JPH04203301A - turbine stationary blade - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a turbine stationary blade that forms a high-temperature combustion gas flow path in a gas turbine.

[Conventional technology]

Gas turbine stationary blades are formed from a row of blades in which a large number of blades are arranged annularly within a cylindrical casing.

Fig. 2 is an external view of a part of the stator blade row as seen from the upstream side of the combustion gas flow, and the outer shroud 5 is fitted and fixed to a retainer ring (not shown) fixed in the casing of the gas turbine device. The inner shroud 4 is fitted and fixed to a server 1 ring (not shown), and the inner and outer shrouds 4
, 5 are arranged with airfoil sections 1 having an airfoil cross-sectional shape, and are arranged at equal intervals on a circumference with a central hair at the axial center O. Combustion gas passes through the flow path between the blades and is blown at high speed onto the rotor blades installed on the wake side. Ceramic stationary vanes use ceramic as the member forming the combustion gas flow path, and utilize its excellent heat resistance to increase the combustion gas temperature and reduce the amount of cooling air, thereby improving the thermal efficiency of the gas turbine. Structural ceramics used for this purpose have advantages such as excellent heat resistance, but because they are brittle materials, their deformability is extremely low, and there are many restrictions on structural strength compared to metal materials. Ru. To solve these problems, Japanese Patent Application Laid-Open No. 61-899
No. 04 proposes a composite ceramic stator vane in which the frame is made of metal parts and the parts exposed to combustion gas are made of ceramic.

[Problem to be solved by the invention]

As described above, the ceramic forming the ceramic stator vane is a brittle material, so there is a problem in that it is easily damaged by impact force. Ceramic components in ceramic stator blades are subjected to external forces such as pressure, and if the holding method is inappropriate, the ceramic components may be displaced in the blade height direction, in-plane direction, or rotationally, causing damage to other adjacent components. There is a high risk of collision and damage. Also, the displacement of the airfoil reduces the fluid performance of the stator vane. Therefore, a holding structure that reliably restrains the displacement of ceramic components is essential to ensure the reliability of ceramic stator blades.

As shown in FIG. 2, the stator vane row has a large number of stator blades arranged in an annular manner, and gaps are provided between each blade corresponding to the amount of thermal expansion of the blade in the circumferential direction that occurs during operation.

Although a thin plate is installed in the gap to prevent cooling air from leaking, it is not possible to completely prevent leakage, which is a factor in reducing the efficiency of the gas turbine. That is, reducing the gap is effective in improving the efficiency of the gas turbine.

[Means to solve the problem]

In order to achieve the above object, the present invention includes an inner shroud and an outer shroud fixed in a casing, a ceramic shell disposed between the two shrouds and forming a wing section, and a combustion gas flow path together with the ceramic shell. In a turbine stator blade including an inner ceramic sidewall and an outer ceramic sidewall, the ceramic shell and the ceramic sidewall are connected to a metal shroud via a heat insulating material in a blade height direction and an in-plane direction perpendicular to the direction. It is held fixed in the
It is characterized by being formed into a connecting structure that prevents rotational displacement.

In the turbine stator blade, either one of the inner and outer ceramic side walls forming the inner and outer cylindrical wall surfaces of the combustion gas flow path and the ceramic shell installed between the ceramic side walls is insulated. It is preferable that the shroud is held by a metal shroud through a material, and the one held member holds the other member. Further, it is preferable that the ceramic shell and the ceramic sidewall are each held by a metal shroud via a heat insulating material. Further, the structure for preventing rotational displacement is preferably formed by a metal blade core passing through the inside of the ceramic shell and connecting the inner and outer shrouds. In addition, the ceramic sidewall is divided between blades or adjacent blades in the circumferential direction of the stator vane cascade by one blade, every several blades, or a combination thereof, and in the axial direction of the vane cascade, either integrally or between each blade. It is best to have it divided into several pieces. Further, at least one of the metal inner and outer shrouds is preferably formed integrally with a plurality of stator blades. In addition, it is preferable that a buffer member is provided to adjust the difference in thermal deformation between the metal wing core and the ceramic member. Here, the buffer member may have a structure with a spring structure or an inorganic material with high tensile deformability. Examples include a structure in which the material is used as a part of the heat insulating material, or a structure in which both are used. Further, it is preferable that the ceramic sidewall is fixedly held in the blade height direction by a ceramic shell having a flange-like projection formed at the end of the blade. Further, it is preferable that a protrusion provided at the end of the ceramic shell prevents displacement and rotational displacement of the shell in an in-plane direction perpendicular to the blade height direction.

