JP2001304551A - Method for making combustion liner for gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a method for making a combustion liner for a gas turbine having a superior stability in metallic structure when it is used in a high temperature range for a longer hour, having a light deterioration in its mechanical characteristic and having a superior aging deterioration. SOLUTION: There is provided a method for making a combustion liner including a rolling step for rolling an alloy cast iron 1 to make a flat plate-like material 2; a cylindrical body making step for bending the plate-like material 2 into a cylindrical shape, welding connecting seams of the cylindrical material, applying a mechanical machining work to form a cylindrical body 3; and a strain removing and annealing processing step for heating the cylindrical body for a predetermined period of time.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for manufacturing a gas turbine combustor liner forming a combustion chamber of a gas turbine combustor used for thermal power generation or the like.

[0002]

2. Description of the Related Art From the viewpoint of effective use of energy resources, research and development on high-efficiency gas turbines for power generation have been actively pursued. Due to the improvement in efficiency, the temperature at the gas turbine inlet has been increased. However, it is an extremely severe environment for materials for high-temperature components constituting a gas turbine, and there are problems such as a decrease in strength at high temperatures, remarkable high-temperature corrosion and high-temperature oxidation.

Hitherto, as a material for a combustor liner, RA333 or Hastelloy-X (trade name of Mitsubishi Materials Corporation, Ni base) which is a solid solution strengthened alloy having excellent heat resistance and workability has been applied. With the rise of combustion gas temperature, HS188 (Mitsubishi Materials Corp., Co-based), a solid solution strengthened alloy with better heat resistance, has also been applied. In addition, thermal barrier coating (TBC) has been applied to the inner surface of the combustor liner, and at the same time, the development and improvement of the cooling structure and manufacturing process of the combustor liner have been promoted. (JP-A-8-278029, JP-A-7-332668).

In a conventional method for manufacturing a combustor liner for a gas turbine, as shown in FIG. 17, first, an alloy ingot 1 made of a Ni-based or Co-based alloy having excellent heat resistance and workability is prepared.
Is subjected to hot rolling, and then subjected to cold rolling to produce a flat plate material 2. Next, after the plate-shaped plate member 2 is subjected to a solution heat treatment, it is formed into a cylindrical shape by performing a bending process, and the joint is longitudinally welded to produce a cylindrical body 3. By subjecting the cylindrical body 3 to machining such as bulge forming and drilling, a combustor liner 12 having excellent heat resistance is provided.

[0005]

[Problems to be solved by the invention] However, FIG.
A gas turbine combustor liner was fabricated using the conventional method shown.
If used for a long time at high temperature, the combustor liner
It has been found that significant structural changes occur in the substrate
You. Conventional combustor liner materials such as Hastelloy-X and HS188
Undissolved carbide in the new material structure of M₆C-type carbide (M
Cr, Mo or W) only precipitates at high temperatures
M when used for a long time in the temperature range (600 ° C ~) _{twenty three}C₆Type carbide
(M is Cr, Mo or W) and embrittlement phase (μ phase, Laves phase)
It has been found that new precipitation occurs.

[0006] These precipitates are often generated from dislocations of the metal structure introduced in the rolling step and the bending process in the production of the liner, and significantly deteriorate the mechanical properties of the combustor liner substrate (ductility and ductility). Impact value). In addition, since the embrittlement phase is likely to be a starting point of a crack, there is a risk that the liner may be broken during use and may be broken. Therefore, if the conventional combustor liner is used for a long time in a gas turbine in which the temperature is increasing, the reliability is poor, and as a countermeasure, repair or replacement must be performed early.

[0007] Therefore, development of TBC and cooling structure has been promoted, but it is difficult to increase the thickness of TBC as a current technology.
Considering the case where BC is peeled off, the base material itself needs to have sufficient durability. In addition, in the case of a combustor liner that has been used for a long time, cracks often occur at the cooling holes and at the ends, but the complexity of the cooling holes is considered to be a factor that increases the origin of such cracks. Should be simplified. Furthermore, these techniques mean that the manufacturing process is complicated, which leads to an increase in the cost of the combustor liner.

Accordingly, the present invention has been made in view of the conventional problems, and has excellent stability of the metallographic structure when used for a long time at a high temperature range, and has little deterioration in mechanical properties. An object of the present invention is to provide a method for manufacturing a combustor liner for a gas turbine having excellent aging characteristics.

