JP2000146185A - Composite material component, combustor liner and their manufactures - Google Patents

Abstract

PROBLEM TO BE SOLVED: To prevent a decrease in a strength by welding and to provide a sufficient high temperature strength by vacuum sealing two or more types of alloy powders containing different components in a laminar state in a direction parallel to or perpendicular to an axial center of an extruding direction of a container. SOLUTION: An alloy powder 11 is sealed in a metal capsule 10, then an alloy powder 12 and finally the powder 11 are sealed. Two types alloy powders 11, 12 containing different components are vacuum sealed in a laminar state in a direction perpendicular to an axial center of an extruding direction of the capsule 10, and then sintered and solidified by hot extruding. Or, the powder is sealed between the capsule and an outside partition plate, the powder containing different components is sealed between an inside partition plate and the outside plate, the powder containing two types of different components is vacuum sealed in a laminar state in an emitting (radial) direction from the axial center of the extruding direction of the capsule, the inside and outside plates are removed, and then sintered and solidified by hot extruding.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a technique for a composite material part which is applied to, for example, a combustor liner for a gas turbine and has excellent weldability and high-temperature strength, and a method for producing the same.

[0002]

2. Description of the Related Art In gas turbines for power generation, research and development for improving the efficiency of gas turbines are being actively conducted in order to effectively use energy resources. In gas turbines, the higher the gas temperature at the combustor outlet, the higher the power generation efficiency,
Higher gas turbine inlet temperatures are being promoted. However, the environment is extremely severe for materials for high-temperature components such as rotor blades, stationary blades, and combustors that constitute gas turbines, resulting in problems such as reduced strength at high temperatures, significant high-temperature corrosion, and high-temperature oxidation. I have.

At present, Ni-base superalloys applied to high-temperature components such as moving blades, stationary blades, and combustors of gas turbines include:
γ 'precipitated phase (intermetallic compound of Ni and Al, Ni ₃ Al)
Is used as a strengthening factor, but since the γ 'precipitated phase can be stably present at a temperature of 1000 ° C. or less, the operating temperature of the Ni-base superalloy is limited to 1000 ° C. or less.

[0004] Specifically, taking a combustor liner as an example,
In the conventional 1100-1300 degreeC class gas turbine, the combustor liner base material temperature was about 550-650 degreeC.
In recent years, the temperature of gas turbines has increased, and in the future 1600
It is anticipated that super-degree C gas turbines will be realized and that the substrate temperature of the combustor liner will approach about 1000 ° C. Therefore,
As a next-generation combustor liner material, a material having heat resistance at 1000 ° C. is required. However, the conventional combustor material has a low high-temperature strength as described above, and the conventional combustor material is used as the next-generation combustor liner material. It was considered difficult to apply.

Therefore, as a next-generation combustor liner material, development and research of an oxide dispersion-strengthened (ODS) alloy has been studied as a material that satisfies the strength at an ultra-high temperature. The ODS alloy is a material having excellent high-temperature strength up to a high temperature close to the melting point of the matrix metal by introducing ceramic dispersed particles that are stable even at a high temperature, and is an extremely stable heat-resistant material.

ODS having excellent high temperature strength
A method of manufacturing a gas turbine combustor liner using an alloy is disclosed in Japanese Patent Application Laid-Open No. 8-200681.

FIG. 11 is a diagram showing the structure of a prior art combustor liner described in the above publication.

As shown in FIG. 11, a cylindrical combustor liner 1 is formed by joining a plurality of ODS alloy ring-shaped materials 2 in the longitudinal direction.

The method for manufacturing the combustor liner 1 is as follows.
A ring-shaped material 2 made of an ODS alloy is prepared, and then the ring-shaped material 2 is joined at a joint 3 by diffusion bonding, electron beam (EB) welding, TIG (TIG) welding or brazing, and joined in the longitudinal direction. I do.

According to such a method, the combustor liner 1 having excellent high-temperature strength and excellent heat resistance even at a high temperature close to 1000 ° C. can be manufactured.

[0011]

SUMMARY OF THE INVENTION However, ODS
It is clear that when an alloy is used, the strength of the joint 3 is significantly reduced. For example, in the conventional ODS alloy combustor liner 1 shown in FIG.
Therefore, there is a problem that the high-temperature strength of the combustor liner 1 itself is significantly reduced.

FIG. 12 shows a ring-shaped material 2 made of an ODS alloy.
The ring-shaped material 2 is formed by using four types of methods such as diffusion bonding, EB welding, TIG welding or brazing.
It is a figure which shows the result of having performed the tensile test of the joining part 3 of FIG.

As shown in FIG. 12, as a result of the tensile test, the strength of the joint (joint 3 shown in FIG. 11) formed by diffusion bonding, EB welding, TIG welding and brazing is as follows.
It was found that the strength was lower than that of the ring-shaped material 2 made of the ODS alloy.

