JP3915423B2 - Gas turbine combustor liner structure and repair method - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a gas turbine combustor liner structure and a repair method thereof.
[0002]
[Prior art]
FIG. 2 shows a general structural sectional view of a gas turbine. The gas turbine is roughly composed of a compressor 1, a combustor 2 and a turbine 3.
[0003]
The compressor 1 adiabatically compresses air sucked into the gas path 4 from the atmosphere as a working fluid, and the combustor 2 mixes fuel with the compressed air supplied from the compressor 1 and burns to generate high-temperature and high-pressure gas. The turbine 3 generates rotational power when the combustion gas introduced from the combustor 2 is expanded. Exhaust gas from the turbine 3 is released into the atmosphere. The remaining power obtained by subtracting the power for driving the compressor 1 from the rotational power generated in the turbine 3 becomes the power generated by the gas turbine and drives the generator.
[0004]
As shown in FIG. 1, the combustor includes a liner 5, a transition piece 6, a liner 5, and a flow sleeve 7 positioned outside the transition piece 6 for promoting cooling.
[0005]
The liner 5 is processed into a cylindrical shape after processing the cooling hole 13 as a cooling hole in the corrugated plate, and a circular lip 17 is attached to the inner peripheral side of the cooling hole 13 to directly contact the cooling air, It has a function of cooling the liner 5.
[0006]
Therefore, on the inner surface of the liner 5, the temperature difference between the region exposed to the high-temperature combustion gas and the region where cooling is intended increases, and high thermal stress tends to be generated.
[0007]
The liner 5 exposed to such a harsh environment is most likely to be damaged, such as combustion vibration due to thermal fatigue and unstable combustion, and is a part that regulates the life as a part of the combustor 2.
[0008]
As an example of a method for repairing the liner 5 of such a combustor, JP-A-61-61
There is a “combustion chamber structure” disclosed in Japanese Patent No. 231331. This structure is intended for aircraft engines, and was damaged by forming a tubular liner by nesting a plurality of annular members made of heat-resistant and high-strength material difficult to weld in the axial direction. It is easy to replace and repair parts.
[0009]
On the other hand, as a liner for a welded structure, those disclosed in JP-A-55-85822 are known. The known example discloses a state in which a liner member divided into a plurality in the axial direction of the liner has a shape whose inner diameter changes in the axial direction, and a small diameter portion and a large diameter portion are inserted and welded together. Has been.
[0010]
[Problems to be solved by the invention]
In recent years, in gas turbine facilities, an increase in output has been demanded in order to cope with an increase in power demand in summer, and an increase in efficiency for the purpose of energy saving has been demanded.
[0011]
As a means for increasing the output, there is a tendency to increase the annular flow passage area, that is, the size of the gas turbine. Further, as means for improving efficiency, there is a tendency to increase the compressor pressure ratio and improve the combustion temperature.
[0012]
Since these are all directly linked to the increase in temperature and pressure load acting on the combustor, it is expected that the combustor will be exposed to higher temperature, higher pressure load, and higher combustion vibration environment. There is a need to improve the service life and extend the service life.
[0013]
Furthermore, in recent years, with the increasing social demand for price reduction, there is an urgent need to reduce power generation costs. In particular, the cost of repairing high-temperature parts such as combustors and turbine blades and stators occupies much of the repair cost of gas turbines, and it is required to reduce the periodic inspection period and man-hours.
[0014]
In addition, since the actual load environment of the actual power plant varies, the initial cooling design may not necessarily be the optimal design. Therefore, a cooling design that appropriately corresponds to the actual load environment is also important for extending the life of the combustor.
[0015]
However, in the structure of the above known example, due to the use of heat-resistant and high-strength material that is difficult to weld, since the fitting structure is adopted, the rigidity of the liner cannot be sufficiently secured, and combustion vibration Is not enough.
[0016]
An object of the present invention is to facilitate repair and replacement of a gas turbine combustor liner.
