for cooling air passages provided in the wing outer plate a and the inner wing plates S and C, respectively, and the inner wing plate bee is joined to the inner surface of the wing outer plate a by the following method. was.

(a) Brazing method (b) Welding method (c) Diffusion bonding method However, in the method (a) above, the entire joint surface of the blade outer plate a and the blade inner plate A and C is bonded. However, the brazing filler metal blocks holes d and e, and in the method (b) above, it is not possible to join the outer blade plate a and the inner blade plate s and c over the entire joint surface. In addition, in the method mentioned above, the inner blade plate, c
If a force is not applied to the wing outer plate a from the inside, sufficient joint strength cannot be obtained, but with a wing of this shape, even and large pressure from the inside applies force to the entire surface of the inner wing plate c. Each of them had various problems, such as being unable to do so.

The present invention can solve the problems of the conventional method described above, by dividing a blade skin substantially linearly in the chord length direction and forming grooves for cooling air passages on the inner surface of the divided blade skin. The present invention relates to a method for manufacturing a hollow blade for a gas turbine, characterized in that after bonding the blade inner plate having the above structure by diffusion bonding, the divided blade outer plate is bonded by diffusion bonding.

Embodiments of the present invention will be described below with reference to the drawings.

As shown in Figs. 2 and 4, the wing skin 1 is divided into an upper wing skin 1a and a lower wing skin 1b by cutting approximately straight along the chord length direction (left-right direction in Fig. 4) K. An upper wing inner plate 2 and a lower wing inner plate 3 are separately attached to the inner surfaces of the upper wing outer plate 1a and the lower wing outer plate 1b, respectively.

The lower wing inner plate 3 attached to the inner surface of the lower wing outer plate 1b has an inner member 3a, an intermediate member 3b, and an outer member 3c that are curved along the inner surface of the lower wing outer plate 1b, as shown in FIG. A vertical groove 4 for a cooling air passage is formed on the side surface of the lower wing outer plate 1b of the inner member 3a and the outer member 3c,
Further, a lateral groove 5 is formed on the side surface of the lower wing outer plate 1b of the intermediate member 3b, and furthermore, a small hole 6 is provided in each of the grooves 4 and 5.

Further, as shown in FIG. 4, a small hole 7 is formed in the lower wing outer plate 1b at a position that coincides with the longitudinal groove 4 of the inner material 3a, and other parts are also connected to the guide hole 8.9. / do hole 10 is formed.

The upper wing inner plate 2 attached to the inner surface of the upper wing outer plate 1a includes an inner member 2a and an intermediate member 2 each having a shape that is curved in a direction reflecting the respective curvatures of the lower wing inner plate 3 in FIG.
b, is formed from the outer material 2c, and the lower wing inner plate 3
The vertical groove 4 of the inner member 2a matches the small hole 7 provided in the upper wing outer plate 1a.

Next, a procedure for manufacturing the hollow blade for a gas turbine according to the present invention will be explained.

In Fig. 4.5.6, 11.12.13.14 are joined by pressing the upper wing inner plate 2 and the lower wing inner plate 3 against the upper wing outer plate 1a and the lower wing outer plate 1b with equal force. The jig for performing this is shown.

First, as shown in FIG. 5, in a state where the inner material 2a, the intermediate material 2b, and the outer material 2c are sequentially supported on the inner surface of the upper wing outer panel 1a, the upper wing inner panel 2 is supported by the jig 13, and the upper The blade outer plate 1a is supported by a jig 11.

In this state Vci-, if a pressing force is applied from the direction of the arrow for a predetermined period of time while maintaining the specific temperature and atmosphere of the materials constituting the upper wing outer plate 1a and the upper wing inner plate 2,
The inner material 2a is attached to the inner surface of the upper wing outer plate 1a.
The intermediate material 2b is for the intermediate material 2b, and the outer material 2 is for the intermediate material 2b.
c are diffusion bonded via the convex portions formed in the grooves 4 and 5, respectively.

