JP2024120505A - Turbine and heat shield - Google Patents

Abstract

To provide a turbine which can easily prevent damage and can improve sealing characteristics between heat insulation pieces.SOLUTION: A turbine in an embodiment has a heat insulation member with a plurality of heat insulation pieces arranged in a rotation direction of a turbine rotor in a portion of an external peripheral surface of the turbine rotor that lies opposite a stationary blade. Each of the plurality of heat insulation pieces includes a front end face located on a front side in the rotation direction, and a rear end face located on a rear side in the rotation direction, with a protrusion provided on either of the front end face and the rear end face and a recess provided in the other of the front end face and the rear end face. The protrusion is formed integrally with the heat insulation piece. By the protrusion being accommodated in the recess between the plurality of heat insulation pieces, a clearance between the plurality of heat insulation pieces is sealed.SELECTED DRAWING: Figure 2

Description

Embodiments of the present invention relate to turbines and heat shields.

In power plants equipped with turbines such as gas turbines, the temperature of the working medium supplied to the inlet of the turbine is increased to improve power generation efficiency. For this reason, turbines are provided with heat shields to protect components such as the turbine rotor and blades from the high-temperature working medium and maintain their strength.

The heat shield device is, for example, a heat shield provided on the portion of the outer circumferential surface of the turbine rotor that faces the stationary blades, and the heat shield is, for example, composed of multiple heat shield pieces arranged in the rotational direction of the turbine rotor. It has also been proposed to introduce a cooling fluid into the space between the heat shield and the turbine rotor.

Patent No. 4460471 Patent No. 3040656 WO2016-142982 JP 2008-151007 A JP 2011-038491 A

[A] Configuration of turbine stage Fig. 8A is a diagram showing a main part of a turbine stage in a turbine according to a related art. Fig. 8A shows a schematic partial cross section of a vertical plane (xz plane), in which the vertical direction is the vertical direction z, the horizontal direction is the first horizontal direction x, and the direction perpendicular to the paper surface is the second horizontal direction y. In Fig. 8A, the flow direction of the working medium M is shown by a thick arrow, with the left side being the upstream side Us and the right side being the downstream side Ds.

[A-1] Turbine rotor 43
In the turbine 4, the turbine rotor 43 is housed in the casing 41, and is configured to rotate in a rotation direction R by the working medium M flowing in the axial direction along the rotation axis AX. The turbine rotor 43 has a rotor disk 432 provided on a rotor main body 431. The rotor main body 431 extends along the rotation axis AX. A plurality of rotor disks 432 are provided so as to protrude in a convex shape from the outer circumferential surface of the rotor main body 431. The plurality of rotor disks 432 are arranged at intervals in the axial direction (x) along the rotation axis AX. And, moving blades 46 are provided on the outer circumferential surface of the rotor disk 432.

[A-2] Moving blade 46
The rotor blade 46 has an implant portion 461 provided on the inner side (lower side in FIG. 8A ) in the radial direction of the turbine rotor 43. The implant portion 461 is fitted into the outer circumferential surface of the rotor disk 432.

[A-3] Stator blade 45
The stator vanes 45 are disposed on the inner circumferential surface of the casing 41. The stator vanes 45 are provided with an inner diaphragm ring 451 on the inner side in the radial direction of the turbine rotor 43. The inner circumferential surface of the inner diaphragm ring 451 is provided with a seal fin 451f.

[A-4] Heat shielding member 50
A heat shield 50 is provided as a heat shield device on a portion of the outer circumferential surface of the turbine rotor 43 facing the stator vanes 45. Here, the heat shield 50 is supported on a portion of the outer circumferential surface of the rotor body 431 constituting the turbine rotor 43 facing the inner circumferential surface of the diaphragm inner ring 451. The heat shield 50 isolates the turbine rotor 43 from a main flow path through which the working medium flows inside the casing 41, and is provided to protect the turbine rotor 43 from heat of the working medium.

The heat shield member 50 includes a heat shield plate 51 and legs 52, and the heat shield plates 51 and legs 52 are provided sequentially in the radial direction of the turbine rotor 43 from the outside to the inside (from the top to the bottom in FIG. 8A).

In the heat shield member 50, the heat shield plate 51 includes a portion that extends along the rotation axis AX of the turbine rotor 43. The heat shield plate 51 is installed so that a gap is provided between the outer peripheral surface of the heat shield plate 51 and the inner peripheral surface of the diaphragm inner ring 451, and a space SP is provided between the inner peripheral surface of the heat shield plate 51 and the outer peripheral surface of the rotor body 431.

In the heat shield member 50, the legs 52 extend in the radial direction of the turbine rotor 43. An engaged groove TR is formed in the outer peripheral surface of the rotor body 431 facing the inner peripheral surface of the diaphragm inner ring 451, and the radially inner portion of the legs 52 engages with the engaged groove TR. The legs 52 are configured to be engaged with the engaged groove TR, for example, by being inserted in the axial direction. Alternatively, the legs 52 may be configured to be engaged with the engaged groove TR, for example, by being inserted in the rotational direction R.