[0017]
[Means for Solving the Problems]
As an example of means for achieving the object of the present invention, a corrugated plate provided with cooling holes is processed into a corrugated plate shape by bending, and a liner cap into which a fuel nozzle is inserted is attached to one end surface of the corrugated plate cylinder. In addition, a leaf spring that is inserted into the transition piece is attached to the outer surface of the corrugated cylinder at the other end, a cylindrical lip is attached to the inner peripheral surface of the cooling hole, and cooling is performed by releasing heat from the lip. In the container, the liner is divided into a plurality of members in the axial direction, the members are joined by welding, the liner is formed, and only the damaged member is replaced to facilitate repair and replacement.
[0018]
DETAILED DESCRIPTION OF THE INVENTION
FIG. 1 is a structural diagram of a gas turbine combustor. A combustor 2 includes a cylindrical liner 5 in which combustion is performed, and a working fluid from a cylindrical flow path of the liner 5 to an annular flow path of the gas turbine. It is composed of a transition piece 6, a liner 5 and a flow sleeve 7 that are located outside the transition piece 6 and that promotes cooling of the outer surface.
[0019]
The working fluid 8 discharged from the compressor is guided to the inlet side of the liner 5 through a gap 9 between the transition piece 6 and the flow sleeve 7. At this time, the flow rate of the working fluid 8 increases between the flow sleeve 7 and the liner 5 and the transition piece 6, so that the heat transfer capability increases, and cooling of the outer surfaces of the liner 5 and the transition piece 6 is promoted. The working fluid 8 that has flowed into the liner 5 is mixed with the fuel sprayed from the fuel spray nozzle 10 and burned, and then flows into the transition piece 6.
[0020]
The working fluid 8 that has flowed into the transition piece 6 is discharged to the flow path of the turbine 3. Since the liner 5 has a cylindrical shape, the transition piece 6 has a cylindrical shape at the inlet and an inverted trapezoidal shape at the outlet in order to discharge to the annular flow path of the gas turbine. Further, a frame portion 11 is provided near the exit of the transition piece 6 in order to ensure rigidity in consideration of creep resistance.
[0021]
The liner 5 is supported on the inlet side by having an insertion part between the nozzle 10 and the liner 5 is supported by inserting the leaf spring 12 joined to the liner 8 into the transition piece 6 to determine the position on the outlet side.
[0022]
The transition piece 6 is supported on the inner surface on the inlet side by a leaf spring 12 joined to the liner 5, and has a fitting portion that restrains only deformation in the circumferential direction of the inlet cross section between the transition sleeve 6 and the flow sleeve 7. It is supported on the upstream side. On the outlet side, the position is determined by being supported by the casing.
[0023]
The flow sleeve 7 is supported on the inner surface on the inlet side by having a fitting portion that restrains only the circumferential deformation of the inlet cross section between the transition piece 6 and the casing, and on the outlet side, The position is determined by being coupled to the casing together.
[0024]
In the liner 5 of the present invention, the corrugated plate 14 provided with the cooling holes 13 is processed into a corrugated cylindrical shape by bending, and the liner cap 15 into which the fuel spray nozzle 10 is inserted is attached to one end surface of the corrugated plate cylinder 16. At the other end, a leaf spring 12 to be inserted into the transition piece 6 is attached to the outer surface of the corrugated cylinder 16 at the other end, a tubular lip 17 is attached to the inner peripheral surface of the cooling hole 13, and heat is radiated from the lip 17. In the gas turbine combustor that performs cooling, the liner 5 is divided into a plurality of cylindrical members in the axial direction, and each member is joined by welding to form a liner, and by replacing only the damaged member, It is characterized by easy repair and replacement.
[0025]
These characteristics will be described below in accordance with more specific examples. 1 and 4 are diagrams of a combustor liner structure that facilitates repair, which best represents the characteristics of the present invention, as Embodiment 1, and FIGS. 5 and 6 illustrate the characteristics of the present invention. It is a figure which shows the procedure of the repair method best expressed.
[0026]
The working fluid 8 discharged from the compressor 1 is guided to a gap 9 between the flow sleeve 7 and the transition piece 6 as shown in FIG. Since the flow velocity of the working fluid 8 increases in the gap 9, the cooling effect on the outer surface of the transition piece 6 is enhanced.
