Manufacturing methods for high-temperature components, rotating machinery, and high-temperature components

Abstract

A high-temperature component, rotating machinery, and a method for manufacturing the high-temperature component are disclosed. One embodiment of the high-temperature component includes: a first surface having a wear-resistant layer; and a second surface continuous with and intersecting the first surface, having a heat-insulating coating. The heat-insulating coating is also formed on a portion of the first surface from a first connection point between the first and second surfaces to the first surface. The wear-resistant layer is formed on the surface of the heat-insulating coating in the region on the first surface where the heat-insulating coating is formed. This allows for effective reduction of heat load while suppressing manufacturing costs.

Description

Technical Field

[0001] This disclosure relates to high-temperature components, rotating machinery, and methods for manufacturing high-temperature components. Background Technology

[0002] For example, in machines such as gas turbines where high-temperature working gases flow inside, the components constituting the machine include high-temperature components that are exposed to the working gases and thus become relatively hot.

[0003] For such high-temperature components, techniques are known, for example, to suppress the temperature rise of the high-temperature component by implementing a heat-insulating coating (see, for example, Patent Document 1).

[0004] Prior art literature

[0005] Patent documents

[0006] Patent Document 1: Japanese Patent Application Publication No. 2012-92824

[0007] For example, even for a high-temperature component, there may be situations where the temperature is higher at the upstream side of the working gas flow direction than at the downstream side, or where the temperature varies from location to location. Therefore, it is desirable to apply a heat-insulating coating to the parts where the temperature tends to be higher, but considering the construction cost of the heat-insulating coating, it is desirable to have a narrow application range. Summary of the Invention

[0008] In view of the above, the object of at least one embodiment of the present disclosure is to provide a high-temperature component that can effectively reduce heat load while suppressing manufacturing costs, and a rotating machine having the high-temperature component.

[0009] (1) The high-temperature component of at least one embodiment of this disclosure includes:

[0010] The first surface has a wear-resistant layer; and

[0011] The second surface, which is continuous with and intersects with the first surface, is provided with a heat-insulating coating.

[0012] The heat-insulating coating is also formed on a portion of the first surface from the first connection point between the first surface and the second surface to the first surface.

[0013] The wearable layer is formed on the surface of the heat-insulating coating in the region on the first surface where the heat-insulating coating is formed.

[0014] (2) The rotating machinery of at least one embodiment of the present disclosure has a high-temperature component with the structure described in (1) above.

[0015] (3) The manufacturing method of the high-temperature component according to at least one embodiment of the present disclosure includes the following steps:

[0016] A wear-resistant layer is formed on the first surface; and

[0017] A heat-insulating coating is formed on a second surface that is continuous with and intersects the first surface.

[0018] In the process of forming the heat-insulating coating, the heat-insulating coating is also formed on a portion of the first surface, within the range from the first connection position between the first surface and the second surface to the first surface.

[0019] In the process of forming the wearable layer, the wearable layer is formed on the surface of the heat insulation coating in the area on the first surface where the heat insulation coating is formed.

[0020] Invention Effects

[0021] According to at least one embodiment of the present disclosure, a high-temperature component capable of effectively reducing heat load while suppressing manufacturing costs, and a rotating machine having the high-temperature component, can be provided. Attached Figure Description

[0022] Figure 1 This is a schematic diagram showing the overall structure of a gas turbine, an example of rotating machinery.

[0023] Figure 2 This is a cross-sectional view showing the gas flow path of a turbine.

[0024] Figure 3 This is a diagram of one of the segmented bodies constituting a segmented ring as viewed from the axial upward flow side.

[0025] Figure 4 yes Figure 3 Sectional view in direction IV-IV.

[0026] Figure 5 yes Figure 4 An enlarged view of part A.

[0027] Figure 6 This is a diagram showing the segment of one embodiment viewed from the radial inside.

[0028] Figure 7 yes Figure 6 Sectional view along line VII-VII.

[0029] Figure 8 This is a flowchart illustrating the manufacturing sequence of a segment in one embodiment.

[0030] Explanation of reference numerals in the attached figures:

[0031] 1...High-temperature components;

[0032] 10...gas turbine;

[0033] 11...compressor;

[0034] 13... Turbine;

[0035] 32... Combustion gas flow path;

[0036] 41... Turbine blades (moving blades);

[0037] 41t...blade end face;

[0038] 50...segmentation ring;

[0039] 51...segmentation;

[0040] 53...Main body;

[0041] 61...Axial cooling passage (cooling passage);

[0042] 71... Adhesive coating;

[0043] 73... Thermal Barrier Coating (TBC);

[0044] 75...Abrasion-resistant layer;

[0045] 77...groove section;

[0046] 521...First connection position;

[0047] 522...Second connection position;

[0048] 531...First page;

[0049] 532...Second page;

[0050] 533... Third page. Detailed Implementation

[0051] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. The dimensions, materials, shapes, and relative arrangements of the constituent components described in the embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0052] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" indicate relative or absolute configurations, not only in a strict sense, but also in a state of relative displacement by angle or distance with tolerance or to the extent that the same function can be obtained.