[0009]

According to a first aspect of the present invention, there is provided a method for manufacturing a combustor liner for a gas turbine, the method comprising: rolling an alloy ingot to produce a flat plate; Bending the plate material into a cylindrical shape, welding a seam and performing machining to form a cylindrical body, and a configuration having a distortion removal annealing process step of heating the cylindrical body at a predetermined temperature for a predetermined time. I do.

In the present invention, the strain (dislocation) introduced in the liner manufacturing process (rolling process, bending process, etc.) can be removed by performing the strain removing annealing process after rolling, bending, and machining. . Since the dislocations introduced in the liner manufacturing process are likely to be the starting point of the generation of precipitates after use, removing the dislocations allows for a combustor liner that has excellent stability of the metallographic structure with less generation of precipitates after operation. Can be provided. Furthermore, since the deterioration of the mechanical characteristics caused by the generation of the precipitate can be prevented, it is possible to provide a combustor liner having excellent aging characteristics.

According to a second aspect of the present invention, there is provided a method of manufacturing a combustor liner for a gas turbine according to the first aspect of the present invention, wherein an alloy plate material manufactured by a rolling method is also subjected to a strain relief annealing treatment. .

According to the present invention, the strain introduced in the rolling step is removed by subjecting the alloy sheet material manufactured by the rolling method to a strain removing annealing treatment, and the precipitation generated from dislocations as a starting point during operation. Since the precipitation of substances can be suppressed, it is possible to provide a combustor liner excellent in the stability of the metal structure. Further, it is possible to prevent the deterioration of the mechanical characteristics caused by the precipitation of the precipitates, and it is possible to provide a combustor liner having excellent aging characteristics.

According to a third aspect of the present invention, there is provided a method for manufacturing a combustor liner for a gas turbine according to the first or second aspect of the present invention, wherein a hot rolling method is used when an alloy plate is manufactured by using a rolling method. It is characterized in that it is used.

In the conventional method for manufacturing a combustor liner, since a cold rolling method is used when manufacturing a sheet material, the amount of distortion introduced in the rolling process is very large. In the present invention, by producing a flat plate by a hot rolling method having a high rolling temperature, the strain introduced during rolling can be reduced, and the precipitation of precipitates generated from dislocations during operation can be suppressed. Thus, it is possible to provide a combustor liner excellent in the stability of the metal structure. Further, since the deterioration of the mechanical characteristics caused by the precipitation of the precipitate can be prevented, it is possible to provide a combustor liner having excellent aging characteristics.

According to a fourth aspect of the present invention, there is provided a method for manufacturing a combustor liner for a gas turbine, wherein when a cylindrical combustor liner is manufactured, it is melted into a hollow cylindrical shape using a casting method, thereby forming a welded portion. It is characterized by making an integrated combustor liner without any.

In the conventional method of manufacturing a combustor liner, a flat plate is manufactured by using a rolling method, and the plate is processed into a cylindrical shape by performing a bending process. Therefore, the manufacturing process is complicated, and The amount of distortion introduced into the combustor liner becomes very large. In the present invention, the manufacturing process can be omitted because the rolling process to the sheet material and the bending process to the cylindrical shape can be omitted by melting the integrated cylindrical liner having no welded portion using the casting method. Therefore, the cost can be reduced, and the cost can be reduced.

Further, since the present invention does not require longitudinal welding of joints, cracks due to welding defects can be suppressed, and cost can be significantly reduced. In addition, this combustor liner has low distortion,
Precipitation of precipitates generated from dislocations during operation is unlikely to occur, and the stability of the metallographic structure is extremely excellent.Since the mechanical properties caused by the precipitation of precipitates are small, the deterioration over time is excellent. A combustor liner can be provided.

According to a fifth aspect of the present invention, there is provided a method for manufacturing a combustor liner for a gas turbine, comprising: forming a cylindrical combustor liner; and forming an MCrAlY alloy layer (M is at least Ni or Co) on the inner surface of the combustor liner as a bond coat. (1) is coated with a ceramic layer mainly composed of stabilized zirconia as a top coat.

In the present invention, it is possible to lower the substrate temperature of the combustor liner during operation by coating the inner surface of the combustor liner with a ceramic layer mainly composed of stabilized zirconia having a low thermal conductivity. Therefore, it is possible to provide a combustor liner having excellent aging characteristics.