Similarly, as shown in FIG. 6, the lower wing outer plate 1b and the lower wing inner plate 3 are also diffusion bonded by pressing the jigs 12 and 14 in the direction of the arrow under the same conditions.

The upper wing skin plate 1a and the lower wing skin plate 1b to which the wing inner plates 2 and 3 are joined are cured again at a temperature and atmosphere determined for the materials of the wing skin plates 1a and 1b, as shown in FIG. Ingredients 11.1
By applying pressure in the direction of the arrow through 2, the hollow blade for a gas turbine of the present invention is formed by diffusion bonding.

When performing the above-mentioned diffusion bonding, the blade outer plate is separated approximately linearly along the chord length direction, and the inner plate also has a surface shape between the grooves. It is possible to secure the bonding surface, and therefore each bonding surface is
2, 13, and 14, the bonding can be easily performed by pressing uniformly and with a predetermined pressure.

It should be noted that the present invention is not limited to the above-mentioned embodiments, and although the explanation has been given by taking as an example the case where the inner blade has a triple structure, it is understood that this can be similarly implemented in the case of a single layer or multiple layers, and that Even if the plate has holes, grooves, corrugations, etc. other than shown in the drawings to allow the cooling fluid to pass through, the same process can be carried out, and the blade skin may be divided into two or more pieces at positions other than those shown in the drawings. We have described the case of diffusion bonding as a bonding method, but we have also explained that an insert material may be inserted into the bonding surface to make bonding easier. Of course, various changes may be made within the scope.

According to the above-described method for manufacturing a hollow blade for a gas turbine of the present invention, (1) the blade outer plate is divided into a plurality of pieces to form a cooling fluid passage inside the blade, so that a hollow blade with a complicated internal shape is produced; can be easily manufactured.

(11) By dividing the wing outer plate, when joining the wing inner plate to the wing outer plate, any pressure for joining can be easily and reliably applied evenly.

(iii) Item (11) above improves the bonding conditions and ensures the bonded state, thereby preventing fluid leakage at the bonding surfaces between multiple members of the wing outer plate, the wing inner plate, and the wing inner plate. .

(By properly performing the ψ joint, the heat conduction characteristics between the blade outer plate and the blade inner plate improve, and the cooling effect improves.

(ψ Improving the strength of the joint also improves the strength of the blade.

(Vi) By cutting the dividing surface of the blade outer plate linearly along the chord length direction, a sufficient joint area can be ensured.

etc., exhibits various excellent effects.

[Brief explanation of drawings]

Fig. 1 is a cross-sectional view showing an example of a wing formed by the conventional manufacturing method, Fig. 2 is a partially cutaway perspective view of a hollow airfoil formed by the manufacturing method of the present invention, and Fig. 3. 4 is an explanatory enlarged perspective view showing an example of the inner wing plate, FIG. 4 is an explanatory drawing showing the shape and joint state of the wing when FIG. 2 is viewed in the IV-IV force direction, and FIG. An explanatory diagram of the state of connection between the plate and the upper wing inner plate,
FIG. 6 is an explanatory diagram of the joined state of the lower wing outer plate and the lower wing inner plate. 1 is a wing skin plate, 1a is an upper wing skin plate, 1b is a lower wing skin plate, 2
is the upper wing inner plate, 3 is the lower wing inner plate, 4 is the vertical groove, 5 is the horizontal groove,
6.7 is a small hole, 11.12.13.14 is a jig.

Claims (1)

[Claims] 1 After dividing the blade outer plate approximately linearly in the chord length direction and bonding the blade inner plate having cooling air passage grooves to the inner surface of the divided wing outer plate by diffusion bonding, the above-mentioned division is performed. A method for manufacturing a hollow blade for a gas turbine, characterized in that the blade outer plates are bonded together by diffusion bonding.