[0053] For example, expressions such as "same," "equal," and "homogeneous" that indicate the state of equality of things not only indicate a state of strict equality, but also indicate a state of difference in the degree to which the same function can be obtained due to the existence of tolerances.

[0054] For example, the descriptions of shapes such as quadrilaterals and cylindrical shapes not only refer to quadrilaterals and cylindrical shapes in a strict geometric sense, but also to shapes that include concave and convex parts, chamfered parts, etc., within the range where the same effect can be obtained.

[0055] On the other hand, expressions such as "possessing," "containing," "equipped with," "including," or "having" a constituent element are not exclusive expressions that exclude the existence of other constituent elements.

[0056] Figure 1 This is a schematic diagram showing the overall structure of a gas turbine, an example of rotating machinery. Figure 2 This is a cross-sectional view showing the gas flow path of a turbine.

[0057] In this embodiment, such as Figure 1 As shown, the gas turbine 10 is constructed by coaxially arranging the compressor 11, burner 12, and turbine 13 on a rotor 14, with a generator 15 connected to one end of the rotor 14. It should be noted that, in the following description, the direction in which the axis of the rotor 14 extends is defined as axial direction Da, the circumferential direction centered on the axis of the rotor 14 is defined as circumferential direction Dc, and the direction perpendicular to the axis Ax of the rotor 14 is defined as radial direction Dr.

[0058] Compressor 11 compresses air AI drawn in from the air inlet through multiple stationary and moving vanes, thereby generating high-temperature, high-pressure compressed air AC. Combustor 12 supplies a specified amount of fuel FL to the compressed air AC and combusts it, thereby generating high-temperature, high-pressure combustion gas FG. Turbine 13 drives rotor 14 to rotate through multiple stationary and moving vanes, thereby driving generator 15 connected to rotor 14.

[0059] In addition, such as Figure 2As shown, in the turbine 13, the turbine stator blade 21 is configured such that the hub side of the airfoil 23 is fixed to the inner shroud 25 and the front end side is fixed to the outer shroud 27. The turbine rotor blade 41 is configured such that the base end of the airfoil 43 is fixed to the platform 45. Furthermore, the outer shroud 27 and the dividing ring 50 disposed on the front end side of the rotor blade 41 are supported in the turbine housing 30 via the heat insulation ring 54, and the inner shroud 25 is supported by the support ring 31. Therefore, the 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 dividing ring 50.

[0060] It should be noted that the inner shield 25, the outer shield 27, and the dividing ring 50 function as gas passage surface forming components. A gas passage surface forming component refers to a component that has a gas passage surface that divides the combustion gas flow path 32 and contacts the combustion gas FG.

[0061] The burner 12, moving blades 41 (e.g., platform 45), stationary blades 21 (e.g., inner shroud 25, outer shroud 27), and dividing ring 50 are high-temperature components 1 that come into contact with the combustion gas FG and are used in high-temperature environments, requiring cooling by a cooling medium. In the following description, as an example of a cooling structure for the high-temperature component 1, the cooling structure of the dividing ring 50 of the gas turbine 10, which is composed of multiple dividing bodies 51 arranged in a ring along the circumferential direction Dc, will be described.

[0062] Figure 3 This is a diagram showing one of the segmented bodies 51 constituting a segmented ring 50 in one embodiment, viewed from the upstream side of the axial direction Da.

[0063] Figure 4 yes Figure 3 Sectional view in direction IV-IV.

[0064] Figure 5 yes Figure 4 An enlarged view of part A.

[0065] Figure 6 This is a diagram showing the segment 51 of one embodiment viewed from the radial inside of Dr.

[0066] Figure 7 yes Figure 6 Sectional view along line VII-VII.

[0067] (Regarding segmentation 51)

[0068] In one embodiment, the dividing ring 50 is composed of a plurality of dividing bodies 51 arranged in a ring shape on the circumferential direction Dc. For example... Figure 3 and Figure 4As shown, each segment 51 includes a plate-shaped main body 53 with an axial cooling passage 61 inside, and a protrusion 55 protruding radially outward from the main body 53. In one embodiment of the segment 51, the protrusion 55 includes a protrusion 55u on the upstream side of the axial direction Da and a protrusion 55d on the downstream side of the axial direction Da.

[0069] In addition, in one embodiment of the split body 51, two wall portions 56 that connect the protrusion 55u on the upstream side of the axial direction Da and the protrusion 55d on the downstream side of the axial direction Da are provided near the end of the circumferential direction Dc.