Further, the present invention provides a gas turbine apparatus including a combustor, stator blades, and rotor blades, in which at least the first stage stator blade is formed of any one of the turbine stator blades described above.

[Effect]

The ceramic shell and ceramic sidewall, which are ceramic parts, are held in the height direction of the blade and in the plane perpendicular to this direction by a metal shroud or metal blade core, and by inserting a heat insulating material between them, high temperature It is possible to insulate between the ceramic part and the metal part, reduce the temperature gradient within the ceramic part, and facilitate cooling of the metal part. In other words, it is possible to reduce thermal stress and reduce cooling air. When the heat insulating material has high elastic deformability, it is possible to adjust the difference in the amount of thermal deformation between the metal component and the ceramic component. On the other hand, ceramic parts are subject to external forces such as pressure,
The ceramic parts can be fixed by restraining displacement including rotation by increasing the area of the holding part, holding the ceramic shell and ceramic sidewall individually, and holding the shroud and the blade core in two places. It is possible to prevent the airfoil from colliding with other parts and being damaged, and at the same time, it is possible to prevent the fluid performance from deteriorating due to a change in the shape of the gas flow path formed in the wing. Furthermore, since the value of stress generated in the holding portion can be suppressed to a low value, stable displacement can be restrained without causing damage to the ceramic parts or the heat insulating material.

Note that if the difference in the amount of thermal deformation in the blade height direction between the ceramic component and the metal component is adjusted using a spring structure, more complete adjustment will be possible.

In addition, a flat ceramic side wall with a hole in the center for combination with a ceramic shell has little margin in shape and dimension, which often causes problems in terms of manufacturing or strength reliability. By changing the dividing structure and holding structure, the above problems can be solved, and the degree of freedom in the assembly structure of the blade row can be increased.

If a metal shroud is manufactured in one piece in a shape that corresponds to several stator blades, the number of gaps between the blades of the stator blade row can be reduced, reducing the amount of cooling air leakage and improving the efficiency of the gas turbine. can be expected. At the same time, when assembling the blade row to the gas turbine main body, several stationary blades can be attached at once, improving work efficiency.

Furthermore, among the ceramic components, the ceramic shell is exposed to the highest temperature combustion gas. In addition, in the event of an emergency such as a gas turbine accident, a sudden thermal shock may occur due to a fuel cutoff. Therefore, materials that have a high heat resistance and are resistant to thermal shock are suitable for use in the ceramic shell. On the other hand, although ceramic sidewalls have a relatively low temperature, they are used in a complicated environment and have a complicated shape, so their strength and
lO- A material with excellent toughness is suitable. The reliability of the ceramic stator blade can be improved by manufacturing each component with ceramics having the above characteristics.

By applying the above-described ceramic stator blade to at least the first stage stator blade of a gas turbine section consisting of a combustor, stator blades, and rotor blades, it is possible to provide a gas turbine device with excellent efficiency and reliability.

〔Example〕

An embodiment of the present invention will be described below with reference to FIGS. 1 and 3. 3 is a cross-sectional view taken along line A-A in FIG. 1 or 2, and FIG. 1 is a schematic vertical cross-sectional view taken along line B-B in FIG. The basic structure of one ceramic stator blade that is the outer peripheral side of the ceramic stator blade and forms the gas turbine stator blade row is shown. In FIG. 1, the outer peripheral part of the blade exposed to combustion gas is formed by a ceramic shell 1 having an airfoil-shaped cross section, and the inside thereof is composed of a heat insulating material 8 and a metal blade core 6. (See Figure 3). The appearance of the shell 1 is shown in FIG. Both ends of this shell 1 are assembled by fitting into recesses provided on corresponding surfaces of inner and outer ceramic side walls 2 and 3 to match the shape of the end faces of the shell 1, and the inner and outer side walls 2 and 3 are fitted with recesses provided in corresponding surfaces to match the shape of the end faces of the shell 1.

