JP5550699B2 - Gas turbine components - Google Patents

Description

  The present invention relates to a gas turbine member.

  The gas turbine includes a compressor, a combustor, and a turbine. The combustor combusts air and fuel compressed by the compressor, and the generated high-temperature and high-pressure gas (combustion gas) is generated by the turbine. Inflate to generate power. During operation of the gas turbine, if the temperature of the surface of the member inside the gas turbine to be heated rises excessively, there may be a problem such as deterioration of the surface of the member. Therefore, conventionally, various techniques have been devised for suppressing the temperature rise of the surface of the member inside the gas turbine to be heated. The following patent document discloses an example of a technique for supplying a cooling medium from a hole provided in a part of a blade and film cooling the blade surface.

JP 2001-173405 A

  In film cooling, if the cooling medium from the hole provided in a part of the blade does not stay near the surface of the member but penetrates the combustion gas, it may be difficult to suppress the temperature rise on the surface of the member. There is. Further, a smaller coolant flow rate is preferable because the performance of the gas turbine is improved.

  An object of this invention is to provide the member for gas turbines which can protect the surface of a member from combustion gas effectively using a cooling medium, and can suppress the fall of the performance of a gas turbine.

According to the first aspect of the present invention, a base material, a recess formed on the surface of the base material, an air supply port arranged inside the recess, and a surface of the base material around the recess A heat shield having an overhang portion that is supported by the base material so as to cover the first region, overhangs from the first region to the concave portion and faces the air supply port at a position away from the air supply port. The first region is disposed on one side in a first direction substantially parallel to the surface of the substrate with respect to the recess, and the overhanging portion is disposed on the other side in the first direction. A gas turbine member is provided that extends , the recess is long in a second direction intersecting the first direction, and a plurality of the air supply ports are arranged in the second direction at a predetermined interval .
Moreover, according to the 1st aspect of this invention, the base material, the recessed part formed in the surface of the said base material, the air supply opening arrange | positioned inside the said recessed part, and the said base material around the said recessed part An overhang portion that is supported by the base material so as to cover the first region on the surface of the surface, overhangs from the first region to the concave portion, and faces the air supply port at a position away from the air supply port. A heat shielding film, wherein the first region is disposed on one side in a first direction substantially parallel to the surface of the base material with respect to the recess, and the overhang portion is located in the other direction of the first direction. A gas turbine member provided with a linear reinforcing member that extends to the side and extends over the overhang portion and a base portion of the heat shield film connected to the first region and reinforces the heat shield film is provided. Is done.

According to the first aspect of the present invention, the air supply port is provided inside the recess, and the heat shield film having the overhang portion facing the air supply port is provided at a position away from the air supply port. The cooling medium supplied from the air vent hits the overhang portion. Therefore, it is possible to prevent the cooling medium supplied from the air supply port from penetrating the combustion gas without staying in the vicinity of the surface of the member. Further, the cooling medium supplied from the air supply port can be guided to a desired part such as the surface of the member, and the temperature rise at the part can be suppressed. Moreover, it can suppress that the surface of a base material deteriorates with a heat | fever by arrange | positioning a thermal-insulation film | membrane. Further, since the overhang portion is formed of the heat shield film, it can withstand high temperatures. Therefore, the surface of the member can be effectively protected from the combustion gas. In addition, the cooling medium can be used effectively. Therefore, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.
Furthermore, in the gas turbine member according to the first aspect, the first region is a region arranged on one side in the first direction substantially parallel to the surface of the substrate with respect to the recess, and the overhang portion is the first By forming so as to extend to the other side in the direction, the cooling medium supplied from the air supply port can be guided to the other side. When the combustion gas generated in the combustor is supplied to the member from one side in the first direction, a desired portion on the other side with respect to the air supply port can be cooled with a cooling medium from the air supply port. . In addition, the cooling medium can be used effectively. Therefore, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.
In addition, by making the overhang portion longer in the second direction, the cooling medium supplied from each of the plurality of air supply ports can be favorably guided to a desired site by the overhang portion. Further, since the cooling medium can be used effectively, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.
Furthermore, the strength of the heat shield film can be increased by providing a linear reinforcing member that is disposed over the overhang portion and the base of the heat shield film connected to the first region and reinforces the heat shield film. it can.

  In the gas turbine member according to the first aspect, the recess is disposed on one side in the first direction with respect to the air supply port, and the first surface is connected to the first region, and the first direction with respect to the air supply port A second surface which is disposed on the other side and is inclined so as to approach the second region of the surface of the base material disposed on the other side in the first direction with respect to the recess from the air supply port toward the other side. By having it, the cooling medium supplied from the air supply port can smoothly flow to the other side while being guided by the overhang portion and the inclined second surface. Therefore, a desired portion on the other side with respect to the air supply port can be satisfactorily cooled by the cooling medium from the air supply port. In addition, the cooling medium can be used effectively. Therefore, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.