First, when the ODS alloy ring-shaped material 2 is joined by melting, as in EB welding and TIG welding, the metal oxide particles and matrix metal, which are reinforcing factors, are separated at the joint 3. In order to do
It is considered that the strength of the ring-shaped material 2 made of the ODS alloy was significantly reduced. On the other hand, when diffusion bonding and brazing were performed, it is considered that the strength was reduced because the oxide particles did not exist in the bonding portion 3. Furthermore, in the case of diffusion bonding or brazing, not only the strength is reduced, but also the fatigue strength and impact strength are reduced because the ODS alloy element and the insert material react at the bonding interface to form a brittle intermetallic compound. It is conceivable that it will decrease.

That is, there has been a problem that the strength at the joint 3 of the ring-shaped material 2 made of the ODS alloy is reduced, and the high-temperature strength of the combustor liner 1 itself is significantly reduced.

SUMMARY OF THE INVENTION The present invention has been made to solve such a problem, and a composite material component, a combustor liner, and a method for producing the composite material component having sufficient high-temperature strength by preventing a reduction in strength due to welding. The purpose is to provide.

[0017]

According to a first aspect of the present invention, there is provided a method of manufacturing a composite material part, comprising: enclosing an alloy powder in a container in a vacuum; When manufacturing the container, two or more kinds of alloy powders having different components in a direction parallel or perpendicular to the axial center of the extrusion direction of the container are enclosed in a layer, and then sintered and solidified. And

According to the present invention, two or more alloy powders having different components are encapsulated in a layer in a direction parallel or perpendicular to the axial center of the extrusion direction of the container, so that composite material parts having different functions are provided. Can be obtained.

According to a second aspect of the present invention, in the method for producing a composite material part according to the first aspect, when producing a hollow circular tube, two or more alloy powders having different components in a radial direction from the axial center of the container. Is encapsulated in a layer and then sintered and solidified.

According to the present invention, a composite material part having different functions in the inner layer and the outer layer of the circular tube can be obtained.

The third aspect of the present invention is the first or second aspect.
In the method for producing a composite material part described above, at least one or more of the alloy powders is an alloy powder including a ceramic powder obtained by subjecting a metal powder and a ceramic powder to a mechanical alloying treatment.

An alloy obtained by subjecting a metal powder and a ceramic powder to mechanical alloying maintains a sufficient high-temperature strength even at an ultra-high temperature near the melting temperature, so that two or more different alloy powders are used. When encapsulating in layers, a composite material part having excellent high-temperature strength can be obtained by encapsulating an alloy powder containing ceramic powder in a portion where high-temperature strength is required.

The invention according to claim 4 is the invention according to claims 2 and 3.
When manufacturing a combustor liner using the method for manufacturing a composite material component described, enclose a metal powder containing no ceramic powder inside the container, and enclose an alloy powder containing the ceramic powder further inside the alloy powder. The invention is characterized in that two kinds of alloy powders having different components are sealed in the container in two layers in a radial direction from the axial center of the container.

In the present invention, it is necessary to seal an ODS alloy powder capable of maintaining sufficient high-temperature strength even at an ultra-high temperature near the melting temperature in an inner layer of a gas turbine combustor liner which becomes a high temperature, and it is necessary to join by welding or the like. A gas turbine combustor liner having both high-temperature strength and weldability can be obtained by enclosing the alloy powder having excellent weldability in the outer layer of the combustor liner. In addition, since the ODS alloy is very expensive, the cost can be reduced by applying the ODS alloy only to a portion where high-temperature strength is required, rather than manufacturing the entire combustor liner with the ODS alloy. .

According to a fifth aspect of the present invention, in the method for manufacturing a combustor liner according to the fourth aspect, a metal powder containing no ceramic powder is sealed further inside the alloy powder sealed in two layers, and the inside of the container is filled. Two or more alloy powders having different components are sealed in three layers radially from the axial center of the container.

In the present invention, cracks that occur during hot extrusion can be prevented by enclosing metal powder in a contact surface with a container such as a metal capsule.

During hot extrusion, a large resistance stress is generated at the contact surface between the metal capsule, which is a container, and the alloy powder. However, since the alloy powder containing ceramic powder has poor ductility, the vicinity of the contact surface is poor. Cracks easily. Therefore, as in the present invention, by encapsulating an alloy containing no ceramic powder in the contact surface (a portion that comes into contact with a container such as a metal capsule), sufficient ductility can be imparted near the contact surface and cracks are not generated. Can be prevented.

Further, according to the present invention, since the alloy powder excellent in weldability is sealed in the outer layer of the combustor liner which requires welding or the like, high temperature strength and weldability are obtained. A combustor liner for a gas turbine can be obtained.

The invention according to claim 6 is the invention according to claim 4 or 5.
In the method for producing a combustor liner according to the above, the alloy powder comprises:
It is characterized by containing one of Ni, Co and Fe as a main component.