[0070] In one embodiment of the partition body 51, a recessed portion, namely a space portion 57, is formed, which is surrounded by a protrusion 55u on the upstream side of the axial direction Da, a protrusion 55d on the downstream side of the axial direction Da, and two wall portions 56 and is recessed in the radially inward direction Dr.

[0071] like Figure 2 As shown, in one embodiment, the partition 51 is arranged such that its inner surface 511, which is radially inner to the inside of the combustion gas, faces the combustion gas flow path 32 through which the combustion gas FG flows. On the radially inner side of the main body 53, within a certain gap, moving blades 41 that rotate around the rotor 14 are arranged. To suppress the temperature rise caused by the heat input from the high-temperature combustion gas FG, a plurality of axial cooling passages 61 extending along the axial direction Da are formed in the main body 53.

[0072] Multiple axial cooling passages 61 are arranged in parallel on the circumferential Dc.

[0073] like Figure 4 As shown, in one embodiment, the split body 51 has a manifold 63 extending circumferentially on the main body 53 on the upstream side of the axial direction Da, near the protrusion 55u on the upstream side of the axial direction Da.

[0074] The upstream end 61u of the axial cooling passages 61 on the axial Da side is connected to the manifold 63. The downstream end 61d of the axial cooling passages 61 on the axial Da side opens at the end face 53d of the main body 53 on the downstream side of the axial Da side.

[0075] In one embodiment, the partition 51 is formed with a plurality of air passages 65 that connect the space portion 57 to the manifold 63.

[0076] Although not illustrated, in one embodiment of the gas turbine 10, each of the segmented sections 51 is configured to supply cooling air CA from the radially outer side of the main body 53 to the space section 57. The cooling air CA supplied to the space section 57 is supplied to the manifold 63 via the air passage 65.

[0077] The cooling air CA supplied to the manifold 63 is distributed to each axial cooling passage 61 and flows in each axial cooling passage 61, and is discharged from the end 61d on the downstream side of the axial Da into the combustion gas FG. In this process, the main body 53 of the split body 51 is convectively cooled.

[0078] One embodiment of the segment 51 has a first surface 531, which is the radially inner side of the main body 53 made of metal substrate, a third surface 533, which is the end surface 53u on the axial Da upstream side 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.

[0079] In one embodiment of the partition 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.

[0080] In one embodiment of the partition 51, an adhesive coating 71 is formed on the first surface 531, the second surface 532, and the third surface 533 near the second connection position 522. The adhesive coating 71 is composed, for example, of an MCrAlY alloy (M represents metallic elements such as Ni, Co, and Fe, or a combination of two or more of them).

[0081] (Heat insulation coating 73)

[0082] In one embodiment of the partition 51, a thermal barrier coating (TBC) 73 is formed on the adhesive coating 71 of the second surface 532.

[0083] The heat-insulating coating 73 is preferably a ceramic layer composed of ZrO2-based materials, such as ZrO2 partially or fully stabilized with Y2O3, i.e., YSZ (yttrium-stabilized zirconium oxide).

[0084] In one embodiment of the partition 51, the heat-insulating coating 73 is also formed in a portion R1 of the first surface 531, extending from the first connection position 521 between the first surface 531 and the second surface 532 to the first surface 531. It should be noted that in another embodiment of the partition 51, the heat-insulating coating 73 is not formed in the region R2 outside the portion R1 of the first surface 531 extending from the first connection position 521 to the first surface 531.

[0085] In one embodiment of the partition 51, the heat insulation coating 73 is also formed in a portion of region R3 of the third surface 533 from the second connection position 522 of the second surface 532 and the third surface 533 to the third surface 533.

[0086] The heat-insulating coating 73 has a uniform thickness on the second surface 532. In addition, the heat-insulating coating 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 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.

[0087] (Abrasion-resistant layer 75)

[0088] In one embodiment of the segment 51, an abrasive layer 75 is formed on the adhesive coating 71 of the first surface 531.

[0089] In one embodiment of the segment 51, the first surface 531 is opposite the blade tip surface 41t of the moving blade 41 in the radial direction Dr. Therefore, even if the gap between the wearable layer 75 of the first surface 531 and the blade tip surface 41t of the moving blade 41 is set to be relatively narrow and the wearable layer 75 of the first surface 531 and the blade tip surface 41t of the moving blade 41 may come into contact, although the wearable layer 75 is cut and thinned, the segment 51 and the moving blade 41 can be protected from damage.

[0090] The wearable layer 75 is preferably a ceramic layer made of the same material as the heat-insulating coating 73, namely a ZrO2-based material, such as ZrO2 partially or fully stabilized with Y2O3, namely YSZ (yttrium-stabilized zirconium oxide).

