High-temperature components, rotating machinery, and methods for manufacturing high-temperature components

Abstract

To provide a high-temperature component that can efficiently reduce a heat load while reducing manufacturing costs.SOLUTION: A high-temperature component according to an embodiment comprises: a first surface on which an abradable layer is provided; and a second surface continuous with the first surface, intersecting with the first surface, and on which a heat shield coating layer is provided. The heat shield coating layer is also formed on a portion of the first surface from a first connection position between the first surface and the second surface to the first surface. The abradable layer is formed on a surface of the heat shield coating layer in a region where the heat shield coating layer is formed on the first surface.SELECTED DRAWING: Figure 5

Description

Technical Field

[0001] The present disclosure relates to a high-temperature component, a rotating machine, and a method for manufacturing a high-temperature component.

Background Art

[0002] For example, in a machine such as a gas turbine in which high-temperature working gas flows internally, the components constituting the machine include high-temperature components that reach a relatively high temperature due to being exposed to the working gas or the like. It is known that for such high-temperature components, for example, applying a thermal barrier coating can suppress the temperature rise of the high-temperature component (see, for example, Patent Document 1).

Prior Art Literature

Patent Literature

[0003]

Patent Document 1

Summary of the Invention

Problem to be Solved by the Invention

[0004] For example, even for a single high-temperature component, the temperature may vary depending on the region: for example, a region located on the upstream side in the flow direction of the working gas has a higher temperature than a region located on the downstream side. Therefore, it is desirable to apply a thermal barrier coating to regions that tend to reach relatively high temperatures, but considering the application cost of the thermal barrier coating, it is desirable to narrow the application range of the thermal barrier coating.

[0005] In view of the above circumstances, an object of at least one embodiment of the present disclosure is to provide a high-temperature component capable of efficiently reducing thermal load while suppressing manufacturing cost, and a rotating machine including the high-temperature component.

Means for Solving the Problem

[0006] (1) A high-temperature component according to at least one embodiment of the present disclosure is: The first surface is provided with an abradable layer, A second surface is continuous with the first surface, intersects with the first surface, and has a heat-shielding coating layer provided on it, Equipped with, The heat-shielding coating layer is also formed on a portion of the first surface, extending from the first connection point between the first surface and the second surface to the first surface. The abradable layer is formed on the surface of the heat-shielding coating layer in the region where the heat-shielding coating layer is formed on the first surface.

[0007] (2) A rotating machine according to at least one embodiment of the present disclosure is The system includes high-temperature components as described in (1) above.

[0008] (3) A method for manufacturing a high-temperature component according to at least one embodiment of the present disclosure is: A step of forming an abrasive layer on the first surface, A step of forming a heat-shielding coating layer on a second surface that is continuous with the first surface and intersects with the first surface, Equipped with, In the step of forming the heat-shielding coating layer, the heat-shielding coating layer is also formed on a part of the first surface from the first connection position between the first surface and the second surface to the first surface, In the step of forming the abradable layer, the abradable layer is formed on the surface of the heat-shielding coating layer in the region on the first surface where the heat-shielding coating layer is formed. [Effects of the Invention]

[0009] According to at least one embodiment of this disclosure, it is possible to provide a high-temperature component that can efficiently reduce thermal load while suppressing manufacturing costs, and a rotating machine equipped with this high-temperature component. [Brief explanation of the drawing]

[0010] [Figure 1] This is a schematic diagram showing the overall configuration of a gas turbine as an example of a rotating machine. [Figure 2]This is a cross-sectional view showing the gas flow path of a turbine. [Figure 3] This is a view of one of the divided parts constituting a divided ring according to one embodiment, seen from the axial upstream side. [Figure 4] This is a cross-sectional view taken along the line IV-IV in Figure 3. [Figure 5] This is an enlarged view of section A in Figure 4. [Figure 6] This is a view of a divided body according to one embodiment, seen from the radially inner side. [Figure 7] This is a cross-sectional view taken along the line VII-VII in Figure 6. [Figure 8] This is a flowchart showing the manufacturing procedure for a divided body according to one embodiment. [Modes for carrying out the invention]

[0011] Hereinafter, several embodiments of this disclosure will be described with reference to the attached drawings. However, the dimensions, materials, shapes, relative arrangements, etc., of the components described or shown in the drawings as embodiments are not intended to limit the scope of this disclosure, but are merely illustrative examples. For example, expressions describing relative or absolute arrangements such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" should not only strictly describe such arrangements, but also describe states of relative displacement with tolerances or angles or distances that allow for the same function to be achieved. For example, expressions such as "identical," "equal," and "homogeneous" that describe things being in an equal state not only describe a state of being strictly equal, but also describe a state in which there is a tolerance or a difference that is sufficient to achieve the same function. For example, expressions describing shapes such as squares or cylinders shall not only represent geometrically precise shapes such as squares or cylinders, but also shapes that include protrusions, chamfers, etc., to the extent that the same effect can be achieved. On the other hand, expressions such as "to possess," "to be equipped with," "to have," "to include," or "to have" a single component are not exclusive expressions that exclude the existence of other components.

[0012] Fig. 1 is a schematic diagram showing the overall configuration of a gas turbine as an example of a rotating machine, and Fig. 2 is a cross-sectional view showing a gas flow path of the turbine.