  In the gas turbine member according to the first aspect, by disposing the air supply port on the third surface of the recess between the first surface and the second surface, the cooling medium supplied from the air supply port can be You can get enough inside. That is, since the cooling medium supplied from the air supply port flows out through the concave portion (opening of the concave portion), uneven supply of the cooling medium, and hence generation of uneven cooling can be reduced. Therefore, the desired part can be cooled satisfactorily. In addition, the cooling medium can be used effectively. Therefore, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.

  In the gas turbine member according to the first aspect, the heat shield film includes a first portion having an overhang portion, and a second portion disposed so as to cover the second region and the second surface. From the first part flows out of the gap formed between the edge of the first part and the second part. As a result, it is possible to further reduce the supply unevenness of the cooling medium and the occurrence of the cooling unevenness. Therefore, the desired part can be cooled satisfactorily. In addition, the cooling medium can be used effectively. Therefore, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.

  In the gas turbine member of the first aspect, the surface of the second portion can be favorably cooled by forming the gap so that the gap guides the cooling medium to the surface of the second portion. In addition, the cooling medium can be used effectively. Therefore, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.

  In the gas turbine member of the first aspect, the speed (flow velocity) of the cooling medium flowing out from the gap can be suppressed by making the gap larger than the air supply port. Therefore, it is possible to prevent the cooling medium supplied from the air supply port and flowing out of the gap from penetrating the combustion gas without staying in the vicinity of the surface of the member. In addition, it is possible to further reduce the unevenness in supply of the cooling medium, and hence the occurrence of uneven cooling. Therefore, it is possible to suppress the temperature rise at the desired site. Further, since the cooling medium can be used effectively, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.

  In the gas turbine member according to the first aspect, the overhang portion is elongated in the second direction, so that the cooling medium supplied from each of the plurality of air supply ports can be favorably supplied to the desired portion by the overhang portion. Can be guided to. Further, since the cooling medium can be used effectively, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.

  In the gas turbine member according to the first aspect, by forming a plurality of recesses in the second direction intersecting the first direction at predetermined intervals, for example, the flow rate of the cooling medium can be reduced with respect to the member surface having a pressure distribution. It is possible to adjust and use the cooling medium effectively. Moreover, the flow volume of a cooling medium can be reduced and the performance of a gas turbine can be improved.

  In the gas turbine member according to the first aspect, the strength of the heat shield film can be further increased by disposing the reinforcing member inside the heat shield film.

  According to the present invention, the performance of a gas turbine can be improved.

It is a figure which shows an example of the gas turbine which concerns on 1st Embodiment. It is a figure which shows an example of the wing | blade which concerns on 1st Embodiment. It is a top view which shows a part of wing | blade which concerns on 1st Embodiment. It is a sectional side view which shows a part of wing | blade which concerns on 1st Embodiment. It is a figure for demonstrating an example of the manufacturing method of the wing concerning a 1st embodiment. It is a figure for demonstrating an example of the manufacturing method of the wing concerning a 1st embodiment. It is a figure for demonstrating an example of the manufacturing method of the wing concerning a 1st embodiment. It is a figure for demonstrating an example of the manufacturing method of the wing concerning a 1st embodiment. It is a top view which shows a part of wing | blade which concerns on 2nd Embodiment. It is a sectional side view which shows a part of wing | blade which concerns on 2nd Embodiment. It is a figure for demonstrating an example of the manufacturing method of the wing | blade which concerns on 2nd Embodiment. It is a figure for demonstrating an example of the manufacturing method of the wing | blade which concerns on 2nd Embodiment. It is a figure for demonstrating an example of the manufacturing method of the wing | blade which concerns on 2nd Embodiment. It is a figure for demonstrating an example of the manufacturing method of the wing | blade which concerns on 2nd Embodiment. It is a sectional side view which shows a part of wing | blade which concerns on 3rd Embodiment.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. In the following description, an XYZ orthogonal coordinate system is set, and the positional relationship of each part will be described with reference to this XYZ orthogonal coordinate system. A predetermined direction in the horizontal plane is the X-axis direction, a direction orthogonal to the X-axis direction in the horizontal plane is the Y-axis direction, and a direction orthogonal to each of the X-axis direction and the Y-axis direction (vertical direction, vertical direction) is the Z-axis direction. To do. In addition, the rotation (inclination) directions around the X, Y, and Z axes are the θX, θY, and θZ directions, respectively.