The outer side walls 2 and 3 are connected to the metal inner wall through the heat insulating material 7.
They are fitted into recesses provided in the outer shrouds 4, 5 to match the outer shapes of the inner and outer sidewalls 2, 3 (see FIG. 3). Further, the metal wing core 6, which is manufactured integrally with the outer shroud 5, is attached to the inner shroud 4 after each part is assembled.
and are joined by welding 9.

The thrust force that shell 1 receives from the combustion gas is
is supported by the inner and outer shrouds 4.5 through the inner and outer sidewalls 2.3 and the insulation material 7, and the pressure that the inner and outer sidewalls 2.3 receive in the blade height direction is due to the insulation material. It is supported by the inner and outer shrouds 4 and 5 via the inner and outer shrouds 7. Applicable, within.

The outer shrouds 4, 5 are secured to the gas turbine body in a manner similar to conventional metal shrouds. At this time, compressive stress is mainly generated in each holding part, but considering that the fracture strength of ceramics against compressive stress is generally several times greater than that of tensile stress, there is a risk that each holding part will break. is low, and therefore the displacement of the shell 1 can be stably restrained.

Note that the structure in which the inner and outer sidewalls 2 and 3 are held by the inner and outer shirarou 4 and 5 is not limited to the entire circumference of the sidewalls as shown in FIG. 3, but is held on two opposing sides. structure is also possible.

Furthermore, since the present ceramic stator vane has a structure in which a ceramic component is held by a metal component, the amount of thermal deformation between the two components due to temperature changes during assembly and operation differs. - As an example, the difference Δ in the amount of thermal deformation in the blade height direction between the metal blade core 6 and the ceramic shell 1 of a ceramic stator blade with a blade height of 100 mm is estimated. Temperature T during assembly. = 20℃, operating temperature is blade core T1 = 600℃, shell T2 = 13oO℃, root, △
= (Thermal elongation of the wing core 6) - (Thermal elongation of the shell 1) = (ax
・ (TI To) ax・ (T2 To)
) L? 0.25mm Here, α, = coefficient of linear expansion of blade core - 12 x 10-'/”
C1α2=linear expansion coefficient of shell-3,5x I Cr'
/'C,L-blade height is 100+m. That is, during the above operation, the amount of thermal elongation of the blade core 6 is larger than that of the shell 1 by about 0.3 m. In this example.

Part or all of the heat insulating material 7 has excellent elastic deformability.

Further, it is made of a cloth woven from a heat-resistant inorganic material, such as ceramic fiber (alumina fiber, SiC fiber, etc.), and gives the heat insulating material 7 a predeformation that exceeds the above-mentioned thermal deformation difference Δ. .

Therefore, there are no gaps between parts during operation, and
Stable holding is possible. The connection structure between the blade core 6 and the shroud is not limited to this embodiment, and the blade core 6 and the inner and outer shrouds 4 and 5 may be manufactured separately and connected by welding, or the blade core 6 and the inner shroud 4 may be connected by welding. A structure may be adopted in which the outer shroud 5 is manufactured integrally and connected to the outer shroud 5 by welding, or a structure in which the outer shroud 5 is connected by screw fastening.

Cooling of the inner and outer shrouds 4, 5 and the blade core 6, which are metal parts, will be explained. As shown by the arrow a in FIG. The blade core 6 is cooled through a flow path 11 provided inside, and the blade core 6 is guided to the outer periphery of the blade core from a horizontal hole 1o provided approximately at the center in the blade height direction. A flow passage 12 is provided on the outer periphery of the blade core 6 in the blade height direction over the entire circumference, and the cooling air passes through the flow passage 12 and further cools the blade core 6 before passing through the inner and outer shrouds 4°. It passes through a flow path 13 provided in 5 and is discharged to the outside.

