JPH107477A - Protection coating film structure of ceramic part, gas turbine blade, ball bearing and inspection of coating film - Google Patents

Abstract

PROBLEM TO BE SOLVED: To suppress the frictional force to a low level and prevent the breakage or cracking of a ceramic part by applying an ion implantation treatment to a ceramic part to be brought into contact with a metallic part. SOLUTION: This gas turbine blade is composed of a metallic core 31 attached to a core part 29, a ceramic sleeve 32 encircling the outer side of the core metal 31 and a metallic blade cover 33 covering the core metal 31 and the sleeve 32. The sleeve 32 contacting with the blade cover 33 is covered with a coating layer 37 subjected to ion implantation treatment to modify the crystalline texture of the ceramic part into amorphous texture.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to, for example, a protective coating structure for a ceramic member in which a ceramic member in contact with a metal member is subjected to ion implantation, a gas turbine blade having the protective coating structure, and a protective coating structure having the protective coating structure. Ball bearings and coating inspection methods.

[0002]

2. Description of the Related Art For example, in a gas turbine plant, research and development for increasing the temperature of a combustion gas at the inlet of a gas turbine from 1000 ° C. to 1500 ° C. or higher in order to achieve high output and high thermal efficiency have been promoted. Gas turbine inlet combustion gas temperature 15
When the temperature is increased to 00 ° C. or higher, in a conventional gas turbine blade,
There is a limit in strength and heat resistance.

[0003] Conventional gas turbine blades use cobalt-based alloy steel or nickel-based alloy steel as a blade base material. However, if the temperature of the combustion gas at the inlet of the gas turbine is increased to 1500 ° C or more, the allowable stress of the material itself is increased. Beyond the value, safe driving is becoming difficult. For this reason, recently, there have been many proposals of cooling blades for cooling gas turbine blades using air or steam as an alternative to gas turbine blades using heat-resistant steel.

When air or steam is used as a cooling medium for gas turbine blades, the medium is obtained from an air compressor, a boiler, or the like. However, the consumption of the medium is extremely large. In consideration of heat settlement, it does not lead to improvement in thermal efficiency, and the combustion gas temperature at the gas turbine inlet 100
There is a problem that the temperature is lowered as compared with the gas turbine plant at 0 ° C.

[0005] Recently, studies have been made to improve the thermal efficiency of the entire power plant in combination with the thermal efficiency of the gas turbine itself. One of them is to improve heat resistance without using a cooling medium such as air or steam. Research and development of gas turbine blades using rich ceramics are in progress.

Gas turbine blades using ceramics
Ceramics themselves have the fragility of tensile load, shear load and impact force.In view of this point, recently the core of blade element is made of core metal using heat-resistant steel, and the outer blade element is sleeved. A technique in which the surroundings are formed of shaped ceramics and skillfully combined while taking advantage of both materials is disclosed in, for example,
Published in 140402.

[0007]

Problems to be Solved by the Invention
No. 2 discloses a gas turbine rotor blade shown in FIGS.
As shown in FIG. 4, the core part 2 of the blade element 1 is made of a core metal 3 made of a nickel-based alloy, the outside of which is surrounded by a sleeve 4 made of ceramics. The tip (top) wire A is formed by pressure molding a wing cover 6 made of a nickel-based alloy.

In the gas turbine blade, the centrifugal force generated during rotation is received by the blade cover 6, and the reaction force (compression force) is generated.
In order to prevent a tensile load and a shear load from acting on the sleeve 4. In addition, the metal core 3 is provided with a wing cover 6 from an implanted portion 7 implanted on a rotating shaft (not shown).
The cooling air is supplied to the cooling holes 5 formed toward the fins, and the cooling air cools the implanted part 7, the metal core 3, and the wing cover 6, thereby protecting the combustion gas against thermal shock. Is being planned.