According to a sixth aspect of the present invention, there is provided a method for manufacturing a combustor liner for a gas turbine, wherein an MCrAlY alloy layer (M is at least one of Ni and Co) as a bond coat on an inner surface of the combustor liner.
After coating, a strain removal annealing treatment is performed.

In the present invention, the inner surface of the combustor liner is coated with an MCrAlY alloy layer (M is at least one of Ni and Co) as a bond coat, and then subjected to a strain relief annealing treatment so as to bond with the liner substrate. By diffusing the elements at the interface of the coat, the adhesion of the bond coat can be improved. In addition, since the strain introduced in the liner manufacturing process can be removed, precipitation of precipitates generated from dislocations during operation can be suppressed, and a combustor liner with excellent metallographic stability can be provided. can do. Furthermore, it is possible to prevent deterioration of mechanical properties caused by precipitation of precipitates,
A combustor liner having excellent aging characteristics can be provided.

According to a seventh aspect of the present invention, in the method for manufacturing a combustor liner for a gas turbine, the strain removal annealing treatment is performed at a temperature of 1200 ° C.
It is carried out for 1 hour to 10 hours in a temperature range of 1300 ° C.

In the present invention, the strain introduced in the liner manufacturing process can be removed by performing the strain removal annealing treatment at a temperature in the range of 1200 ° C. to 1300 ° C., so that the dislocations originate from the dislocations during operation. Precipitates can be suppressed. If the annealing temperature is less than 1200 ° C, sufficient effects cannot be obtained.
If the temperature exceeds 00 ° C, the base material undergoes local melting and the strength of the base material is significantly reduced.
A temperature range of 1300 ° C is desirable.

In the present invention, since the strain introduced in the liner manufacturing process can be removed by performing the strain removal annealing treatment for 1 hour to 10 hours, the precipitates generated from dislocations during operation can be removed. Can be suppressed. If the distortion removal annealing time is less than 1 hour, a sufficient effect cannot be obtained, and if it exceeds 10 hours, no further effect can be expected and the cost is high. Therefore, the distortion annealing time is 1 hour to 10 hours. Is desirable.

[0025] The method of manufacturing a combustor liner for a gas turbine according to claim 8 is characterized in that the alloy constituting the combustor liner is either Ni-based or Co-based. In the present invention, a gas turbine combustor liner having excellent heat resistance can be provided by configuring the combustor liner with either a Ni-based alloy or a Co-based alloy having excellent heat resistance.

When the gas turbine combustor liner according to the present invention is used for a power generation gas turbine system, a power generation gas turbine system having excellent reliability can be provided.

[0027]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS (First Embodiment) FIG. 1 is a diagram showing a method of manufacturing a combustor liner for a gas turbine according to a first embodiment of the present invention. That is, after the alloy ingot 1 is subjected to hot rolling and cold rolling in order to produce a plate-shaped plate material 2, a solution heat treatment is performed, and after forming into a cylindrical shape by bending, the seam is elongated. The cylindrical body 3 having a combustor liner shape is produced by welding. After the cylindrical body 3 is machined, a distortion removing annealing process is performed to produce the combustor liner 4 of the present invention.

According to the present embodiment, the distortion (dislocation) of the metal structure introduced in the preceding rolling step, bending, or the like is performed by performing the strain removal annealing treatment on the cylindrical body 3 after the forming and welding. Can be removed. Since the dislocation is likely to be a starting point of the generation of a precipitate after use, it is possible to provide the combustor liner 4 which is excellent in the stability of the metal structure in which the precipitate is hardly generated by removing the dislocation. Further, since it is possible to prevent the mechanical characteristics from deteriorating due to the generation of precipitates, it is possible to provide the combustor liner 4 having excellent aging characteristics.

Next, in the first embodiment, FIG.
For the following examples shown in the table, deterioration of the metallographic structure and mechanical properties during long-term use was evaluated. In Example 1, after performing a hot rolling and a cold rolling in order on an alloy ingot having a chemical composition shown in the table to produce a flat plate material, a solution heat treatment was performed at 1175 ° C. for 1 hour. After forming into a cylindrical shape by bending, the joint was longitudinally welded to produce a combustor liner-shaped cylindrical body, which was subjected to a strain removal annealing treatment at 1200 ° C. for 2 hours.

In Example 2, a flat ingot was prepared by subjecting an alloy ingot having the indicated chemical composition to hot rolling and cold rolling in order, and then subjected to a solution heat treatment at 1175 ° C. for one hour. Then, after forming into a cylindrical shape by bending, the joint was longitudinally welded to produce a combustor liner-shaped cylindrical body.