[0013] In the present embodiment, as shown in Fig. 1, the gas turbine 10 is configured such that a compressor 11, a combustor 12, and a turbine 13 are coaxially arranged by a rotor 14, and a generator 15 is connected to one end of the rotor 14. In the following description, the direction in which the axis of the rotor 14 extends is defined as an axial direction Da, the circumferential direction centered on the axis of the rotor 14 is defined as a circumferential direction Dc, and the direction perpendicular to the axis Ax of the rotor 14 is defined as a radial direction Dr.

[0014] In the compressor 11, air AI taken in from an air intake passes through a plurality of stationary vanes and moving blades and is compressed, thereby generating high-temperature and high-pressure compressed air AC. The combustor 12 supplies a predetermined fuel FL to the compressed air AC and combusts the same, thereby generating high-temperature and high-pressure combustion gas FG. In the turbine 13, the high-temperature and high-pressure combustion gas FG generated in the combustor 12 passes through a plurality of stationary vanes and moving blades, thereby driving and rotating the rotor 14, and driving the generator 15 connected to the rotor 14.

[0015] Further, as shown in Fig. 2, in the turbine 13, a turbine stationary vane (stationary vane) 21 is configured such that the hub side of an airfoil portion 23 is fixed to an inner shroud 25, and the tip side thereof is fixed to an outer shroud 27. A turbine moving blade (moving blade) 41 is configured such that the base end portion of an airfoil portion 43 is fixed to a platform 45. The outer shroud 27 and a split ring 50 arranged on the tip end side of the moving blade 41 are supported by a casing (turbine casing) 30 via a heat shield ring 54, and the inner shroud 25 is supported by a support ring 31. Therefore, a combustion gas flow path 32 through which the combustion gas FG passes is formed along the axial direction Da as a space surrounded by the inner shroud 25, the outer shroud 27, the platform 45, and the split ring 50.

[0016] The inner shroud 25, the outer shroud 27, and the divided ring 50 function as gas path surface forming members. A gas path surface forming member is a member that divides the combustion gas passage 32 and has a gas path surface into which the combustion gas FG comes into contact.

[0017] The combustor 12, rotor blades 41 (e.g., platform 45), stator blades 21 (e.g., inner shroud 25 and outer shroud 27), and segmented ring 50 are high-temperature components 1 used in a high-temperature environment in which they come into contact with combustion gas FG, and require cooling by a cooling medium. In the following description, as an example of a cooling structure for high-temperature components 1, the cooling structure of the segmented ring 50 of a gas turbine 10, which is composed of multiple segmented bodies 51 arranged in an annular shape along the circumferential direction Dc, will be described.

[0018] Figure 3 is a view of one of the divided parts 51 constituting the divided ring 50 according to one embodiment, as seen from the upstream side of the axial direction Da. Figure 4 is a cross-sectional view taken along the line IV-IV in Figure 3. Figure 5 is an enlarged view of section A in Figure 4. Figure 6 is a view of a divided body 51 according to one embodiment, seen from the inside in the radial direction Dr. Figure 7 is a cross-sectional view taken along the line VII-VII in Figure 6.

[0019] (Regarding the divided body 51) In one embodiment, the divided ring 50 is composed of a plurality of divided bodies 51 arranged in an annular shape in the circumferential direction Dc. As shown in Figures 3 and 4, each divided body 51 comprises a plate-shaped main body portion 53 having an axial cooling passage 61 inside, and a protruding portion 55 that protrudes radially outward from the main body portion 53. In the divided body 51 of one embodiment, the protruding portion 55 includes a protruding portion 55u on the upstream side of the axial direction Da and a protruding portion 55d on the downstream side of the axial direction Da. Furthermore, in the divided body 51 according to one embodiment, two wall portions 56 connecting the projection 55u on the upstream side of the axial direction Da and the projection 55d on the downstream side of the axial direction Da are provided near the end in the circumferential direction Dc. In one embodiment of the divided body 51, a space 57 is formed which is a recessed portion that is recessed in the radial direction Dr inward, surrounded by a protruding portion 55u on the upstream side of the axial direction Da, a protruding portion 55d on the downstream side of the axial direction Da, and two wall portions 56.

[0020] As shown in Figure 2, in one embodiment, the divided body 51 is arranged such that its inner surface 511 on the radially inner side Dr faces the combustion gas passage 32 through which the combustion gas FG flows. On the radially inner side Dr of the main body 53, a rotor blade 41 that rotates around the rotor 14 is arranged with a certain gap between them. To suppress the temperature rise due to heat input from the high-temperature combustion gas FG, a plurality of axial cooling passages 61 extending in the axial direction Da are formed in the main body 53. Multiple axial cooling passages 61 are arranged in parallel in the circumferential direction Dc.

[0021] As shown in Figure 4, in one embodiment, the divided body 51 has a manifold 63 extending in the circumferential direction on the main body portion 53, which is upstream of the axial Da projection 55u on the axial Da upstream side. The upstream ends 61u of the multiple axial cooling passages 61 are connected to the manifold 63. The downstream ends 61d of the multiple axial cooling passages 61 are open to the downstream end face 53d of the main body 53.