[0091] In one embodiment of the segment 51, the wearable layer 75 is formed on the surface of the heat insulation coating 73 in the region R1 on the first surface 531 where the heat insulation coating 73 is formed.

[0092] The wearable layer 75 formed on the surface of the heat insulation coating 73 on the first surface 531 is formed such that its thickness gradually decreases as it approaches the first connection position 521.

[0093] It should be noted that, preferably, in the region (hereinafter referred to as the overlapping region OR) where the heat insulation coating 73 and the wearable layer 75 are formed on the first surface 531, the thickness of the heat insulation coating 73 and the wearable layer 75 is formed to gradually vary along the axial direction Da, so that the distance between the surface 75a (the surface inside the radial direction Dr) of the wearable layer 75 and the first surface 531 is constant regardless of the position of the axial direction Da.

[0094] In one embodiment of the segment 51, the wearable layer 75 may be provided only on the first surface 531, and not on the second surface 532 and the third surface 533.

[0095] In one embodiment of the segment 51, the wearable layer 75 is formed with a plurality of grooves 77 to improve machinability. The grooves 77 preferably extend along the first surface 531 in a direction inclined relative to the axial direction Da and the circumferential direction Dc.

[0096] It should be noted that at the bottom 77a of the groove 77, the adhesive coating 71 that is in contact with the wearable layer 75 may or may not be exposed.

[0097] In one embodiment of the segment 51, the overlapping region OR preferably does not overlap with the blade tip face 41t of the moving blade 41 in the axial direction Da, but it may partially overlap. It should be noted that the overlapping region OR is preferably located at least upstream of the central position Cp of the axial direction Da of the blade tip face 41t of the moving blade 41. That is, the downstream end of the heat-insulating coating 73 formed on the first surface 531 is preferably located upstream of the central position Cp of the axial direction Da of the blade tip face 41t of the moving blade 41.

[0098] In one embodiment of the segment 51, by having the above-described structure, the following effects are achieved.

[0099] That is, in one embodiment, the segment 51 includes a first surface 531 on which a wearable layer 75 is provided, and a second surface 532 that is continuous with and intersects the first surface 531 and is provided with a heat-insulating coating 73. The heat-insulating coating 73 is also formed on a portion 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. The wearable layer 75 is formed on the surface of the heat-insulating coating 73 in the region R1 on the first surface 531 where the heat-insulating coating 73 is formed.

[0100] The second surface 532 of the partition 51 faces the combustion gas flow path 32 and is upstream of the flow of combustion gas FG. Therefore, it has a larger heat load and its temperature is more likely to rise compared with other areas.

[0101] According to one embodiment of the partition body 51, heat input from the second surface 532 can be suppressed by the heat-insulating coating 73. Furthermore, the heat-insulating coating 73 is not formed in the region downstream of the overlapping region OR of the first surface 531 along the axial direction Da (i.e., the aforementioned region R2), thereby reducing the construction cost of the heat-insulating coating 73. Thus, a partition body 51 that effectively reduces heat load while suppressing manufacturing costs can be provided.

[0102] One embodiment of the gas turbine 10 includes the partition 51 described in one embodiment above.

[0103] Therefore, it is possible to effectively 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.

[0104] In one embodiment of the segment 51, it is preferable that the thickness of the heat-insulating coating 73 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.

[0105] Therefore, compared to cases where, for example, the thickness of the heat insulation coating 73 decreases sharply at a location far from the first connection position 521, the wearable layer 75 formed on the surface of the heat insulation coating 73 is not easily peeled off from the heat insulation coating 73.

[0106] In one embodiment of the segment 51, it is preferable that the wearable layer 75 formed on the surface of the heat-insulating coating 73 on the first surface 531 gradually decreases in thickness as it approaches the first connection position 521 along the axial direction Da.

[0107] Therefore, compared to cases where the thickness of the wearable layer 75 decreases sharply at a certain location near the first connection position 521, the wearable layer 75 formed on the surface of the heat insulation coating 73 is not easily peeled off from the heat insulation coating 73.

[0108] In one embodiment of the partition 51, it is preferable that the second surface 532 is a chamfered surface formed between the third surface 533, which extends in a direction intersecting the first surface 531, and the first surface 531.

[0109] Combustion gas FG flows along the surface of the first surface 531, and the third surface 533 is located upstream of the flow direction of combustion gas FG. Therefore, by forming a chamfered surface, namely the second surface 532, between the third surface 533 and the first surface 531, the heat input from combustion gas FG to the split body 51 can be suppressed.

[0110] In one embodiment of the segment 51, preferably, the heat-insulating coating 73 is also formed on a portion of the third surface 533 from the second connection position 522 of the third surface 533 and the second surface 532 to the third surface 533.

[0111] This allows for the suppression of heat input from the third surface 533.

