JPH01321084A - Laser beam spot welding method for gas turbine combustor - Google Patents

Abstract

PURPOSE:To improve strength of weld zones and welding quality by forming a bead pattern of laser beam spot welding into a square spiral shape and performing lap welding of inner cylinder rings and waveform plates adjacent mutually. CONSTITUTION:The inner cylinder rings 1 and the waveform plates 2 being adjacent mutually are pressed via a jig and the laser beam spot weld zones 3 where the prescribed quantities of gaps are held are formed. A laser beam machine is then set to the outsides of the inner cylinder rings 1 and the waveform plates 2 to perform laser beam spot welding on the spot weld zones while being shielded by N2 gas, etc. At this time, the bead pattern of the spot weld zones 3 is formed into the square spiral shape to shift from the center to the outside and laser beam machining is performed. By this method, ring 1 end fitting parts hold large welding areas and are subjected to laser beam spot welding. Accordingly, the need for brazing the weld zones is eliminated and welding strength is improved. Since welding is performed automatically, welding quality is also improved.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a method for laser spot welding of a plurality of inner cylinder rings constituting a gas turbine combustor inner cylinder.

[Conventional technology]

As shown in the side view of FIG. 5, the gas turbine combustor inner cylinder is composed of a plurality of inner cylinder rings 1 each having a combustor inner cylinder diameter arranged in the axial direction, and adjacent ends of which are fitted into each other. To join the mating ends, a corrugated plate is interposed between the mating inner cylinder rings 1, and the overlapping parts of each inner cylinder ring and the corrugated plate are welded by resistance spot welding. ing.

However, resistance spot welding is difficult to automate, and attempts have been made to adopt laser spot welding, but this method uses a combination of Ni brazing and laser spot welding to provide strength. It is not comparable in strength to spot welding.

[Problem to be solved by the invention]

The present invention was proposed in view of these circumstances, and
Welding of the fitting part of the end of the inner cylinder ring is performed by automated laser spot welding to secure a large welding area, and welding of the gas turbine combustor that does not require any brazing process and produces a high-strength welded part. The purpose is to provide a laser spot welding method.

[Means to solve the problem]

To this end, the present invention employs laser spot welding using a laser processing machine when overlapping and welding the fitting ends of each adjacent ring of a plurality of axially arranged inner cylinder rings constituting the gas turbine combustor inner cylinder through a corrugated plate. It is characterized in that the bead pattern of the overlap welded portion used is a rectangular spiral shape that moves from the center to the outside.

[For production]

With the above configuration, the welding of the fitting part of the end of the inner cylinder ring can be performed by automated laser spot welding to secure a large welding area, and it is possible to obtain a welded part with high welding strength that does not require any brazing process. A method for laser spot welding of a gas turbine combustor can be obtained.

〔Example〕

An embodiment of the laser spot welding method for a gas turbine combustor according to the present invention will be explained with reference to the drawings. FIG. 1 is a plan view showing the implementation procedure, FIG. 2 is a cross-sectional side view, FIG. 3 is a vertical cross-sectional plan view, and FIG. FIG. 4 is an explanatory diagram of the same bead pattern as above.

In FIGS. 1 to 3, the laser spot welding part 6 is
Pressure is applied to each overlapped part of the inner cylinder ring 1 and the corrugated plate 2 using a jig stretched out from the center of the inner side to maintain the gap between the overlapped parts at 0.2 am or less, and the inner cylinder ring 1. Set the laser processing machine from the outside of the corrugated plate 2, and cut the average amount cuff 5.
0W, continuous beam, lens focus 190.5"#CO2 laser with speed 850sn/min - Place the workpiece within ±1 inch from the focus of the beam, and protect the spot weld with N2 gas as shown in Figure 4. A rectangular spiral bead pattern is formed moving from the center to the outside, and laser spot welding is performed over a large welding area.

In addition, at the end of one spot welding, the laser output is sloped down (8 seconds), and the beam is repeatedly rotated around the outer periphery of the laser spot welding part 3 of the workpiece until it stops completely. The laser spot welding part 3 is protected by N2 gas.

〔Effect of the invention〕

In short, according to the present invention, when the fitting ends of each adjacent ring of a plurality of axially arranged inner cylinder rings constituting the gas turbine combustor inner cylinder are overlap welded via a corrugated plate, a laser processing machine is used. Laser spot welding is used to automate welding of the end fitting part of the inner cylinder ring by making the bead pattern of the lap weld into a rectangular spiral shape that moves from the center to the outside.Large welding area is ensured by laser spot welding. The present invention is industrially extremely useful because it provides a laser spot welding method for a gas turbine combustor that can obtain a welded part with high weld strength without requiring any brazing treatment.

[Brief explanation of the drawing]

Fig. 1 is a plan view showing an implementation procedure of an embodiment of the laser spot welding method for a gas turbine combustor according to the present invention, Fig. 2 is a cross-sectional side view thereof, Fig. 3 is a longitudinal sectional front view, and Fig. 4 is the same as above. An explanatory diagram of the bead pattern, FIG. 5 is a side view showing the inner cylinder of the gas turbine combustor. 1... Inner cylinder ring, 2... Corrugated plate, 3... Laser spot welding part. Agent Masa Tsukamoto, Patent Attorney Figure 1 Figure 2 Figure 3 Figure 4 Figure 5

Claims (1)

[Claims] Laser spot welding using a laser processing machine is used to overlap and weld the fitting ends of each adjacent ring of a plurality of axially arranged inner cylinder rings constituting the gas turbine combustor inner cylinder through a corrugated plate. A method for laser spot welding of a gas turbine combustor, characterized in that the bead pattern of the overlap welded part is a rectangular spiral shape moving from the center to the outside.