[0027]
In the diffusion combustion type in which the fuel 8 that has passed through the gap 9 is not mixed with air before combustion, a part of the working fluid 8 is guided to the inside of the liner 5 from the cooling hole 13 provided on the outer surface of the liner 5. The remainder of the fuel is cooled and the remainder flows into the liner 5 together with the fuel sprayed from the fuel spray nozzle 10 and used for combustion. Further, in the premix combustion type in which fuel is mixed with air before combustion, all the working fluids may be used for combustion without providing the liner cooling holes 13 in the liner 5.
[0028]
As shown in FIG. 1, the fuel spray nozzle 10 is inserted into an insertion portion 18 provided on the inlet side of the liner 5.
[0029]
The combustion working fluid 8 after combustion is discharged from the liner 5 through the transition piece 6 to the annular flow path of the turbine 3.
[0030]
In the figure, the liner 5 is welded with a leaf spring 12 on the outlet side and inserted into the transition piece 6.
[0031]
The transition piece 6 is a fitting portion in which the liner 5 is inserted via the leaf spring 12 on the inlet side and is included in the flow sleeve 7 and is restrained only in the circumferential direction of the inlet cross section on the inlet side. Supported. Further, a frame portion 11 is provided near the exit of the transition piece 6 in order to increase rigidity.
[0032]
As shown in FIG. 3, in the conventional liner, a cylindrical lip 17 is joined to a corrugated plate 14 processed into a cylindrical shape having a cooling hole 13 at a portion located on the inner periphery of the cooling hole. The cooling air flowing into the liner 5 cools the lip 17 to cool the entire liner.
[0033]
In the liner structure of the present invention, as shown in FIG. 4, the liner 5 is divided into a plurality of cylindrical members in the axial direction, and the members 19 are joined by welding to form a liner. Further, as shown in FIG. 5, the damaged member 20 is cut and replaced with a new member 21 as shown in FIG. 6 to facilitate repair and replacement of the damaged portion.
[0034]
In addition, when a site with significant damage is known in advance, a liner structure including a replacement member 22 whose shape is optimized so as to include the site may be adopted as shown in FIG.
[0035]
Further, as shown in FIG. 8, the life of the liner can be extended by replacing the liner cap 15 that is easily damaged.
[0036]
Further, as shown in FIG. 9, in another conventional liner, a plate 24 having cooling ribs 23 is processed into a cylindrical shape, and cooling of the entire liner is performed by disturbance of cooling air generated around the cooling ribs 23. The structure to plan was adopted.
[0037]
In the liner structure of the present invention, as shown in FIG. 10, the liner 5 is divided into a plurality of cylindrical members in the axial direction, and each member is joined by welding with a circular tubular member 25 corresponding to a rib to form a liner. is doing. Further, the damaged member 26 is cut as shown in FIG. 11 and replaced with a new member 27 as shown in FIG. 12, thereby facilitating repair and replacement of the damaged portion.
[0038]
In addition, when a site with significant damage is known in advance, a liner structure including the replacement member 25 including the site may be employed.
[0039]
Further, as shown in FIG. 13, the life of the liner can be extended by replacing the liner cap 15 that is easily damaged.
[0040]
Furthermore, as shown in FIG. 14, in another conventional liner, a plate 29 having a semicircular slit 28 is processed into a cylindrical shape, and the slit 28 is bent into the cylinder to bend from the cooling hole to the inside of the liner. The cooling air liner that flows into the cooling airline is cooled.
[0041]
In the liner structure of the present invention, as shown in FIG. 15, the liner 5 is divided into a plurality of cylindrical members 30 whose inner diameter changes in the axial direction, and the side with the smaller inner diameter is inserted into the side with the larger inner diameter of the adjacent member. The liner is formed by bonding together. In addition, the damaged member 31 is cut as shown in FIG. 16 and replaced with a new member 32 as shown in FIG.