[0022] In one embodiment, the divided body 51 has a plurality of air passages 65 that connect the space 57 and the manifold 63.

[0023] Although not shown in the figures, in one embodiment of the gas turbine 10, each segmented body 51 is configured to be supplied with cooling air CA from the radially outside Dr of the main body 53 to the space 57. The cooling air CA supplied to the space 57 is then supplied to the manifold 63 via the air passage 65. The cooling air CA supplied to the manifold 63 is distributed to each axial cooling passage 61 and flows through each axial cooling passage 61, and in the process of being discharged into the combustion gas FG from the downstream end 61d on the axial side Da, the main body 53 of the divided body 51 is cooled by convection.

[0024] In one embodiment, the divided body 51 has a first surface 531 which is the radially inner surface Dr of the main body 53 which is a metal substrate, a third surface 533 which is the end surface 53u on the axially upstream side Da of the main body 53, and a second surface 532 which is a chamfered surface formed between the first surface 531 and the third surface 533. In one embodiment of the divided body 51, the connection position between the first surface 531 and the second surface 532 is referred to as the first connection position 521, and the connection position between the second surface 532 and the third surface 533 is referred to as the second connection position 522.

[0025] In one embodiment of the divided body 51, a bond coat layer 71 is formed on the first surface 531, the second surface 532, and the third surface 533 near the second connection position 522. The bond coat layer 17 is made of, for example, an MCrAlY alloy (where M represents a metallic element such as Ni, Co, Fe, or a combination of two or more of these).

[0026] (Heat-shielding coating layer 73) In one embodiment of the divided body 51, a thermal barrier coating (TBC) layer 73 is formed on the bond coat layer 71 on the second surface 532. The heat-shielding coating layer 73 is preferably a ceramic layer composed of a ZrO2-based material, such as YSZ (yttria-stabilized zirconia), which is ZrO2 partially or fully stabilized with Y2O3. In one embodiment of the divided body 51, the heat-shielding coating layer 73 is also formed in a portion of the first surface 531, R1, from the first connection position 521 between the first surface 531 and the second surface 532 to the first surface 531. In one embodiment of the divided body 51, the heat-shielding coating layer 73 is not formed in any region R2 other than the portion of the first surface 531, R1, from the first connection position 521 to the first surface 531. In one embodiment of the divided body 51, the heat-shielding coating layer 73 is also formed in a portion of the third surface 533, R3, from the second connection position 522 between the second surface 532 and the third surface 533 to the third surface 533.

[0027] The heat-shielding coating layer 73 has a uniform thickness on the second surface 532. Furthermore, the heat-shielding coating layer 73 is formed such that its thickness gradually decreases from the first connection position 521 to the first surface 531 as it moves away from the first connection position 521 along the axial direction Da, and from the second connection position 522 to the third surface 533 as it moves away from the second connection position 522 along the radial direction Dr.

[0028] (Abraded layer 75) In one embodiment of the divided body 51, an abradable layer 75 is formed on the bond coat layer 71 on the first surface 531. In one embodiment of the divided body 51, the first surface 531 faces the tip surface 41t of the rotor blade 41 in the radial direction Dr. Therefore, by setting the clearance between the abradable layer 75 of the first surface 531 and the tip surface 41t of the rotor blade 41 to be relatively narrow, even if there is a risk of contact between the abradable layer 75 of the first surface 531 and the tip surface 41t of the rotor blade 41, although the abradable layer 75 will be cut and thinned, damage to both the divided body 51 and the rotor blade 41 can be avoided.

[0029] The abradable layer 75 is preferably a ceramic layer composed of a ZrO2-based material, the same material as the heat-shielding coating layer 73, for example, YSZ (yttria-stabilized zirconia), which is ZrO2 partially or fully stabilized with Y2O3.

[0030] In one embodiment of the divided body 51, the abradable layer 75 is formed on the surface of the heat-shielding coating layer 73 in the region R1 on the first surface 531 where the heat-shielding coating layer 73 is formed. The abradable layer 75 formed on the surface of the heat-shielding coating layer 73 on the first surface 531 is formed such that its thickness gradually decreases as it approaches the first connection position 521. Furthermore, in the region on the first surface 531 where the heat-shielding coating layer 73 and the abradable layer 75 are formed (hereinafter referred to as the overlapping formation region OR), it is preferable that the thickness of the heat-shielding coating layer 73 and the abradable layer 75 are formed to gradually change along the axial direction Da, so that the distance between the surface 75a of the abradable layer 75 (the surface on the radial side Dr) and the first surface 531 remains constant regardless of the position in the axial direction Da.

[0031] In one embodiment of the divided body 51, the abradable layer 75 is provided only on the first surface 531 and does not need to be provided on the second surface 532 and the third surface 533.

[0032] In one embodiment of the divided body 51, the abradable layer 75 has a plurality of grooves 77 formed therein to improve machinability. The grooves 77 may, for example, extend along the first surface 531 in a direction inclined with respect to the axial Da and circumferential Dc directions. Furthermore, at the bottom 77a of the groove 77, the bond coat layer 71 in contact with the abradable layer 75 may or may not be exposed.

