JP5916294B2 - Gas turbine blade and method for manufacturing the same - Google Patents

Description

  The present invention relates to a gas turbine blade and a manufacturing method thereof, and more particularly to a cooling structure for a tip shroud of a gas turbine blade.

  A structure called a tip shroud is often attached to the tip of the gas turbine blade that protrudes axially and circumferentially from the tip of the gas turbine blade. The chip shroud generally has two roles. One is to introduce more hot gas from the combustor to the blade surface of the gas turbine blade to improve energy efficiency. The other is that when the gas turbine is operated and the gas turbine blades are rotating at high speed, the tip shrouds of adjacent gas turbine blades are brought into contact with each other, thereby suppressing vibration of the gas turbine blades. That is.

  During operation of the gas turbine, the temperature of the gas turbine rotor blade becomes high, so that the gas turbine rotor blade is cooled by supplying cooling air to the internal space of the gas turbine rotor blade. At this time, the chip shroud is similarly cooled by the cooling air by supplying the cooling air to the internal space.

  Japanese Patent Application Laid-Open No. 11-13402 and Japanese Patent No. 3340301 disclose a technique for cooling a chip shroud by providing a cooling passage in the chip shroud. Japanese Unexamined Patent Publication No. 2009-168017 discloses a technique for cooling a chip shroud by providing a cooling cavity inside the chip shroud.

  The gas turbine rotor blades disclosed in these patent documents receive high-temperature gas and rotate in a specific rotation direction. In the structure of the gas turbine rotor blades of these three patent documents, the cooling air discharged from the tip shroud is discharged in both the direction having the velocity component in the rotation direction and the direction having the velocity component in the opposite direction to the rotation direction. It is configured to be.

  However, according to the inventors' investigation, the structure of the chip shroud disclosed in the above patent document has room for improvement in the output and energy efficiency of the gas turbine.

  JP 2007-77986 A, JP 2006-105084 A, and JP 2008-95695 A disclose a cooling structure of a tip portion of a gas turbine rotor blade. However, these patent documents do not relate to cooling of a gas turbine blade provided with a tip shroud.

Japanese Patent Laid-Open No. 11-13402 Japanese Patent No. 3403501 JP 2009-168017 A JP 2007-77986 A JP 2006-105084 A JP 2008-95695 A

  Accordingly, an object of the present invention is to provide a technique for improving the output and / or energy efficiency of a gas turbine for a gas turbine rotor blade having a structure for cooling a tip shroud with cooling air.

  In one aspect of the present invention, a gas turbine rotor blade that receives a high-temperature gas and rotates in a specific rotation direction is provided. The gas turbine rotor blade includes an airfoil portion having a blade surface formed thereon, an inner peripheral surface joined to a tip of the airfoil portion, and a tip shroud having an outer peripheral surface facing the inner peripheral surface. The airfoil is configured to supply cooling air to the tip shroud. The chip shroud is configured to discharge cooling air supplied through its internal space to the outside of the chip shroud. The chip shroud is configured to discharge cooling air having a flow rate of more than 50% of the total amount of supplied cooling air so as to have a velocity component in the direction opposite to the rotation direction. In such a gas turbine rotor blade, the reaction of cooling air released from the tip shroud works on the gas turbine rotor blade, so that the output and / or energy efficiency of the gas turbine can be improved.

  In order to improve the output and / or energy efficiency of the gas turbine, the chip shroud is configured so that the cooling air having a flow rate of 70% or more of the total amount of supplied cooling air has a velocity component in the direction opposite to the rotation direction. It is more preferable that it is configured to be released into the water. Further, in order to further improve the output and / or energy efficiency of the gas turbine, the chip shroud is configured to discharge the entire amount of the cooling air supplied thereto so as to have a velocity component in the direction opposite to the rotation direction. It is even more preferred that

  In one embodiment, the airfoil has a cooling passage for supplying cooling air to the tip shroud, and the tip shroud has a cooling air hole for discharging the cooling air supplied from the cooling passage.

  In another embodiment, the airfoil has a cavity for supplying cooling air to the tip shroud, and the tip shroud has a plurality of cooling air holes for discharging cooling air supplied from the cavity.