<First Embodiment>
A first embodiment will be described. FIG. 1 is a diagram illustrating an example of a gas turbine 100 according to the first embodiment. In FIG. 1, the gas turbine 100 includes a compressor 1, a combustor 2, and a turbine 3. In addition, the gas turbine 100 includes a compressor 1, a combustor 2, and a rotor 4 disposed at the center of the turbine 3. The compressor 1, the combustor 2, and the turbine 3 are arranged in order from the front side to the rear side of the air flow along the axis R of the rotor 4.

  Here, in the following description, a direction parallel to the axis R is appropriately referred to as an axial direction, and a rotation (tilt) direction around the axis R is appropriately referred to as a circumferential direction.

  The compressor 1 compresses air. The compressor 1 includes a compressor casing 12 having an air intake 11 for taking in air, a compressor vane 13 disposed in the compressor casing 12, and a compressor blade 14 disposed in the compressor casing 12. It has. The compressor vane 13 is attached to the compressor casing 12. A plurality of compressor vanes 13 are arranged in the circumferential direction. The compressor blade 14 is attached to the rotor 4. A plurality of compressor blades 14 are arranged in the circumferential direction. The compressor stationary blades 13 and the compressor rotor blades 14 are alternately arranged in the axial direction.

  The combustor 2 supplies fuel to the air compressed by the compressor 1 (hereinafter referred to as “compressed air”), and ignites with a burner, whereby a high-temperature and high-pressure gas (hereinafter referred to as “combustion gas”). ). The combustor 2 includes an inner cylinder (combustion cylinder) 21 that mixes and burns compressed air and fuel inside having a burner (not shown), and a tail cylinder 22 that guides combustion gas from the inner cylinder 21 to the turbine 3. And an outer cylinder 23 for guiding the compressed air from the compressor 1 to the inner cylinder 21. A plurality of the combustors 2 are arranged in the circumferential direction with respect to the combustor casing 24.

  The turbine 3 generates power by the combustion gas generated by the combustor 2. The turbine 3 includes a turbine casing 31, a turbine stationary blade 32 disposed in the turbine casing 31, and a turbine rotor blade 33 disposed in the turbine casing 31. The turbine stationary blade 32 is attached to the turbine casing 31. A plurality of turbine stationary blades 32 are arranged in the circumferential direction. The turbine rotor blade 33 is attached to the rotor 4. A plurality of turbine blades 33 are arranged in the circumferential direction. These turbine stationary blades 32 and turbine dynamic prizes 33 are alternately arranged in the axial direction. An exhaust chamber 34 having an exhaust diffuser 34 a continuous with the turbine 3 is provided on the rear side of the turbine casing 31.

  The rotor 4 is rotatably supported by the bearings 41 and 42 around the axis R. The bearing 41 is disposed on the compressor 1 side, and the bearing 42 is disposed on the exhaust chamber 34 side. A drive shaft of a generator (not shown) is connected to the end of the rotor 4 on the exhaust chamber 34 side.

  Next, an example of the operation of the gas turbine 100 will be described. The air taken in from the air intake port 11 of the compressor 1 passes through the plurality of compressor stationary blades 13 and the compressor moving blades 14 and is compressed into high-temperature / high-pressure compressed air. And in the combustor 2, a predetermined fuel is supplied with respect to compressed air, and it is burned, A high temperature and a high pressure combustion gas is produced | generated. The combustion gas passes through the turbine stationary blade 32 and the turbine rotor blade 33 of the turbine 3 to rotate the rotor 4. Power is generated by applying power to the generator connected to the rotor 4. The exhaust gas after rotating the rotor 4 is converted into a static pressure by the exhaust diffuser 34a of the exhaust chamber 34 and then released to the atmosphere.

  FIG. 2 is a view showing the turbine rotor blade 33. In FIG. 2, the turbine rotor blade 33 includes a platform 43 and a blade 50 provided on the platform 43. The blade 50 includes a base 51 and a heat shield film 52 formed on at least a part of the surface of the base 51. The blade 50 includes a plurality of air supply ports 53 on the surface. The air supply ports 53 are disposed on the abdomen 50A and the back part 50B of the wing 50, respectively.

  In the present embodiment, high-temperature and high-pressure combustion gas generated in the combustor 2 is supplied to the blade 50 from the front side (+ X side) of the blade 50. The combustion gas supplied to the front edge 50C of the blade 50 flows along the abdomen 50A and the back 50B, and flows backward (−X side) from the rear edge 50D. In the following description, the flow of the combustion gas flowing along the surface of the blade 50 including the abdomen 50A and the back part 50B is appropriately referred to as a main stream 200.

  3 is an enlarged view of a part of the abdomen 50A of the wing 50, and FIG. 4 is a side sectional view of FIG. 2, 3, and 4, the blade 50 includes a base material 51, a concave portion 54 formed on the surface of the base material 51, an air supply port 53 disposed inside the concave portion 54, and a concave portion 54. And a thermal barrier film 52 supported by the substrate 51 so as to cover the first region 61 on the surface of the surrounding substrate 51. The heat shielding film 52 has an overhang portion 52 </ b> H that overhangs from the first region 61 to the recess 54 and faces the air supply port 53 at a position away from the air supply port 53.