From the cylinders 3 of Examples 1 and 2 obtained as described above, test pieces for evaluating the structure during long-term use were collected. Each test piece was subjected to a heat aging treatment at 700 ° C., and the following aging materials after aging for 1000 hours, 6000 hours, and 12000 hours were evaluated. First, SEM (scanning electron microscope) for the cross-section of unaged and aged materials
Observation was performed, and the area ratio of the precipitate was measured using image analysis on the SEM photograph. FIG. 2 shows the results of the heat aging test.

As a result of this test, it was found that in Example 1 in which the strain removal annealing treatment was performed, the increase in precipitates due to the heat aging was small, and the stability of the metal structure was excellent. Therefore, by performing the strain removal annealing treatment as in the first embodiment, it is possible to provide a combustor liner for a gas turbine having excellent metallographic structure stability.

Next, a tensile test piece was collected from each aging material,
Tensile tests were performed at room temperature. FIG. 3 shows the results (elongation) of the room temperature tensile test. As a result of the tensile test, in Example 1 in which the strain removal annealing treatment was performed, almost no decrease in ductility causing cracking of the liner was observed even after long-term heat aging, and the long-term durability was excellent. I understand. Therefore, by performing the strain removal annealing treatment as in the first embodiment, it is possible to provide a gas turbine combustor liner having excellent aging characteristics.

(Second Embodiment) FIG. 4 shows a second embodiment of the present invention.
It is a figure which shows the manufacturing method of the combustor liner for gas turbines of 1st Embodiment. That is, after the alloy ingot 1 is subjected to hot rolling and cold rolling in order to produce a plate-shaped plate material 2, subjected to a strain relief annealing treatment, further formed into a cylindrical shape by bending, and then joined. A cylindrical body 3 having a combustor liner shape is produced by longitudinal welding. After the cylindrical body 3 is machined, a distortion removing annealing process is performed to produce the combustor liner 4 of the present invention.

According to the present embodiment, the dislocation of the metal structure, which is the starting point of the generation of precipitates, can be removed by performing the strain removal annealing treatment on the flat plate material 2. It is possible to provide the combustor liner 4 which is excellent in the stability of the metallographic structure in which the generation of substances is small.
Further, since it is possible to prevent the mechanical characteristics from deteriorating due to the generation of precipitates, it is possible to provide the combustor liner 4 having excellent aging characteristics.

Next, in the present embodiment, the following examples were evaluated for deterioration in metallographic structure and mechanical properties during long-term use. In Example 3, a flat plate was produced by sequentially performing hot rolling and cold rolling on an alloy ingot having the chemical composition shown in the table of FIG. 16 and then annealing at 1200 ° C. for 2 hours to remove strain. After performing the treatment and forming into a cylindrical shape by bending, the joint was longitudinally welded to produce a combustor liner-shaped cylindrical body, and a distortion removing annealing treatment was performed at 1200 ° C. for 2 hours.

From the cylindrical body 3 of Example 3 obtained as described above, a test piece for tissue evaluation during long-term use was collected. After subjecting this test piece to heat treatment aging at 700 ° C., the area ratio of precipitates in the aging material was measured and compared with Examples 1 and 2 described above.

FIG. 5 shows the results of the heat aging test. As a result of this test, it was found that in Example 3 in which the plate material 2 was subjected to the strain removal annealing treatment, the increase in precipitates due to the heat aging was the smallest, and the stability of the metal structure was excellent. Therefore, a gas turbine combustor liner excellent in the stability of the metal structure can be provided by performing the strain removal annealing treatment on the plate material as in the present embodiment.

Next, a tensile test piece was collected from the aged material and subjected to a tensile test at room temperature, and a comparison was made with Examples 1 and 2. FIG. 6 shows the results (elongation) of the room temperature tensile test. As a result of the tensile test, in Example 3 in which the plate material was subjected to the strain removal annealing treatment, even after the long-term heat aging treatment, almost no decrease in ductility causing cracking of the liner was observed, and the long-term durability was reduced. It turned out to be excellent. Therefore, a gas turbine combustor liner having excellent aging characteristics can be provided by performing the strain removal annealing treatment on the plate material as in the present embodiment.