[0033] In one embodiment of the divided body 51, the overlapping formation region OR does not need to overlap with the tip surface 41t of the rotor blade 41 in the axial direction Da, but it may partially overlap. The overlapping formation region OR is preferably located upstream of the central position Cp in the axial direction Da of the tip surface 41t of the rotor blade 41. That is, the downstream end of the heat-shielding coating layer 73 formed on the first surface 531 is preferably located upstream of the central position Cp in the axial direction Da of the tip surface 41t of the rotor blade 41.

[0034] In one embodiment of the divided body 51, having the above-described configuration, the following effects are achieved. In other words, the divided body 51 according to one embodiment comprises a first surface 531 on which an abradable layer 75 is provided, and a second surface 532 that is continuous with the first surface 531, intersects with the first surface 531, and on which a heat-shielding coating layer 73 is provided. The heat-shielding coating layer 73 is also formed on a part of the first surface 531 from the first connection position 521 between the first surface 531 and the second surface 532 to the first surface 531. In the region R1 on the first surface 531 where the heat-shielding coating layer 73 is formed, the abradable layer 75 is formed on the surface of the heat-shielding coating layer 73.

[0035] The second surface 532 of the divided body 51 faces the combustion gas flow path 32 and is oriented upstream of the combustion gas FG flow. As a result, it experiences a larger heat load and its temperature rises more easily compared to other regions. According to one embodiment of the divided body 51, heat input from the second surface 532 can be suppressed by the heat-shielding coating layer 73. Furthermore, by not forming the heat-shielding coating layer 73 in the region downstream of the overlapping formation region OR of the first surface 531 in the axial direction Da (i.e., the region R2 described above), the cost of applying the heat-shielding coating layer 73 can be reduced. This makes it possible to provide a divided body 51 that can efficiently reduce the heat load while suppressing manufacturing costs.

[0036] A gas turbine 10 according to one embodiment includes the divided body 51 according to the above-described embodiment. This makes it possible to efficiently reduce the heat load while suppressing the manufacturing cost of the high-temperature component 1 of the gas turbine 10, and to improve the reliability of the gas turbine 10 while suppressing the manufacturing cost of the gas turbine 10.

[0037] In one embodiment of the divided body 51, the heat-shielding coating layer 73 is preferably such that its thickness gradually decreases from the first connection position 521 to the first surface 531 as it moves away from the first connection position 521 in the axial direction Da. As a result, the abradable layer 75 formed on the surface of the heat-shielding coating layer 73 is less likely to peel off from the heat-shielding coating layer 73 compared to, for example, a case where the thickness of the heat-shielding coating layer 73 decreases sharply at a certain position away from the first connection position 521.

[0038] In one embodiment of the divided body 51, the abradable layer 75 formed on the surface of the heat-shielding coating layer 73 on the first surface 531 preferably has a gradually decreasing thickness as it approaches the first connection position 521 along the axial direction Da. As a result, compared to, for example, a case where the thickness of the abradable layer 75 decreases sharply at a certain position approaching the first connection position 521, the abradable layer 75 formed on the surface of the heat-shielding coating layer 73 becomes less likely to peel off from the heat-shielding coating layer 73.

[0039] In one embodiment of the divided body 51, the second surface 532 is preferably a chamfered surface formed between the third surface 533, which extends in a direction intersecting the first surface 531, and the first surface 531. Since the combustion gas FG flows along the surface of the first surface 531 and the third surface 533 is located upstream in the direction of the combustion gas FG flow, forming a chamfered surface, i.e., the second surface 532, between the third surface 533 and the first surface 531 can suppress the heat input from the combustion gas FG to the divided body 51.

[0040] In one embodiment of the divided body 51, the heat-shielding coating layer 73 may also be formed on a portion of the third surface 533, extending from the second connection position 522 between the third surface 533 and the second surface 532 to the third surface 533. This makes it possible to suppress heat input from the third surface 533.

[0041] In one embodiment of the divided body 51, it is preferable to provide a plurality of axial cooling passages 61 that extend along the first surface 531 in a direction away from the second surface 532. This makes it possible to suppress the temperature rise of the first surface 531.

[0042] In one embodiment, the high-temperature component 1 may be a divided body 51 that constitutes a divided ring 50 of the gas turbine 10, which is formed in an annular shape along the circumferential direction Dc of the gas turbine 10. This makes it possible to provide a segmented body 51 that can efficiently reduce the thermal load while suppressing manufacturing costs.

[0043] In one embodiment of the divided body 51, the second surface 532 is preferably located upstream of the first surface 531 in the axial direction Da. The first surface 531 is preferably facing the tip surface 41t of the rotor blade 41 in the radial direction Dr. The position of the downstream end of the heat-shielding coating layer 73 formed on the first surface 531 in the axial direction Da, that is, the position of the downstream end of the overlapping formation region OR, is preferably located upstream of the central position Cp of the tip surface 41t in the axial direction Da.