[0112] In one embodiment of the partition 51, it is preferable to have a plurality of axial cooling passages 61 extending along the first surface 531 in a direction away from the second surface 532.

[0113] Therefore, it is possible to suppress the temperature rise of the first surface 531.

[0114] In one embodiment, the high-temperature component 1 may also be a segment 51 that constitutes a segment ring 50 of the gas turbine 10 formed in a ring shape along the circumferential direction Dc of the gas turbine 10.

[0115] Therefore, it is possible to provide a split body 51 that can effectively reduce heat load while suppressing manufacturing costs.

[0116] In one embodiment of the segment 51, it is preferable that the second surface 532 is located upstream of the first surface 531 in the axial direction Da. Preferably, the first surface 531 is opposite the blade tip surface 41t of the moving blade 41 in the radial direction Dr. Preferably, the downstream end of the heat-insulating coating 73 formed on the first surface 531 in the axial direction Da, i.e., the downstream end of the overlapping region OR, is located upstream of the blade tip surface 41t in the axial direction Da, compared to the central position Cp of the blade tip surface 41t in the axial direction Da.

[0117] Therefore, since the second surface 532 is located upstream of the first surface 531 in the axial direction Da, it tends to have a higher temperature than the first surface 531, but the heat input from the second surface 532 can be suppressed by the heat insulation coating 73.

[0118] Furthermore, the first surface 531 and the blade tip surface 41t of the moving blade 41 are opposite each other in the radial direction Dr. Therefore, even if the gap between the wearable layer 75 of the first surface 531 and the blade tip surface 41t of the moving blade 41 is set to be relatively narrow and the wearable layer 75 of the first surface 531 and the blade tip surface 41t of the moving blade 41 may come into contact, although the wearable layer 75 is cut and thinned, the split body 51 and the moving blade 41 can still avoid damage.

[0119] Furthermore, on the first surface 531, in the region (region R2) downstream of the axial direction Da compared to the overlapping region OR, the heat insulation coating 73 is not formed. Therefore, the construction cost of the heat insulation coating 73 can be suppressed, and the risk of contact between the heat insulation coating 73 and the blade tip 41t of the moving blade 41 can be reduced, thus suppressing damage to the heat insulation coating 73 and the moving blade 41.

[0120] (Manufacturing method of high-temperature component 1)

[0121] Hereinafter, one embodiment of the manufacturing method of the high-temperature component 1 will be described.

[0122] In the following description, the manufacturing method of the segment 51 of the above-described embodiment will be used as an example to illustrate the manufacturing method of the high-temperature component 1.

[0123] Figure 8 This is a flowchart illustrating the manufacturing sequence of the segment 51 of one embodiment described above.

[0124] One embodiment of the manufacturing method of the segment 51 includes a step S1 of forming an adhesive coating 71, a step S3 of forming a heat-insulating coating 73, a step S5 of forming a wearable layer 75, a step S7 of forming a groove 77, and a step S9 of removing resin.

[0125] (Step S1 for forming the adhesive coating 71)

[0126] Step S1, which forms the adhesive coating 71, is a step of forming the adhesive coating 71 on the surface of the main body 53 of the segment 51.

[0127] In step S1 of forming the adhesive coating 71, the aforementioned MCrAlY alloy or other spray powder is sprayed onto the surface of the main body 53, specifically the first surface 531, the second surface 532, and the third surface 533 near the second connection position 522, thereby forming the adhesive coating 71.

[0128] (Step S3 for forming the heat-insulating coating 73)

[0129] Step S3, which forms the heat-insulating coating 73, is a step of forming the heat-insulating coating 73 on a second surface 532 that is continuous with and intersects the first surface 531.

[0130] In step S3, the heat insulation coating 73 is formed by spraying a spraying powder, for example, containing the ZrO2-based material described above, onto the adhesive coating 71 of the second surface 532, thereby forming the heat insulation coating 73.

[0131] It should be noted that in step S3 of forming the heat-insulating coating 73, for example, when the first surface 531, which is downstream of the first connection position 521 in the axial direction Da, is not masked, and the plating powder is sprayed onto the adhesive coating 71 on the second surface 532, it is permissible to blow the plating powder onto the first surface 531 to form the heat-insulating coating 73 on the first surface 531. Thus, in step S3 of forming the heat-insulating coating 73, the heat-insulating coating 73 is also formed on a portion (region R1) of the first surface 531 within the range from the first connection position 521 between the first surface 531 and the second surface 532 to the first surface 531.

[0132] Thus, as described above, the heat-insulating coating 73 is formed such that its thickness gradually decreases as it moves away from the first connection position 521 along the axial direction Da within the range from the first connection position 521 to the first surface 531.