Here, the legs 52 are configured to divide the space SP between the inner circumferential surface of the heat shield 51 and the outer circumferential surface of the rotor body 431 into an upstream space SU located on the upstream side Us in the axial direction, and a downstream space SD located on the downstream side Ds in the axial direction.

The cooling fluid CF is introduced into the upstream space SU. Here, for example, the cooling fluid CF is introduced from an inlet formed in the turbine rotor 43. In addition, the cooling fluid CF introduced into the upstream space SU is introduced into the downstream space SD via the gap between the leg portion 52 and the engaged groove TR. The cooling fluid CF introduced into the upstream space SU and the downstream space SD is blown out into the main flow path through which the working medium flows, via the gap between the heat shield 51 and the implant portion 461. This prevents the working medium from flowing into the upstream space SU and the downstream space SD.

Figure 8B is a diagram showing a portion of a turbine according to the related art where a heat shield 50 is provided. Figure 8B shows a schematic cross section of the x1-x1 portion shown in Figure 8A, which is a vertical plane (yz plane) perpendicular to the rotation axis AX of the turbine rotor 43 in the heat shield 50.

As shown in FIG. 8B, the heat shield member 50 includes a plurality of heat shield pieces 500. The plurality of heat shield pieces 500 are parts obtained by dividing the heat shield member 50 in the rotation direction R of the turbine rotor 43. The heat shield pieces 500 are in an arc shape along the rotation direction R, and the heat shield member 50 is configured in a ring shape by arranging the plurality of heat shield pieces 500 so that they are aligned in the rotation direction R.

The heat shield piece 500 includes a heat shield plate piece 510 and a leg piece 520. A plurality of the heat shield plate pieces 510 of the heat shield piece 500 are arranged in the rotation direction R of the turbine rotor 43 to form the heat shield plate 51 of the heat shield member 50. A plurality of the leg pieces 520 of the heat shield piece 500 are arranged in the rotation direction R of the turbine rotor 43 to form the leg 52 of the heat shield member 50.

As shown in FIG. 8B, each of the heat shield pieces 500 includes a forward end face SF located on the forward side Fw in the direction of rotation R, and a rearward end face SB located on the rearward side Bw in the direction of rotation R.

The rear end surface SB of the heat shield piece 500 shown in FIG. 8A is shown. As shown in FIG. 8A, the rear end surface SB of the heat shield piece 500 is formed with a recess R51 and a recess R52. The seal pin 61 is housed inside the recess R51, and the seal pin 62 is housed inside the recess R52. The seal pin 61 and the seal pin 62 are installed to seal between the multiple heat shield pieces 500 lined up in the rotation direction R.

Figure 8C is an enlarged view of a portion of a heat shield 50 in a turbine according to a related art. In Figure 8C, an enlarged view is shown between a pair of heat shield pieces 500 arranged adjacent to each other in the rotation direction R in a vertical plane (yz plane) in the heat shield 50, which is perpendicular to the rotation axis AX of the turbine rotor 43. Here, an enlarged view is shown of a portion (X portion in Figure 8B) between a pair of heat shield pieces 510 constituting a heat shield 51. In Figure 8C, the horizontal direction is essentially the rotation direction R, with the left side being the forward side Fw of the rotation direction R and the right side being the rear side Bw of the rotation direction R. In Figure 8C, the vertical direction essentially corresponds to the radial direction.

As shown in FIG. 8C, the seal pin 61 shown in FIG. 8A is interposed between a pair of heat shield pieces 510. The seal pin 61 is, for example, a cylindrical rod-shaped body. Here, a recess R510 is formed in the rear end surface SB of the heat shield piece 510 located on the forward side Fw of the rotation direction R, and the seal pin 61 is housed inside the recess R510. Although not shown, the other seal pin 62 shown in FIG. 8A has the same shape as the seal pin 61, and the other seal pin 62 is also housed in the recess R520 like the seal pin 61.

[B] Problems During operation of the turbine, a large centrifugal force is applied to each of the heat shield pieces 500 in the radial direction as the turbine rotor 43 rotates. This causes a gap to widen between the front end face SF of one heat shield piece 500 and the rear end face SB of the other heat shield piece 500 located on the front side Fw of the first heat shield piece 500. If this gap becomes wider than expected due to a malfunction or the like, in the related art described above, there is a possibility that the seal pin 61 will fall off the recess R51 and the seal pin 62 will fall off the recess R52. As a result, there is a possibility that damage or the like will occur.

In addition, due to the centrifugal force applied during operation of the turbine, the seal pin 61 moves radially outward inside the recess R51, as shown in FIG. 8C. As a result, a communication passage LC that connects the upstream space SU and the downstream space SD may be formed inside the recess R51. As a result, the flow rate of the cooling fluid CF flowing from the upstream space SU to the downstream space SD may increase. In other words, the sealing characteristics between the heat shield pieces 500 may deteriorate. As a result, the performance of the turbine may deteriorate.