On the other hand, the shell 1 and sidewalls 2 and 3, which are exposed to combustion gas, are made of ceramics and have excellent heat resistance.
No cooling is required. Further, since the amount of heat flowing into the blade core 6 and shrouds 4 and 5, which are metal parts, is blocked by the heat insulating material 7 or 8 having excellent heat insulation properties, the amount of heat is sufficiently smaller than that of conventional metal stationary blades. Therefore, it is possible to improve the temperature of the combustion gas, and the amount of air required to cool the metal parts can be reduced to about 1/10 compared to the conventional method. Namely.

This ceramic stator vane can contribute to improving the efficiency of gas turbines by increasing the combustion gas temperature and reducing the amount of cooling air.

In addition, since it is possible to keep the temperature of metal parts low,
The material of the metal parts may be a popular material with relatively low heat resistance, such as stainless steel, which is easier to manufacture than conventional blades made of super heat-resistant steel, and can reduce manufacturing costs. I can figure it out.

In addition, in FIG. 1, there is only one flow path 11 provided inside the blade core 6, but by providing a plurality of channels as shown in FIG. It is also possible to adjust the flow rate distribution. In addition, cooling air can be taken in not only from the outer circumference of the outer shroud 5 as shown in FIG. 1, but also by providing a flow passage 11 inside the blade core 6 from the inner circumference side of the inner shroud 4. The internal cooling of the inner circumferential side of the blade core 6 can be enhanced, and the same effects as described above can be obtained, and furthermore, the inner circumferential wall of the inner shroud 4 can be cooled. Furthermore, cooling air passages may be additionally provided inside the inner and outer shrouds 4 and 5, thereby increasing the cooling of the inner and outer shrouds 4 and 5. Further, the discharge passage 13 is not limited to the inside of the inner and outer shrouds 4 and 5, but may be inside the heat insulating material 7.

115= The shell 1 and sidewalls 2 and 3, which are directly exposed to high-temperature combustion gas, are made of structural ceramics with excellent heat resistance. Shell 1 is the part that reaches the highest temperature and is also subject to severe thermal shock, so a material with excellent heat resistance and thermal shock resistance at high temperatures is suitable, such as silicon carbide, especially pressureless sintered silicon carbide when considering a complex shape. Plain is suitable. In addition, depending on the usage conditions, sialon, silicon nitride, or ceramic composites, such as ceramic fiber reinforced ceramics (SiCm fiber /SiC composite material, etc.). The sidewall 2゜3 may be made of any of the above materials, but since the temperature conditions are milder than that of the shell 1, it may be made of a material with excellent strength and toughness, even if its heat resistance is slightly inferior to that of the material of the shell 1. For example, the above Sialon,
If silicon nitride or the like is used, strength reliability can be improved.

The heat insulating material 8 needs to have heat resistance and heat insulation properties, as well as being able to fill the narrow gap between the shell 1 and the blade core 6. They are made from inorganic materials or fluid and hardenable ceramic fillers. When a breathable material such as a ceramic fiber fabric is used, the cooling air flowing on the outer surface of the blade core 6 also flows inside the heat insulating material 8, thereby improving the cooling effect. In addition, by using a hardening filler, the thrust force applied to the shell 1 can be shared and held by the blade core 6, which further stabilizes the restraint against displacement and improves the reliability of the ceramic stator blade. I can figure it out. Furthermore, by providing the above-mentioned air-permeable material on the outer periphery of the blade core 6 and creating a space between the air-permeable material and the shell 1 with a curable filler, a ceramic vane having the above-mentioned characteristics can be obtained.

Other embodiments of the displacement restraint structure are shown in FIGS. 5 to 9.

