JPH10102175A - Co-base heat resistant alloy, member for gas turbine, and gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To attain a long service life and a high reliability, required of a gas turbine member, by providing a composition composed essentially of Co and precipitating or crystallizing an intermetallic compound with a structure of specific type. SOLUTION: This Co-base heat resistant alloy has a composition composed essentially of Co and containing, by weight, 5-10% Al and 0.2-2.0% C and also has a structure in which an intermetallic compound with an E21 type structure is precipitated or crystallized. For example, by using this alloy, a columnar crystal solidified from a leading edge 4 side to a trailing edge 3 side is formed in a wing part 1, and also a columnar crystal is formed in the same direction in a side wall 2. The E21 type intermetallic compound is composed essentially of CO3 AlC. B is incorporated by 0.005-1% into the alloy. The Co-base heat resistant alloy is subjected to solution heat treatment at 1200-1300 deg.C and then to aging treatment at 900-1100 deg.C. By this method, the Co-base heat resistant alloy, having high strength, high ductility, high thermal fatigue resistance, and corrosion resistance, can be obtained.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a novel Co-based heat-resistant alloy requiring heat-resistant fatigue resistance and high-temperature strength, a gas turbine component and a gas turbine used therefor.

[0002]

2. Description of the Related Art As a material for a gas turbine component which is used at a high temperature of 700 ° C. or more and requires strength,
So far, Ni-based alloys and Co-based alloys have been used. N
The i-base alloy is precipitation-strengthened mainly by the γ 'phase, while the Co-base alloy is precipitation-strengthened mainly by the M ₂₃ C ₆ or MC type carbide phase. In general, Ni-based alloys are superior in strength. This is because the γ 'phase is easily dispersed uniformly by heat treatment, is dispersed at a high volume ratio, and has a positive temperature dependence of strength. On the other hand, a Co-based alloy is excellent in corrosion resistance and ductility. This is due to the ductility and corrosion resistance of the Co matrix. JP-A-59-129746 and JP-A-62-129746
The Co-base alloy for engine valves and valve seats described in Japanese Patent No. 164844 and the high-ductility Co-base alloy described in Japanese Patent Application Laid-Open No. 60-100462 have a γ 'phase (Ni ₃ (A
l, Ti)), Ni, Al, and Ti are added for the purpose of strengthening the precipitation.

[0003]

The combustion temperature of gas turbines is being increased more and more with the aim of increasing the efficiency, and the material temperature during operation is exceeding 900 ° C. at the maximum. There is a demand for the development of materials that can be used reliably in such harsh environments. In response to this heat resistance requirement, Ni-based alloys have obtained higher high-temperature strength by developing unidirectionally solidified materials and single crystal materials.
In addition, with the development of coating technology, it has become possible to resist corrosion and oxidation. Co-based alloys have been used for members that do not require high strength because of their corrosion resistance and the ability to repair welds, but such members have higher high-temperature strength as the temperature of the material used rises. Ni
Base alloys have been used. In order to cope with an increase in the temperature of the used material, it is necessary to increase the strength of the Co-based alloy.

[0004] Thermal fatigue of components due to startup and shutdown and cooling during operation has become an increasingly important destructive factor due to an increase in the temperature of the material used. It is considered that the higher the material strength and the higher the ductility, the better the thermal fatigue resistance. Among the heat-resistant alloys currently used, Ni-base alloys having higher strength
Superior in thermal fatigue resistance to o-base alloys. However, the Co-based alloy is more excellent in ductility, and the higher strength C
Excellent heat fatigue resistance is expected for o-based alloys.

For the above reasons, attempts have been made to increase the strength by taking advantage of the excellent corrosion resistance and ductility of the Co-based alloy. For the purpose of introducing the same reinforcer and Ni based alloy Co matrix, Co ₃ Ti with the same L1 ₂ -type structure and crystal structure of the gamma 'phase, a-Co ₃ Ta have been studied. However, these phases have problems with phase stability at high temperatures.