However, in the gas turbine blade having such a structure, since the high-temperature heat of the combustion gas is received directly, each member undergoes thermal expansion due to thermal expansion. Among the thermal expansion of each member, the thermal expansion coefficient of the core metal 3 and the blade cover 6 made of the nickel-based alloy is 1.5 × 10 ⁻⁵ / ° C., whereas that of the ceramic sleeve 4 is 3. 5-4 × 10 ^-6 / ° C
And the difference is ４ to ５. For this reason, during the rotation, the sleeve 4 keeps away from the wing cover 6 and generates a frictional force at the contact portion 6a of the wing cover 6, and along with the generation of the frictional force, a tensile stress or a shearing stress is generated on the cross section thereof. Therefore, there is a risk of breakage and cracking.

As an example of solving such a problem,
For example, JP-A-6-307201 is disclosed. The outline of this publication is, as shown in FIGS. 15 and 16, a wing cover 6 covering the sleeve 4 and the core 3.
Of these, the leg 12 is pressed against the metal core 3, and the protruding pieces 9, 9 made of a flexible material are provided on the contact portion 8 of the sleeve 4, and the nickel base alloy sealing piece 10 is provided between the protruding pieces 9, 9. And a cutout 11 shown in FIG. 15 is formed in the cross section of the protruding pieces 9, 9.

In the gas turbine blade, the frictional force generated at the contact portion 8 between the sleeve 4 and the blade cover 6 during rotation is changed by the elastic deformation of the protruding pieces 9, 9 of the flexible material and the cut portion 11.
Thus, tensile stress and shearing force associated with the frictional force between the sleeve 4 and the wing cover 6 are prevented from increasing.

However, in the gas turbine rotor blade having this structure, the tensile stress and the shear stress caused by the frictional force generated in the contact portion 8 between the sleeve 4 and the metal core 3 are applied to the projecting pieces 9 of the flexible material. Because it is absorbed by elastic deformation, it can effectively absorb tensile stress and shear stress when the operation is short or when the number of start and stop cycles is small, but when the operation is long, it starts and stops. Is repeated frequently, the protruding pieces 9, 9 of the flexible material reach the plastic region due to thermal fatigue due to thermal shock over a long period of time and creep under high temperature and high stress, and the tensile stress accompanying the frictional force is increased. In some cases, the sleeve 4 could be damaged or cracked.

Further, as recently, when the blade height increases as the temperature of the combustion gas increases, the thermal stress of the sleeve 4 due to the difference in thermal expansion between the blade cover 6 and the blade cover 6 is shown by hatching in FIG. As described above, the high stress value is distributed over a wide area of the ventral side 12, the trailing edge 13 or the back side 14 of the blade element 1, and the thermal stress value allowed when the blade height is low is also reduced. As the height increases, the allowable thermal stress value exceeds the allowable thermal stress value, and it is necessary to take measures against breakage or cracking of the sleeve 4 caused by the high thermal stress value.

On the other hand, not only gas turbine rotor blades but also gas turbine stationary blades have ceramics applied to blade portions 15 (nozzles) and both ends are made of a cobalt-based alloy or a nickel-based alloy holder as shown in FIG. 16 and 16, a heat insulating material 17 and a heat insulating layer 18 (heat-resistant paint) are provided between the wing portion 15 and the holders 16 and 16 to cope with the high temperature of the combustion gas. A high thermal stress value due to a difference in thermal elongation between the holders 16 and 16 is generated in the wing 15, and the wing 15
It is necessary to take measures against breakage or cracks.

Further, in a bearing, for example, a ball bearing, a ceramic member and a metal member are used in combination. However, a frictional force acts on a contact portion between the ceramics member and the metal member. With the increase, a high tensile stress or the like is generated in the ceramic part, and there is a risk of breakage or cracking of the ceramic member, and an early solution is desired.

The present invention has been made in view of the above circumstances, and a frictional force is suppressed by performing ion implantation on a contact portion between a ceramic member and a metal member, so that the ceramic member may be damaged or cracked. It is an object of the present invention to provide a protective coating structure of a ceramic member in which the prevention of the occurrence of cracks is achieved.