In the present invention, as a matrix metal constituting a combustor liner for a gas turbine, an ODS alloy containing Ni as a main component is required when high temperature strength is required, and an ODS alloy is required when high temperature oxidation resistance is required. O whose main component is Co
A DS alloy is preferably used. In the case where intermediate high-temperature strength and oxidation resistance between the two are required and cost reduction is required, an ODS alloy containing Fe as a main component may be used. As described above, by selecting the matrix metal in consideration of the use environment and required characteristics of the device, a product satisfying the required characteristics can be obtained.

The invention according to claim 7 is the invention according to claim 4 or 5.
In the above described method for manufacturing a combustor liner, the ceramic powder is an oxide such as Y ₂ O ₃ or Al ₂ O ₃ .

Since oxides such as Y ₂ O _{3 and} Al ₂ O ₃ do not form a solid solution in the metal matrix, sufficient high-temperature strength can be maintained even at an extremely high temperature near the melting temperature. Therefore, in the present invention, by using an oxide such as Y ₂ O ₃ or Al ₂ O ₃ as the ceramic powder constituting the alloy powder, a product having excellent high-temperature strength can be obtained.

According to an eighth aspect of the present invention, in the method for manufacturing a combustor liner according to any one of the fourth to seventh aspects, the temperature at which sintering and solidification is performed is set to 800 ° C. or more and 1300
It is characterized by having a temperature of less than ° C.

As a method for sintering and solidifying, for example, a method such as hot extrusion or HIP processing can be applied.

In the present invention, when the temperature at the time of sintering is lowered, a very large resistance stress acts at the time of sintering, so that large equipment is required. In addition, the temperature during sintering is 800 ° C.
If it is lower than 800 ° C., cracks may occur during plastic working, so the temperature is specified to be 800 ° C. or higher. Further, in order for the ODS alloy to exhibit sufficient high-temperature strength, it is necessary to apply heat treatment to the ODS alloy to lengthen the crystal grains. However, it is necessary to apply sufficient strain as a driving force during plastic working. is there. However, when the temperature at the time of plastic working is relatively high, the strain is released, so the temperature at the time of sintering was set to less than 1300 ° C. in order to add an appropriate strain.

According to a ninth aspect of the present invention, in the method for manufacturing a combustor liner according to any one of the fourth to eighth aspects, when the thick pipe is manufactured by sintering and solidifying, the diameter of the thick pipe is finally reduced. The diameter of the combustor liner to be obtained is made smaller, and the thick pipe is subjected to an expanding process to obtain a combustor liner.

In the present invention, the equipment required for sintering can be reduced by setting the diameter of the thick pipe produced by sintering and solidification to be smaller than the diameter of the combustor liner finally obtained. The stress generated in the combustor liner of the gas turbine during operation is mainly thermal stress due to the temperature difference between the front and back surfaces, and a large stress is generated in the circumferential direction of the combustor liner. Grains need to grow. Therefore, when the pipe expansion process is performed in the present invention, since distortion is added in the circumferential direction of the combustor liner, the crystal grains after the heat treatment are elongated in the circumferential direction, thereby having excellent high-temperature strength in the circumferential direction. A combustor liner can be obtained.

[0038] The invention according to claim 10 is the invention according to claims 4 to 9.
The method for producing a combustor liner according to any one of the above,
The heat treatment is performed at a temperature lower than ℃.

In the present invention, when a heat treatment for the purpose of coarsening the crystal grains of the ODS alloy is performed, if the heat treatment temperature is low, the crystal grains do not sufficiently coarsen, so that sufficient high-temperature strength can be obtained. In addition, at a high temperature where the heat treatment temperature is close to the melting point, high-temperature strength is reduced because local melting occurs. Therefore, in the present invention, the heat treatment temperature is 1100 ° C. or higher and 1
It was defined as less than 370 ° C.

The composite material part according to the eleventh aspect is manufactured by the method for manufacturing a composite material part according to any one of the first to third aspects.

According to a twelfth aspect of the present invention, there is provided a combustor liner according to any one of the fourth to tenth aspects.

According to the eleventh and twelfth aspects of the present invention, it is possible to obtain a composite material component such as a combustor liner, which can prevent a decrease in strength due to welding and sufficiently have high-temperature strength.

[0043]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of the present invention will be described below with reference to FIGS.

First Embodiment (FIGS. 1 to 3) In the present embodiment, a composite material part was produced by combining two or more alloys having different characteristics.

FIG. 1 is a view schematically showing a process for producing a composite material part.

As shown in FIG. 1A, an alloy powder 11 was first sealed in a metal capsule 10 as a container. Next, the alloy powder 11 having a component different from that of the alloy powder 11 and, finally, the alloy powder 11 initially sealed are sealed.
Two kinds of alloy powders 1 having different components in the direction perpendicular to the axial center with the extrusion direction of the metal capsule 10 as the axial center.
1, 12 were vacuum-sealed in layers. Thereafter, the mixture was sintered and solidified by hot extrusion to obtain a round bar-shaped composite material part 13 shown in FIG. 1 (b).