Each figure is a schematic vertical cross-sectional view showing the basic structure near the outer shroud 5 in FIG. 1, and the inner shroud 4 and its vicinity are omitted. FIG. 5 shows that the outer shroud 5 is fitted into the shell 1 through an airfoil-shaped through hole provided in the outer sidewall 3, and is connected to the outer shroud 5 via a flange-shaped projection 15 provided on the outer periphery of the end of the shell 1 and a heat insulating material 7. This is to hold the blade in the height direction.

The sidewall 3 only needs to be provided with a through hole, which is easier to manufacture than the concave groove shown in FIG. 1, and has excellent reliability because it does not have a concave corner where stress can be concentrated.

FIG. 6 shows another example of the holding structure for the shell 1 and the outer sidewall 3. The end portion of the shell 1 is held in a wing-shaped recess provided in an outer shroud 5 via a heat insulating material 7, and displacement is restrained by the shroud 5 in both the wing height direction and the right angle direction. The outer sidewall 3 is fitted into the shell 1, and is held in the blade height direction in the same manner as in FIG. 5, but is held in the in-plane direction by the shell 1. According to this structure, the thrust force received by the shell 1 is directly supported by the outer shroud 5.

Compared to FIG. 5, the external force applied to the outer sidewall 3 is reduced. In addition, the outer side wall 3 is made of ceramics.
By covering the surface of the combustion gas flow path of the metal outer shroud 5, damage to the shroud 5 caused by exposure to combustion gas can be avoided.

FIG. 7 shows another retaining structure of the outer sidewall 3,
The outer periphery of the sidewall 3 is held from the inside by an outer shroud 5 via a heat insulating material 7. According to this structure, compared to FIG. 6, by covering the side surface of the outer shroud 5 with the ceramic outer side wall 3, the side surface of the shroud 5 can be protected from combustion gas flowing into the gap.

Other retaining structures for the outer sidewall 3 are shown in FIGS. 8 and 9. That is, the sidewall 3 is held by the outer shroud 5 via the heat insulating material 7 in the blade height direction and in-plane direction. A wing-shaped through hole is provided in the side wall 3, and the shell 1 is fitted into the through hole.

FIG. 8 shows a case in which the shell 1 is held in the wing surface direction by the sidewall 3, and FIG. 9 shows a case in which it is held by the outer shroud 5 via a heat insulating material 7. Although FIGS. 8 and 9 show an example in which a part of the outer shroud 5 is assembled by welding, the welding position is not limited to the illustrated location, but may be any other location where assembly is possible.

Another example of the holding structure for the shell 1 is shown in FIGS. 10 and 11. As shown in FIG. 10, a cylindrical projection 16 is provided at the end of the shell 1, and the projection 16 is held by a recess provided in the outer shroud 5 via a heat insulating material 7 (FIG. 11).
. The shape of the protrusion 16 is not limited to a cylindrical shape, but may be any shape, and can be selected depending on the magnitude of the force that the shell 1 receives and the ease of processing. The heat insulating material 7 around the protrusion 16 is made of a different material or by a construction method different from that of the heat insulating material 7 in other parts, for example, a recess provided in the outer shroud 5 corresponding to the protrusion 16 is provided with a hole communicating with the outer circumferential side of the shroud 5. (not shown), the communication hole may be filled with a curable filler having fluidity, and the heat insulating material 7 in other parts may be a heat insulating material having high elastic deformability. Further, as shown in FIG. 12, even if a recess is provided at the end of the shell 1 and the connecting iron 17 is fitted into the recess, the tenth
The same effect as shown in the figure can be obtained. The connecting rod 17 is made of a material with excellent heat insulation, heat resistance, and strength, such as ceramics.

Figure 13, Figure 14 and Figure 15 show sidewall 2,
3 shows an example of another holding structure. FIG. 13 is a schematic external view of a part of the ceramic stator vane row of this example, and FIG. 14 is the first
3 is a cross-sectional view taken along the line A--A in FIG. 3, and FIG. 15 is a schematic vertical cross-sectional view corresponding to the cross-sectional view taken along the line B--B in FIG. In addition,
FIG. 15 shows the structure of FIG. 9 as an example of holding the shell 1. Inside as shown in Figures 13 and 14.