  In the following description, for the sake of simplicity, it is assumed that the surface of the blade 50 (the surface of the base material 51) in the abdomen 50A is substantially parallel to the XZ plane. The overhang portion 52H is sufficiently larger than the air supply port 53 in the XZ plane.

  In the present embodiment, the first region 61 on the surface of the substrate 51 is a region disposed on the + X side (front edge portion 50 </ b> C side) in the X-axis direction with respect to the recess 54. The thermal barrier film 52 is supported by the first region 61. In the present embodiment, the thermal barrier film 52 is also disposed in the second region 62 on the surface of the base material 51 disposed on the −X side (the rear edge portion 50D side) with respect to the concave portion 54.

  The concave portion 54 is disposed on the + X side with respect to the air supply port 53, is disposed on the −X side with respect to the first surface 71 connected to the first region 61, and the air supply port 53, and extends from the air supply port 53 to − The second surface 72 is inclined so as to approach the second region 62 toward the X side. The thermal barrier film 52 is also disposed on the second surface 72.

  Further, the recess 54 has a third surface 73 disposed between the first surface 71 and the second surface 72. With respect to the Y-axis direction, the third surface 73 is arranged at a position farthest from the surface (first and second regions 61, 62) of the base member 51 among the first, second and third surfaces 71, 72, 73. Is done. The air supply port 53 is disposed on the third surface 73. In the present embodiment, at least a part of the heat shield film 52 is disposed on the third surface 73. The heat shield film 52 may not be disposed on the third surface 73.

  In the following description, the thermal barrier film 52 having the overhang portion 52H and disposed on the + X side with respect to the concave portion 54 is appropriately referred to as a first portion 521 and covers the second region 62 and the second surface 72. The heat shielding film 52 arranged as described above is appropriately referred to as a second portion 522.

  The overhang portion 52H is disposed so as to extend from the first region 61 in the −X direction. A predetermined gap 58 is formed between the edge of the first portion 521 (the tip of the overhang portion 52H) and the second portion 522. The gap 58 is sufficiently larger than the air supply port 53.

  As shown in FIGS. 2 and 3, the recess 54 is long in the Z-axis direction. A plurality of the recesses 54 are arranged in the X-axis direction in the abdomen 50A between the front edge part 50C and the rear edge part 50D. A plurality of air supply ports 53 are arranged in the Z-axis direction at predetermined intervals inside each of the plurality of recesses 54.

  A plurality of overhang portions 52H are provided so as to correspond to the plurality of recesses 54, respectively. The overhang portion 52H is long in the Z-axis direction.

  Similar to the abdomen 50A, the back part 50B can also be provided with a heat shield film 52 having a recess 54, an air supply port 53, and an overhang part 52H. In the present embodiment, a plurality of air supply ports 53 are also arranged at the front edge portion 50 </ b> C of the blade 50.

  The base material 51 is made of metal. The thermal barrier film 52 is also called TBC (Thermal Barrier Coating) and functions as a protective film for suppressing deterioration of the surface of the substrate 51. When the surface of the base material 51 becomes high temperature, the surface of the base material 51 may be oxidized or deteriorated. The thermal barrier film 52 has at least one of a function of suppressing the oxidation of the surface of the substrate 51 and a function of suppressing an increase in the temperature of the surface of the substrate 51.

  In the present embodiment, the thermal barrier film 52 includes a metal bonding layer 52A formed so as to be in contact with the surface of the substrate 51 and a ceramic layer 52B formed so as to be in contact with the surface of the metal bonding layer 52A. . The metal bonding layer 52 </ b> A has a function of suppressing the oxidation of the base material 51. The metal bonding layer 52A is coated by, for example, a spraying method. The ceramic layer 52 </ b> B has a function of suppressing heat conduction to the base material 51. The ceramic layer 52B is coated by, for example, a thermal spraying method. The metal bonding layer 52A is thinner than the ceramic layer 52B.

  In the present embodiment, the metal bonding layer 52A can be formed of an MCrAlY alloy having excellent corrosion resistance and oxidation resistance. M in the MCrAlY alloy is a single element such as Ni, Co, or Fe, or a combination of two or more elements. In the present embodiment, the ceramic layer 52B is a zirconia ceramic layer. As the zirconia ceramic layer, ZrO2 having a low thermal conductivity and partially stabilized by a stabilizing material such as Y2O3 (addition amount 8 wt%) is used.