As shown in FIG. 1 (b), a composite material part 13 in the shape of a round bar has an alloy powder 14 in which alloy powder 11 is sintered and solidified at both ends, and an alloy powder 1 between these alloys 14.
2 comprises a sintered and solidified alloy 15.

FIG. 2 is a view schematically showing a process of manufacturing a composite material part having a shape different from that of FIG.

As shown in FIG. 2 (a), first, two kinds of inner partition plates 17 and outer partition plates 18 having different radii were placed in a hollow metal capsule 16 for a circular tube. The alloy powder 19 is placed between the metal capsule 16 and the outer partition plate 18.
Is sealed between the inner partition plate 17 and the outer partition plate 18 with an alloy powder 20 having a different composition from the alloy powder 19, and is radiated (radially) from the axial center of the extrusion direction of the metal capsule 16.
Two kinds of alloy powders 19 and 20 having different components were vacuum-sealed in layers. Then, the inner partition plate 17 and the outer partition plate 1
8 is removed and then sintered and solidified by hot extrusion to obtain a hollow tubular composite material part 21 shown in FIG.
I got

As shown in FIG. 2 (b), the hollow circular composite material component 21 is composed of an alloy 22 obtained by sintering and solidifying an alloy powder 19 and an alloy powder 20 disposed further inside the alloy 22. And a sintered and solidified alloy 23.

FIG. 3 is a schematic view showing a manufacturing process of a composite material part made of a material different from that of FIG. Note that FIG.
Are substantially the same as those shown in FIG. 1, and the description of the same parts will be omitted by using the reference numerals in FIG.

In FIG. 3A, as the alloy powder 11 shown in FIG. 1, a metal-ceramic alloy powder 24 obtained by subjecting a metal powder and a ceramic powder to a mechanical alloying treatment was used. Then, a round composite material part 25 shown in FIG. 3B was obtained.

As shown in FIG. 3B, an alloy 26 obtained by sintering and solidifying an alloy powder 24 is disposed at both ends of a composite material part 25 having a round bar shape.

According to the present embodiment, as shown in FIG.
By encapsulating alloy powders 11 and 12 having different components in layers perpendicular to the axial center of the extrusion direction, alloy 14 in which alloy powder 11 is sintered and solidified and alloy 14 in which alloy powder 12 is sintered and solidified are formed. The composite material part 13 having the function of the composite material 15 can be obtained.

Further, an alloy powder having excellent oxidation resistance and OD
When an alloy powder having an excellent high-temperature strength such as an S alloy is vacuum-sealed in two layers from the bottom surface of the metal capsule 10, that is, in a direction perpendicular to the axial center of the extrusion direction, the front surface (or the back surface) is excellent. A plate-shaped composite material part having oxidation resistance and having excellent high-temperature strength on the back surface (or the front surface) can be obtained. On the other hand, an alloy powder having an excellent high temperature strength such as an ODS alloy and an alloy powder having an excellent weldability are mixed with a metal capsule 10.
When vacuum-sealed from the side in a state where it is laid sideways, that is, in two layers in a direction parallel to the axial center of the extrusion direction, the upper part (or lower part) in the longitudinal direction has excellent high-temperature strength, The lower part (or upper part) can obtain a rod-shaped composite material part having excellent weldability.

Although the composite material part 13 in the shape of a round bar is manufactured in FIG. 1, a composite material part in the shape of a circular tube or a plate may be manufactured.

According to the present embodiment, as shown in FIG. 2, the alloy powder 19 is further radiated from the center of the axis of the metal capsule 16 in the radial (radial) direction. By encapsulation, the outer layer of the circular tube has the function of the alloy 22 in which the alloy powder 19 is sintered and solidified, and the outer layer of the circular tube has the function of the alloy 23 in which the alloy powder 20 is sintered and solidified. Tubular composite material part 21
Can be obtained.

Further, for example, in one circular pipe, an alloy powder excellent in weldability is sealed, and an ODS
By encapsulating an alloy powder having an excellent high-temperature strength such as an alloy, it is possible to obtain a circular pipe in which the inner layer of the circular pipe has excellent high-temperature strength and the outer layer of the circular pipe has excellent weldability.

Further, according to this embodiment, as shown in FIG. 3, the metal-ceramic alloy powder 24 and the alloy powder 1
2 in a layered manner in a direction perpendicular to the axial center of the extrusion direction, so that alloy powder 24 having ceramic powder is
A composite material part 25 having the function of an alloy 26 obtained by sintering and solidifying and an alloy 15 obtained by sintering and solidifying the alloy powder 12 can be obtained. Here, since the alloy 26 in which the alloy powder 24 is sintered and solidified has stable ceramic particles dispersed therein, it has excellent high-temperature strength even at an ultra-high temperature near the melting temperature.

Therefore, according to this embodiment, it is possible to obtain a composite material part having different characteristics in one product by combining two or more alloys having different characteristics.