(Third Embodiment) FIG. 7 shows a third embodiment of the present invention.
It is a figure which shows the manufacturing method of the combustor liner for gas turbines of 1st Embodiment. That is, a flat plate-shaped plate material 2 is produced by subjecting the alloy ingot 1 to hot rolling, subjected to a strain removing annealing treatment, further formed into a cylindrical shape by bending, and longitudinally welded at the joint. A combustor liner-shaped cylindrical body 3 is manufactured. This cylindrical body 3
After performing the machining, the combustor liner 4 of the present invention is manufactured by performing a strain removal annealing process.

According to the present embodiment, the flat plate 2 is manufactured by the hot rolling method having a relatively high temperature without using the cold rolling method in which a large amount of distortion is introduced. It is possible to provide a combustor liner 4 that can reduce the amount of precipitates generated from dislocations during operation and that is excellent in the stability of the metal structure. Further, it is possible to prevent the deterioration of the mechanical characteristics caused by the precipitation of the precipitate, and it is possible to provide the combustor liner 4 having excellent aging characteristics.

Next, in the present embodiment, the following examples were evaluated for deterioration of the structure and mechanical properties during long-term use. In Example 4, a flat plate was produced by subjecting an alloy ingot having a chemical composition shown in the table of FIG. 16 to a hot rolling method, and then subjected to a strain removal annealing treatment at 1200 ° C. for 2 hours. Then, after forming into a cylindrical shape by bending, the joint is longitudinally welded to produce a combustor liner-shaped cylindrical body at 1200 ° C.
For 2 hours.

From the cylinder obtained in Example 4 as described above, a test piece for tissue evaluation during long-term use was collected. After subjecting this test piece to heat treatment aging at 700 ° C., the area ratio of the precipitate in the aging material was measured and compared with Examples 2 and 3 described above.

FIG. 8 shows the results of the heat aging test. As a result of this test, it was found that in Example 4 in which the sheet material was manufactured by the hot rolling method, the increase in the precipitates due to the heat aging was the least and the stability of the metal structure was excellent. Therefore, by performing the strain removal annealing treatment on the sheet material produced by hot rolling as in the present embodiment, it is possible to provide a combustor liner having excellent metallographic structure stability.

Next, a tensile test was carried out at room temperature on a tensile test specimen collected from the aged material, and the change in ductility due to the heat aging was examined. The results were compared with those in Examples 2 and 3. FIG. 9 shows the results (elongation) of the tensile test at room temperature. As a result of the tensile test, in Example 3 in which the sheet material produced by hot rolling was subjected to the strain removing annealing treatment, even after long-time heat aging, almost no decrease in ductility causing cracking of the liner was observed. , It was found to be excellent in long-term durability. Therefore, by performing the strain removal annealing treatment on the sheet material manufactured by hot rolling as in the present embodiment, it is possible to provide a combustor liner having excellent aging characteristics.

(Fourth Embodiment) FIG. 10 shows a fourth embodiment of the present invention.
It is a figure which shows the manufacturing method of the combustor liner for gas turbines of 1st Embodiment. That is, first, an alloy melt 6 is cast into a hollow cylindrical mold 5 to melt an integrated cylindrical body 7,
The cast combustor liner 8 of the present invention is made by performing machining and strain removal annealing.

According to the present embodiment, the integral cylindrical body 7 having no welded portion is melted by using the casting method.
Since the rolling process and the bending process into a cylindrical shape can be omitted, the manufacturing process can be shortened, and the cost can be reduced. Further, since longitudinal welding is not required, cracks caused by welding defects can be suppressed. Further, since there is no rolling step and bending step in which distortion is introduced, it is possible to provide the combustor liner 8 having a very small amount of dislocation of the metal structure. This combustor liner 8 can provide a combustor liner 8 that is excellent in aging characteristics because deterioration of mechanical properties caused by precipitation of precipitates generated from dislocations during operation is small.

(Fifth Embodiment) FIG. 11 shows a fifth embodiment of the present invention.
It is a figure which shows the manufacturing method of the combustor liner for gas turbines of 1st Embodiment. That is, after a cylindrical combustor liner 4 is manufactured, a MCrAlY alloy layer (M is at least one of Ni and Co) is coated as a bond coat 10 on a substrate 9 on the inner surface of the combustor liner 4, and then a top coat is formed. As 11, a ceramic layer containing stabilized zirconia as a main component is coated. The distortion removal annealing process in the first to fourth embodiments (corresponding to FIGS. 1, 3, 4, and 7) may be performed, but is not always necessary.