An object of the present invention is to provide a Co-based heat-resistant alloy having excellent corrosion resistance, strength and heat fatigue resistance at high temperatures, a member for a gas turbine, and a gas turbine.

[0007]

Means for Solving the Problems The present invention is mainly composed of Co, containing Al5～10% and C0.2～2.0% by weight, E2 ₁ type structure intermetallic compound out precipitation or crystal A Co-based heat-resistant alloy characterized in that:

[0008] The E2 ₁ type structure intermetallic compound Co ₃ A
It is preferable that the base composition be 1C.
5 to 1% by weight, and the alloy may be any of a columnar crystal, a polycrystal, and a single crystal. In particular, the alloy is mainly composed of Co, and has an Al content of 5 to 10% and a C of 0.2 to 2.0.
% Of the Al content and the C content in FIG.
%, C 0.7%), B (Al 6.6%, C 0.2%), C
(Al 9.1%, C 1.6%), D (Al 7.5%, C2.
(0%) is preferably within an area surrounded by a line connecting the points sequentially.

According to the present invention, Co is used as a main component,
Containing 5-10% and 0.2-2.0% C, 1200 ° C
After performing a solution treatment at a temperature of ３００1300 ° C., 900 ° C.
A method for producing a Co-based heat-resistant alloy, characterized by performing aging treatment at a temperature of １1100 ° C.

According to the present invention, Co is used as a main component, and
Containing 5-10% and C0.2～2.0%, is in the gas turbine member, characterized by comprising the Co-based alloy intermetallic compounds E2 ₁ type structure is out precipitation or crystallization, specific Specifically, there are a blade, a nozzle, a liner for a combustor, and a transition piece, at least one of which is made of the above-mentioned Co-based heat-resistant alloy, a compressor, a combustor, a turbine blade fixed to a turbine disk, and the turbine. And a turbine nozzle provided corresponding to the blade.

FIG. 2 shows E2 ₁ having a basic composition of Co ₃ AlC.
A high-temperature strength is achieved by showing the crystal structure of the type-structure intermetallic compound and using it as a main reinforcing phase. E2 ₁
Type structure is a structure in which the third element has entered the body-centered position of the L1 ₂ type structure shown in FIG. Rather, the Co ₃ AlC phase is L1
C as a stabilizing element in the Co ₃ Al ₂ type structure is also believed that present in the body-centered position. Thus two-phase alloy consisting of Co ₃ AlC phase and the Co phase similar to L1 ₂ type structure, high-temperature strength similarly to Ni-based alloy reinforced with gamma 'phase (Ll ₂ -type structure) is expected. In order to obtain a structure in which the Co ₃ AlC phase is uniformly dispersed, Al 5 to 10 w
t.%, C0.2 to 2 wt.% must be contained. Further, in order to suppress breakage due to grain boundaries and improve ductility, B1% or less is added by weight.

Further, by producing a columnar crystal material or a single crystal material by unidirectional solidification, fracture and corrosion through grain boundaries can be reduced, and higher high-temperature strength, high ductility and high corrosion resistance can be obtained.

The role of each element contained in the Co-base alloy constituting the gas turbine component will be described below.

Co, which is a main component, has a higher melting point and higher ductility than Ni, and also has a higher melting point of sulfide, which is advantageous in terms of corrosion resistance.

[0015] Al contributes to the strength which make E2 ₁ type structure intermetallic compound together with C to be described later as a reinforcing phase other, oxidation resistance creating a stable oxide film, thereby contributing to the corrosion resistance, more than 3% by weight the addition to the E2 ₁ type structure intermetallic compound appears, since different phase is added more than 10% excess temperature strength appears to decrease, and 3-10%. In particular, it is preferably 5 to 9.1%.

[0016] C another contributes to the strength as E2 ₁ type structure intermetallic compound made this strengthening phase with the aforementioned Al, 0.2% or more by weight to contribute to the strength by solid solution in the matrix or grain boundaries added, E2 ₁ type structure is to appear intermetallic compound, it is impaired toughness appear graphite when 2.0% or more is added excessively. In particular, 0.5
~ 1.50% is preferred.