Therefore, the problem that the present invention aims to solve is to provide a turbine and a heat shield device that can easily prevent damage, improve the sealing characteristics between the heat shield pieces, and easily improve the performance of the turbine.

The turbine of the embodiment includes a casing, a turbine rotor that is housed in the casing and rotates by the flow of a working medium in the axial direction along the rotation axis, and a turbine stage including stationary blades installed inside the casing and moving blades installed on the outer peripheral surface of the turbine rotor, and the turbine stages are provided in the axial direction. The turbine of the embodiment has a heat shield member in which a plurality of heat shield pieces are arranged in the rotation direction of the turbine rotor on a portion of the outer peripheral surface of the turbine rotor facing the stationary blades. Each of the plurality of heat shield pieces includes a front end face located on the front side in the rotation direction and a rear end face located on the rear side in the rotation direction, and a convex portion is provided on one of the front end face and the rear end face, and a concave portion is provided on the other of the front end face and the rear end face. The convex portion is formed integrally with the heat shield piece. The convex portion is housed in the concave portion between each of the plurality of heat shield pieces, thereby sealing between each of the plurality of heat shield pieces.

FIG. 1 is a diagram showing an example of a main part of a turbine according to a first embodiment. FIG. 2 is a diagram showing a main part of a portion where turbine stages are provided in the turbine according to the first embodiment. FIG. 3A is a schematic diagram showing a rear end surface SB of a heat shield piece 500 constituting the heat shield 50 of the first embodiment. FIG. 3B is a schematic diagram showing a front end surface SF of a heat shield piece 500 constituting the heat shield 50 of the first embodiment. FIG. 3C shows an enlarged view of the space between a pair of heat shield pieces 500 arranged adjacent to each other in the rotation direction R in the heat shield 50 of the first embodiment. FIG. 4A is a schematic diagram showing a rear end surface SB of a heat shield piece 500 constituting a heat shield 50 of the second embodiment. FIG. 4B is a schematic diagram showing a front end surface SF of a heat shield piece 500 constituting a heat shield 50 of the second embodiment. FIG. 5A is a schematic diagram showing a rear end surface SB of a heat shield piece 500 constituting a heat shield 50 according to the third embodiment. FIG. 5B is a schematic diagram showing a front end surface SF of a heat shield piece 500 constituting a heat shield 50 of the third embodiment. FIG. 6 shows an enlarged view of a space between a pair of heat shield pieces 500 arranged adjacent to each other in the rotation direction R in a heat shield 50 according to the fourth embodiment. FIG. 7 shows an enlarged view of a space between a pair of heat shield pieces 500 arranged adjacent to each other in the rotation direction R in a heat shield 50 according to the fifth embodiment. FIG. 8A is a diagram showing a main part of a portion where turbine stages are provided in a turbine according to the related art. FIG. 8B is a diagram showing a portion where a heat shield 50 is provided in a turbine according to the related art. FIG. 8C is an enlarged view of a portion of a heat shield 50 in a turbine according to the related art.

<First embodiment>

[A] Turbine Configuration FIG. 1 is a diagram showing an example of a main part of a turbine according to a first embodiment.

Figure 1 shows a partial cross section of a vertical plane (xz plane), with the vertical direction being the vertical direction z, the horizontal direction being the first horizontal direction x, and the direction perpendicular to the paper surface being the second horizontal direction y. Also, in Figure 1, the flow of the working medium flowing through the turbine 4 is indicated by thick arrows, with the left side being the upstream side Us and the right side being the downstream side Ds.

As shown in FIG. 1, the turbine 4 includes a casing 41 and a turbine rotor 43. The turbine 4 is, for example, a multi-stage type, and includes a plurality of turbine stages 47. The turbine 4 is, for example, a gas turbine.

Each part that makes up the turbine 4 will be explained in turn.

The casing 41 has, for example, a double structure having an inner casing 41a and an outer casing 41b, and the outer casing 41b houses the inner casing 41a inside. In the casing 41, stator vanes 45 are installed on the inner peripheral surface of the inner casing 41a. A plurality of stator vanes 45 are arranged in the rotation direction R (circumferential direction) of the turbine rotor 43, and the plurality of stator vanes 45 constitute a stator vane row. The stator vane row has multiple stages, and the multiple stages of stator vane rows are lined up in the axial direction (first horizontal direction x) along the rotation axis AX of the turbine rotor 43.

The turbine rotor 43 is a cylindrical rod-shaped body, and the rotation axis AX extends in the first horizontal direction x. The turbine rotor 43 is housed inside the casing 41 and is supported so as to rotate by the flow of the working medium in the axial direction along the rotation axis AX. The turbine rotor 43 has moving blades 46 installed on its outer circumferential surface. A plurality of moving blades 46 are arranged in the rotation direction R of the turbine rotor 43, and the plurality of moving blades 46 constitute a moving blade cascade. The moving blade cascade has multiple stages, similar to the stator blade cascade, and the multiple stages of moving blade cascades are lined up in the axial direction (x) along the rotation axis AX of the turbine rotor 43. In other words, the turbine stage 47, which is composed of the stator blade cascade and the moving blade cascade, has multiple stages, and the multiple turbine stages 47 are arranged so as to be lined up in the axial direction along the rotation axis AX.