Second Embodiment (FIGS. 4 and 5) In this embodiment, a combustor liner for a gas turbine was manufactured.

FIG. 4 is a view schematically showing a process of manufacturing a combustor liner for a gas turbine.

As shown in FIG. 4A, two types of inner partition plates 17 and outer partition plates 18 having different radii were placed in a metal capsule 16 for a hollow circular tube. Then, an alloy powder 27 containing no ceramic powder is interposed between the metal capsule 16 and the outer partition plate 18 and a mechanical alloying process is performed between the inner partition plate 17 and the outer partition plate 18 with the metal powder and the ceramic powder. The obtained metal-ceramic alloy powder 24 was sealed. Then, after removing the inner partition plate 17 and the outer partition plate 18, the alloy powder 27 is sintered and solidified by hot extrusion, and the alloy powder 27 is sintered and solidified as shown in FIG. Was obtained from the sintered and solidified alloy 26. And
The circular pipe 29 was machined to obtain a gas turbine combustor liner 30 shown in FIG.

FIG. 5 is a view schematically showing a process of manufacturing a combustor liner for a gas turbine, which is an improvement of the combustor liner shown in FIG.

As shown in FIG. 5 (a), first, three kinds of partition plates having different radii were placed in a metal capsule 16 for a hollow circular tube. These partition plates include a first partition plate 31 inside the metal capsule 16, a second partition plate 32 inside the first partition plate 31, and a third partition plate 33 inside the second partition plate 32. did. Then, an alloy powder 27 containing no ceramic powder is sealed between the metal capsule 16 and the first partition plate 31, and the metal-ceramic alloy powder 24 is placed between the first partition plate 31 and the second partition plate 32. Further, an alloy powder 34 containing no alloy powder 27 or a ceramic powder different from the alloy powder 27 was sealed between the second partition plate 32 and the third partition plate 33.

Then, the first partition plate 31 and the second partition plate 32
After removing the third partition plate 33 and sintering and solidifying by hot extrusion, the alloy powder 27 shown in FIG.
28 (or alloy 35 in which alloy powder 34 has been sintered and solidified), alloy 26 in which alloy powder 24 has been sintered and solidified, and alloy 28 in which alloy powder 27 has been sintered and solidified. The resulting circular tube 36 was obtained. Then, the circular tube 36 was machined to obtain a gas turbine combustor liner 37 shown in FIG.

According to the present embodiment, as shown in FIG.
A combustor liner 30 can be obtained in which the inner layer is made of alloy 26 with ceramic powder and the outer layer is made of alloy 28 without ceramic powder. Here, since the alloy 26 forming the inner layer of the combustor liner 30 has stable ceramic particles dispersed therein, it has excellent high-temperature strength even at an ultra-high temperature near the melting temperature. In addition, since the alloy 28 forming the outer layer of the combustor liner 30 does not contain ceramic particles, a decrease in high-temperature strength due to joining as in the conventional example shown in FIG. 12 does not occur. Therefore, the inner layer of the combustor liner 30, which becomes hot during operation, has excellent high-temperature strength, and the outer layer of the combustor liner 30, which is a joint portion, does not cause a decrease in strength due to welding. The gas turbine combustor liner 30 having both weldability can be obtained.

In FIG. 5, alloys 28 and 35 containing no ceramics are further formed inside the alloy 26 to form a three-layer structure.

Usually, when hot extrusion is performed, a large resistance stress is generated at the contact surface between the metal capsule 16 and the alloy powder. Therefore, in the case of the alloy 26 containing ceramic powder having poor ductility, the vicinity of the contact surface Cracks may occur.
However, as in the present embodiment, by encapsulating the alloys 28 and 35 containing no ceramic powder inside the metal capsule 16 and outside the third partition plate 33 as the contact surface, sufficient ductility is provided near the contact surface. It can prevent the occurrence of cracks.

Also, as for the combustor liner 37, the inner surface of the combustor liner 37, which becomes hot during operation, has excellent high-temperature strength, and the outer surface of the combustor liner 37, which is a joint, causes a decrease in strength due to welding. Therefore, a gas turbine combustor liner 37 having sufficient high-temperature strength and weldability can be obtained.

Third Embodiment (FIGS. 6 and 7) In this embodiment, a combustor liner is manufactured by changing the main component of the alloy powder sealed inside the metal capsule. , A high temperature tensile test and an oxidation resistance evaluation test were performed.

Example 1 In this example, a Ni—Cr alloy powder not containing ceramics was first sealed inside a metal capsule, and then N 2 was added.
An alloy powder obtained by adding 1 wt% of Y ₂ O ₃ as a ceramic powder to an alloy powder obtained by adding 20 wt% of Cr containing i as a main component is further sealed inside, and sintered and solidified by hot extrusion to obtain a combustor. A liner was made.