In order to increase both tensile strength, creep strength and ductility, the amount of Al and the amount of C in FIG.
5.0%, C0.7%), B (Al6.6%, C0.2)
%), C (9.1% Al, 1.6% C), D (7.5% Al)
%, C2.0%) is preferably in a region surrounded by a line connecting the points sequentially.

B strengthens grain boundaries and improves ductility and tensile strength, but lowers creep strength and, when added in excess, conversely decreases ductility and toughness. An appropriate amount of addition is 0 to 1%.

[0019] The E2 ₁ type structure intermetallic compound 900 ° C.
Since the above is stable, Co
The strength of the gas turbine component made of the base alloy is maintained even at 900 ° C. or higher. In addition, since the Co-based alloy has both high strength and high ductility, the gas turbine component has good thermal fatigue resistance.

The precipitation or crystallization of Co intermetallic compound is preferably 5 to 60% by volume, particularly preferably 10 to 40% by volume. It is preferable to increase the amount up to 60% by volume depending on the use temperature.

When casting into the gas turbine component, a columnar crystal or a single crystal material is formed by unidirectional solidification.
Grain boundaries, which are the starting points of fracture and corrosion, can be reduced, and high strength, high ductility, and high corrosion resistance can be obtained. Ordinary polycrystals can also be used. By subjecting these castings to the above-described heat treatment, the structure that was non-uniform immediately after casting can be made uniform, and the structure can be controlled to a shape having excellent strength, thereby obtaining high strength and high ductility characteristics.

[0022]

BEST MODE FOR CARRYING OUT THE INVENTION

(Example 1) Table 1 shows the chemical composition (% by weight) of the test materials. Test materials Nos. 1 to 12 were prepared by casting an alloy having a predetermined composition melted in a vacuum high-frequency melting furnace at a casting temperature of 1550 ° C. and a mold temperature of 1 °.
A columnar crystal casting was prepared by a unidirectional solidification method at 535 ° C. and a lowering speed of 200 mm / h, from 1300 to 1250.
After the solution treatment at 1 ° C. for 1 hour, an aging treatment at 1100 ° C. for 8 hours was performed. Test material No. 13 is a conventional Co-based alloy FSX
At -414, it was produced by a normal coagulation method, and was subjected to a solution treatment at 1150 ° C for 4 hours and then an aging treatment at 982 ° C for 4 hours.

[0023]

[Table 1] FIG. 4 is an electron micrograph of the test material No. 3. As shown in the figure, a rectangular Co ₃ AlC phase of 0.1 to 2 μm square is uniformly distributed in a volume ratio of 17.1%, which is similar to the structure of the γ ′ phase strengthened Ni-based alloy. I have. Fine precipitates distributed between the rectangular precipitates are also precipitates at the time of cooling after the aging treatment with the Co ₃ AlC phase. According to the microstructure observation, the alloy of the present invention that has been subjected to the aging treatment has a Co ₃ AlC phase having a volume ratio sufficient to contribute to the strength up to at least 1100 ° C. Most of the precipitates are 1 μm or less,
There are two particles having a particle size of 1 μm or more in the area of μm ² .

A tensile and creep rupture test piece (parallel diameter: 6 mm) and a thermal shock test piece (disc shape, diameter: 61 mm) were processed from these test materials, and were subjected to a room temperature tensile test and a creep rupture test (temperature 816 ° C., stress 17.6 kgf / mm ² ) and a thermal shock test (heat cycle 900 ° C. for 30 minutes-200 ° C.).
The results of the room temperature tensile test and the creep rupture test are shown in Tables 2 and 3, respectively. In the thermal shock test, the length of the crack generated at the outer edge of the test piece was compared with the number of thermal cycles for the supplied materials Nos. The results are shown in FIG.