Another object of the present invention is to form a coating layer by subjecting a ceramic member in contact with a metal member to ion implantation, and to reduce the occurrence of tensile stress and the like due to frictional force of the metal member by the coating layer. It is an object of the present invention to provide a gas turbine blade having a protective coating structure for protecting a ceramic member from damage or cracks while suppressing the damage.

Still another object of the present invention is to form a coating layer by subjecting a ceramic bearing body in contact with a metal ball to an ion implantation treatment, and the frictional force generated during rotation of the ball by the coating layer. An object of the present invention is to provide a ball bearing provided with a protective coating structure that protects the bearing body from breakage or cracks while suppressing the tensile stress associated therewith.

Another object of the present invention is to provide a method for inspecting the coating of a ceramic member in which a coating layer is formed by subjecting a ceramic member in contact with a metal member to ion implantation, and the thickness of the coating layer is easily measured. Is to do.

[0020]

SUMMARY OF THE INVENTION The protective coating structure for a ceramic member according to the present invention has the following objects.
As described in claim 1, the ceramic member is provided with a coating layer that has been subjected to ion implantation for modifying the crystal structure of the ceramic member to be amorphous.

In order to achieve the above object, in the protective coating structure for a ceramic member according to the present invention, the ion for modifying the crystal structure of the ceramic member to be amorphous is nitrogen ion. It is characterized by being.

In order to achieve the above object, the protective coating structure of a ceramic member according to the present invention has an ion implantation amount of 2 to modify the crystal structure of the ceramic member to be amorphous. × 10 ¹⁷ ions / cm ² or more.

According to a fourth aspect of the present invention, there is provided a gas turbine blade having a ceramic member protective coating structure according to the present invention, wherein a metal core is provided on a core portion of the gas turbine blade. On the other hand, in a gas turbine blade in which the outer surface of gold is surrounded by a ceramic sleeve, and the metal core and the sleeve are covered with a metal blade cover, the crystal structure of the ceramic member is not changed by the sleeve in contact with the blade cover. It is characterized in that a coating layer subjected to an ion implantation treatment for reforming into a crystalline state is formed.

According to a fifth aspect of the present invention, there is provided a gas turbine blade having a protective coating structure for a ceramic member according to the present invention. In a gas turbine blade having a heat insulating material mounted between the blade portion and the holder, a coating layer was formed on the blade portion by performing an ion implantation process for modifying the crystal structure of the ceramic member to be amorphous. It is characterized by the following.

According to the present invention, there is provided a ball bearing provided with a protective coating structure for a ceramic member according to the present invention. In a ball bearing provided with a flexible metal ball, a film layer on which an ion implantation process for modifying a crystal structure of a ceramic member to be amorphous is formed on the bearing body.

According to a seventh aspect of the present invention, there is provided a method for inspecting a coating film on a ceramic member, wherein the ion implantation treatment for modifying the crystal structure of the ceramic member to be amorphous is performed. The indenter of the hardness tester is pressed against the formed coating layer to check whether the depth of the indenter is a predetermined thickness of the coating layer.

[0027]

DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described below with reference to the accompanying drawings.

FIG. 1 is a schematic partial view showing an embodiment in which the present invention is applied to a gas turbine blade. Prior to the description of the embodiment of the gas turbine rotor blade, a typical example of a gas turbine plant will be described with reference to FIG.

The gas turbine plant 19 has an air compressor 21 coaxially with the gas turbine 20. The gas turbine plant 19 guides the compressed air generated by driving the air compressor 21 to the gas turbine combustor 22, and fuels the fuel in a combustion chamber 24 formed in a combustor liner 23 of the gas turbine combustor 22. The combustion gas is guided to the gas turbine 20 via the transition piece 25, and the gas turbine 20 is driven to perform work, and the generator (not shown) connected to the gas turbine 20 is rotationally driven. It has become.

The gas turbine 20 has a plurality of rows 28 along the axial direction.
6. Gas turbine blades 27.