[0044] As a result, although the second surface 532 tends to have a higher temperature than the first surface 531 because it is located upstream of the first surface 531 in the axial direction Da, the heat input from the second surface 532 can be suppressed by the heat-shielding coating layer 73. Furthermore, the first surface 531 faces the tip surface 41t of the rotor blade 41 in the radial direction Dr. Therefore, by setting the clearance between the abradable layer 75 of the first surface 531 and the tip surface 41t of the rotor blade 41 to be relatively narrow, even if there is a risk of contact between the abradable layer 75 of the first surface 531 and the tip surface 41t of the rotor blade 41, although the abradable layer 75 will be cut and thinned, damage to both the segmented body 51 and the rotor blade 41 can be avoided. Furthermore, since the heat-shielding coating layer 73 is not formed in the region downstream of the overlapping formation region OR in the axial direction (region R2) on the first surface 531, the cost of applying the heat-shielding coating layer 73 can be reduced, and the risk of contact between the heat-shielding coating layer 73 and the tip surface 41t of the rotor blade 41 can be reduced, thereby suppressing damage to the heat-shielding coating layer 73 and the rotor blade 41.

[0045] (Manufacturing method for high-temperature component 1) The following describes one embodiment of a method for manufacturing the high-temperature component 1. In the following description, the method for manufacturing the divided body 51 according to the above embodiment will be used as an example to explain the manufacturing method of the high-temperature component 1. Figure 8 is a flowchart showing the manufacturing procedure for the divided body 51 according to the above-described embodiment. A method for manufacturing a divided body 51 according to one embodiment includes the steps of: S1 forming a bond coat layer 71; S3 forming a heat-shielding coating layer 73; S5 forming an abradable layer 75; S7 forming a groove 77; and S9 removing the resin.

[0046] (Step S1: Forming the bond coat layer 71) Step S1, which involves forming the bond coat layer 71, is a step in which the bond coat layer 71 is formed on the surface of the main body portion 53 of the divided body 51. In step S1, which involves forming the bond coat layer 71, the bond coat layer 71 is formed by thermal spraying the aforementioned MCrAlY alloy powder or the like onto the surface of the main body portion 53, specifically the first surface 531, the second surface 532, and the third surface 533 near the second connection position 522.

[0047] (Step S3: Forming the heat-shielding coating layer 73) Step S3, which involves forming the heat-shielding coating layer 73, is a step in which the heat-shielding coating layer 73 is formed on a second surface 532 that is continuous with the first surface 531 and intersects with the first surface 531. In step S3, which involves forming the heat-shielding coating layer 73, the heat-shielding coating layer 73 is formed by thermal spraying a thermal spray powder containing, for example, the ZrO2-based material described above onto the bond coat layer 71 on the second surface 532.

[0048] In step S3, which forms the heat-shielding coating layer 73, masking is not applied to the first surface 531 downstream of the first connection position 521 in the axial direction Da. When thermal spraying powder is sprayed onto the bond coat layer 71 on the second surface 532, the thermal spraying powder is allowed to flow onto the first surface 531, forming the heat-shielding coating layer 73 on the first surface 531. As a result, in step S3, which forms the heat-shielding coating layer 73, the heat-shielding coating layer 73 is also formed on a part of the first surface 531 (region R1) from the first connection position 521 between the first surface 531 and the second surface 532 to the first surface 531. In this way, as described above, the heat-shielding coating layer 73 is formed such that its thickness gradually decreases from the first connection position 521 to the first surface 531 as it moves away from the first connection position 521 along the axial direction Da.

[0049] Similarly, in step S3 for forming the heat-shielding coating layer 73, for example, masking is not applied to the third surface 533 radially outward from the second connection position 522. When thermal spraying powder is sprayed onto the bond coat layer 71 on the second surface 532, it is permitted that the thermal spraying powder flows onto the third surface 533 and forms the heat-shielding coating layer 73 on the third surface 533. As a result, in step S3 for forming the heat-shielding coating layer 73, the heat-shielding coating layer 73 is also formed on a portion of the third surface 533 from the second connection position 522 between the second surface 532 and the third surface 533 to the third surface 533. In this way, as described above, the heat-shielding coating layer 73 is formed such that its thickness gradually decreases from the second connection position 522 to the third surface 533 as it moves away from the second connection position 522 along the radial direction Dr.

[0050] (Step S5: Forming the abradable layer 75) Step S5, which involves forming the abradable layer 75, is a step in which the abradable layer 75 is formed on the first surface 531. In step S5, which involves forming the abradable layer 75, the abradable layer 75 is formed by thermal spraying a mixture of thermal spray powder containing, for example, the ZrO2-based material described above and a resin powder such as polyester onto the bond coat layer 71 on the first surface 531. In step S5, which involves forming the abradable layer 75, the abradable layer 75 containing a resin such as polyester is formed uniformly on the first surface 531 (i.e., without grooves 77).

[0051] (Step S7: Forming the groove 77) Step S7, which involves forming the groove 77, is a step in which the above-described groove 77 is formed in the abradable layer 75 that is uniformly formed on the first surface 531 after the step S5, which involves forming the abradable layer 75. Step S7 for forming the groove 77 involves forming the groove 77 by applying a cutting process, such as water jet machining, to the abradable layer 75 uniformly formed on the first surface 531.

[0052] (Process S9 for removing resin) Step S9, which involves removing the resin, is a step in which the resin is removed from the abradable layer 75 which contains a resin such as polyester. In step S9, which involves removing the resin, the divided body 51, which has undergone step S7 to form the groove portion 77, is subjected to a heat treatment to remove the resin contained in the abradable layer 75.