[0025]

[Table 2]

[0026]

[Table 3] In the tensile properties at room temperature shown in Table 1, the test materials Nos. 1 to 12 exceeded 0.2% proof stress and tensile strength, and the test materials Nos. 10 and 11 exceeded the conventional materials in elongation and drawing. In the creep rupture characteristics, the test materials 2 to 6, 8 to 12 exceeded the rupture time, and the elongation / drawing showed a high level of ductility, which was about the same or lower than that of the conventional material. The test material to which B was added improved the elongation and drawing, but shortened the creep rupture time. In the test materials Nos. 8 and 12 with low elongation and drawing, graphite precipitated in the grains and at the grain boundaries was observed, and the precipitation of the graphite caused the decrease in ductility. In addition, in the test materials Nos. 7 and 11, a CoAl phase having a B2-type structure was observed in addition to the Co ₃ AlC phase. According to FIG. 5, the number of thermal cycles at which cracks were generated was larger than that of the conventional material, and thermal fatigue resistance was recognized.

From the above results, it was confirmed that the alloy of the present invention is superior in strength, ductility and thermal fatigue resistance to the conventional material.

Example 2 A gas turbine nozzle shown in FIGS. 6 and 7 was manufactured using an alloy having the same composition as the test material No. 10 shown in Table 1 of Example 1. A wax model having the shape shown in FIGS. 6 and 7 is immersed in a liquid in which an acrylic resin is dissolved in methyl ethyl ketone, air-dried, and then immersed in a slurry (zircon flower + colloidal silica + alcohol) to form a stack (first layer zircon sand, Two or more layers of Charmot sand) were sprayed, and this was repeated several times to mold a mold. The mold was dewaxed and fired at 900 ° C.

Next, this mold is provided in a vacuum furnace,
An alloy having the same composition as the test material No. 10 was melted by vacuum melting, and cast into a mold in a vacuum. In addition, for the shapes shown in FIGS. 6 and 7, a mold was prepared so that the direction parallel to the sidewall was the solidification direction, and after casting the alloy in a vacuum furnace, the mold was removed from the furnace at a constant speed. After drawing out and manufacturing a columnar crystal structure unidirectionally solidified in a direction parallel to the side wall, the same heat treatment as in Example 1 was performed to manufacture a nozzle. In this embodiment, the wings 1 formed columnar crystals solidified from the leading edge 4 side to the trailing edge 3 side, and the side walls 2 also formed columnar crystals in the same direction.

(Example 3) A gas turbine bucket shown in FIG. 8 was manufactured using an alloy having the same composition as the test material No. 3 shown in Table 1 of Example 1. A wax model having the shape shown in FIG. 8 is immersed in a solution in which an acrylic resin is dissolved in methyl ethyl ketone, air-dried, and then slurried (zircon flower +
Stack by immersing in colloidal silica + alcohol (first layer zircon sand, second layer or later Charmouth sand)
And this was repeated several times to form a mold.
The mold was dewaxed and fired at 900 ° C. The mold is made so that the longitudinal direction of the bucket is in the solidification direction.

Next, the mold is provided in a vacuum furnace,
An alloy having the same composition as the test material No. 3 was melted by vacuum melting, and cast into a mold in a vacuum. Thereafter, the mold was pulled out of the furnace at a constant speed and solidified in one direction in a direction parallel to the longitudinal direction, and then subjected to the same heat treatment as in Example 1 to produce a bucket. In the present embodiment, the platform 5, shank 7 and dovetail 8 are unidirectionally solidified in this order from the tip of the wing portion 1 to obtain a columnar crystal bucket.

Example 4 A gas turbine combustor liner shown in FIG. 9 was manufactured using an alloy having the same composition as the test material No. 10 shown in Table 1 of Example 1. A metal mold having an inner diameter about 0.2 mm larger than the outer diameter of the combustor liner shown in FIG. 9 is rotated at a constant speed in a vacuum around a water cooling pipe inside or outside the mold. Test material N by vacuum melting
An alloy having the same composition as o.10 was melted and cast into a mold in a vacuum. The cast casting was taken out after cooling, subjected to the same heat treatment as in Example 1, and then machined to produce a combustor liner. The combustor liner has a rectangular projection 9 at one end and the other end having the same thickness as the projection and has a wide width and a large thickness. The projections 9 are provided at substantially equal intervals in the middle to provide reinforcement. Used.

