JPS62106224A - Support device for gas turbine combustor - Google Patents

Abstract

PURPOSE:To make small the torsional vibration acting on a transition piece and reduce the wear on a side seal by increasing the number of rear side support points of the transition piece and providing the support position on both side faces of the transition piece. CONSTITUTION:On the rear side face of a transition piece 4 a base 14 of the subject device is welded. A bracket 19 for mounting a transition piece 4 to a gas turbine casing is formed in a plate form, and the base 18 and the bracket 19 are connected by a pin 20. The device is mounted at two places so that the device is symmetrical with respect to both side faces. With this arrangement torsional vibration of the transition piece 4 generated around the support device becomes small. As a result, the up-and-down vibration 16 of the transition piece 4 in the vicinity of a side seal 17 also becomes small and reduces the wear on the side seal 17. Further, air 2 of relatively low temperature from a compressor directly hits the surface of the transition piece 4 round the support base 18, where a largest stress develops and lowers the metal temperature, restraining drop in the tensile strength.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Application of the Invention] The present invention relates to a support device for a gas turbine combustor tractor 7 bead.

[Redundant background]

FIG. 5 is a diagram of the gas turbine combustor 6 and its surroundings. The air 2 compressed by the compressor 1 passes through several to several transition pieces 4 arranged around the rotor 3. Then, it flows around the combustor inner cylinder 5, and then flows into the cylinder through the air hole formed in the combustor inner cylinder 5. Here, it is mixed and diffused with the fuel sprayed from the fuel nozzle 6, ignited by the spark plug 7, and combusted. The combustion gas 8 passes through the combustor inner cylinder 5 and the transition piece 4, flows into the turbine section 9, rotates the rotor 3, becomes exhaust gas 10, and is emitted to the atmosphere. As a method of supporting the transition piece 4, two places in front 1111 of the transition piece 4 (on the upstream side in the flow direction of the combustion gas 8) are placed so that the heat elongates in the direction opposite to the flow of the combustion gas 8 of the tiger 7 and the bead 4. The support part has a structure that allows
11, and the support part on the rear side (downstream side in the flow direction of combustion gas 8) of the transition piece 4 is made by Japanese Patent Application Laid-Open No. 57-16.
No. 8024 and ASME 81-GT-31 F
It is a support device as seen in 'ig, 8.
As shown in Figure 5, the dorsal side of the transition piece (
The rotor 3 was supported at a point (radially outward) around the rotor 3. Details of the conventional rear support device 12 of this transition piece are shown in FIG.

Support@fit is ik on the body of transition piece 4
[[The attached base 13, the bracket 14 attached and fixed to the gas turbine loaning, and the base 1
3 and a bin 15 connecting the bracket 14.

With reference to FIG. 7, a case will be described in which a conventional support device is used. The transition piece 4 is constantly exposed to complex vibrations due to mechanical vibrations generated by gas turbine operation and combustion vibrations generated when air reacts with fuel.

Therefore, twisting occurs around the rear support @t12 of the transition piece 4, and vibrations 16 mainly appear on both sides of the rear end of the transition piece. A plate-shaped seal called a side 7-rule 17 is inserted between adjacent trunnion position 7 beads to prevent the air 2 from the compressor from directly flowing into the turbine. However, this side 7-rule 17 is likely to wear out due to the upper and lower vibrations 16 of the transition piece 4. This side/-le 17
When the wear of the gas turbine becomes severe, the leakage of air 2 into the turbine increases, causing a decrease in the efficiency of the gas turbine.

On the other hand, a large load acts on the support ax2 in order to suppress the moment of inertia caused by the vibration of the entire rear side of the transition piece 4. In addition, this support device 12
The back side of the transition piece 4 to which it is attached is not directly exposed to the low-temperature air 2 from the compressor, and the metal temperature increases, reducing the tensile strength of the material itself. , cracks were likely to occur in the main body of the transition piece 4 around the support device 12.