  The metal bonding layer 52 </ b> A reduces the difference in linear expansion coefficient between the base material 51 and the ceramic layer 52 </ b> B to relieve thermal stress, and suppresses the ceramic layer 52 </ b> B from peeling from the base material 51. Since the ceramic layer 52B hardly transfers heat to the base material 51 even when a high-temperature gas or the like is blown, it is possible to suppress an increase in the surface temperature of the base material 51.

  The metal bonding layer 52A is sprayed using a low pressure plasma spraying method in a vacuum or a reduced pressure argon atmosphere. The spraying temperature in the low pressure plasma spraying is about 700 to 900 ° C. The ceramic layer 52B is sprayed using an atmospheric pressure plasma spraying method in an air atmosphere. The spraying temperature in atmospheric pressure plasma spraying is about 100 to 500 ° C.

  In the present embodiment, the thermal spraying is performed as described above, and the heat-shielding film 52 is formed by laminating the metal bonding layer 52A and the ceramic layer 52B.

  The air supply port 53 blows out and supplies the cooling medium supplied from the inside of the blade 50 to the outside. In the present embodiment, the cooling medium is a gas. The base material 51 is formed with a hole 59 penetrating the base material 51.

  At least a part of the cooling medium supplied from the air supply port 53 forms a film 90 of the cooling medium on the surface of the blade 50 to suppress the temperature increase of the blade 50. In the present embodiment, air is supplied from the air supply port 53. The cooling medium film 90 formed on the surface of the blade 50 in order to suppress the temperature rise of the blade 50 is also referred to as a cooling film or the like. In the following description, the cooling medium film 90 formed on the surface of the blade 50 by the cooling medium supplied from the air supply port 53 is appropriately referred to as a cooling medium film 90.

  As an example, the size (diameter) of the air supply port 53 is about 0.5 mm to 1.0 mm. The thickness of the thermal barrier film 52 is about 0.3 mm to 0.6 mm. The thickness of the base material 51 is about 3 mm.

  Next, an example of the action of the blade 50 when the cooling medium is supplied from the air supply port 53 will be described. The cooling medium blown out from the air supply port 53 strikes the overhang portion 52H and flows inside the recess 54. The cooling medium supplied from the air supply port 53 and flowing inside the recess 54 flows out from the gap 58 to the outside of the recess 54. The gap 58 is formed so as to guide the cooling medium to the surface of the second portion 522, and the cooling medium flowing out of the gap 58 forms the cooling medium film 90 on the surface of the blade 50 (the surface of the second portion 522). Form. By forming the cooling medium film 90, the main flow 200 (combustion gas) can be prevented from bringing heat to the surface of the blade 50. Therefore, the temperature rise on the surface of the blade 50 can be suppressed.

  According to the present embodiment, the air supply port 53 is provided inside the recess 54, and the heat shield film 52 having the overhang portion 52 </ b> H facing the air supply port 53 at a position away from the air supply port 53 is provided. The cooling medium supplied from the air supply port 53 hits the overhang portion 52H. Therefore, it is possible to suppress the cooling medium supplied from the air supply port 53 from penetrating into the main flow 200 without staying in the vicinity of the surface of the blade 50. In addition, since the overhang portion 52H is formed, the cooling medium supplied from the air supply port 53 can be smoothly guided to the surface of the blade 50, and the temperature rise on the surface of the blade 50 can be suppressed. it can. Moreover, it can suppress that the surface of the base material 51 deteriorates with a heat | fever by arrange | positioning the thermal-insulation film | membrane 52. FIG. Further, since the overhang portion 52H is formed of the heat shield film 52, it can withstand high temperatures.

  In addition, since the overhang portion 52H is sufficiently larger than the air supply port 53, the cooling medium supplied from the air supply port 53 does not stay in the vicinity of the surface of the blade 50 but more reliably penetrates into the mainstream 200. Can be suppressed.

  In addition, when the main flow 200 flows from the + X side to the −X side, the overhang portion 52H is formed to extend to the −X side, so that the cooling medium supplied from the air supply port 53 is changed to the −X side. Can lead to. When the main flow 200 flows from the + X side to the −X side, the surface of the blade 50 on the −X side with respect to the air supply port 53 can be cooled by the cooling medium from the air supply port 53.

  In the present embodiment, since the second surface 72 (slope) is provided in the concave portion 54, the cooling medium supplied from the air supply port 53 is guided by the overhang portion 52 </ b> H and the second surface 72. , Can flow smoothly to the -X side. Therefore, the surface of the blade 50 on the −X side with respect to the air supply port 53 can be satisfactorily cooled by the cooling medium from the air supply port 53.

  In addition, the air supply port 53 is disposed on the third surface 73 farthest from the surface of the base member 51 among the first, second, and third surfaces 71, 72, and 73 of the concave portion 54. The cooling medium supplied from 53 can be sufficiently distributed inside the recess 54. Therefore, the occurrence of unevenness of the cooling medium film 90 (cooling medium supply unevenness, cooling unevenness) can be suppressed.

