JPH11211087A - Gas turbine flame propagation tube - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve assembling performance of a flame propagation tube and to reduce the replacting cost thereof due to damage. SOLUTION: The gas turbine flame propagation tube 1 comprises a tubular body 10 interconnecting two adjacent combustors 2, 2 among a plurality of combustors 2, 2 producing combustion gas of a gas turbine and the flame of combustion gas propagates from one of two combustors 2, 2 to the other through the tubular body 10. The tubular body 10 comprises two tubular parts 10a, 10b split at one central point in the axial direction thereof and these two tubular parts 10a, 10b are coupled removably in series through fitting structure.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flame transmission tube of a multi-can gas turbine, and more particularly to a device for the structure of a flame transmission tube.

[0002]

2. Description of the Related Art In a multi-can type gas turbine used in a power plant or the like, a gas turbine flame propagation tube connecting a plurality of combustors is used. Representative gas turbine equipment provided with this flame propagation tube will be described with reference to FIGS.

[0003] The gas turbine equipment shown in FIG. 3 compresses the atmosphere with an air compressor 101 coaxially connected to a turbine 100, supplies the compressed air to a cylindrical combustor 102, and a liner in the combustor 102. The fuel is combusted in the portion 102a, and the high-temperature combustion gas generated by the combustion is guided to the moving blade 105 via the turbine stationary blade 104 via the transition piece 103, and the moving blade 105 is rotated to rotate the turbine 1 Do the work.

Among them, a plurality (six in FIG. 4) of the gas turbine combustors 102 are arranged at predetermined intervals in the circumferential direction of the gas turbine rotating shaft AX as shown in the front view of FIG. A flame propagation tube 106 is arranged between two adjacent combustors 102,102. At least one (two in FIG. 4) combustor 102 is provided with an igniter 107.

[0005] The gas turbine combustor 10 having the above-described configuration is used.
In step 2, the compressed air and the fuel are mixed to form a combustible mixed gas. The combustible mixed gas ignites when the igniter 107 generates an electric spark, generates a flame, and expands. Therefore, there is a difference in internal pressure between the combustor 102 in which the igniter 107 is installed and the combustor 102 in which the igniter 107 is not installed. Is introduced, thereby igniting the combustible mixed gas in the combustor 102 where the igniter 107 is not installed.
Thereafter, the combustion gas is guided to the combustor 102 without the igniter 107 via the flame propagation tube according to the same principle, and finally the combustion gas is generated in all the combustors 102.

The plurality of combustors 102... 102
Are connected by a flame propagation tube, the number of igniters 107 to be installed can be reduced, and even if the combustor 102 is misfired for any reason, the adjacent combustor 102 can immediately re-ignite, so that more stable combustion can be achieved. There is an advantage that it can be maintained.

FIG. 5 is an assembled sectional view of a conventional flame propagation tube 106. At the time of rated operation, the adjacent combustors 102, 1
02, a high-temperature gas may flow through the flame propagation tube 106 from the high-pressure combustor 103 to the low-pressure combustor 103. Therefore, a balance hole 108 for taking in outside air is provided in the flame propagation tube 106.
When there is a pressure difference between the combustors 102 and 102, air is received from the balance holes 108 to maintain the pressure balance, and high-temperature combustion gas flows between the combustors 102 and 102. The components of the flame propagation tube 106 are prevented from being damaged by heat. In addition, the air entering from the balance hole 108 simultaneously
By lowering the temperature of the flame by being mixed with the flame propagating between 2 and 102, it has a role to amplify the above-described effect of preventing the thermal damage.

Also, two adjacent combustors 102, 10
When assembling the flame propagation tube 106 connecting the two, one end of the flame propagation tube is inserted from the inside of the flow sleeve 109 into the hole 110 provided in the flow sleeve 109 of the combustor, and this is supported by the support 111. (The reference numeral 112 in the drawing denotes the color of the combustor liner 102a,
Reference numeral 113 indicates an entrance portion).

[0009]

In the above-mentioned conventional gas turbine, the number of cans in the combustor can be reduced as much as possible.
If it is unavoidable to increase the mounting angle of the combustor or if the diameter of the combustor is considerably reduced due to the flammability problem in the combustor, the distance between adjacent combustors will increase. Therefore, it is necessary to use a long gas turbine flame propagation tube, and when the inner diameter of the flow sleeve is almost equal to the length of the flame propagation tube, or when the length of the flame propagation tube is longer than the inner diameter of the flow sleeve, etc. is there.

As described above, when the length of the flame propagation tube is increased, when the flame propagation tube is inserted into the hole from the inside of the flow sleeve, the end of the flame propagation tube located on the opposite side of the hole and the inner surface of the flow sleeve. Interfere with each other, making assembly very difficult.