[0053] As described above, a method for manufacturing a high-temperature component 1 according to one embodiment includes a step S5 of forming an abradable layer 75 on a first surface 531, and a step S3 of forming a heat-shielding coating layer 73 on a second surface 532 that is continuous with and intersects the first surface 531. In step S3 of forming the heat-shielding coating layer 73, the heat-shielding coating layer 73 is also formed on a part of the first surface 531 (region R1) from the first connection position 521 between the first surface 531 and the second surface 532 to the first surface 531. In step S5 of forming the abradable layer 75, the abradable layer 75 is formed on the surface of the heat-shielding coating layer 73 in the region R1 on the first surface 531 where the heat-shielding coating layer 73 is formed.

[0054] According to a manufacturing method for a high-temperature component 1 according to one embodiment, when the temperature of the second surface 532 tends to be higher than that of the first surface 531, it is possible to provide a high-temperature component 1 in which the heat input from the second surface 532 can be suppressed by the heat-shielding coating layer 73. Furthermore, by not forming the heat-shielding coating layer 73 on the first surface 531 except for a part of the first surface 531 (region R1) from the first connection position 521 to the first surface 531, the cost of applying the heat-shielding coating layer 73 can be reduced. As a result, it is possible to provide a high-temperature component 1 that can efficiently reduce the heat load while suppressing manufacturing costs.

[0055] In step S3, where the heat-shielding coating layer is formed, it is preferable to form the heat-shielding coating layer 73 such that its thickness gradually decreases from the first connection position 521 to the first surface 531 as it moves away from the first connection position 521. As a result, compared to, for example, the case where the heat-shielding coating layer 73 is formed such that its thickness decreases sharply at a certain position away from the first connection position 521, the abradable layer 75 formed on the surface of the heat-shielding coating layer 73 becomes less likely to peel off from the heat-shielding coating layer 73.

[0056] This disclosure is not limited to the embodiments described above, but also includes modified forms of the embodiments described above, as well as forms that combine these forms as appropriate. For example, in the divided body 51 according to one embodiment, the second surface 532, which is a chamfered surface, does not need to be formed. In this case, the first surface 531 and the third surface 533 are directly connected. In this case, the radially inner region of the third surface 533, which tends to have a relatively high temperature, is considered to be the same region as the second surface 532 described above (hereinafter referred to as the virtual second region), and the heat-shielding coating layer 73 may be provided in this virtual second region. Furthermore, the heat-shielding coating layer 73 may also be formed on a part of the first surface 531, from the connection point between the first surface 531 and this virtual second region to the first surface 531. The abradable layer 75 may be formed on the surface of the heat-shielding coating layer 73 in the region of the first surface 531 where the heat-shielding coating layer 73 is formed.

[0057] The contents described in each of the above embodiments can be understood, for example, as follows: (1) A high-temperature component 1 (divided body 51) according to at least one embodiment of the present disclosure comprises a first surface 531 on which an abradable layer 75 is provided, and a second surface 532 which is continuous with the first surface 531, intersects with the first surface 531, and on which a heat-shielding coating layer 73 is provided. The heat-shielding coating layer 73 is also formed on a part of the first surface 531 from a first connection position 521 between the first surface 531 and the second surface 532 to the first surface 531. In the region R1 on the first surface 531 where the heat-shielding coating layer 73 is formed, the abradable layer 75 is formed on the surface of the heat-shielding coating layer 73.

[0058] According to the configuration described in (1) above, when the temperature of the second surface 532 tends to be higher than that of the first surface 531, the heat input from the second surface 532 can be suppressed by the heat-shielding coating layer 73. Furthermore, by not forming the heat-shielding coating layer 73 on the remaining portion (i.e., region R2) of the first surface 531 relative to the above portion (i.e., region R1), the cost of applying the heat-shielding coating layer 73 can be reduced. This makes it possible to provide a high-temperature component 1 (divided body 51) that can efficiently reduce the heat load while suppressing manufacturing costs.

[0059] (2) In some embodiments, in the configuration of (1) above, the thickness of the heat-shielding coating layer 73 may gradually decrease from the first connection position 521 to the first surface 531 as it moves away from the first connection position 521.

[0060] According to the configuration of (2) above, for example, compared to the case where the thickness of the heat-shielding coating layer 73 decreases sharply at a certain position away from the first connection position 521, the abradable layer 75 formed on the surface of the heat-shielding coating layer 73 becomes less likely to peel off from the heat-shielding coating layer 73.

[0061] (3) In some embodiments, in the configuration of (2) above, the abradable layer 75 formed on the surface of the heat-shielding coating layer 73 on the first surface 531 may gradually decrease in thickness as it approaches the first connection position 521.

[0062] According to the configuration described in (3) above, for example, compared to a case where the thickness of the abradable layer 75 decreases sharply at a certain position approaching the first connection position 521, the abradable layer 75 formed on the surface of the heat-shielding coating layer 73 becomes less likely to peel off from the heat-shielding coating layer 73.

[0063] (4) In some embodiments, in any of the configurations (1) to (3) above, the second surface 532 may be a chamfered surface formed between the first surface 531 and the third surface 533 which extends in a direction intersecting the first surface 531.