  Further, since the cooling medium blown out from the air supply port 53 flows out through the gap 58 between the first portion 521 and the second portion 522 of the heat shielding film 52, the cooling medium film 90 can be further improved. Can be formed. Therefore, the occurrence of uneven cooling can be suppressed.

  In this embodiment, the size of the gap 58 (the size of the entire gap 58) is larger than the size of the air supply port 53 (the sum of the sizes of the plurality of air supply ports 53). The speed (flow velocity) of the cooling medium flowing out can be suppressed. Therefore, the cooling medium film 90 can be formed satisfactorily, and the cooling medium flowing out from the gap 58 can be prevented from penetrating into the main stream 200 without staying in the vicinity of the surface of the blade 50. Moreover, the occurrence of uneven cooling can be further reduced.

  Further, by making the recesses 54 longer in the Z-axis direction and arranging a plurality of air supply ports 53 in the Z-axis direction at predetermined intervals, it is possible to further reduce the occurrence of cooling medium supply unevenness, and hence cooling unevenness. it can.

  Further, by making the overhang portion 52H longer in the Z-axis direction, the cooling medium supplied from each of the plurality of air supply ports 53 can be well guided to a desired portion by the overhang portion 52H. .

  Next, an example of the manufacturing method of the wing | blade 50 is demonstrated with reference to FIG.5, FIG.6, FIG.7 and FIG. 5, FIG. 6, FIG. 7 and FIG. 8 (a) are views of the abdomen 50A viewed from the + Y side, and FIG. 5 (b) is a side sectional view of FIG.

  First, as shown in FIG. 5, a recess 54 and an air supply port 53 (hole 59) are formed on the surface of the substrate 51. For example, the concave portion 54 and the air supply port 53 are formed by electric discharge machining, drilling, cutting, or the like.

  Next, as shown in FIG. 6, a masking member 160 is disposed inside the recess 54 so as to close the air supply port 53. In the present embodiment, the masking member 160 is graphite. The masking member 160 is long in the Z-axis direction so as to correspond to the recess 54.

  Next, as shown in FIG. 7, a thermal barrier film 52 is coated so as to cover the surface of the substrate 51. As described above, the thermal barrier film 52 can be formed by, for example, a thermal spraying method.

  As shown in FIG. 7, the first region 61 and the second region 61 on the surface of the substrate 51 are formed so that the heat shielding film 52 is not formed on at least a part of the side surface of the masking member 160 facing the second surface 72 of the recess 54. The region 62 is coated with a thermal barrier film 52. In the present embodiment, the second surface 72 is also coated with the thermal barrier film 52.

  Further, in the present embodiment, the thermal barrier film 52 is coated with the upper surface of the masking member 160 and the first region 61 of the surface of the base material 51 disposed in substantially the same plane (in a flush state). Is done.

  Next, the masking member 160 is removed. The removal of the masking member 160 includes a process of heating the masking member 160 to disappear. When the masking member 160 made of graphite is heated to, for example, about 800 ° C., it burns and disappears. On the other hand, even if the blade 50 is heated to a temperature at which the masking member 160 disappears (combusts), the base material 51 and the heat shield film 52 are hardly affected. As described above, as shown in FIG. 8, the blade 50 according to the present embodiment is manufactured.

  Note that the masking member 160 is not limited to graphite, and the air supply port 53 can be closed when the thermal barrier film 52 is coated, such as a synthetic resin such as polyethylene resin or fluororesin, or carbon fiber reinforced plastic. Any material can be used as long as it is a material that can be eliminated (burned) without affecting the base material 51 and the thermal barrier film 52 when removed.

  According to the manufacturing method of the present embodiment, after the masking member 160 is disposed so as to close the air supply port 53, the thermal barrier film 52 is coated so as to cover the surface of the substrate 51 and the upper surface of the masking member 160, and thereafter By removing the masking member 160, the thermal barrier film 52 having the overhang portion 52H can be easily formed.

  Further, as shown in FIG. 7, by coating the first region 61 and the second region 62 with the thermal barrier film 52 so that the thermal barrier film 52 is not formed on at least a part of the side surface of the masking member 160, A gap 58 through which the cooling medium from the air supply port 53 flows out can be formed in at least a part of the heat shield film 52.

Further, by coating the heat shield film 52 in a state where the upper surface of the masking member 160 and the first region 61 are arranged in substantially the same plane, the thickness of the heat shield film 52 can be made substantially uniform. The thickness of the overhang portion 52H and the base portion 52K of the heat shield film 52 connected to the first region 61 can be made substantially uniform.