In order to introduce combustion gas supplied as a working medium from a combustor (not shown) into the inside of the casing 41, the turbine 4 is provided with, for example, a gas supply pipe 411, an inlet sleeve 421, and a nozzle box 422. The gas supply pipe 411 is provided outside the outer casing 41b. The inlet sleeve 421 is provided so as to penetrate the inner casing 41a and the outer casing 41b. The nozzle box 422 is provided inside the inner casing 41a.

In the turbine 4, the working medium flows sequentially through the gas supply pipe 411, the inlet sleeve 421, and the nozzle box 422, and then flows in the axial direction (x) along the rotation axis AX of the turbine rotor 43. At this time, the working medium expands in each of the multiple turbine stages 47 arranged in the axial direction (x) along the rotation axis AX to perform work. This causes the turbine rotor 43 to rotate in the rotation direction R. After passing through the final turbine stage 47, the working medium is discharged to the outside of the casing 41 via the exhaust pipe 412.

[B] Configuration of Turbine Stages FIG. 2 is a diagram showing a main portion of a portion where turbine stages are provided in the turbine according to the first embodiment.

In FIG. 2, like FIG. 8A, a partial cross section of a vertical plane (xz plane) is shown. As shown in FIG. 2, in the turbine according to this embodiment, a heat shield 50 is provided as a heat shield device, like the related art (see FIG. 8A) described above. The heat shield 50 includes a heat shield plate 51 and legs 52. Like the related art (see FIG. 8B) described above, the heat shield 50 includes a plurality of heat shield pieces 500 arranged in the rotation direction R. Each of the plurality of heat shield pieces 500 includes a front end face SF located on the front side Fw in the rotation direction R and a rear end face SB located on the rear side Bw in the rotation direction R (see FIG. 8B). In the heat shield piece 500 shown in FIG. 2, the rear end face SB is shown.

Figure 3A is a schematic diagram of the rear end surface SB of the heat shield piece 500 constituting the heat shield member 50 of the first embodiment. Figure 3B is a schematic diagram of the front end surface SF of the heat shield piece 500 constituting the heat shield member 50 of the first embodiment. Figure 3C is an enlarged view of the space between a pair of heat shield pieces 500 arranged adjacent to each other in the direction of rotation R in the heat shield member 50 of the first embodiment. Figure 3C, like Figure 8C, shows an enlarged view of the portion between a pair of heat shield plate pieces 510 constituting the heat shield plate 51 in the heat shield piece 500 (portion X in Figure 8B).

As shown in Figures 2, 3A, 3B, and 3C, in the turbine according to this embodiment, a part of the heat shield piece 500 constituting the heat shield member 50 is different from that in the related art described above (see Figures 8A and 8C). Except for this point and related points, this embodiment is similar to the related art described above, so a description of the overlapping parts will be omitted as appropriate.

As shown in Figures 2, 3A, 3B, and 3C, the heat shield piece 500 of this embodiment has a protrusion T50 on the rear end face SB and a recess R50 on the front end face SF. Here, the protrusion T50 is formed integrally with the heat shield piece 500.

Specifically, in this embodiment, the heat shield piece 500 includes a leg piece 520 that constitutes the leg 52 and a heat shield piece 510 that constitutes the heat shield 51, as shown in Figures 3A and 3B.

As shown in FIG. 3A, the convex portion T50 is T-shaped including a first convex portion T51 and a second convex portion T52. In the convex portion T50, the first convex portion T51 is provided on the front end surface SF of the heat shield piece 510. The first convex portion T51 extends in the axial direction along the rotation axis AX of the turbine rotor 43. In the convex portion T50, the second convex portion T52 is provided on the front end surface SF of the leg piece 520. The second convex portion T52 extends in the radial direction of the turbine rotor 43, and the portion of the second convex portion T52 located on the radially outer side is configured to connect to the first convex portion T51.

As shown in FIG. 3B, the recess R50 is T-shaped and includes a first recess R51 and a second recess R52. In the recess R50, the first recess R51 is provided on the rear end surface SB of the heat shield piece 510. The first recess R51 extends in the axial direction along the rotation axis AX of the turbine rotor 43, similar to the first protrusion T51. In the recess R50, the second recess R52 is provided on the rear end surface SB of the leg piece 520. The second recess R52 extends in the radial direction of the turbine rotor 43, similar to the second protrusion T52, and is configured such that the portion of the second recess R52 located on the radially outer side is connected to the first recess R51.