Example 5 A transition piece for a gas turbine combustor as shown in FIG. 10 was manufactured using an alloy having the same composition as the test material No. 10 shown in Table 1 of Example 1. FIG.
0.2mm from outer diameter of combustor transition piece shown in
A metal mold having a large inner diameter is rotated at a constant speed in a vacuum around a water cooling pipe inside or outside the mold. An alloy having the same composition as the test material No. 10 was melted by vacuum melting, and cast into a mold in a vacuum. The cast cylindrical product was taken out after cooling, and formed into a shape shown in FIG. 10 by hot casting to produce a combustor transition piece. Also,
After the hot forging, the same heat treatment as in Example 1 was performed. FIG.
(B) is a front view in the (c) direction, and FIG. 10 (c) is a front view in the (c) direction.

(Embodiment 6) FIG. 11 is a sectional view of a rotating part of a gas turbine for power generation according to the present invention. 14 is a turbine disk, 10 is a turbine stub shaft, 13 is a turbine stacking bolt, 18 is a turbine spacer, 19 is a distant piece, 16 is a compressor disk, 17 is a compressor blade, 11 is a compressor stacking bolt, and 12 is a compressor stub shaft. is there. The gas turbine of this embodiment has three stages of turbine blades 20 and turbine nozzles 30, respectively.

The first stage blade of the gas turbine in the present embodiment is the columnar crystal casting of No. 10 of the first embodiment,
The wing is 130 mm, and its total length is about 220 mm. The service temperature of 14 kgf / mm ² for 10 ⁵ hours is 930 ° C.
The temperature is 940 ° C, and a complicated air cooling hole is provided inside, so that it is cooled by compressed air during operation. The cooling system is a closed system and the cooling structure is a staggered rib system. On the surface of the blade, Al 2-5% by weight, Cr 20-30
%, Y 0.1 to 1%, and an alloy layer consisting of Ni or Ni + Co with a balance of 50 to 150 μm by plasma melting in a non-oxidizing reduced pressure atmosphere to enhance the corrosion resistance.

The second stage blade and the third stage blade are 12 to 16% Cr, 0.5 to 2% Mo, and 2 to 5% by weight.
%, Al 2.5-5%, Ti 3-5%, Ta 1.5-3
%, Co 8 to 10%, C 0.05 to 0.15%, B 0.0
It is composed of a Ni-based superalloy containing 0.05 to 0.02% and the balance of unavoidable impurities and Ni. These blades have an equiaxed structure obtained by ordinary casting. The second stage blade has an internal cooling hole, and is cooled by compressed air. The service temperature of 14 kgf / mm ² for 10 ⁵ hours of these materials is 840 ° C. to 860 ° C. On the blade surface,
A diffusion coating of Cr or Al was applied to enhance corrosion resistance.

The turbine nozzle 30 of the first stage nozzle is a columnar crystal casting of No. 10 of Example 1, which is shown in FIG. 6, and the cooling is a closed impingement cooling. A portion of the outer surface of the first stage nozzle that is in contact with the flame is provided with a thermal barrier coating layer. It consists of fine columnar crystal, a Y ₂ O ₃ stabilized zirconia layer having a columnar crystal structure of the double structure having a columnar crystal macroscopic columnar crystals of the following diameters 10μm in fine diameter 50~200μm It is provided to a thickness of 100 to 200 μm by vapor deposition and comprises a bonding layer between a base metal and a zirconia layer. The bonding layer is a thermal sprayed layer composed of an alloy containing 2 to 5% of Al, 20 to 30% of Cr, and 0.1 to 1% of Y, with the balance being Ni or Ni + Co. The alloy layer also has the effect of improving corrosion resistance.