  As described above, according to the present embodiment, the cooling medium blown out from the air supply port 53 does not stay in the vicinity of the surface of the blade 50 but is prevented from penetrating into the mainstream 200 and is cooled to the surface of the blade 50. The medium film 90 can be formed satisfactorily. Therefore, since the cooling medium can be used effectively, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.

<Second Embodiment>
Next, a second embodiment will be described. In the following description, the same or equivalent components as those of the above-described embodiment are denoted by the same reference numerals, and the description thereof is simplified or omitted.

  FIG. 9 is an enlarged view of a part of the abdomen 50A of the wing 50 according to the second embodiment, and FIG. 10 is a side sectional view of FIG. A characteristic part of the second embodiment different from the first embodiment described above is that a plurality of recesses 54B are formed at predetermined intervals in the Z-axis direction. 9 and 10 show one recess 54B as a representative of the plurality of recesses 54B.

  As shown in FIG. 9, the shape of the recess 54B in the XZ plane is trapezoidal. In the recess 54B, the side on the front edge 50C side (+ X side) is shorter than the side on the rear edge 50D side (−X side). The air supply port 53 is disposed in each of the recesses 54B. As shown in FIG. 10, the recess 54B has a first surface 71, an inclined second surface 72, and a third surface 73 disposed between the first surface 71 and the second surface 72, The air supply port 53 is disposed on the third surface 73.

  The thermal barrier film 52 includes a first portion 521 and a second portion 522, and the overhang portion 52 </ b> H is provided in the first portion 521. The overhang portion 52 </ b> H is disposed at a position away from the air supply port 53 so as to face the air supply port 53.

  Also in the present embodiment, the cooling medium blown out from the air supply port 53 does not stay in the vicinity of the surface of the blade 50, but penetrates into the mainstream 200, and the cooling medium film 90 is favorably formed on the surface of the blade 50. can do. In addition, according to the present embodiment, since the size of the single recess 54B is relatively small, for example, the flow rate of the cooling medium can be adjusted with respect to the member surface having a pressure distribution to effectively use the cooling medium. It becomes possible. Therefore, the flow rate of the cooling medium can be reduced, and the performance of the gas turbine can be improved.

  11, 12, 13, and 14 are diagrams illustrating an example of a method for manufacturing the blade 50 according to the present embodiment. 11, 12, 13, and 14A are views of the abdomen 50A viewed from the + Y side, and FIG. 11B is a side sectional view of FIG.

  As shown in FIG. 11, a recess 54 </ b> B and an air supply port 53 (hole 59) are formed on the surface of the substrate 51. Next, as shown in FIG. 12, the masking member 160 is disposed inside the recess 54 </ b> B so as to close the air supply port 53. Next, as shown in FIG. 13, a thermal barrier film 52 is coated so as to cover the surface of the substrate 51. Next, the masking member 160 is heated and removed. As described above, as shown in FIG. 14, the blade 50 according to the present embodiment is manufactured.

<Third Embodiment>
Next, a third embodiment will be described. In the following description, the same or equivalent components as those of the above-described embodiment are denoted by the same reference numerals, and the description thereof is simplified or omitted.

  FIG. 15 is a side sectional view showing a part of the blade 50 according to the third embodiment. A characteristic part of the third embodiment different from the first and second embodiments described above is that the thermal barrier film extends over the overhang portion 52H and the base 52K of the thermal barrier film 52 connected to the first region 61. This is in that a linear reinforcing member 150 for reinforcing 52 is provided.

  As shown in FIG. 15, a linear reinforcing member 150 is disposed inside the thermal barrier film 52 so as to extend over the overhang portion 52H and the base portion 52K. The reinforcing member 150 is a metal wire, for example. The reinforcing member 150 is long in the X-axis direction. A plurality of reinforcing members 150 are arranged. A plurality of reinforcing members 150 are arranged in the Z-axis direction. Note that some of the plurality of reinforcing members 150 may be arranged to extend in the Z-axis direction. A plurality of linear reinforcing members 150 may be crossed to form a mesh-shaped reinforcing member.

  When the blade 50 shown in FIG. 15 is manufactured, the concave portion 54 (54B) and the air supply port 53 (hole 59) are formed in the substrate 51, and the masking member 160 is disposed so as to close the air supply port 53, A linear reinforcing member 150 is disposed across the surface of the material 51 (first region 61) and the upper surface of the masking member 160. Then, the thermal barrier film 52 is coated in a state where the reinforcing member 150 is disposed. As a result, the reinforcing member 150 is disposed inside the thermal barrier film 52. Then, the wing | blade 50 which concerns on this embodiment can be manufactured by heating and removing the masking member 160. FIG.