[0133] Similarly, in step S3 of forming the heat-insulating coating 73, for example, when the third surface 533, which is radially outside the second connection position 522, is not masked, and plating powder is sprayed onto the adhesive coating 71 of the second surface 532, plating powder is allowed to be blown onto the third surface 533 to form the heat-insulating coating 73 on the third surface 533. Thus, in step S3 of forming the heat-insulating coating 73, the heat-insulating coating 73 is also formed on a portion of the third surface 533 within the range from the second connection position 522 of the second surface 532 and the third surface 533 to the third surface 533.

[0134] Thus, as described above, the heat-insulating coating 73 is formed such that, within the range from the second connection position 522 to the third surface 533, the thickness gradually decreases as it moves away from the second connection position 522 along the radial direction Dr.

[0135] (Process S5 for forming the wear-resistant layer 75)

[0136] The process S5 for forming the wearable layer 75 is the process of forming the wearable layer 75 on the first surface 531.

[0137] In step S5, the wearable layer 75 is formed by spraying a mixture of spray powder containing, for example, the ZrO2-based material described above and resin powder such as polyester onto the adhesive coating 71 on the first surface 531.

[0138] It should be noted that in step S5, which forms the wearable layer 75, the wearable layer 75 containing a resin such as polyester is uniformly formed on the first surface 531 (i.e., in the absence of the groove 77).

[0139] (Process S7 for forming groove 77)

[0140] The process S7 for forming the groove 77 is the process of forming the groove 77 on the wearable layer 75 uniformly formed on the first surface 531 after the process S5 for forming the wearable layer 75.

[0141] The process S7 of forming the groove 77 is to form the groove 77 by performing cutting processing, such as water jet processing, on the wearable layer 75 uniformly formed on the first surface 531.

[0142] (S9, resin removal process)

[0143] The resin removal process S9 is a process of removing resin from the abrasive layer 75 containing resins such as polyester.

[0144] In the resin removal process S9, the segment 51, which was subjected to the process S7 in which the groove 77 was formed, is subjected to heat treatment by heating, thereby removing the resin contained in the wearable layer 75.

[0145] As described above, a method for manufacturing a high-temperature component 1 according to one embodiment includes a step S5 of forming a wearable layer 75 on a first surface 531, and a step S3 of forming a heat-insulating coating 73 on a second surface 532 that is continuous with and intersects the first surface 531. In step S3 of forming the heat-insulating coating 73, the heat-insulating coating 73 is also formed on a portion (region R1) of the first surface 531 from the first connection position 521 of the first surface 531 and the second surface 532 to the first surface 531. In step S5 of forming the wearable layer 75, the wearable layer 75 is formed on the surface of the heat-insulating coating 73 in the region R1 of the first surface 531 where the heat-insulating coating 73 is formed.

[0146] According to a manufacturing method of a high-temperature component 1 according to one embodiment, a high-temperature component 1 can be provided that can suppress heat input from the second surface 532 by means of a heat-insulating coating 73 when there is a tendency for the temperature of the second surface 532 to be higher than that of the first surface 531. Furthermore, in the range from the first connection position 521 to the first surface 531, except for a portion of the first surface 531 (region R1), the heat-insulating coating 73 is not formed on the first surface 531, thereby reducing the construction cost of the heat-insulating coating 73. Thus, a high-temperature component 1 that can effectively reduce heat load while suppressing manufacturing costs can be provided.

[0147] In step S3 of forming the heat insulation coating, it is preferable to form the heat insulation coating 73 in such a way that the thickness gradually decreases as it moves away from the first connection position 521 to the first surface 531.

[0148] Therefore, compared to the case where the heat insulation coating 73 is formed in such a way that the thickness of the heat insulation coating 73 decreases sharply at a location far from the first connection position 521, the wearable layer 75 formed on the surface of the heat insulation coating 73 is not easily peeled off from the heat insulation coating 73.

[0149] This disclosure is not limited to the above-described embodiments, but also includes methods obtained by modifying the above-described embodiments and methods obtained by appropriately combining these methods.

[0150] For example, in one embodiment of the partition 51, the second surface 532, which serves as a chamfered surface, may not be formed. In this case, the first surface 531 and the third surface 533 are directly connected. Moreover, in this case, the radially inner region of the third surface 533, where the temperature tends to be relatively high, is considered to be the same region as the second surface 532 described above (hereinafter referred to as the hypothetical second region), and a heat-insulating coating 73 may be provided in this hypothetical second region. Furthermore, it is preferable that the heat-insulating coating 73 is also formed on a portion of the first surface 531 from the connection point between the first surface 531 and the hypothetical second region to the first surface 531. The wear-resistant layer 75 is preferably formed on the surface of the heat-insulating coating 73 in the region of the first surface 531 where the heat-insulating coating 73 is formed.

[0151] The contents described in the above embodiments shall be understood as follows.