Example 2 In this example, first, a ceramic-free Ni—Cr alloy powder was sealed inside a metal capsule, and then a C
The alloy powder obtained by adding 1 wt% of Y ₂ O ₃ as a ceramic powder to the alloy powder containing 20 wt% of Cr containing o as a main component is further sealed inside, and sintered and solidified by hot extrusion to obtain a combustor. A liner was made.

Embodiment 3 In this embodiment, first, a ceramic-free Ni—Cr alloy powder was sealed inside a metal capsule, and then F
The alloy powder obtained by adding 1 wt% of Y ₂ O ₃ as a ceramic powder to the alloy powder obtained by adding 20 wt% of Cr containing e as a main component is further encapsulated, and sintered and solidified by hot extrusion to obtain a combustor. A liner was made.

The thus-obtained combustor liners of Examples 1 to 3 were subjected to a heat treatment at 1300 ° C., and then a test piece was taken from a portion formed of an alloy containing ceramics, and then subjected to a tensile test. A test and an oxidation resistance evaluation test were performed. The test temperature in the tensile test was 100
0 ° C. and the oxidation resistance evaluation test was performed at 1000 ° C. at 1000 ° C.
The weight increase due to oxidation was measured for the test piece after heating for a period of time. FIG. 6 shows the test results.

As is apparent from FIG. 6, the tensile strength of Example 1 was higher than 200 MPa and the Ni-base was excellent, but the oxidation resistance was high in Example 2.
Shows an oxidation weight of about 70 mg / cm ^2, and the Co group is excellent. On the other hand, the Fe group of Example 3 is
It has intermediate strength and oxidation resistance between the two. Therefore, the main component of the alloy powder is preferably selected based on the use environment and required characteristics of the equipment in consideration of characteristics such as high-temperature strength and oxidation resistance.

Next, a combustor liner was manufactured by variously changing the ceramic powder added to the alloy powder from Example 4 to Example 6, and a high-temperature tensile test was performed.

Embodiment 4 In this embodiment, a ceramic-free Ni—Cr alloy powder is first sealed inside a metal capsule, and then N 2
1 wt% as ceramic particles in i-Cr alloy powder
Alloy powder to which Y ₂ O ₃ is added is further enclosed inside,
The combustor liner was fabricated by sintering and solidifying by hot extrusion.

Example 5 In this example, a ceramic-free Ni—Cr alloy powder was first sealed inside a metal capsule, and then a C—C
1 wt% as ceramic particles in o-Cr alloy powder
The alloy powder to which Al ₂ O ₃ was added was further sealed inside, and sintered and solidified by hot extrusion to produce a combustor liner.

Embodiment 6 In this embodiment, first, a Ni—Cr alloy powder containing no ceramics was sealed inside a metal capsule, and then F
1 wt% as ceramic particles in e-Cr alloy powder
The alloy powder to which carbide was added was further enclosed inside, and sintered and solidified by hot extrusion to produce a combustor liner.

[0096] The thus obtained combustor liners of Examples 4 to 6 were subjected to a heat treatment at 1300 ° C., and thereafter, test specimens were taken from a portion formed of an alloy containing ceramics, and were subjected to a tensile test. The test was performed. The test temperature in the tensile test was set to 1000 ° C. FIG. 7 shows the test results.

As is evident from FIG. 7, in Example 6 using carbide as the ceramic powder constituting the alloy powder, the tensile strength was lower than 130 MPa, whereas Y ₂
Example 4 and Example 5 using O ₃ and Al ₂ O ₃
All have a tensile strength exceeding 150 MPa, and excellent high-temperature strength can be obtained. Therefore, by using an oxide such as Y ₂ O ₃ and Al ₂ O ₃ as the ceramic powder, excellent high-temperature strength can be obtained.

Fourth Embodiment (FIG. 8) In this embodiment, when hot extrusion is performed on a metal capsule enclosing an alloy powder, a combustor liner is manufactured at various extrusion temperatures, and a high-temperature tensile test is performed. Was.

First, a Ni—Cr alloy powder not containing ceramics was sealed inside the metal capsule, and then N 2
1 wt% as ceramic particles in i-Cr alloy powder
Of Y ₂ O ₃ was further enclosed inside, the extrusion temperature was changed from 800 ° C. to 1300 ° C., and sintering and solidification were performed by hot extrusion to produce a combustor liner.

[0085] The thus-obtained combustor liner was subjected to a heat treatment at 1300 ° C, and then a test piece was taken from a portion formed of an alloy containing ceramics, and a tensile test was performed. The test temperature in the tensile test was 10
The temperature was set to 00 ° C. FIG. 8 shows the test results.