  In the above-described first to third embodiments, the case where the overhang portion 52H and the entire air supply port 53 face each other has been described as an example. However, the overhang portion 52H and a part of the air supply port 53 are described. And may be arranged so as to face each other. For example, the length (overhang amount) of the overhang portion 52H in the X-axis direction may be shortened so that a part of the air supply port 53 faces the overhang portion 52H.

  In each of the above-described embodiments, at least a part of the cooling medium blown out from the air supply port 53 is supplied substantially perpendicularly to the back surface of the overhang portion 52H facing the air supply port 53. The air supply port 53 (hole 59) is formed so that the air supply port 53 (hole 59) is inclined with respect to the back surface of the hang portion 52H, and the cooling medium is supplied from the direction inclined with respect to the back surface of the overhang portion 52H. You may be made to do.

  In each of the above-described embodiments, the case where the present invention is applied to the blade 50 of the turbine rotor blade 33 has been described as an example. However, of course, the present invention may be applied to the turbine stator blade 32 or the compressor stator blade. 13 and compressor blade 14 may be applied. In addition, the present invention can be applied to a member (high temperature member) heated to a high temperature in the gas turbine 100 without being limited to the blades. For example, the present invention can be applied to the combustor casing 24 or the turbine casing 31. When the present invention is applied to the casings 24 and 31, for example, the inner surface of the casings 24 and 41 is provided with a recess and an air supply port, and the heat shield film 52 having an overhang portion 52 H facing the air supply port is provided in the casing 24. , 41 is coated on the inner surface. In order to coat the thermal barrier film 52, the air supply port 53 is blocked using the masking member 160. Further, the reinforcing member 150 can be disposed on the heat shield film 52. By doing so, it is possible to suppress a decrease in the performance of the gas turbine 100.

50 ... Wings, 51 ... Base material, 52 ... Thermal barrier film, 52H ... Overhang, 52K ... Base, 53 ... Air supply port, 54 ... Recess, 58 ... Gap, 61 ... First region, 62 ... Second region , 71 ... 1st surface, 72 ... 2nd surface, 73 ... 3rd surface, 100 ... Gas turbine, 150 ... Reinforcement member, 160 ... Masking member, 521 ... 1st part, 522 ... 2nd part

Claims (11)

A substrate;
A recess formed on the surface of the substrate;
An air supply port arranged inside the recess,
The air supply port is supported by the base material so as to cover the first region of the surface of the base material around the concave portion, and overhangs from the first region to the concave portion so as to be away from the air supply port. And a thermal barrier film having an overhang portion opposed to,
The first region is arranged on one side in a first direction substantially parallel to the surface of the substrate with respect to the recess,
The overhang portion extends to the other side in the first direction ,
The recess is long in a second direction intersecting the first direction,
A plurality of the air supply ports are members for gas turbines arranged in the second direction at predetermined intervals . The overhang portion, the second direction longer claim 1, wherein the gas turbine member. Wherein said overhang portion and is connected to the first region disposed over the base of the Saeginetsumaku, for a gas turbine according to claim 1 or 2, including a linear reinforcing member for reinforcing the heat shield layer Element. A substrate;
A recess formed on the surface of the substrate;
An air supply port arranged inside the recess,
The air supply port is supported by the base material so as to cover the first region of the surface of the base material around the concave portion, and overhangs from the first region to the concave portion so as to be away from the air supply port. And a thermal barrier film having an overhang portion opposed to,
The first region is arranged on one side in a first direction substantially parallel to the surface of the substrate with respect to the recess,
The overhang portion extends to the other side in the first direction,
A gas turbine member comprising a linear reinforcing member that is disposed over the overhang portion and a base portion of the heat shield film connected to the first region and reinforces the heat shield film. The gas turbine member according to claim 4 , wherein a plurality of the recesses are formed at predetermined intervals in a second direction intersecting the first direction. The gas turbine member according to any one of claims 3 to 5, wherein the reinforcing member is disposed inside the thermal barrier film. The recess is disposed on one side in the first direction with respect to the air supply port, and is disposed on the other side in the first direction with respect to the air supply port, and a first surface connected to the first region. A second surface that is inclined so as to approach a second region of the surface of the base material that is disposed on the other side in the first direction with respect to the recess from the air supply port toward the other side. The member for gas turbines as described in any one of Claim 1 to 6 which has. The gas turbine member according to claim 7 , wherein the air supply port is disposed on a third surface of the recess between the first surface and the second surface. The thermal barrier film includes a first portion having the overhang portion, and a second portion arranged to cover the second region and the second surface,
The gas turbine member according to claim 7 or 8 , wherein the cooling medium from the air supply port flows out from a gap formed between an edge of the first portion and the second portion. The gas turbine member according to claim 9 , wherein the gap guides the cooling medium to a surface of the second portion. The gas turbine member according to claim 9 or 10 , wherein the gap is larger than the air supply port.

Images