[0152] (1) The high-temperature component 1 (segment 51) of at least one embodiment of the present disclosure includes: a first surface 531 on which a wearable layer 75 is provided; and a second surface 532 continuous with and intersecting the first surface 531, on which a heat-insulating coating 73 is provided. The heat-insulating coating 73 is also formed on a portion 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. The wearable layer 75 is formed on the surface of the heat-insulating coating 73 in the region R1 of the first surface 531 in which the heat-insulating coating 73 is formed.

[0153] According to the structure described in (1) above, in cases where 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-insulating coating 73. Furthermore, if the heat-insulating coating 73 is not formed on the remaining portion (i.e., region R2) of the first surface 531 relative to the aforementioned portion (i.e., region R1), the construction cost of the heat-insulating coating 73 can be reduced. Thus, a high-temperature component 1 (segment 51) that effectively reduces heat load while suppressing manufacturing costs can be provided.

[0154] (2) In several embodiments, based on the structure of (1) above, it is preferable that the thickness of the heat insulation coating 73 gradually decreases as it moves away from the first connection position 521 to the first surface 531.

[0155] According to the structure described in (2) above, compared to the case where the thickness of the heat insulation coating 73 decreases sharply at a location far from the first connection position 521, the wearable layer 75 formed on the surface of the heat insulation coating 73 is not easily peeled off from the heat insulation coating 73.

[0156] (3) In several embodiments, based on the structure of (2) above, it is preferable that the wearable layer 75 formed on the surface of the heat insulation coating 73 on the first surface 531 gradually decreases in thickness as it approaches the first connection position 521.

[0157] According to the structure described above (3), compared to the case where the thickness of the wearable layer 75 decreases sharply at a certain position near the first connection position 521, the wearable layer 75 formed on the surface of the heat insulation coating 73 is not easily peeled off from the heat insulation coating 73.

[0158] (4) In several embodiments, based on any of the structures in (1) to (3) above, it is preferred that the second surface 532 is a chamfered surface formed between the third surface 533, which extends in a direction intersecting the first surface 531, and the first surface 531.

[0159] According to the structure described above (4), 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 of the flow direction of the working gas (combustion gas FG), then by forming a chamfered surface, namely 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 (segment 51) can be suppressed.

[0160] (5) In several embodiments, based on the structure of (4) above, it is preferred that the heat insulation coating 73 is also formed on a portion (region R3) of the third surface 533 from the second connection position 522 of the third surface 533 and the second surface 532 to the third surface 533.

[0161] According to the structure described in (5) above, heat input from the third surface 533 can be suppressed.

[0162] (6) In several embodiments, based on any of the structures in (1) to (5) above, it is preferable to have a plurality of cooling passages (axial cooling passages 61) extending along the first surface 531 in a direction away from the second surface 532.

[0163] According to the structure described in (6), the temperature rise of the first surface 531 can be suppressed.

[0164] (7) In several embodiments, based on any of the structures in (1) to (6) above, it is preferred that the high-temperature component 1 is a segment 51 constituting a segment ring 50 of the gas turbine 10 formed in an annular shape along the circumferential direction Dc of the gas turbine 10.

[0165] According to the structure described in (7), the partition 51 has any of the structures described in (1) to (6) and can provide a partition 51 that can effectively reduce heat load while suppressing manufacturing costs.

[0166] (8) In several embodiments, based on the structure described in (7) above, it is preferable that the second surface 532 is located upstream of the first surface 531 in the axial direction Da of the gas turbine 10. Preferably, the first surface 531 is opposite to the blade tip face 41t of the moving blade 41 of the gas turbine 10 in the radial direction Dr of the gas turbine 10. Preferably, the downstream end of the heat insulation coating 73 formed on the first surface 531 is located upstream of the axial direction Da, which is closer to the center position Cp of the blade tip face 41t in the axial direction Da.

[0167] According to the structure described above (8), the second surface 532 tends to have a higher temperature than the first surface 531 because it is located upstream of the axial direction Da of the gas turbine 10 relative to the first surface 531, but the heat input from the second surface 532 can be suppressed by the heat insulation coating 73.

[0168] According to the structure described in (8) above, the first surface 531 and the blade tip face 41t of the moving blade 41 of the gas turbine 10 are opposite each other in the radial direction Dr of the gas turbine 10. Therefore, even if the gap between the wearable layer 75 of the first surface 531 and the blade tip face 41t of the moving blade 41 is set to be relatively narrow, the wearable layer 75 of the first surface 531 and the blade tip face 41t of the moving blade 41 may come into contact. Although the wearable layer 75 is cut and thinned, the high-temperature component 1 (segment 51) and the moving blade 41 can be protected from damage.