According to the present embodiment, the inner surface of the combustor liner is coated with the MCrAlY alloy layer as the bond coat 10 and then as the top coat 11 with the ceramic layer mainly composed of stabilized zirconia having a low thermal conductivity. By doing so, the base material temperature of the combustor liner 4 during operation can be lowered, so that a combustor liner having excellent aging characteristics can be provided.

(Sixth Embodiment) FIG. 12 shows a sixth embodiment of the present invention.
It is a figure which shows the manufacturing method of the combustor liner for gas turbines of 1st Embodiment. That is, after the cylindrical combustor liner 4 is manufactured, the MCrAlY alloy layer (M is at least one of Ni and Co) is coated as a bond coat 10 on the base material 9 on the inner surface of the combustor liner 4 and then strain is removed. An annealing treatment is performed, and a ceramic layer mainly composed of stabilized zirconia is coated as the top coat 11. The distortion removal annealing process in the first to fourth embodiments (corresponding to FIGS. 1, 3, 4, and 7) may be performed, but is not always necessary.

According to the present embodiment, the inner surface of the combustor liner is coated with the MCrAlY alloy layer as the bond coat 10 and then subjected to a strain relief annealing treatment, so that the interface between the liner substrate 9 and the bond coat 10 is formed. The element is diffused to form a bond coat with the liner substrate 9.
Since the adhesion of the coating layer 10 can be improved, it is possible to provide the combustor liner 4 in which the peeling of the coating layer hardly occurs.

Further, according to the present embodiment, the strain introduced in the liner manufacturing process is removed by performing the strain removal annealing treatment, and the precipitation of precipitates generated from dislocations in the metal structure during operation is suppressed. Therefore, it is possible to provide a combustor liner excellent in the stability of the metal structure. Furthermore, since the deterioration of the mechanical characteristics caused by the precipitation of the precipitate can be prevented, it is possible to provide a combustor liner having excellent aging characteristics.

(Seventh Embodiment) In the present embodiment, a heat aging test was performed on an example manufactured by changing the temperature of the strain removal annealing treatment applied to the combustor liner.

In Example 5, an alloy ingot having a chemical composition shown in the table of FIG. 16 was subjected to a solution heat treatment at 1175 ° C. for 1 hour on a flat plate produced by a rolling method, followed by bending. After producing a combustor liner-shaped cylinder, a strain removal annealing treatment was performed at 1150 ° C. for 2 hours.

In Example 6, the ingot of the alloy having the chemical composition shown in the same table was subjected to a solution heat treatment at 1175 ° C. for 1 hour on a flat plate produced by the rolling method, and furthermore, the combustor was bent by bending. After producing a liner-shaped cylinder, a strain removal annealing treatment was performed at 1200 ° C. for 2 hours.

In Example 7, the alloy ingot having the chemical composition shown in the same table was subjected to a solution heat treatment at 1175 ° C. for 1 hour on a flat plate produced by a rolling method, and further, the combustor was bent by bending. After producing a liner-shaped cylinder, a strain removal annealing treatment was performed at 1250 ° C. for 2 hours.

In Example 8, an ingot of an alloy having the chemical composition shown in the same table was subjected to a solution heat treatment at 1175 ° C. for 1 hour on a plate-like sheet material produced by a rolling method, and further subjected to a bending process to produce a combustor. After producing a liner-shaped cylindrical body, a strain removal annealing treatment was performed at 1320 ° C. for 2 hours.

The test materials of Examples 5 to 8 obtained as described above were subjected to a heat aging treatment and then subjected to a tensile test at room temperature. Figure 13 shows the room temperature tensile test results (tensile strength,
Elongation).

As a result of the tensile test, when the strain removal annealing temperature of Example 5 was set at 1150 ° C., a decrease in ductility was observed, and the strain removal annealing temperature of Example 6 was reduced to 13 ° C.
When the temperature was set to 20 ° C., a decrease in tensile strength was observed. On the other hand, the distortion removal annealing process of the seventh and eighth embodiments was performed.
At 1200 ° C. and 1250 ° C., no remarkable change in tensile properties was observed, and the strain relief annealing treatment was performed from 1200 ° C. to 13 ° C.
It can be said that by performing the process in the temperature range of 00 ° C., a combustor liner having excellent aging characteristics can be provided.