[0064] According to the configuration described in (4) above, for example, if the working gas (combustion gas FG) flows along the surface of the first surface 531 and the third surface 533 is located upstream in the direction of flow of the working gas (combustion gas FG), then by forming a chamfered surface, i.e., the second surface 532, between the third surface 533 and the first surface 531, the heat input from the working gas (combustion gas FG) to the high-temperature component 1 (divided body 51) can be suppressed.

[0065] (5) In some embodiments, in the configuration of (4) above, the heat-shielding coating layer 73 may also be formed on a part of the third surface 533 (region R3) from the second connection position 522 between the third surface 533 and the second surface 532 to the third surface 533.

[0066] According to the configuration in (5) above, heat input from the third surface 533 can be suppressed.

[0067] (6) In some embodiments, the configuration of (1) to (5) above may include a plurality of cooling passages (axial cooling passages 61) that extend along the first surface 531 in a direction away from the second surface 532.

[0068] According to the configuration described in (6) above, the temperature rise of the first surface 531 can be suppressed.

[0069] (7) In some embodiments, in any of the configurations (1) to (6) above, the high-temperature component 1 may be a divided body 51 that constitutes a divided ring 50 of the gas turbine 10, which is formed in an annular shape along the circumferential direction Dc of the gas turbine 10.

[0070] According to the configuration of (7) above, by having the divided body 51 have any of the configurations of (1) to (6) above, it is possible to provide a divided body 51 that can efficiently reduce the heat load while suppressing manufacturing costs.

[0071] (8) In some embodiments, in the configuration of (7) above, the second surface 532 is preferably located upstream of the first surface 531 in the axial direction Da of the gas turbine 10. The first surface 531 is preferably facing the tip surface 41t of the rotor blade 41 of the gas turbine 10 in the radial direction Dr of the gas turbine 10. The position of the downstream end of the heat-shielding coating layer 73 formed on the first surface 531 in the axial direction Da is preferably located upstream of the central position Cp of the tip surface 41t in the axial direction Da.

[0072] According to the configuration described in (8) above, the second surface 532 is located upstream of the first surface 531 in the axial direction Da of the gas turbine 10, and therefore tends to have a higher temperature than the first surface 531. However, the heat input from the second surface 532 can be suppressed by the heat-shielding coating layer 73. According to the configuration described in (8) above, the first surface 531 faces the tip surface 41t of the rotor blade 41 of the gas turbine 10 in the radial direction Dr of the gas turbine 10. Therefore, by setting the clearance between the abradable layer 75 of the first surface 531 and the tip surface 41t of the rotor blade 41 to be relatively narrow, even if there is a risk of contact between the abradable layer 75 of the first surface 531 and the tip surface 41t of the rotor blade 41, although the abradable layer 75 will be cut and thinned, damage to both the high-temperature component 1 (divided body 51) and the rotor blade 41 can be avoided. Furthermore, according to the configuration of (8) above, if the heat-shielding coating layer 73 is not formed on the remaining portion (region R2) of the first surface 531 relative to the above portion (region R1), the cost of applying the heat-shielding coating layer 73 can be reduced, and the risk of contact between the heat-shielding coating layer 73 and the tip surface 41t of the rotor blade 41 can be reduced, thereby suppressing damage to the heat-shielding coating layer 73 and the rotor blade 41.

[0073] (9) A rotating machine (gas turbine 10) according to at least one embodiment of the present disclosure comprises a high-temperature component 1 having any of the configurations described in (1) to (8) above.

[0074] According to the configuration described in (9) above, the manufacturing cost of the high-temperature component 1 of the rotating machine (gas turbine 10) can be suppressed while efficiently reducing the heat load, and the manufacturing cost of the rotating machine (gas turbine 10) can be suppressed while improving the reliability of the rotating machine (gas turbine 10).

[0075] (10) A method for manufacturing a high-temperature component 1 according to at least one embodiment of the present disclosure includes a step S5 of forming an abradable layer 75 on a first surface 531, and a step S3 of forming a heat-shielding coating layer 73 on a second surface 532 that is continuous with and intersects the first surface 531. In step S3 of forming the heat-shielding coating layer 73, the heat-shielding coating layer 73 is also formed on a part of the first surface 531 (region R1) from a first connection position 521 between the first surface 531 and the second surface 532 to the first surface 531. In step S5 of forming the abradable layer 75, the abradable layer 75 is formed on the surface of the heat-shielding coating layer 73 in the region R1 on the first surface 531 where the heat-shielding coating layer 73 is formed.

[0076] According to the method described in (10) above, when the temperature of the second surface 532 tends to be higher than that of the first surface 531, a high-temperature component 1 can be provided in which the heat input from the second surface 532 can be suppressed by the heat-shielding coating layer 73. Furthermore, by not forming the heat-shielding coating layer 73 on the remaining portion (region R2) of the first surface 531 relative to the above-mentioned portion (region R1), the application cost of the heat-shielding coating layer 73 can be reduced. This makes it possible to provide a high-temperature component 1 that can efficiently reduce the heat load while suppressing manufacturing costs.