As shown in FIG. 8, the extrusion temperature was 1300 ° C.
Above, the high-temperature strength rapidly decreases. In order for the ODS alloy containing ceramics to exhibit sufficient high-temperature strength, it is necessary to perform heat treatment to lengthen the crystal grains, but it is necessary to impart sufficient distortion as a driving force during plastic working. However, when the temperature at the time of plastic working becomes high, the strain is released and the high-temperature strength is reduced. That is, when the extrusion temperature is set to 1300 ° C. or more, the strain is released and the high-temperature strength is reduced. Further, when the extrusion temperature is lowered, a very large resistance stress is exerted at the time of extrusion, so that large equipment is required, and cracks may be generated during plastic working. For this reason, the extrusion temperature was set to 800 ° C. or higher.

Therefore, according to the present embodiment, by setting the extrusion temperature in the production of the combustor liner to 800 ° C. or more and less than 1300 ° C., a combustor liner having excellent high-temperature strength can be obtained.

Fifth Embodiment (FIG. 9) In the present embodiment, a pipe expanding process is performed in a process of manufacturing a combustor liner for a gas turbine.

FIG. 9 is a schematic view showing a process of manufacturing a gas turbine combustor liner subjected to a pipe expansion process. Note that FIG. 9 is substantially the same as the step shown in FIG. 4 in the second embodiment, and therefore, the same portions are denoted by the reference numerals in FIG.

As shown in FIG. 9A, two types of inner partition plates 17 and outer partition plates 18 having different radii were first placed in a metal capsule 16 for a hollow circular tube. Then, an alloy powder 27 containing no ceramic powder is interposed between the metal capsule 16 and the outer partition plate 18, and a mechanical alloying process is performed between the inner partition plate 17 and the outer partition plate 18 with the metal powder and the ceramic powder. The obtained metal-ceramic alloy powder 24 was sealed. Then, after removing the inner partition plate 17 and the outer partition plate 18, the alloy powder 27 is sintered and solidified by hot extrusion, and the alloy powder 27 is sintered and solidified as shown in FIG. From the alloy 26 sintered and solidified. The diameter of the thick pipe 38 is smaller than that of the finally obtained gas turbine combustor liner. Then, the thick pipe 38 was subjected to a pipe expansion process and finished by machining to obtain a combustor liner 39 for a gas turbine shown in FIG. 9C.

According to this embodiment, by setting the diameter of the thick pipe 38 produced by hot extrusion to be smaller than the diameter of the combustor liner 39 for the gas turbine which is finally obtained, it is necessary for hot extrusion. Equipment can be reduced. Further, during operation of the gas turbine, the stress generated in the combustor liner 39 is mainly thermal stress due to the temperature difference between the front and back surfaces, and a large stress is generated in the circumferential direction of the combustor liner 39. It is necessary to grow crystal grains of the ODS alloy in the circumferential direction. Therefore, in performing the pipe expansion process in the present embodiment, in order to add distortion in the circumferential direction of the combustor liner 39, the crystal grains after the heat treatment are elongated in the circumferential direction of the combustor liner 39, and the high temperature in the circumferential direction is excellent. A strong combustor liner 39 can be obtained.

Sixth Embodiment (FIG. 10) In this embodiment, after producing a combustor liner for a gas turbine by hot extrusion, heat treatment was performed at various temperatures, and then a high temperature tensile test was performed.

First, a ceramic-free Ni—Cr alloy powder is sealed inside the metal capsule, and then Ni—Cr alloy powder is added.
1 wt% Y ₂ as ceramic particles in Cr alloy powder
The alloy powder to which O ₃ was added was sealed further inside. Then, it was sintered and solidified by hot extrusion to produce a combustor liner, and heat treatment was performed by changing the heat treatment temperature from 800 ° C. to 1370 ° C.

[0094] With respect to the combustor liner thus obtained, a test piece was sampled from a portion formed of an alloy containing a ceramic and subjected to a tensile test. The test temperature in the tensile test was set to 1000 ° C. FIG. 10 shows the test results.

As shown in FIG. 10, when the heat treatment temperature is 110
If the temperature is lower than 0 ° C., the crystal grains of the ODS alloy including the ceramic are not sufficiently coarsened.
Lower than Pa, and sufficient high-temperature strength could not be obtained. On the other hand, at a high temperature of 1370 ° C. or more, the tensile strength is 80 MPa because local melting occurs.
And the high-temperature strength was low.

Therefore, according to the present embodiment, when the heat treatment is performed on the combustor liner, the heat treatment temperature is 1100.
By setting the temperature in the range of not less than 1 ° C. and less than 1370 ° C., a combustor liner having excellent high-temperature strength can be obtained.

[0097]

As described above, by using the method for producing a composite material part of the present invention, a composite material part having two or more functions can be obtained, and by applying this composite material part. Thus, a gas turbine combustor liner having excellent high-temperature strength and weldability can be obtained at low cost.

[Brief description of the drawings]

FIG. 1 is a schematic view showing a manufacturing process of a composite material part according to a first embodiment of the present invention.

FIG. 2 is a schematic view showing a manufacturing process of a composite material part according to the first embodiment of the present invention.

FIG. 3 is a schematic view showing a manufacturing process of a composite material part according to the first embodiment of the present invention.