  In yet another embodiment, the airfoil has a plurality of cooling passages for supplying cooling air to the tip shroud, and the tip shroud is connected to the plurality of cooling passages and connected to the cavities for discharging the cooling air. And cooling air holes.

  In yet another embodiment, the tip shroud extends from a position supplied from the airfoil in a direction having a component in the rotational direction to reach a specific position, and has a component in the direction opposite to the rotational direction from the specific position. And has a flow path that reaches the opening through which the cooling air is discharged.

  In another aspect of the present invention, a method for manufacturing a gas turbine rotor blade includes a step of producing a through hole penetrating a tip shroud, and a cooling air hole is formed by closing a front opening in the rotation direction of the through hole. A process.

  In still another aspect of the present invention, a method for manufacturing a gas turbine rotor blade includes a step of forming a plurality of through holes penetrating a tip shroud, a communication portion communicating the through holes, and a front side in a rotation direction of the communication portion. Forming a cooling air hole by closing the opening. In this case, the through hole and the communication portion may be formed by inserting a discharge electrode composed of a plurality of discharge rods and a root portion supporting the discharge rod into the chip shroud.

  ADVANTAGE OF THE INVENTION According to this invention, the output and / or energy efficiency of a gas turbine can be improved about the gas turbine rotor blade which has a structure which cools a chip | tip shroud with cooling air.

It is a side view which shows the structure of the gas turbine rotor blade of one Embodiment of this invention. It is a top view which shows the structure seen from the outer peripheral side of the gas turbine rotor blade of FIG. It is sectional drawing which shows the structure of the gas turbine rotor blade of FIG. It is a top view which shows the structure of the chip | tip shroud in one Embodiment of this invention. It is a top view which shows the structure of the chip | tip shroud in one Embodiment of this invention. 4B is a cross-sectional view showing the structure of the chip shroud of FIGS. 4A and 4B. FIG. The proportion of the flow rate of the cooling air discharged from the tip shroud so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade, and the temperature at the highest temperature in the vicinity of the tip in the tip shroud rotation direction It is a graph which shows an example of the relationship of a raise. It is sectional drawing which shows the structure of the gas turbine rotor blade of other embodiment of this invention. It is a top view which shows the structure of the chip | tip shroud of the gas turbine rotor blade of FIG. It is a top view which shows the structure of the chip | tip shroud in other embodiment of this invention. It is sectional drawing which shows the structure of the chip | tip shroud of FIG. It is a top view which shows the structure of the chip | tip shroud in other embodiment of this invention. It is a top view which shows the manufacturing process of a gas turbine rotor blade provided with the chip | tip shroud of the structure of FIG. It is a top view which shows the manufacturing process of a gas turbine rotor blade provided with the chip | tip shroud of the structure of FIG. It is a top view which shows the structure of the chip | tip shroud in other embodiment of this invention. It is sectional drawing which shows the structure of the cooling air hole provided in the chip | tip shroud of FIG. It is sectional drawing which shows the structure of the chip | tip shroud in further another embodiment of this invention. It is a top view which shows the structure of the chip | tip shroud in other embodiment of this invention. It is sectional drawing which shows the structure of the chip | tip shroud of FIG. It is sectional drawing which shows the structure of the slit provided in the chip | tip shroud of FIG.

  FIG. 1 is a side view showing the structure of a gas turbine blade according to an embodiment of the present invention. The gas turbine rotor blade 1 generally includes a blade root 2 connected to a rotor disk (not shown) of the gas turbine, an airfoil 3 on which a blade surface is formed, and a tip of the airfoil 3. The tip shroud 4 is joined, and the fin 5 is joined to the outer peripheral surface of the tip shroud 4 (the surface facing the surface (inner peripheral surface) to which the airfoil portion 3 is bonded). The fins 5 are provided so as to protrude from the outer peripheral surface of the chip shroud 4 to the outer side in the radial direction of the rotor disk.

  FIG. 2 is a top view showing the structure of the tip shroud 4 and the fins 5 joined thereto. The gas turbine rotor blades 1 are arranged side by side in the circumferential direction of the rotor disk. The tip shrouds 4 of the adjacent gas turbine rotor blades 1 are close to each other, and during operation of the gas turbine, the portion A of the adjacent tip shroud 4 abuts autonomously as the gas turbine rotor blade 1 rotates at high speed. . This contributes to reducing the vibration of the gas turbine rotor blade 1 during operation. Moreover, the fin 5 is provided so that it may extend | stretch in the circumferential direction. The upstream side where the high temperature gas flows across the fin 5 is a relatively high pressure region, and the opposite side (downstream side) is a relatively low pressure region.