Second stage nozzle 25 and third stage nozzle 27
In weight, Cr 21-24%, Co 18-23%, C
0.05 to 0.20%, W1 to 8%, Al1 to 2%, Ti
2-3%, Ta 0.5-1.5%, B 0.005-0.15
% And a Ni-based superalloy consisting of Ni and unavoidable impurities. These nozzles have an equiaxed structure obtained by ordinary casting. In particular, it is not necessary to provide a thermal barrier coating layer, but a diffusion coating of Cr or Al is applied to the second stage nozzle in order to enhance corrosion resistance. Each has an internal cooling hole and is cooled by compressed air. The service temperature of these materials at ⁶ kgf / mm ² for 10 ⁵ hours is 840 ° C. to 860 ° C. The same heat treatment is applied to the cast material. The two-stage and three-stage nozzles are arranged such that each center is located substantially at the center between the blades.

In the present embodiment, C 0.03 to 0.1%, Cr 12 to 18%, Ti 1.
2 to 2.2%, Fe 30 to 40%, Nb 2.5 to 3.5
%, B 0.002-0.01%, and the balance is substantially Ni. The Ni-based forged alloy is:
450 ° C, 10 ⁵ h Creep rupture strength of 50 kgf / mm ²
Thus, the strength required as a material for a high-temperature gas turbine is sufficiently satisfied.

The compressor blades have 17 stages and the resulting air compression ratio is 18. Natural gas and light oil are used as fuels.

The combustor consists of the liners and the transition pieces of Examples 4 and 5.

The first stage nozzle in this embodiment has a vane formed integrally between the outer side wall and the inner side wall, and is formed in a crescent shape with one end rounded and formed of a hollow thin material so that cooling air flows into the inside. Be composed. A large number of cooling holes are provided in the vane portion so that cooling air flows in from both sidewalls and passes to the outside at the upstream reading etch portion, and cooling air flows from the end of the downstream recess and the end face of the tip thereof. Many cooling holes are provided so as to communicate with the outside.

The first-stage blade shown in FIG. 8 is used. The wing portion is formed in a crescent shape with one end rounded on the upstream side, and a cooling passage flows from the dovetail so that cooling air flows inside. The cooling hole is provided so as to flow out from the tip of the blade portion and the end face of the blade portion on the downstream side of the combustion gas. The single-crystal casting in this embodiment is obtained by solidifying the platform, shank, and dovetil sequentially from the wing portion side, and the platform and the seal fin extend horizontally almost at right angles from the wing portion. The seal fin has a shape extending substantially at a right angle, and prevents leakage of combustion gas.

The overall structure of the two-stage nozzle is substantially the same as that of the first-stage nozzle. In this embodiment, the two-stage nozzle has two vanes. Cooling air enters through the outer sidewall,
Cooling holes that flow out from the inner side wall side and flow out from the trailing edge on the downstream side of the vane are provided at the vane tip. The inside of the vane is hollow, and the vane is constituted by a thin member having a thickness of 0.5 to 3 mm. In the present embodiment, two vanes are provided, but any one to three vanes can be used. The overall structure of the three-stage nozzle is almost the same as that of the two-stage nozzle. The inside of the vane is hollow, and a cooling medium flows in to cool the vane.

The entire stage structure of the two-stage blade is almost the same as that of the first-stage blade, but a large number of cooling holes are provided straight inside so that the cooling air flows from the dovetail side to the end. The overall structure of the three-stage blade is almost the same as the two-stage blade, and is solid.

With the above configuration, a gas turbine with a higher reliability and a higher overall balance can be obtained, the gas inlet temperature to the first stage turbine nozzle is 1500 ° C., the metal temperature of the first stage turbine blade is 920 ° C., and the exhaust gas of the gas turbine is exhausted. The temperature is 650 ° C., and a power generation gas turbine having a power generation efficiency of 37% or more in LHV display can be achieved.

[0047]

According to the present invention, a Co-based heat-resistant alloy having high strength, high ductility, high thermal fatigue resistance and corrosion resistance can be obtained.
Long life and high reliability can be achieved as a member for a gas turbine.

[Brief description of the drawings]

FIG. 1 is a diagram showing the relationship between Al and C content.

Figure 2 illustrates a unit cell of E2 ₁ type structure.

FIG. 3 shows a unit cell of the L1 ₂ -type structure.

FIG. 4 is an electron micrograph showing a metal structure.

FIG. 5 is a view showing the results of a thermal shock test.