[0169] Furthermore, according to the structure described above (8), if the heat insulation coating 73 is not formed on the remaining part (region R2) of the first surface 531 relative to the aforementioned part (region R1), the construction cost of the heat insulation coating 73 can be suppressed, and the risk of contact between the heat insulation coating 73 and the blade tip 41t of the moving blade 41 can be reduced, thereby suppressing damage to the heat insulation coating 73 and the moving blade 41.

[0170] (9) The rotating machinery (gas turbine 10) of at least one embodiment of the present disclosure has a high-temperature component 1 with any of the structures in (1) to (8) above.

[0171] According to the structure described above (9), the heat load can be effectively reduced while suppressing the manufacturing cost of the high-temperature component 1 of the rotating machinery (gas turbine 10), and the reliability of the rotating machinery (gas turbine 10) can be improved while suppressing the manufacturing cost of the rotating machinery (gas turbine 10).

[0172] (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 a wearable layer 75 on a first surface 531, and a step S3 of forming a heat-insulating coating 73 on a second surface 532 that is continuous with and intersects the first surface 531. In step S3 of forming the heat-insulating coating 73, the heat-insulating coating 73 is also formed in a portion (region R1) 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 step S5 of forming the wearable layer 75, the wearable layer 75 is formed on the surface of the heat-insulating coating 73 in the region R1 on the first surface 531 where the heat-insulating coating 73 is formed.

[0173] According to the method described in (10) above, a high-temperature component 1 can be provided that, even when the temperature of the second surface 532 tends to be higher than that of the first surface 531, can suppress heat input from the second surface 532 through the heat-insulating coating 73. Furthermore, if the heat-insulating coating 73 is not formed on the remaining portion (region R2) of the first surface 531 relative to the aforementioned portion (region R1), the construction cost of the heat-insulating coating 73 can be reduced. Thus, a high-temperature component 1 can be provided that effectively reduces heat load while suppressing manufacturing costs.

[0174] (11) In several embodiments, based on the method described in (10) above, it is preferable that, in the step S3 of forming the heat insulation coating 73, the heat insulation coating 73 is formed in such a way that the thickness gradually decreases as it moves away from the first connection position 521 to the first surface 531.

[0175] According to the method described in (11) above, compared to the case where the heat insulation coating 73 is formed in such a way that the thickness of the heat insulation coating 73 decreases sharply at a location far from the first connection position 521, the wearable layer 75 formed on the surface of the heat insulation coating 73 is not easily peeled off from the heat insulation coating 73.

Claims

1. A high-temperature component, wherein, The high-temperature component includes: The first surface has a wear-resistant layer; and The second surface, which is continuous with and intersects with the first surface, is provided with a heat-insulating coating. The heat-insulating coating is also formed on a portion of the first surface from the first connection point between the first surface and the second surface to the first surface. The wearable layer is formed on the surface of the heat-insulating coating in the region on the first surface where the heat-insulating coating is formed. The thickness of the heat-insulating coating gradually decreases as it moves away from the first connection position from the first connection position to the first surface.

2. The high-temperature component according to claim 1, wherein, The wearable layer formed on the surface of the heat-insulating coating on the first surface gradually decreases in thickness as it approaches the first connection location.

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

4. The high-temperature component according to claim 3, wherein, The heat-insulating coating is also formed on a portion of the third surface from the second connection position between the third surface and the second surface to the third surface.

5. The high-temperature component according to claim 1 or 2, wherein, The high-temperature component has multiple cooling channels extending along the first surface in a direction away from the second surface.

6. The high-temperature component according to claim 1 or 2, wherein, The high-temperature component is a segment that forms a segmented ring of the gas turbine, which is formed in a ring shape along the circumference of the gas turbine.

7. The high-temperature component according to claim 6, wherein, The second surface is located upstream of the first surface along the axial direction of the gas turbine. The first surface is opposite the blade tip face of the moving blade of the gas turbine in the radial direction of the gas turbine. The downstream end of the heat-insulating coating formed on the first surface is located on the upstream side of the axial direction, which is closer to the center position of the blade end face in the axial direction.

8. A rotating machine, wherein, The rotating machinery includes a high-temperature component as described in any one of claims 1 to 3.

9. A method for manufacturing a high-temperature component, wherein, The manufacturing method of the high-temperature component includes the following steps: A wear-resistant layer is formed on the first surface; and A heat-insulating coating is formed on a second surface that is continuous with and intersects the first surface. In the process of forming the heat-insulating coating, the heat-insulating coating is also formed on a portion of the first surface, within the range from the first connection position between the first surface and the second surface to the first surface. In the process of forming the wearable layer, in the area on the first surface where the heat-insulating coating is formed, the wearable layer is formed on the surface of the heat-insulating coating. In the process of forming the heat-insulating coating, the heat-insulating coating is formed in such a way that its thickness gradually decreases as it moves away from the first connection position from the first connection position to the first surface.

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