As shown in FIG. 3C, the convex portion T50 is configured to be accommodated in the concave portion R50 between a pair of heat shield pieces 500 arranged adjacent to each other in the rotation direction R. Specifically, the first convex portion T51 constituting the convex portion T50 is accommodated in the first concave portion R51 constituting the concave portion R50. Although not shown, similar to the relationship between the first convex portion T51 and the first concave portion R51, the second convex portion T52 constituting the convex portion T50 is accommodated in the second concave portion R52 constituting the concave portion R50. In other words, among a pair of heat shield pieces 500 arranged adjacent to each other in the rotation direction R, the convex portion T50 protruding in the rotation direction R at the rear end surface SB of one heat shield piece 500 (first heat shield piece) is accommodated in the concave portion R50 recessed in the rotation direction R at the front end surface SF of the other heat shield piece 500 (second heat shield piece) located on the rear side Bw of the one heat shield piece 500.

In this embodiment, for example, the convex portion T50 and the concave portion R50 are formed by machining the main body of the heat shield piece 500. Alternatively, a member constituting the convex portion T50 may be prepared separately from the main body of the heat shield piece 500, and the member constituting the convex portion T50 may be joined to the main body of the heat shield piece 500 by welding or the like.

[C] Summary As described above, in the turbine of this embodiment, the heat shield 50 installed as a heat shield device has the protrusions T50 housed in the recesses R50 between each of the multiple heat shield pieces 500. In this way, the heat shield 50 of this embodiment seals the spaces between each of the multiple heat shield pieces 500.

In this embodiment, unlike the related art, seal pins 61, 62 (see FIG. 8A) are not provided, and the protrusion T50 is formed integrally with the heat shield piece 500. Therefore, even if a large centrifugal force is applied to each of the multiple heat shield pieces 500 during operation of the turbine 4 and the width of the gap between the multiple heat shield pieces 500 increases, in this embodiment, unlike the seal pins 61, 62 (see FIG. 8A) of the related art, the protrusion T50 does not fall off. As a result, in this embodiment, it is possible to prevent the occurrence of damage, etc.

In addition, in this embodiment, unlike the seal pins 61, 62 (see FIG. 8A) of the related art, the protrusion T50 does not move inside the recess R51 even when centrifugal force is applied during operation of the turbine. Therefore, in this embodiment, even if a communication passage that communicates between the upstream space SU and the downstream space SD exists inside the recess R51, the cross-sectional area of the communication passage is constant, so the flow rate of the cooling fluid CF flowing from the upstream space SU to the downstream space SD does not change. In other words, in this embodiment, the sealing characteristics between the heat shield pieces 500 do not decrease even during operation of the turbine. In addition, in this embodiment, it is possible to suppress leakage of the cooling fluid CF from between the multiple heat shield pieces 500 into the main flow path through which the working medium flows in the turbine. As a result, in this embodiment, it is possible to prevent a decrease in the performance of the turbine.

[D] Modifications In the above embodiment, a case has been described in which, in a pair of heat shield pieces 500 arranged adjacent to each other in the rotational direction, the protrusion T50 is provided on the rear end face SB of one heat shield piece 500 (first heat shield piece), and the recess R50 is provided on the front end face SF of the other heat shield piece 500 (second heat shield piece) located on the rear side Bw of the first heat shield piece 500. However, this is not limited to the above. The recess R50 may be provided on the rear end face SB of the first heat shield piece 500, and the protrusion T50 may be provided on the front end face SF of the other heat shield piece 500. It is sufficient that each of the multiple heat shield pieces has a protrusion on one of the rear end face SB and the front end face SF that face each other in the pair of heat shield pieces 500 arranged adjacent to each other in the rotational direction.

Second Embodiment
[A] Configuration of heat shield piece 500 Fig. 4A is a schematic diagram showing a rear end surface SB of a heat shield piece 500 constituting the heat shield member 50 of the second embodiment. Fig. 4B is a schematic diagram showing a front end surface SF of a heat shield piece 500 constituting the heat shield member 50 of the second embodiment.

As shown in Figures 4A and 4B, in this embodiment, a portion of the heat shield piece 500 is different from that of the first embodiment described above (see Figures 3A and 3B). Except for this point and related points, this embodiment is similar to the first embodiment described above, so a description of the overlapping parts will be omitted as appropriate.

As shown in Figures 4A and 4B, the heat shield piece 500 of this embodiment has a protrusion T50 on the rear end face SB and a recess R50 on the front end face SF.

In the heat shield piece 500 of this embodiment, the convex portion T50 includes a first convex portion T51 and a second convex portion T52, as shown in FIG. 4A. However, in this embodiment, the first convex portion T51, unlike the first embodiment, has a first radial convex portion T511 and a first axial convex portion T512.

As shown in FIG. 4A, the first radial protrusion T511 extends in the radial direction of the turbine rotor 43 in the heat shield piece 510. The first radial protrusion T511 is formed so as to be aligned with the second protrusion T52 in the radial direction. In contrast, the first axial protrusion T512 extends in the axial direction of the turbine rotor 43 in the heat shield piece 510. That is, in the heat shield piece 500 of this embodiment, the protrusion T50 is formed in a cross shape.

In the heat shield piece 500 of this embodiment, the recess R50 includes a first recess R51 and a second recess R52, as shown in FIG. 4B. However, in this embodiment, the first recess R51, unlike the first embodiment, has a first radial recess R511 and a first axial recess R512.