As shown in FIG. 1, the gas turbine rotor blade 27 is formed of a nickel-based alloy core bar 31 having a cooling hole 30 in a core portion 29, and a ceramic sleeve 32 is provided outside the core bar 31. A blade element surrounded by is formed. A wing cover 33 having a cooling hole 30 is covered on the tip (top) of the cored bar 31 and the sleeve 32.
Of the wing cover 33 and the sleeve 32, and a coating layer 37 obtained by ion-implanting the sleeve 32 between the leg 35 and the sleeve 32.
Is provided. The leg 35 of the wing cover 33 is provided with a positioning piece 36 for holding the sleeve 32 at an appropriate position against fluctuations such as vibration.

The coating layer 37 coated on the ceramic sleeve 32 is obtained by ionizing atoms, for example, nitrogen evaporated by a vacuum evaporation method or an ion plating method in plasma to deposit a film on the surface of the sleeve 32. is there.

In depositing a film on the sleeve 32, nitrogen ions are modified in order to modify the crystal structure of the ceramic base material to make it amorphous (amorphous layer) and to make its hardness 60-70% of that of the ceramic base material. If the injection amount is 2 × 10 ¹⁷ ions / cm ² or more, and the friction coefficient of the ceramic member not implanted with nitrogen ions is 1, the nitrogen ions are implanted until the friction coefficient decreases to 0.2. You.

When the amount of nitrogen ions implanted into the ceramic member is 2 × 10 ¹⁷ ions / cm ² and the amount of implantation is the reference 1, the coefficient of friction of the ceramic member becomes 0.2 as shown in FIG. Experiments confirmed that the coefficient of friction was significantly lower than that of the ceramic member to which nitrogen ions had not been implanted.

As described above, if nitrogen ions for modifying the crystal structure of the ceramic member are implanted and the coefficient of friction is suppressed to be low by the sliding action of the coating on the surface of the base material, a high load acts on the ceramic member. However, the ceramic member can be protected from breakage or cracking even if tensile stress or the like is generated with a high load. However, in order to sufficiently impart a slipping effect to the coating for modifying the crystal structure of the ceramic member, the effect is influenced by the amount of nitrogen ions injected and the modification depth of the base material. FIG. 4 schematically illustrates the relationship between the amount of implanted nitrogen ions and the change in the crystal structure of the ceramic member. If the amount of implanted nitrogen ions is less than 2 × 10 ¹⁷ ions / cm ² , the region (I) As shown in (1), there is no change in the crystal structure of the ceramic member. However, when the input amount of nitrogen ions is 2 × 10 ¹⁷ ions / cm ² or more, as shown in a region (II), the ceramic member changes to an amorphous part at a surface depth of 0.5 μm, When the injection amount is increased, as shown in a region (III), the surface of the ceramic member changes to amorphous. As described above, in order to make the ceramic member amorphous and keep the friction coefficient low, it is desirable that the input amount of nitrogen ions be 2 × 10 ¹⁷ ions / cm ² or more.

The conditions for implanting nitrogen ions into the ceramic member to modify its crystal structure to amorphous are as follows:
Ion energy of 400 KeV, temperature of 185 to 210 ° C,
The degree of vacuum is 10 ^-6 Torr.

Next, the operation of the gas turbine blade will be described.

When the gas turbine plant is stopped, no centrifugal force is generated in the gas turbine rotor blades.
2, the contact load W (pressing force) acting on the leg 35 of the wing cover 33 and the tangential force (frictional force) associated with the relative movement of the wing cover 33 with the leg 35 are zero, as shown in FIG. Yes, only the weight of the leg 35 of the wing cover 33 is received.

When the gas turbine plant starts the start-up operation and the gas turbine rotor blades rotate and receive the high temperature heat of the combustion gas, the sleeve 32 and the blade cover 33 receive the centrifugal force and the thermal expansion due to the thermal expansion. coming out. In this case, the sleeve 32 stays away from the wing cover 33 subjected to the centrifugal force, and a contact load W is generated on the leg 35.
Further, the sleeve 32 is thermally expanded due to thermal expansion.
A tangential force F is generated due to the relative movement with the leg 35. The tangential force F is proportional to the contact load W as shown in FIG. The maximum value of the contact load W corresponds to a centrifugal load generated when the sleeve 32 receives a centrifugal force.