[Purpose of the invention]

It is an object of the present invention to reduce the movement of the transition piece, thereby reducing wear on the side rail, and to prevent cracks in the transition piece body around the mounting of the support device, thereby improving reliability. The objective is to provide a high quality gas turbine combustor.

[Summary of the invention]

The present invention increases the rear support of the transition piece from one point to two points, reduces the load applied to the support part, and also moves the support positions to both sides of the transition piece. Reduces the torsional vibrations acting on the transition piece, thereby increasing the
-Less wear on the wheels. The thermal elongation in the lateral direction, which is a problem due to having two rear support points, can be released by combining the support device with a plate-shaped bracket and a bottle joint. It is.

[Embodiments of the invention]

FIG. 1 shows an embodiment of the present invention. The base 18 of the device is attached to the rear side surface of the transition piece 4. A bracket 19I″i for attaching the transition piece 4 to the gas turbine loafing is made in a plate shape 9. The base 18 and the bracket 19 are connected by a pin 20.

Install this device in two locations symmetrically on both sides.

Figure 2 is a comparison of one device viewed from the back side of the transition piece, and Figure 3 is a comparison view of the device from the side of the transition piece. Next, a countermeasure against thermal expansion in the lateral direction (tangential direction centered on the gas turbine rotor) of the transition piece after the start of gas turbine operation, which is a problem caused by supporting the transition piece in two places, will be explained.

When the transition piece 4 undergoes thermal elongation 21 in the lateral direction as shown in FIG. 3, the plate-shaped bracket 19 bends outward and escapes in the direction of the arrow 22. However, in this case, the thermal elongation direction 21 and the arrow 2 which is the direction in which the bracket 19 is released
2 do not match, at the joint between the base 18 and the bracket 19.

Rotation or birth. In order to allow for this rotation, the base 18 and the bracket 19 are connected through the bin 20 so as to be perpendicular to the longitudinal direction of the bracket 19, as shown in FIG.

Finally, the present invention will be implemented and the effects will be shown in the case where the present invention is insufficient. Figure 4 is 1
FIG. 4 is a view of the transition piece 4 with which the present device is attached, seen from the rear.

Since the transition piece 4 is supported by two plackets 19 on both sides of the transition piece 4, the torsional vibration of the transition piece 4 centered on the support device, which occurs when the transition piece 4 is supported at one place as in the past, is reduced. ,the result,
On the transition piece 4 near the side seal 17.
The lower vibration 16 is also reduced, and wear of the vertical seal 17 can be reduced.

In addition, by placing the supporting position on the side of the transition piece 4, as shown in FIG.

As mentioned above, it is effective to reduce the temperature of the metal that directly contacts the surface of the transition piece 4 around the support base 18, where the largest stress is applied, and to suppress the decrease in tensile strength due to the rise in temperature of the material itself. Furthermore, since the stress acting on the support portion can be reduced, the durability of the transition piece can be improved.

〔Effect of the invention〕

According to the present invention, it is possible to reduce the vibration of the transition piece, thereby reducing the wear of the side seal.

In addition, the attachment of the support device can prevent cracks in the transition piece body around the part, improving durability and reliability.

[Brief explanation of drawings]

FIG. 1 is a perspective view of a transition piece having a support device according to an embodiment of the present invention, FIG. 2 is a front view of a support device according to the present invention, and FIG. 3 is a side view of a transition piece having a support device according to the present invention. Fig. 4 is a rear view of a transition piece with a support device according to the present invention, Fig. 5 is a cross-sectional view of the gas turbine air flow, the combustor and the surroundings of the transition piece, and Fig. 6 is a rear view of a conventional transition piece. A perspective view of the device, FIG. 7, is a side view of a transition bead with a conventional support device.

Claims (1)

[Scope of Claims] 1. A support device for a gas turbine combustor, characterized in that downstream side support of a combustion gas flow of a transition piece of the gas turbine combustor is performed at two locations on both sides of the transition piece. 2. A support device for a gas turbine combustor according to claim 1, characterized in that the support device for a gas turbine combustor has a structure that does not restrict the thermal expansion of the transition piece in the lateral direction by combining a pin and a flat plate.