As shown in FIG. 4B, the first radial recess R511 extends in the radial direction of the turbine rotor 43 in the heat shield piece 510. The first radial recess R511 is formed so as to be aligned with the second recess R52 in the radial direction. In contrast, the first axial recess R512 extends in the axial direction of the turbine rotor 43 in the heat shield piece 510. That is, in the heat shield piece 500 of this embodiment, the recess R50 is formed in a cross shape.

[B] Summary As described above, in the heat shield piece 500 of this embodiment, the first convex portion T51 constituting the convex portion T50 has the first radial convex portion T511 and the first axial convex portion T512. And, in the heat shield piece 500 of this embodiment, the first concave portion R51 constituting the concave portion R50 has the first radial concave portion R511 and the first axial concave portion R512. Therefore, in this embodiment, the shape of the gap between the convex portion T50 and the concave portion R50 is more complex than in the first embodiment, so that the pressure loss of the cooling fluid CF passing through the gap between the convex portion T50 and the concave portion R50 increases. As a result, in this embodiment, it is possible to suppress leakage of the cooling fluid CF from the upstream space SU to the downstream space SD more than in the first embodiment.

Third Embodiment
[A] Configuration of heat shield piece 500 Fig. 5A is a schematic diagram showing a rear end surface SB of a heat shield piece 500 constituting the heat shield member 50 of the third embodiment. Fig. 5B is a schematic diagram showing a front end surface SF of a heat shield piece 500 constituting the heat shield member 50 of the third embodiment.

As shown in Figures 5A and 5B, in this embodiment, a portion of the heat shield piece 500 is different from that of the second embodiment described above (see Figures 4A and 4B). Except for this point and related points, this embodiment is similar to the second embodiment described above, so a description of the overlapping parts will be omitted as appropriate.

As shown in Figures 5A and 5B, the heat shield piece 500 of this embodiment has a convex portion T50 on the rear end face SB and a concave portion R50 on the front end face SF.

The heat shield piece 500 of this embodiment includes a first convex portion T51 and a second convex portion T52, as shown in FIG. 5A.

In the convex portion T50 of this embodiment, as shown in FIG. 5A, the first convex portion T51 has a first radial convex portion T511 and a first axial convex portion T512, similar to the second embodiment. However, in this embodiment, unlike the second embodiment, the first convex portion T51 includes multiple first radial convex portions T511. The multiple first radial convex portions T511 intersect with the first axial convex portions T512 and are arranged in a line with spaces between them in the axial direction.

In the convex portion T50 of this embodiment, the second convex portion T52 has a second radial convex portion T521 and a second axial convex portion T522, as shown in FIG. 5A, unlike the second embodiment. The second radial convex portion T521 extends in the radial direction of the turbine rotor 43 in the leg piece 520. In contrast, the second axial convex portion T522 extends in the axial direction of the turbine rotor 43 in the leg piece 520. In this embodiment, the second convex portion T52 includes a plurality of second axial convex portions T522. The plurality of second axial convex portions T522 intersect with the second radial convex portion T521 and are arranged in a line with a gap between them in the radial direction.

In the heat shield piece 500 of this embodiment, the recess R50 includes a first recess R51 and a second recess R52, as shown in FIG. 5B.

In the recess R50 of this embodiment, as shown in FIG. 5B, the first recess R51 has a first radial recess R511 and a first axial recess R512, similar to the second embodiment. However, in this embodiment, unlike the second embodiment, the first recess R51 includes multiple first radial recesses R511. The multiple first radial recesses R511 intersect with the first axial recesses R512 and are arranged in a line with spaces between them in the axial direction.

In the recess R50 of this embodiment, the second recess R52 has a second radial recess R521 and a second axial recess R522, as shown in FIG. 5B, unlike the second embodiment. The second radial recess R521 extends in the radial direction of the turbine rotor 43 in the leg piece 520. In contrast, the second axial recess R522 extends in the axial direction of the turbine rotor 43 in the leg piece 520. In this embodiment, the second recess R52 includes a plurality of second axial recesses R522. The plurality of second axial recesses R522 intersect with the second radial recess R521 and are arranged in a line with a gap between them in the radial direction.

[B] Summary As described above, in the heat shield piece 500 of this embodiment, the first convex portion T51 constituting the convex portion T50 has a first radial convex portion T511 and a first axial convex portion T512. And, in the heat shield piece 500 of this embodiment, the first concave portion R51 constituting the concave portion R50 has a first radial concave portion R511 and a first axial concave portion R512. In this embodiment, the first radial convex portion T511 is provided in a plurality of portions, and the plurality of first radial convex portions T511 are arranged in a spaced relationship in the axial direction. Similarly, the first radial concave portions R511 are provided in a plurality of portions, and the plurality of first radial concave portions R511 are arranged in a spaced relationship in the axial direction.