In the present embodiment, as shown in FIG. 5, a coating layer 35 is provided which has been subjected to an ion implantation process using nitrogen ions to modify the crystal structure of the ceramic member of the sleeve 32 to make it amorphous. During the rotation of the gas turbine blade due to the sliding action of the coating layer 35, even if the contact load W acting on the leg 35 of the blade cover 33 from the sleeve 32 increases along the straight line R in FIG. In addition, the increase of the tangential force and zero are repeated in a meandering manner, and the maximum increase is suppressed to a range of 0.2 or less.

Therefore, in the present embodiment, even if the contact load W acting on the leg 35 from the sleeve 32 due to the centrifugal load and the thermal expansion increases, the tangential force F is suppressed by the coating layer 35. Sleeve 32 with force
The sleeve 32 can be protected from breakage or cracks caused by the tensile stress and the like, because the tensile stress and the shear stress generated in the sleeve 32 can be kept low.

FIG. 7 is a schematic view showing a second embodiment in which the present invention is applied to a gas turbine stationary blade.

The gas turbine stationary blade 38 holds both ends of a ceramic blade 38 a formed in a bay-shaped curved surface with holders 39, 39 made of a cobalt-based alloy or a nickel-based alloy, and the blade 38 a and the holder 39. , 39 insulation 40
Further, a heat-insulating layer 41 (heat-resistant paint) is provided, and a coating layer 42 that has been subjected to a nitrogen ion implantation process is provided between the wing portion 38 a and the heat insulating material 40.

In this embodiment, the wings 38 made of ceramics are used.
a, the crystal structure of the ceramic member is modified to be amorphous and the coefficient of friction is kept low. Therefore, a tangential force due to thermal expansion acts between the heat insulating material 40 and the holder 39. Also, the tangential force can be suppressed low due to the sliding of the coating layer 42.

Therefore, in this embodiment, the wings 38a
The tangential force generated in the wing portion 38a can be suppressed low by the coating layer 42, so that the tensile stress and shear stress generated in the wing portion 38a due to the tangential force can be suppressed low.
a can be prevented from being damaged or cracked.

FIG. 8 is a schematic view showing a third embodiment in which the present invention is applied to a ceramic ball bearing.

The ball bearing 43 includes a bearing body 44 made of ceramics and a rotating cylinder 45 made of metal. A ball 46 is provided between the bearing body 44 and the rotating cylinder 45 by a retainer or the like. The ball 46 is rotated by the rotational force of a rotating shaft (not shown) fitted.

In this embodiment, the bearing body 44 is provided with a coating layer 47 which has been subjected to a nitrogen ion implantation treatment, and the coating layer 47 changes the crystal structure of the bearing body 44 into an amorphous structure. The resulting tangential force (frictional force) is kept low by the sliding action of the coating layer 47.

Therefore, in this embodiment, the ball 46
Since the tangential force generated due to the rotation of the bearing body 44 is suppressed low by the sliding action of the coating layer 47, the tensile stress or the like acting on the bearing body 44 is reduced, and the damage or crack of the bearing body 44 can be prevented. .

By the way, when a ceramic member is subjected to a nitrogen ion implantation treatment to modify the crystal structure of its base material to be amorphous, the modified layer has an appropriate depth or as a result of long-term use, It is necessary to constantly check the amount of wear.

The presence of an amorphous substance can be usually observed with an electron microscope. However, if the number of observations is large, it is difficult to observe the number of individual observations with an electron microscope.

Therefore, a hardness tester is used in the coating inspection method according to the present invention as a method for confirming the presence or absence of an amorphous material in a ceramic member.

When confirming the presence or absence of the amorphous material in the ceramic member, a load of 1 g is applied to the indenter of the hardness tester. A load is applied to the indenter until a predetermined time T, and thereafter, the load is maintained at a constant load. As shown in FIG. 9, the depth of the indenter to which the load was applied was the characteristic A of the ceramic member into which nitrogen ions had not been implanted, and the nitrogen ions 1 × 10 ¹⁷
When the ion / cm ² characteristic B of the ceramic member when injected, a characteristic C of the ceramic member when implanting nitrogen ions 2 × 10 ¹⁷ ions / cm ² or more, characteristic C is most deeply appear.