Although the effect of the balance hole is provided as described above, the inlet of the flame propagation tube may be damaged by receiving a high-temperature gas. When the flame transmission tube is damaged beyond repair as described above, it is necessary to replace the entire flame transmission tube even if only the entrance of the flame transmission tube is damaged.

The present invention has been made in view of such conventional circumstances, and has as its object to improve the assemblability of a flame transmission tube and to reduce replacement costs due to damage to the flame transmission tube.

[0013]

In order to achieve the above object, a gas turbine flame spreader according to the present invention comprises two adjacent combustors among a plurality of combustors for producing combustion gas of a gas turbine. A tubular body that interconnects between the two combustors, through which the flame of the combustion gas is propagated from one of the two combustors to the other combustor, The tubular body is constituted by a plurality of tubular parts divided in the axial direction, and the tubular parts are detachably connected in series in a fitting structure.

Preferably, the plurality of tubular parts are two tubular parts obtained by dividing the tubular body at one central portion in the axial direction, or the tubular body is divided into two axial ends.
It is assumed that there are three tubular parts divided at each location.

As described above, when the gas turbine flame propagation tube is formed into a two-part structure having a fitting structure near the center in the longitudinal direction or a three-part structure having a fitting structure near both ends in the longitudinal direction, The length per piece (tubular part) of the flame-spreading tube with a two-piece structure is about half that of the length of the integrated flame-propagating pipe of the above, and the middle piece of the flame-spreading pipe with a three-piece structure is about 70% Since the pieces at both ends are quite short, about 20% in length, the end of the flame propagation tube located on the side opposite to the hole side of the flow sleeve and the inner surface of the flow sleeve at the time of assembling the flame propagation tube are different from each other. There is no inconvenience such as interference, which greatly improves the assemblability of the flame propagation tube.

Further, in the case of the conventional integrated flame propagation tube, even if a very small area at the entrance of the flame propagation tube is damaged, it is necessary to replace the entire flame propagation tube, which may increase costs more than necessary. However, in the case of the two-piece structure, only the damaged tubular part is replaced, and in the case of the three-piece structure, only the short tubular part at the end is replaced, so that the cost can be reduced. There is also an advantage that it can be done.

[0017]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a gas turbine flame transmission tube according to the present invention will be described below with reference to the drawings.

(First Embodiment) A gas turbine flame propagation tube 1 shown in FIG. 1 is a two-combustor 2 of a plurality of combustors 2... And a tubular body 10 that connects the two combustors 2 to each other, and the igniter is not installed from the combustor 2 provided with the igniter 3 of the two combustors 2 through the tubular body 10. The flame of the combustion gas is propagated toward the combustor 2.

The tubular main body 10 is composed of two tubular parts 10a and 10b divided near the center in the longitudinal direction of the flame propagation tube 1, and the two tubular parts 10a and 10b are connected to each other by a fitting part forming a pair. (A pair of concave and convex portions) It is configured to be detachably connected in series via 11a and 11b. Balance holes 12 are formed at predetermined positions on the outer surface of each of the tubular parts 10a and 10b.

The steps of assembling the gas turbine flame propagation tube 1 having such a two-part structure will be described with reference to FIG.

First, after assembling the flow sleeve 20 of one of the two adjacent combustors 2, 2, the tubular main body 10 is inserted into the hole 21 for the flame propagation tube formed in the flow sleeve 20. Two tubular parts 10a, 1
0b is connected to the flow sleeve 2
Insert from inside 0. After assembling the liner 22 of the combustor 2, the previously inserted tubular part 10 a is inserted into the collar 23 of the liner 22, and this is fixed with the support 24 (the reference numeral 25 in the drawing indicates an inlet).

Next, the flow sleeve 20 of the other combustor 2 is assembled, and the other tubular part 10b is inserted from the inside of the flow sleeve 10 into the hole 21 for the flame propagation tube drilled in the flow sleeve 20. The assembled tubular parts 10a are fitted with each other at fitting parts 10a and 10b. Then, after assembling the liner 22 of the combustor 2, the tubular component 10 b is inserted into the collar 23 of the liner 22, and this is fixed with the support 24.

Therefore, according to this embodiment, since the length of the flame propagation tube per piece is about half as short as the length of the conventional integral type, the length of the flame transmission tube is smaller than the length of the flow sleeve. It is possible to easily assemble the flame spread tube without the end of the flame spread tube on the opposite side and the flow sleeve interfering with each other.

Even if the flame propagation tube is damaged beyond repair by the high temperature gas flowing in the flame propagation tube due to the pressure difference between the combustors at the time of rated operation,
In the case of the flame propagation tube having the split structure, only the damaged part needs to be replaced, so that the maintenance cost can be greatly reduced.