The outer sidewalls 2, 3 are circumferentially divided at the shell 1. Inner and outer side walls 2 and 3
As shown in FIG. 15, the blades are held on the inner and outer shrouds 4.degree. 5 via heat insulating materials 7 by protrusions 18 projecting in the blade height direction.

According to this embodiment, the inner and outer sidewalls 2゜3 do not require the shell 1 and the fitting holes where stress is concentrated, compared to the above-mentioned embodiments, so the strength reliability is improved, and further processing is possible. It also becomes easier. Furthermore, as shown in FIG. 13, if the dividing positions of the inner and outer sidewalls 2 and 3 and the dividing position of the heat insulating material 7 are set to different positions, the combustion gas flowing in from the gap between the adjacent side walls will be absorbed by the heat insulating material. 7, and the inner and outer shrouds 4.5 or wing cores 6, which are metal parts (Fig. 15)
without damaging it. Therefore, reliability can be improved.

In addition, in this example, the inner and outer side walls 2°3 are
Since it is inserted and fitted into the outer shrouds 4 and 5 in the circumferential direction, the final part of the blade row is assembled with the following structure. That is,
To explain the case of the outer shroud 5 and outer sidewall 3 shown in FIG. 16, a part of the outer shroud 5 is
The shroud 5 can be assembled by welding as in the embodiment shown in Figure 1, and if the gap between the adjacent blades is made slightly larger, the sidewall 3 can be inserted between the adjacent blades in the blade height direction. It becomes possible to combine them, and then assemble them by welding, etc.

Alternatively, as shown in FIG. 17, which corresponds to FIG. 14, the sidewalls may be divided in the axial direction of the blade rows, thereby making the assembly easier. Additionally, since the outer sidewalls 3 and 3' are held separately in the outer shroud 5 (FIG. 16), the generation of secondary stresses due to misalignment during assembly or operation can be avoided. Strength reliability is improved compared to the embodiment shown in FIG.

Furthermore, as shown in FIG. 18, if the sidewall is divided into three parts in the axial direction of the blade row, it becomes possible to insert and assemble the sidewall between adjacent blade parts from the upstream or downstream side of the blade. By narrowing the gap between adjacent parts, it is possible to reduce the inflow of combustion gas. In addition, the upstream side and downstream side walls 3, 3' can be integrally manufactured in a shape corresponding to a plurality of pieces in the circumferential direction and can be attached to the blade row, which is effective in preventing the inflow of combustion gas. Furthermore, assembly efficiency can be improved. The dividing position may be such that each part of the outer sidewall 3゜3', 3''' can be inserted in the axial direction and installed between the shells 1 and 1'; for example, the position shown in Fig. 19 is possible. The outer sidewall 3# can be held in the blade height direction by a structure in which it is held by the outer sidewall 3°3' held on the outer shroud 5, as shown in FIG. A structure in which the side wall 3 is held by a brim-shaped projection provided at the end of the shell 1 (not shown), or a structure in which the above two structures are used together may be used. is not limited to the structure based on the protrusion j8,
For example, it is also possible with the pin 19 shown in FIG.
In this case, the pin 19 can also be applied to the sidewall 3'' shown in FIG. Make it with.

Examples of other ceramic vanes will be described below.

Metal shrouds for several blades are integrally fabricated to form a ceramic stator blade group. Figure 22 shows the appearance of an example in which the inner shroud 4 and blade core 6 corresponding to three blades are fabricated in one piece. show. Other parts manufactured for each blade are combined to form a stationary blade section. Also, within.

A structure may also be adopted in which the outer shroud is manufactured as one piece, and after other parts are assembled, the blade core is joined to the inner and outer shrouds by welding or the like. According to this embodiment, the amount of cooling air leaking from the gap provided between the stationary blades can be reduced, and the performance of the gas turbine can be improved.

〔Effect of the invention〕

According to the present invention, it is possible to prevent displacement, including rotation, of ceramic parts due to external force, thereby avoiding performance deterioration or damage due to collisions between the ceramic parts or with other parts. There are two effects.