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

FIG. 5 is a schematic view illustrating a manufacturing process of a combustor liner for a gas turbine according to a second embodiment of the present invention.

FIG. 6 is a view showing a relationship between a matrix metal and tensile strength or oxidation resistance in a third embodiment of the present invention.

FIG. 7 is a diagram showing a relationship between ceramic powder and tensile strength in a third embodiment of the present invention.

FIG. 8 is a diagram showing a relationship between an extrusion temperature and a tensile strength in a fourth embodiment of the present invention.

FIG. 9 is a schematic view showing a manufacturing process of a gas turbine combustor liner subjected to a pipe expansion process in a fifth embodiment of the present invention.

FIG. 10 is a diagram showing a relationship between a heat treatment temperature and a tensile strength in a sixth embodiment of the present invention.

FIG. 11 is a structural view showing a conventional combustor liner for a gas turbine.

FIG. 12 is a view showing the tensile strength of a ring-shaped material and a joint in the related art.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 10 Metal capsule 11 Alloy powder 12 Alloy powder 13 Composite material component 14 Alloy in which alloy powder 11 was sintered and solidified 15 Alloy in which alloy powder 12 was sintered and solidified 16 Hollow tubular metal capsule 17 Inner partition plate 18 Outer partition plate DESCRIPTION OF SYMBOLS 19 Alloy powder 20 Alloy powder 21 Hollow tubular composite material part 22 Alloy in which alloy powder 19 was sintered and solidified 23 Alloy in which alloy powder 20 was sintered and solidified 24 Metal-ceramic alloy powder 25 Composite material part in round bar shape 26 An alloy in which the alloy powder 24 is sintered and solidified 27 An alloy powder containing no ceramic powder 28 An alloy in which the alloy powder 27 is sintered and solidified 29 Circular tube 30 Combustor liner 31 First partition plate 32 Second partition plate 33 Third Partition plate 34 Alloy powder not containing ceramic powder 35 Alloy powder 34 was sintered and solidified 36 yen gold tube 37 combustor liner 38 thick pipe 39 combustor liner

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁷ Identification symbol FI Theme coat ゛ (Reference) F02C 7/00 B22F 3/14 H

Claims (12)

[Claims] When a product having a fixed cross section such as a round bar, a tube or a plate is produced by hot working and vacuum-sealing an alloy powder in a container, the extrusion direction of the container is set as the axis, A method for producing a composite material component, comprising: laminating two or more alloy powders having different components in a direction parallel or perpendicular to a center in a layer form, and then sintering and solidifying. 2. The method for producing a composite material part according to claim 1, wherein, when producing a hollow circular tube, two or more kinds of alloy powders having different components in a radial direction from the axial center of the container are enclosed in layers. A method for producing a composite material component, characterized by being sintered and solidified thereafter. 3. The method for manufacturing a composite material part according to claim 1, wherein at least one of the alloy powders comprises:
A method for producing a composite material part, comprising an alloy powder containing a ceramic powder obtained by subjecting a metal powder and a ceramic powder to a mechanical alloying treatment. 4. When a combustor liner is manufactured by using the method for manufacturing a composite material part according to claim 2 or 3, metal powder containing no ceramic powder is sealed inside the container, and further inside the alloy powder. A method for manufacturing a combustor liner, comprising: enclosing an alloy powder containing a ceramic powder in a container, and enclosing two kinds of alloy powders having different components in a radial direction from the axial center of the container in the container. 5. The method for producing a combustor liner according to claim 4, wherein metal powder containing no ceramic powder is enclosed inside the alloy powder enclosed in two layers, and two or more kinds of components having different components are contained in the container. 3. A method for producing a combustor liner, wherein the alloy powder of (3) is enclosed in three layers in a radial direction from the axial center of the container. 6. The method for manufacturing a combustor liner according to claim 4, wherein the alloy powder is Ni, Co or Fe.
A method for producing a combustor liner, characterized in that the main component is any of the above. 7. The method for manufacturing a combustor liner according to claim 4, wherein the ceramic powder is an oxide such as Y ₂ O ₃ or Al ₂ O _3. . 8. The method for manufacturing a combustor liner according to claim 4, wherein the temperature at which sintering and solidification is performed is set to 800 ° C. or more and less than 1300 ° C. How to make a liner. 9. The method for manufacturing a combustor liner according to claim 4, wherein when the thick pipe is manufactured by sintering and solidification, the diameter of the thick pipe is finally obtained. A method for producing a combustor liner, characterized in that the diameter is smaller than the diameter and the thick pipe is expanded to obtain a combustor liner. 10. The method for manufacturing a combustor liner according to claim 4, wherein the obtained combustor liner is subjected to a heat treatment at a temperature of 1100 ° C. or more and less than 1370 ° C. How to make a combustor liner. 11. A composite material part produced by the method for producing a composite material part according to claim 1. 12. A combustor liner produced by the method for producing a combustor liner according to any one of claims 4 to 10.