  FIG. 3 is a cross-sectional view showing the structure of the gas turbine rotor blade 1 of FIG. The gas turbine rotor blade 1 has a structure that is cooled by the cooling air 7 supplied to the blade root portion 2. Specifically, a cavity 11 is provided in a portion of the airfoil 3 close to the blade root 2, and a pin fin 12 is provided inside the cavity 11. The portion of the airfoil 3 close to the blade root 2 is effectively cooled by disturbing the flow of the cooling air 7 by the pin fins 12. On the other hand, a cooling channel 13 extending in a direction substantially parallel to the radial direction of the rotor disk is provided at a portion near the tip of the gas turbine rotor blade 1. The cooling flow path 13 extends to the inside of the tip shroud 4 provided at the tip of the airfoil 3, and the cooling air 7 is introduced into the tip shroud 4 through the cooling flow path 13.

  4A and 4B are plan views showing the structure of the tip shroud 4 in one embodiment of the present invention, and FIG. 5 is a cross-sectional view taken along the line BB in FIGS. 4A and 4B. The gas turbine rotor blade 1 rotates in the circumferential direction of the turbine shaft. 4A and 4B, the rotation direction of the gas turbine rotor blade 1 is illustrated by arrows.

  Inside the tip shroud 4, a cooling air hole 6 communicating with the cooling flow path 13 of the airfoil 3 is provided. The cooling air 7 is introduced from the cooling flow path 13 into the cooling air hole 6, whereby the chip shroud 4 is cooled.

  One feature of the gas turbine rotor blade 1 of the present embodiment is that the cooling air 7 is discharged from the cooling air holes 6 of the tip shroud 4. In the gas turbine rotor blade 1 of the present embodiment, the relationship between the direction in which the cooling air 7 is discharged from the cooling air hole 6 and the rotation direction of the gas turbine rotor blade 1 is optimized. Or energy efficiency is improved.

  More specifically, in this embodiment, of the total amount of cooling air 7 supplied to the chip shroud 4, the cooling air 7 having a flow rate higher than 50% has a velocity component in the direction opposite to the rotation direction. It is discharged from the shroud 4 or discharged from the chip shroud 4 so that the entire amount of the cooling air 7 supplied to the chip shroud 4 has a velocity component in the direction opposite to the rotation direction of the gas turbine blade 1. When the cooling air 7 is released in such a direction, the work is performed on the gas turbine rotor blade 1 by the reaction, so that the output and / or energy efficiency of the gas turbine can be improved.

  Here, FIG. 4A shows that the cooling air 7 having a flow rate higher than 50% of the total amount of the cooling air 7 supplied to the chip shroud 4 is discharged from the chip shroud 4 so as to have a velocity component in the direction opposite to the rotation direction. An example of such a structure is shown. In the chip shroud 4 of FIG. 4A, only the cooling air hole 6a out of the plurality of cooling air holes 6 discharges the cooling air 7 so as to have a velocity component in the same direction as the rotation direction. The cooling air 7 is discharged so as to have a velocity component in the direction opposite to the rotation direction. On the other hand, FIG. 4B shows a structure in which the entire amount of the cooling air 7 supplied to the tip shroud 4 is discharged from the tip shroud 4 so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade 1. Show.

  From the viewpoint of improving the output and / or energy efficiency of the gas turbine, it is advantageous that the flow rate of the cooling air 7 discharged from the tip shroud 4 is large so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine blade 1. It is. For example, when the total amount of the cooling air 7 supplied to the tip shroud 4 is 100%, the cooling air 7 discharged from the tip shroud 4 so as to have a velocity component opposite to the rotation direction of the gas turbine rotor blade 1. The proportion of the flow rate of is preferably 70% or more. Further, from the viewpoint of improving the output and / or energy efficiency of the gas turbine, the tip shroud is configured so that the total amount of the cooling air 7 supplied to the tip shroud 4 has a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade 1. Most advantageously, it is released from 4.