(Eighth Embodiment) In the present embodiment, a heating aging test was performed on an example manufactured by changing the time of the strain removal annealing treatment applied to the combustor liner.

In the ninth embodiment, a solution heat treatment at 1175 ° C. for 1 hour was performed on a plate-like plate made by a rolling method for an alloy ingot having the chemical composition shown in the table of FIG. After producing a combustor liner-shaped cylinder, a strain removal annealing treatment was performed at 1200 ° C. for 30 minutes.

In Example 10, the ingots having the chemical compositions shown in the same table were subjected to a solution heat treatment at 1175 ° C. for 1 hour on a flat plate produced by the rolling method, and furthermore, the combustor was bent by bending. After producing the liner-shaped cylinder, a strain removal annealing treatment was performed at 1200 ° C. for 1 hour.

In Example 11, an ingot of an alloy having the chemical composition shown in the same table was subjected to a solution heat treatment at 1175 ° C. for 1 hour on a plate-like sheet material produced by a rolling method, and furthermore, a combustor was formed by bending. After producing a liner-shaped cylindrical body, a strain removal annealing treatment was performed at 1200 ° C. for 12 hours.

The test materials of Examples 9 to 11 obtained as described above were subjected to a heat aging treatment and then subjected to a tensile test at room temperature. Figure 14 shows the room temperature tensile test results (tensile strength,
Elongation).

As a result of the tensile test, a decrease in ductility was observed when the strain removal annealing treatment time in Example 9 was 30 minutes, but no decrease in ductility was observed when the strain removal annealing time was 1 hour in Example 10. Was. Further, if the time exceeds 10 hours in Example 12, no further effect can be expected, and the cost increases.Therefore, by setting the distortion removal annealing time to 1 to 10 hours, a combustor liner having excellent aging characteristics can be obtained. It can be said that it can be provided.

(Ninth Embodiment) In the ninth embodiment, a heating aging test was performed on an example in which the components of the metal constituting the combustor liner were changed.

The twelfth embodiment was prepared using Ni having the chemical composition shown in the table of FIG.
A flat plate material produced by subjecting the base alloy ingot to a rolling method was subjected to a strain removal annealing treatment at 1200 ° C. for 2 hours to obtain a test material.

The thirteenth embodiment has a chemical composition shown in the table of FIG.
A flat plate material produced by subjecting the base alloy ingot to a rolling method was subjected to a strain removal annealing treatment at 1200 ° C. for 2 hours to obtain a test material.

Example 14 was prepared using Fe of the chemical composition shown in the table of FIG.
A flat plate material produced by subjecting the base alloy ingot to a rolling method was subjected to a strain removal annealing treatment at 1200 ° C. for 2 hours to obtain a test material.

The test materials of Examples 12 to 14 obtained as described above were subjected to a heat aging treatment and then subjected to a room temperature tensile test. FIG. 15 shows room temperature tensile test results (tensile strength, elongation). As a result of the tensile test, a decrease in the tensile strength was observed in the Fe-based alloy of Example 14, but Examples 12 and 13
The Ni-base alloy and Co-base alloy showed almost no decrease in tensile strength. Therefore, the combustor liner was composed of either Ni-base alloy or Co-base alloy to provide a combustor with excellent heat resistance. It can be said that a liner can be provided.

(Tenth Embodiment) The tenth embodiment is applied to a gas turbine system for power generation after performing a distortion removal annealing process on a combustor liner before use.

According to the present embodiment, the dislocation of the metal structure, which is likely to be a starting point of the generation of precipitates, can be removed by performing the strain removing annealing treatment on the combustor liner before use. It is possible to provide a combustor liner that is excellent in the stability of the metal structure with less generation of precipitates. Further, since it is possible to prevent the deterioration of the mechanical characteristics due to the generation of the precipitate, it is possible to provide a combustor liner having excellent aging characteristics. By using a combustor liner having excellent aging characteristics, a gas turbine system for power generation having excellent long-term reliability can be provided.

[0073]

As described above, according to the method for producing a combustor liner for a gas turbine of the present invention, the stability of the metallographic structure when used for a long time in a high temperature range is excellent, and the mechanical characteristics are improved. It is possible to provide a combustor liner for a gas turbine which is less likely to deteriorate and has excellent aging characteristics.

[Brief description of the drawings]

FIG. 1 is a flowchart showing a method for manufacturing a combustor liner for a gas turbine according to a first embodiment of the present invention.