FIG. 6 is a perspective view of a gas turbine nozzle.

FIG. 7 is a perspective view of a gas turbine nozzle.

FIG. 8 is a perspective view of a bucket for a gas turbine.

FIG. 9 is a perspective view of a combustor liner for a gas turbine.

FIG. 10 is a view of a transition piece for a gas turbine.

FIG. 11 is a configuration diagram of a gas turbine.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Wing part, 2 ... Side wall, 5 ... Platform, 6 ... Seal fin, 7 ... Shank, 8 ... Dovetil, 20 ... Turbine blade, 30 ... Turbine nozzle.

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Akira Yoshinari 7-1-1, Omikacho, Hitachi City, Ibaraki Prefecture Inside Hitachi Research Laboratory, Hitachi, Ltd. (72) Inventor Shinya Konno 7-1 Omikamachi, Hitachi City, Ibaraki Prefecture No. 1 Inside Hitachi Research Laboratory, Hitachi, Ltd. (72) Inventor Yoshinao Mishima 4259 Nagatsuda, Midori-ku, Yokohama, Kanagawa Prefecture

Claims (12)

[Claims] 1. An alloy comprising Co as a main component and Al 5 to 10% by weight.
And containing C0.2~2.0%, Co-base heat-resistant alloy, wherein the E2 ₁ type structure intermetallic compound is out precipitated or crystallized. Wherein said E2 ₁ type structure intermetallic compound Co ₃ A
The Co-based heat-resistant alloy according to claim 1, wherein the basic composition is 1C. 3. The Co-based heat-resistant alloy according to claim 1, containing 0.0005 to 1% by weight of B. 4. The Co-based heat-resistant alloy according to claim 1, wherein said alloy is a columnar crystal or a single crystal. 5. A composition containing Co as a main component and Al 5 to 10% by weight.
1 (A: 5.0%, C: 0.7%), B (Al: 6.6%,
C (0.2%), C (9.1% Al, 1.6% C), D (Al
(7.5%, C2.0%) is a Co-based heat-resistant alloy, which is in a region surrounded by a line connecting points in sequence. 6. Co is a main component, and Al is 5 to 10% by weight.
And C 0.2 to 2.0%, and 1200 ° C. to 1300
After performing a solution treatment at a temperature of 900 ° C.,
A method for producing a Co-based heat-resistant alloy, comprising aging at a temperature of ° C. 7. Co is a main component, and Al is 5 to 10% by weight.
And containing C0.2~2.0%, gas turbine members, characterized by comprising the Co-based alloy intermetallic compounds E2 ₁ type structure is out precipitated or crystallized. 8. A composition containing Co as a main component and 5 to 10% by weight of Al.
And containing C0.2~2.0%, the gas turbine blade, comprising the Co-based alloy intermetallic compounds E2 ₁ type structure is out precipitated or crystallized. 9. Co is a main component, and Al is 5 to 10% by weight.
And containing C0.2~2.0%, the nozzle for a gas turbine, comprising the Co-based alloy intermetallic compounds E2 ₁ type structure is out precipitated or crystallized. 10. A composition comprising Co as a main component and Al 5 to 10 by weight.
% And containing C0.2～2.0%, the gas turbine combustor liner, characterized in that consisting of Co-based alloy intermetallic compounds E2 ₁ type structure is out precipitated or crystallized. 11. A composition comprising Co as a main component and Al 5 to 10 by weight.
% And containing C0.2～2.0%, the gas turbine combustor transition piece, characterized in that it consists of Co-based alloy intermetallic compounds E2 ₁ type structure is out precipitated or crystallized. 12. A power generating gas turbine comprising a compressor, a combustor, a turbine blade fixed to a turbine disk, and a turbine nozzle provided corresponding to the turbine blade, wherein the combustor liner, At least one of the transition piece, the turbine blade and the turbine nozzle has Co as a main component and has a weight of Al5
10% and containing C0.2～2.0%, gas turbine, comprising the Co-based alloy intermetallic compounds E2 ₁ type structure is out precipitated or crystallized.