[0077] (11) In some embodiments, in the method of (10) described above, in step S3 of forming the heat-shielding coating layer 73, the heat-shielding coating layer 73 may be formed such that the thickness gradually decreases from the first connection position 521 to the first surface 531 as it moves away from the first connection position 521.

[0078] According to the method described in (11) above, for example, compared to the case in which the heat-shielding coating layer 73 is formed such that the thickness of the heat-shielding coating layer 73 decreases sharply at a certain position away from the first connection position 521, the abradable layer 75 formed on the surface of the heat-shielding coating layer 73 becomes less likely to peel off from the heat-shielding coating layer 73. [Explanation of symbols]

[0079] 1. High-temperature components 10 Gas Turbines 11 Compressor 13 Turbine 32 Combustion gas flow path 41 Turbine blades (moving blades) 41t tip surface 50 split ring 51 Split body 53 Main body 61 Axial cooling passage (cooling passage) 71 Bond Coat Layer 73 Thermal Barrier Coating (TBC) layer 75 Absorbable layer 77 Groove 521 First connection position 522 Second connection point 531 Page 1 532 2nd page 533 3rd page

Claims

1. The first surface is provided with an abradable layer, A second surface is continuous with the first surface, intersects with the first surface, and has a heat-shielding coating layer provided on it, Equipped with, The heat-shielding coating layer is formed on a portion of the first surface from the first connection point between the first surface and the second surface to a position midway along the first surface, and is not formed on the first surface in a region further from the first connection point than the midway position. The abradable layer is formed on the surface of the heat-shielding coating layer in the region where the heat-shielding coating layer is formed on the first surface. Page 1 is, A first region located between the first connection position and the intermediate position, where the heat-shielding coating layer and the abradable layer are formed, A second region located further from the first connection position than the aforementioned intermediate position, in which the abradable layer is directly formed without the heat-shielding coating layer, including High-temperature components.

2. The heat-shielding coating layer has a gradually decreasing thickness from the first connection position to the first surface as it moves away from the first connection position. The high-temperature component according to claim 1.

3. The abradable layer formed on the surface of the heat-shielding coating layer on the first surface has a gradually decreasing thickness as it approaches the first connection position. The high-temperature component according to claim 2.

4. The second surface is a chamfered surface formed between the first surface and the third surface, which extends in a direction intersecting the first surface. The high-temperature component according to claim 1 or 2.

5. The heat-shielding coating layer is also formed on a portion of the third surface, extending from the second connection point between the third surface and the second surface to the third surface. The high-temperature component according to claim 4.

6. It comprises a plurality of cooling passages extending along the first surface in a direction away from the second surface, The high-temperature component according to claim 1 or 2.

7. The high-temperature component is a segmented body that constitutes a segmented ring of the gas turbine, which is formed in an annular shape along the circumferential direction of the gas turbine. The high-temperature component according to claim 1 or 2.

8. The second surface is located upstream of the first surface in the axial direction of the gas turbine. The first surface faces the tip surface of the rotor blade of the gas turbine in the radial direction of the gas turbine, The position of the axial downstream end of the heat-shielding coating layer formed on the first surface is located upstream in the axial direction from the axial central position of the chip surface. The high-temperature component according to claim 7.

9. A first surface on which an abradable layer is provided, A second surface is continuous with the first surface, intersects with the first surface, and has a heat-shielding coating layer provided on it, Equipped with, The heat-shielding coating layer is formed on a portion of the first surface extending from the first connection point between the first surface and the second surface to the first surface, and is not formed on any other area of ​​the first surface. The abradable layer is formed on the surface of the heat-shielding coating layer in the region where the heat-shielding coating layer is formed on the first surface. High-temperature component, The high-temperature component is a segmented body that constitutes a segmented ring of the gas turbine, which is formed in an annular shape along the circumferential direction of the gas turbine. The second surface is located upstream of the first surface in the axial direction of the gas turbine. The first surface faces the tip surface of the rotor blade of the gas turbine in the radial direction of the gas turbine, The position of the axial downstream end of the heat-shielding coating layer formed on the first surface is located upstream in the axial direction from the axial central position of the chip surface. High-temperature components.

10. A high-temperature component as described in claim 1 or 2, Rotating machinery.

11. A step of forming an abrasive layer on the first surface, A step of forming a heat-shielding coating layer on a second surface that is continuous with the first surface and intersects with the first surface, Equipped with, In the process of forming the heat-shielding coating layer, the heat-shielding coating layer is also formed on a portion of the first surface from the first connection point between the first surface and the second surface to a position midway along the first surface, and not in a region of the first surface that is further from the first connection point than the midway along the first surface. In the step of forming the abradable layer, in the region on the first surface where the heat-shielding coating layer is formed, the abradable layer is formed on the surface of the heat-shielding coating layer. Page 1 is, A first region located between the first connection position and the intermediate position, in which the heat-shielding coating layer and the abradable layer are laminated, A second region located further from the first connection position than the aforementioned intermediate position, in which the abradable layer is directly formed without the heat-shielding coating layer, including A method for manufacturing high-temperature components.

12. In the step of forming the heat-shielding coating layer, the heat-shielding coating layer is formed such that its thickness gradually decreases from the first connection position to the first surface as it moves away from the first connection position. A method for manufacturing a high-temperature component according to claim 11.

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