(Second Embodiment) A gas turbine flame propagation tube 1 shown in FIG. 2 has three tubular parts 30 obtained by dividing a tubular body 10 similar to the above at two longitudinal ends.
a, 30b, 30c, each of these tubular parts 30a,
30b and 30c are configured to be detachably connected in series via mating portions (a pair of concave and convex portions) 31a, 31b (two end portions), and 31c that form a pair.
Balance holes 32 are formed at predetermined positions on the outer surface of each of the tubular parts 30a.

A process for assembling the gas turbine flame propagation tube 1 having such a three-part structure will be described with reference to FIG.

First, after assembling the flow sleeve 20 of one of the two adjacent combustors 2, 2,
The tubular part 30b located at the center of the three tubular parts is inserted into the flame transmission tube hole 21 of the flow sleeve 20 from the inside of the flow sleeve 20. Then, the tubular part 30a at the end is connected to the collar 23 of the liner 22 in the combustor 2.
The tubular part 30a and the previously inserted tubular part 30b are fitted together via the fitting parts 31a and 31b, and the tubular part 30a is held by the support 24. Fix (reference numeral 2 in the figure)
5 indicates an entrance).

Next, the remaining tubular part 30 of the three
c to the color 15 of the liner 22 in the other combustor 20.
The tubular part 30c and the previously assembled tubular part 30b are fitted via fitting parts 31b and 31c, and the tubular part 3 is inserted.
0c is fixed with the support 24.

Therefore, according to this embodiment, since the length of the flame transmission tube per piece is about 70% shorter than that of the conventional integral type, the flow tube has a flow sleeve. The end of the flame propagation tube on the opposite side of the hole side and the inner surface of the flow sleeve do not interfere with each other,
The flame propagation tube can be easily assembled.

Further, even if the flame propagation tube is damaged beyond repair by the high temperature gas flowing through the flame propagation tube due to the pressure difference between the combustors at the time of rated operation,
In the case of the flame propagation tube having the divided structure, only the extremely short tubular parts at both ends damaged can be replaced, so that the maintenance cost can be greatly reduced.

[0031]

As described above, according to the present invention,
The main body of the flame propagation tube is constituted by a plurality of tubular parts divided in the longitudinal direction, for example, a two-part structure divided at the center in the longitudinal direction, or a three-part structure divided near both ends in the longitudinal direction. In the case of the two-piece structure, the length per piece is about half, and in the case of the three-piece structure, the center piece is about 70%, The piece can be constructed sufficiently short to be about 20%, and the flame propagation tube can be easily assembled without interference between the end of the flame propagation tube on the side opposite to the flame propagation tube hole side of the flow sleeve and the inner surface of the flow sleeve. Can be.

Further, even if the flame propagation tube is damaged beyond repair due to the high temperature gas flowing in the flame propagation tube due to the pressure difference between the combustors at the time of rated operation, for example, a two-part structure In the case of the flame-propagating tube described above, only the damaged tubular part, or in the case of the flame-dividing tube having a three-part structure, only the tubular part having a short end need be replaced, so that the maintenance cost can be greatly reduced. .

[Brief description of the drawings]

FIG. 1 is a schematic sectional view showing a gas turbine flame propagation tube according to a first embodiment.

FIG. 2 is a schematic sectional view showing a gas turbine flame propagation tube according to a second embodiment.

FIG. 3 is a schematic configuration diagram showing the entire configuration of a conventional gas turbine.

FIG. 4 is a schematic front view showing an arrangement of a conventional combustor.

FIG. 5 is a schematic sectional view showing a conventional flame propagation tube.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Gas turbine flame propagation tube 2 ... 2 Combustor 3 Ignition device 10 Tubular body 10a, 10b Two-part structure tubular part 11a, 11b Fitting part 20 Flow sleeve 21 Flame propagation tube hole 22 Combustor liner 23 Collar 24 Support 25 Inlet part 30a, 30b, 30c Tubular part 31a, 31b, 31c of three division structure Fitting part

Claims (3)

[Claims] 1. A gas turbine, comprising: a tubular body interconnecting two adjacent combustors of a plurality of combustors for producing combustion gas of a gas turbine;
A gas turbine flame propagation tube for propagating the flame of the combustion gas from one of the combustors to the other combustor, comprising a plurality of tubular parts obtained by dividing the tubular body in the axial direction. A gas turbine flame propagation tube structure comprising: a tubular structure; 2. The gas turbine flame propagation according to claim 1, wherein the plurality of tubular components are two tubular components obtained by dividing the tubular main body at one central portion in the axial direction. tube. 3. The gas turbine according to claim 1, wherein the plurality of tubular parts are three tubular parts obtained by dividing the tubular main body at two positions at both ends in the axial direction. Flame propagation tube.