Furthermore, in this embodiment, the second convex portion T52 constituting the convex portion T50 has a second radial convex portion T521 and a second axial convex portion T522, and the second concave portion R52 constituting the concave portion R50 has a second radial concave portion R521 and a second axial concave portion R522. There are multiple second axial convex portions T522, and the multiple second axial convex portions T522 are arranged so as to be spaced apart in the radial direction. Similarly, there are multiple second axial concave portions R522, and the multiple second axial concave portions R522 are arranged so as to be spaced apart in the radial direction.

For this reason, in this embodiment, the shape of the gap between the convex portion T50 and the concave portion R50 is more complex than in the second embodiment, so the pressure loss of the cooling fluid CF passing through the gap between the convex portion T50 and the concave portion R50 increases. As a result, in this embodiment, it is possible to suppress leakage of the cooling fluid CF from the upstream space SU to the downstream space SD more than in the second embodiment.

Fourth Embodiment
[A] Configuration of heat shield piece 500 Fig. 6 shows an enlarged view of the space between a pair of heat shield pieces 500 arranged adjacent to each other in the rotation direction R in the heat shield member 50 of the fourth embodiment. Like Fig. 3C, Fig. 6 shows an enlarged view of the portion between a pair of heat shield plate pieces 510 constituting the heat shield plate 51 in the heat shield piece 500 (portion X in Fig. 8B).

As shown in FIG. 6, in this embodiment, the shape of the first protrusion T51 and the shape of the first recess R51 formed on the heat shield piece 510 are different from those in the first embodiment described above (see FIG. 3C). Except for this point and related points, this embodiment is similar to the first embodiment described above, so descriptions of overlapping parts will be omitted as appropriate.

In this embodiment, as shown in FIG. 6, the shape of the tip portion of the first protrusion T51 formed on the heat shield piece 510 is an arc-shaped curved surface, unlike the first embodiment (see FIG. 3C). Also, the shape of the tip portion of the first recess R51 formed on the heat shield piece 510 is an arc-shaped curved surface, similar to the shape of the tip portion of the first protrusion T51, unlike the first embodiment (see FIG. 3C).

Although not shown, the second convex portion T52 and the second concave portion R52 formed on the pair of leg pieces 520 constituting the leg portion 52 in the heat shield piece 500 are configured in a similar manner.

[B] Summary For this reason, in this embodiment, the convex portion T50 can be easily inserted into the concave portion R50 between multiple heat shield pieces 500, making it possible to easily assemble the heat shield member 50 from multiple heat shield pieces 500.

Fifth Embodiment
[A] Configuration of heat shield piece 500 Fig. 7 shows an enlarged view of the space between a pair of heat shield pieces 500 arranged adjacent to each other in the rotation direction R in the heat shield member 50 of the fifth embodiment. Like Fig. 3C, Fig. 7 shows an enlarged view of the portion between a pair of heat shield plate pieces 510 constituting the heat shield plate 51 in the heat shield piece 500 (portion X in Fig. 8B).

As shown in FIG. 7, in this embodiment, the heat shield piece 510 has a plurality of first protrusions T51 and first recesses R51, unlike the first embodiment described above (see FIG. 3C). Except for this point and related points, this embodiment is similar to the first embodiment described above, so descriptions of overlapping parts will be omitted as appropriate.

In this embodiment, as shown in FIG. 7, the multiple first protrusions T51 formed on the heat shield piece 510 are arranged to be spaced apart in the axial direction. Also, the multiple first recesses R51 formed on the heat shield piece 510 are arranged to be spaced apart in the axial direction, similar to the multiple first protrusions T51.

Although not shown in the figure, the second convex portion T52 and the second concave portion R52 formed on the pair of leg pieces 520 constituting the leg portion 52 in the heat shield piece 500 may also be multiple.

[B] Summary In this embodiment, the shape of the gap between the convex portion T50 and the concave portion R50 is more complex than in the second embodiment, so the pressure loss of the cooling fluid CF passing through the gap between the convex portion T50 and the concave portion R50 increases. As a result, in this embodiment, it is possible to suppress leakage of the cooling fluid CF from the upstream space SU to the downstream space SD more than in the second embodiment.

＜Other＞

Although several embodiments of the present invention have been described, these embodiments are presented as examples and are not intended to limit the scope of the invention. These embodiments can be implemented in various other forms, and various omissions, substitutions, and modifications can be made without departing from the spirit of the invention. These embodiments and their modifications are within the scope of the invention and its equivalents as set forth in the claims, as well as the scope and spirit of the invention.