[Brief explanation of the drawing]

FIG. 1 is a schematic longitudinal cross-sectional view of the first embodiment of the present invention, FIG. 2 is a schematic external view showing a stator vane row, and FIG. 3 is an A-A in FIG. 2.
4 is an external view of the shell, FIGS. 5 to 9 are schematic longitudinal sectional views showing the outer peripheral side of other embodiments, and FIG. 10 is a diagram of another embodiment. An external view of the outer periphery of the shell, FIG. 11 is a schematic vertical sectional view showing the outer periphery side,
2 is a partial vertical cross-sectional view of the shell outer periphery showing another embodiment related to FIG. 10, FIG. 13 is a schematic external view of a stator vane row according to another embodiment, and FIG. 14 is a view taken along A-A in FIG. 13. Line cross-sectional view,
15 is a schematic vertical cross-sectional view, FIG. 16 is a schematic vertical cross-sectional view of the outer circumference side part showing other embodiments related to FIG. Figure 13 is a cross-sectional view taken along the line A-A, Figures 20 and 21 are schematic partial longitudinal cross-sectional views showing the sidewall holding structure, and Figure 2
Figure 2 is an external view of the inner shroud. 1... Ceramic shell, 2, 3... Inner and outer ceramic side walls, 4, 5... Inner and outer shrouds,
6... Wing core, 7, 8... Insulation material. Agent Tatsuyuki Unuma Figure 2, Figure 4, Figure 3, Figure 5, Figure 15: Tsuki Hashimi Figure 6! ! Figure 8 Figure 7 Figure 9 Closed -

Claims (1)

[Claims] 1. An inner shroud and an outer shroud fixed in a casing, a ceramic shell disposed between the two shrouds and forming a wing section, and an inner shroud that forms a combustion gas flow path together with the ceramic shell. In a turbine stator blade equipped with a ceramic sidewall and an outer ceramic sidewall, the ceramic shell and the ceramic sidewall are fixedly held in the blade height direction and in the in-plane direction orthogonal to the direction by a metal shroud via a heat insulating material. What is claimed is: 1. A turbine stationary blade characterized in that it is formed into a connecting structure that prevents rotational displacement. 2. In claim 1, either one of the inner and outer ceramic sidewalls forming the inner and outer cylindrical wall surfaces of the combustion gas flow path and the ceramic shell installed between the ceramic sidewalls is provided with a heat insulating material. A turbine stator blade that is held by a metal shroud through which one held member holds the other member. 3. The turbine stator blade according to claim 1, wherein each of the ceramic shell and the ceramic sidewall is held by a metal shroud via a heat insulating material. 4. The turbine stationary blade according to any one of claims 1 to 3, wherein the structure for preventing rotational displacement is formed by a metal blade core that connects the inner and outer shrouds through the inside of the ceramic shell. 5. In any one of claims 1 to 4, the ceramic sidewall is divided in the circumferential direction of the stator vane row by one blade, every several blades, or a combination thereof between the blade parts or between adjacent blade parts, A turbine stator blade that is formed integrally or divided into several pieces in the axial direction of the blade row. 6. The turbine stator blade according to any one of claims 1 to 5, wherein at least one of the metal inner and outer shrouds is integrally formed from a plurality of stator blades. 7. The turbine stationary blade according to any one of claims 1 to 6, further comprising a buffer member for adjusting the difference in thermal deformation between the metal blade core and the ceramic member. 8. The turbine stationary blade according to any one of claims 1 to 7, wherein the ceramic sidewall is fixedly held in the blade height direction by a ceramic shell having a brim-like projection formed at the end of the blade. 9. The turbine stationary blade according to any one of claims 1 to 8, wherein a protrusion provided at an end of the ceramic shell prevents displacement and rotational displacement of the shell in an in-plane direction orthogonal to the blade height direction. . 10. A gas turbine device comprising a combustor, a stator blade, and a rotor blade, wherein at least the first stage stator blade is formed of the turbine stator blade according to any one of claims 1 to 9.