On the other hand, the hardness of the ceramic member is as shown in FIG.
As shown in FIG.
The hardness of the ceramic member E when nitrogen ions 1 × 10 ¹⁷ ions / cm ² are implanted and the hardness of the ceramic portion F when nitrogen ions 2 × 10 ¹⁷ ions / cm ² or more are implanted are defined as the hardness 1 as a standard. In each case, the ceramic member F is 30% lower than the ceramic member D.

As described above, in the coating inspection method according to the present invention, the presence / absence of the amorphousness of the ceramic member can be easily confirmed by the indenter of the hardness meter.

The method for confirming the wear of the amorphous layer of the ceramic member can be visually confirmed.

Generally, the correlation between the friction coefficient and the amount of wear of the amorphous layer and the repetitive load applied to the amorphous layer is shown in FIG.
As shown in FIG. 1, it is known that when the number of repeated loads exceeds a certain value, both the friction coefficient and the wear amount increase rapidly.

As described above, when the number of times of repeated load exceeds a certain value, the amount of abrasion due to the aging of the amorphous material is shown in FIG.
As shown in FIG. 8, the value increases rapidly, so that it can be easily confirmed visually.

[0059]

As described above, the protective coating structure for a ceramic member according to the present invention is provided with a coating layer which has been subjected to an ion implantation process for modifying the crystal structure of the ceramic member to be amorphous, and Since the tensile stress and the shear stress generated due to the tangential force to the metal member due to the sliding action are kept low, breakage and cracking of the ceramic member can be prevented.

Further, in the gas turbine blade having the ceramic member protective coating structure according to the present invention, both the moving blade and the stationary blade are partially formed by a ceramic member, and the ceramic member is subjected to nitrogen ion implantation. Since a coating layer to be modified to be amorphous is provided and the tensile stress or the like generated in the ceramic member is suppressed by this coating layer, breakage and cracking of the ceramic member can be prevented.

Further, in the ball bearing provided with the protective coating structure of the ceramic member according to the present invention, since the bearing body made of ceramics is provided with a coating layer which is subjected to a nitrogen ion implantation treatment to be modified to be amorphous, Even if the frictional force generated during the rotation of the ball acts on the bearing body, the frictional force can be reduced by the coating layer, and the frictional force can be reduced, resulting in damage and cracking of the ceramic bearing body. Can be prevented.

In the method for inspecting the coating of a ceramic member according to the present invention, the presence or absence of the amorphous layer, which has been modified by subjecting the ceramic member to nitrogen ion implantation, is checked by the depth of an indenter of a hardness meter. Therefore, the presence or absence of the amorphous layer can be easily confirmed.

[Brief description of the drawings]

FIG. 1 is a partial schematic view of a first embodiment in which a protective coating structure of a ceramic member according to the present invention is applied to a gas turbine blade.

FIG. 2 is a schematic diagram of a gas turbine plant incorporating the gas turbine blade shown in FIG.

FIG. 3 shows a ceramic member subjected to an ion implantation process;
4 is a graph showing the relationship between the ion implantation amount ratio and the friction coefficient.

FIG. 4 is a schematic view for explaining that a ceramic member has been modified to be amorphous by performing an ion implantation process.

FIG. 5 is a partial schematic view of a gas turbine blade explaining that a tangential force (frictional force) is generated between a ceramic member and a metal member.

FIG. 6 is a graph showing a relationship between a tangential force and a contact load.

FIG. 7 is a schematic view of a second embodiment in which the protective coating structure for a ceramic member according to the present invention is applied to a gas turbine blade.

FIG. 8 is a schematic perspective view of a third embodiment in which the protective coating structure for a ceramic member according to the present invention is applied to a ball bearing.

FIG. 9 is a view for explaining that a coating layer is formed by performing an ion implantation process on a ceramic member and the thickness of the coating layer is detected by a hardness meter.