[0042]
In addition, when a site with significant damage is known in advance, a liner structure including the replacement member 31 including the site may be adopted.
[0043]
Furthermore, as shown in FIG. 18, the life of the liner can be extended by replacing the liner cap 15 that is easily damaged.
[0044]
【The invention's effect】
According to the repair method of the present invention, the gas turbine combustor liner structure is a welded structure, which is advantageous in terms of strength from the usage of the gas turbine, and the repair of the liner causes damage among the members constituting the liner. Repair and replacement are facilitated by replacing only the member. In addition, since only the damaged part is replaced, the total cost of the liner structure can be suppressed.
[0045]
According to the gas turbine combustor liner structure of the present invention, it is possible to easily and economically repair and replace the liner.
[Brief description of the drawings]
FIG. 1 is a cross-sectional view of a gas turbine combustor liner portion employing a liner structure of the present invention.
FIG. 2 is a structural sectional view of a general gas turbine.
FIG. 3 shows a conventional gas turbine combustor liner structure.
FIG. 4 illustrates a gas turbine combustor liner structure of the present invention.
FIG. 5 is a view showing a cutting method for repairing a gas turbine combustor liner according to the present invention.
FIG. 6 is a diagram showing a replacement method for repairing a gas turbine combustor liner according to the present invention.
FIG. 7 is a diagram showing the optimization of the replacement part of the gas turbine combustor liner of the present invention.
FIG. 8 is a view showing a gas turbine combustor liner cap replacement method according to the present invention.
FIG. 9 is a view showing another liner structure in a conventional gas turbine combustor.
FIG. 10 is a view showing another liner structure in the gas turbine combustor of the present invention.
FIG. 11 is a diagram showing a cutting method for repairing another liner in the gas turbine combustor of the present invention.
FIG. 12 is a diagram showing a replacement method for repairing another liner in the gas turbine combustor according to the present invention.
FIG. 13 is a view showing a gas turbine combustor liner cap replacement method according to the present invention.
FIG. 14 is a view showing another liner structure in a conventional gas turbine combustor.
FIG. 15 is a view showing still another liner structure in the gas turbine combustor of the present invention.
FIG. 16 is a view showing a cutting method for repairing still another liner structure in the gas turbine combustor of the present invention.
FIG. 17 is a view showing a replacement method for repairing still another liner structure in the gas turbine combustor of the present invention.
FIG. 18 is a diagram showing a liner cap replacement method in the gas turbine combustor of the present invention.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Compressor, 2 ... Combustor, 3 ... Turbine, 4 ... Gas path, 5 ... Liner, 6 ... Transition piece, 7 ... Flow sleeve, 8 ... Working fluid, 9 ... Gap, 10 ... Fuel spray nozzle, 11 ... Frame , 12 ... leaf spring, 13 ... cooling hole, 14 ... corrugated plate, 15 ... liner cap, 16 ... corrugated plate cylinder, 17 ... lip, 18 ... plug, 19 ... axial member, 20 ... damaged member 21 ... New replacement member, 22 ... Shaped replacement member, 23 ... Rib, 24 ... Plate with processed ribs, 25 ... Circular tubular member corresponding to rib, 26 ... Damaged circle Tubular member, 27 ... replacement tubular member, 28 ... semicircular slit, 29 ... plate with slits processed, 30 ... cylindrical member whose inner diameter changes, 31 ... damaged inner diameter Changing cylindrical member, 32 ... inner diameter for replacement Varying cylindrical member.

Claims (2)

  A plurality of cylindrical axial members made of a material that can be welded are welded together via a circular tubular member corresponding to a rib that covers the opposite ends of the axial members from the outer periphery. A gas turbine combustor liner structure is removed by cutting a tubular member corresponding to the rib in a circumferential direction, and the axial member is welded and integrated through a new tubular member corresponding to the rib. Repair method for gas turbine combustor liner structure to be restored.   A plurality of cylindrical axial members made of a material that can be welded are welded together via a circular tubular member corresponding to a rib that covers the opposite ends of the axial members from the outer periphery. Gas turbine combustor liner structure.

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