FIG. 2 is a diagram showing the results of a heat aging test of Examples 1 and 2.

FIG. 3 is a view showing the results of a tensile test of Example 1 and Example 2.

FIG. 4 is a flowchart showing a method for manufacturing a combustor liner for a gas turbine according to a second embodiment of the present invention.

FIG. 5 is a diagram showing the results of a heating aging test of Example 3 in comparison with Examples 1 and 2.

FIG. 6 is a diagram showing the results of a room temperature tensile test of Example 3 in comparison with Examples 1 and 2.

FIG. 7 is a flowchart showing a method of manufacturing a combustor liner for a gas turbine according to a third embodiment of the present invention.

FIG. 8 is a diagram showing the results of a heat aging test of Example 4 in comparison with Examples 2 and 3.

FIG. 9 is a diagram showing the results of a room temperature tensile test of Example 4 in comparison with Examples 2 and 3.

FIG. 10 is a flowchart showing a method for manufacturing a combustor liner for a gas turbine according to a fourth embodiment of the present invention.

FIG. 11 is a flowchart showing a method for manufacturing a combustor liner for a gas turbine according to a fifth embodiment of the present invention.

FIG. 12 is a flowchart showing a method for manufacturing a combustor liner for a gas turbine according to a sixth embodiment of the present invention.

FIG. 13 is a view showing the results of a room temperature tensile test of Examples 5, 6, 7, and 8.

FIG. 14 is a diagram showing the results of a room temperature tensile test of Examples 9, 10, and 11.

FIG. 15 is a diagram showing the results of a room temperature tensile test of Examples 12, 13, and 14.

FIG. 16 is a table showing chemical compositions and strain removal annealing treatment conditions of Examples 1 to 14.

FIG. 17 is a flowchart showing a method for manufacturing a conventional combustor liner for a gas turbine.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Alloy ingot, 2 ... Flat plate material, 3 ... Cylindrical body, 4 ... Combustor liner, 5 ... Cylindrical mold, 6 ... Alloy melt, 7 ... Cast cylindrical body, 8 ... Cast combustor liner, 9 ... liner substrate,
10… bond coat, 11… top coat, 12… combustor liner made by conventional technology.

Continuation of the front page (72) Inventor Hiroaki Yoshioka 2-4, Suehirocho, Tsurumi-ku, Yokohama-shi, Kanagawa Prefecture F-term in Toshiba Keihin Works (reference) 4K031 AA01 AA02 AB03 AB08 CB22 CB26 CB27 CB41 FA01

Claims (8)

[Claims] 1. A rolling step of rolling an ingot of an alloy to produce a flat plate, and a step of forming a cylindrical body by bending the plate into a cylindrical shape, welding seams and performing machining. And a distortion removing annealing step of heating the cylindrical body at a predetermined temperature for a predetermined time, a method for manufacturing a combustor liner for a gas turbine. 2. The method of manufacturing a combustor liner for a gas turbine according to claim 1, further comprising a strain removing annealing process after the rolling process. 3. The method for producing a combustor liner for a gas turbine according to claim 1, wherein the rolling step is performed by a hot rolling method. 4. A casting step of casting a molten alloy into a hollow cylindrical mold to produce an integrated cylindrical body, and a strain removing annealing in which the cylindrical body is machined and then heated at a predetermined temperature for a predetermined time. And a process for producing a combustor liner for a gas turbine. 5. A process for producing a cylindrical body for machining a cylindrical body formed by bending or casting a plate material, a distortion removing annealing process for heating the cylindrical body at a predetermined temperature for a predetermined time, and the distortion removing annealing process. An MCrAlY alloy layer (M is at least one of Ni and Co)
A method for producing a combustor liner for a gas turbine, comprising: a bond coating step of forming a seed layer; and a top coating step of forming a ceramic layer containing stabilized zirconia as a main component on the surface of the alloy layer. 6. The method for manufacturing a combustor liner for a gas turbine according to claim 5, wherein the strain removing annealing process is performed between the bond coating process and the top coating process. 7. The strain removal annealing treatment is performed at a temperature of 1200 ° C. to 13 ° C.
7. The method for producing a combustor liner for a gas turbine according to claim 1, wherein the method is carried out at a temperature of 00 ° C. for 1 hour to 10 hours. 8. The method for producing a combustor liner for a gas turbine according to claim 1, wherein the material of the cylindrical body is a Ni-based alloy or a Co-based alloy.