FIG. 10 is a view for explaining a hardness of the coating layer by forming a coating layer by performing an ion implantation process on the ceramic member.

FIG. 11 is a graph showing the relationship between the coefficient of friction and the amount of wear and the number of repetitive loads of a coating layer formed by performing ion implantation on a ceramic member.

FIG. 12 is a view for explaining a wear amount of the coating layer by forming a coating layer by performing an ion implantation process on a ceramic member.

FIG. 13 is a schematic view showing a conventional gas turbine blade.

FIG. 14 is a sectional view taken in the direction of arrows XX in FIG. 13;

FIG. 15 is a partial schematic view of a conventional gas turbine blade.

16 is a sectional view taken in the direction of arrows YY in FIG. 15;

FIG. 17 is a diagram showing a distribution of stress acting on a conventional gas turbine blade.

FIG. 18 is a schematic view showing a conventional gas turbine stationary blade.

[Explanation of symbols]

 REFERENCE SIGNS LIST 1 blade element 2 core part 3 core metal 4 sleeve 5 cooling hole 6 blade cover 7 stud part 8 contact part 9 protruding piece 10 seal piece 11 notch 12 ventral side 13 trailing edge 14 back side 15 wing 16 holder 17 heat insulating material REFERENCE SIGNS LIST 18 heat shielding layer 19 gas turbine plant 20 gas turbine 21 air compressor 22 gas turbine combustor 23 combustor liner 24 combustion chamber 25 transition piece 26 gas turbine stationary blade 27 gas turbine rotor blade 28 paragraph 29 core part 30 cooling hole 31 core Gold 32 Sleeve 33 Blade cover 34 Leg 35 Leg 36 Positioning piece 37 Coating layer 38 Gas turbine stationary blade 38a Wing 39 Holder 40 Insulation material 41 Heat shielding layer 42 Coating layer 43 Ball bearing 44 Bearing body 45 Rotating cylinder 46 Ball 47 Coating layer

──────────────────────────────────────────────────続 き Continuation of the front page (51) Int.Cl. ⁶ Identification code Agency reference number FI Technical display location F01D 9/02 101 F01D 9/02 101 F02C 7/00 F02C 7/00 C

Claims (7)

[Claims] 1. A protective coating structure for a ceramic member, wherein a coating layer subjected to an ion implantation process for modifying the crystal structure of the ceramic member to amorphous is formed on the ceramic member. 2. The protective coating structure for a ceramic member according to claim 1, wherein the ions for modifying the crystal structure of the ceramic member to be amorphous are nitrogen ions. 3. The protection of a ceramic member according to claim 1, wherein the ion implantation amount for modifying the crystal structure of the ceramic member to be amorphous is 2 × 10 ¹⁷ ions / cm ² or more. Coating structure. 4. A gas turbine blade in which a metal core is provided in a core portion and the outside of the core is surrounded by a ceramic sleeve, and a metal blade cover is covered on the core and the sleeve. A gas turbine having a protective coating structure for a ceramic member, wherein a coating layer subjected to an ion implantation process for modifying the crystal structure of the ceramic member to be amorphous is formed on a sleeve with which the blade cover contacts. Wings. 5. A gas turbine blade in which both ends of a ceramic wing are held by metal holders and a heat insulating material is mounted between the wing and the holder, the wing has a non-crystalline structure of a ceramic member. A gas turbine blade provided with a protective coating structure for a ceramic member, wherein a coating layer subjected to an ion implantation treatment for modifying the crystallinity is formed. 6. A ball bearing having a rotatable metal ball between a ceramic bearing main body and a rotary cylinder, wherein an ion implantation process for modifying the crystal structure of the ceramic member into the bearing main body to be amorphous. A ball bearing provided with a protective coating structure for a ceramic member, wherein a coating layer provided with a coating is formed. 7. An indenter of a hardness meter is pressed against a coating layer which has been subjected to an ion implantation process for modifying a crystal structure of a ceramic member to be amorphous, and whether the depth of the indenter is a predetermined thickness of the coating layer. Inspection method for ceramic members to confirm