4: turbine, 41: casing, 41a: inner casing, 41b: outer casing, 43: turbine rotor, 45: stator blade, 46: rotor blade, 47: turbine stage, 50: heat shield, 51: heat shield, 52: leg, 61: seal pin, 62: seal pin, 411: gas supply pipe, 412: exhaust pipe, 421: inlet sleeve, 422: nozzle box, 431: rotor main body, 432: rotor disk, 451: diaphragm inner ring, 451f: seal fin, 461: implantation part, 500: heat shield piece, 510: heat shield piece, 520: leg piece, AX: rotating shaft, Bw: rear side, CF: cooling fluid, Ds: downstream side, Fw: front side, LC: communication Path, M: working medium, R: direction of rotation, R50: recess, R51: first recess, R51: recess, R510: recess, R511: first radial recess, R512: first axial recess, R52: second recess, R520: recess, R521: second radial recess, R522: second axial recess, SB: rear end face, SD: downstream space, SF: front end surface, SP: space, SU: upstream space, T50: convex portion, T51: first convex portion, T511: first radial convex portion, T512: first axial convex portion, T52: second convex portion, T521: second radial convex portion, T522: second axial convex portion, TR: engaged groove, Us: upstream side, x: first horizontal direction, y: second horizontal direction, z: vertical direction,

Claims (8)

A casing;
a turbine rotor that is accommodated in the casing and rotates by a working medium flowing in an axial direction along a rotation axis;
a turbine stage including a stationary vane disposed inside the casing and a rotor blade disposed on an outer peripheral surface of the turbine rotor;
A turbine having a plurality of turbine stages provided in the axial direction,
a heat insulating member having a plurality of heat insulating pieces arranged in a rotational direction of the turbine rotor in a portion of an outer circumferential surface of the turbine rotor facing the stationary blades,
Each of the plurality of heat shield pieces is
a front end surface located on the front side in the rotation direction;
a rear end surface located on the rear side in the rotation direction,
A convex portion is provided on one of the front end surface and the rear end surface,
A recess is provided on the other of the front end surface and the rear end surface,
The protrusion is integrally formed with the heat shield piece,
The convex portions are received in the concave portions between the plurality of heat shield pieces, thereby sealing the spaces between the plurality of heat shield pieces.
Turbine. The heat shielding member is
a leg portion having an inner portion engaged with an engaged groove TR formed on an outer circumferential surface of the turbine rotor;
a heat shield located on an outer portion of the leg;
The leg portion is configured to partition an upstream space located on the upstream side in the axial direction and a downstream space located on the downstream side,
The convex portions are accommodated in the concave portions between the plurality of heat shield pieces, thereby sealing between the upstream space and the downstream space and preventing leakage of the cooling fluid from the upstream space to the downstream space.
The turbine of claim 1 . Each of the plurality of heat shield pieces is
A leg piece constituting the leg;
and a heat shield piece constituting the heat shield,
The protrusion is
a first protrusion provided on the one surface of the heat shield piece; and a second protrusion provided on the one surface of the leg piece,
The recessed portion is
a first recess provided on the other surface of the heat shield piece; and a second recess provided on the other surface of the leg piece,
The first protrusions are accommodated in the first recesses between the plurality of heat shield pieces, and the second protrusions are accommodated in the second recesses between the plurality of heat shield pieces.
The turbine of claim 2 . The first protrusion is
a first radial protrusion extending in a radial direction of the turbine rotor in the heat shield piece;
a first axial protrusion extending in the axial direction of the turbine rotor in the heat shield piece,
The first recess includes:
a first radial recess in the heat shield piece, the first radial recess extending in a radial direction of the turbine rotor;
a first axial recess in the heat shield piece extending in the axial direction of the turbine rotor.
The turbine of claim 3. The first protrusion includes a plurality of the first radial protrusions, and the plurality of first radial protrusions are arranged in the axial direction at intervals,
The first recess includes a plurality of the first radial recesses, and the plurality of first radial recesses are arranged at intervals in the axial direction.
The turbine of claim 4. The second protrusion is
a second radial protrusion extending in a radial direction of the turbine rotor on the leg piece;
a second axial protrusion extending in the axial direction of the turbine rotor at the leg piece,
The second recess includes:
a second radial recess in the foot piece extending in a radial direction of the turbine rotor;
a second axial recess in the foot piece extending in the axial direction of the turbine rotor.
A turbine according to any one of claims 3 to 5. The second protrusion includes a plurality of the second axial protrusions, and the plurality of second axial protrusions are arranged at intervals in the radial direction,
The second recess includes a plurality of the second axial recesses, and the plurality of second axial recesses are arranged at intervals in the radial direction.
The turbine of claim 6. A heat insulation device for performing heat insulation in a turbine including a casing, a turbine rotor accommodated in the casing and rotated by a working medium flowing in an axial direction along a rotation axis, and a turbine stage including a stationary vane installed inside the casing and a moving blade installed on an outer peripheral surface of the turbine rotor, the turbine stage being provided in a plurality of turbine stages in the axial direction,
a heat insulating member having a plurality of heat insulating pieces arranged in a rotational direction of the turbine rotor in a portion of an outer circumferential surface of the turbine rotor facing the stationary blades,
Each of the plurality of heat shield pieces is
a front end surface located on the front side in the rotation direction;
a rear end surface located on the rear side in the rotation direction,
A convex portion is provided on one of the front end surface and the rear end surface,
A recess is provided on the other of the front end surface and the rear end surface,
The convex portions are received in the concave portions between the plurality of heat shield pieces, thereby sealing the spaces between the plurality of heat shield pieces.
Heat shielding device.

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