  However, on the other hand, increasing the flow rate of the cooling air 7 discharged from the tip shroud 4 so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade 1 restricts the arrangement of the cooling air holes 6. In particular, the tip shroud 4 may be insufficiently cooled in the vicinity of the tip 4a in the rotational direction. FIG. 6 shows the discharge from the tip shroud 4 so as to have a velocity component in the direction opposite to the rotational direction of the gas turbine rotor blade 1 when the total flow rate of the cooling air 7 supplied to the tip shroud 4 is constant at a specific value. 5 is a graph showing the relationship between the ratio of the flow rate of the cooling air 7 and the temperature rise of the member of the tip shroud 4 where the temperature rises most near the tip 4a in the rotation direction. The temperature rise is defined as 0 when the proportion of the flow rate of the cooling air 7 released so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade 1 is 50%. From the viewpoint of strength, it is preferable that the temperature rise of the member in the tip shroud 4 is 20 ° C. or less. In this case, according to FIG. 6, from the viewpoint of temperature rise, the direction opposite to the rotation direction of the gas turbine rotor blade 1 is achieved. The proportion of the flow rate of the cooling air 7 discharged from the chip shroud 4 so as to have a velocity component is limited to 70% or less. In this case, it is preferable that the proportion of the flow rate of the cooling air 7 discharged from the tip shroud 4 is 70% so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine blade 1.

  However, as described later, at least one of the plurality of cooling air holes 6 has a component in the rotational direction of the gas turbine rotor blade 1 from a position where the cooling air 7 from the airfoil portion 3 is supplied. In the case where the tip shroud 4 is configured to have a portion extending in the direction in which the tip shroud is provided, the problem of cooling of the tip shroud 4 in the vicinity of the tip 4a in the rotation direction is small. In this case, the proportion of the flow rate of the cooling air 7 discharged from the tip shroud 4 can be increased so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade 1, and depending on the design, the cooling air A structure in which the entire amount of the cooling air 7 discharged from the hole 6 is discharged so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade 1 may be employed.

  In the above-described embodiment, the cooling structure inside the airfoil portion 3 of the gas turbine rotor blade 1 can be variously changed in addition to the cooling structure shown in FIG. FIG. 7 is an example of another cooling structure. In the cooling structure of the airfoil 3 in FIG. 7, the core support rib 14 and the inclined turbulator 15 are provided in the cavity 16 inside the airfoil 3. The core support rib 14 is a structural member for maintaining the structure of the airfoil 3. The cavity 16 is configured such that the cooling air 7 flows while cooling the inner surface of the airfoil 3 and reaches the tip of the airfoil 3, and the inclined turbulator 15 disturbs the flow of the cooling air 7, The airfoil 3 is effectively cooled.

  When the cooling structure of the airfoil portion 3 is changed, the structure of the cooling air hole 6 can be changed according to the change. For example, when the cooling structure of FIG. 7 is employed, the cooling air hole 6 is configured to communicate with the cavity 16 inside the airfoil 3 as illustrated in FIG. 8.

  FIG. 9 is a plan view showing a structure of a chip shroud 4 according to another embodiment of the present invention, and FIG. 10 is a cross-sectional view taken along the line JJ of FIG. In the structure of the tip shroud 4 of FIGS. 9 and 10, a cavity 8 communicating with the plurality of cooling flow paths 13 of the airfoil 3 is provided inside the tip shroud 4, and the cooling air holes 6 of the tip shroud 4 are Connected to the cavity 8. The cavity 8 improves the degree of freedom of distribution of the cooling air 7 and contributes to realizing proper distribution of the cooling air 7. For example, the cooling air 7 is such that a large amount of cooling air 7 is supplied to a portion of the chip shroud 4 where a large thermal stress acts, while a relatively small amount of cooling air 7 is supplied to a portion where the thermal stress is small. Can be realized.

  FIG. 11 is a plan view showing a structure of a tip shroud 4 in still another embodiment of the present invention. For example, as shown in FIG. 4B, in the structure in which the entire amount of the cooling air 7 supplied to the tip shroud 4 is discharged so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine blade 1, the tip shroud 4 There is a case where the cooling of the portion in the vicinity of the tip 4a in the rotation direction is insufficient. Therefore, the chip shroud 4 in FIG. 11 has a structure for dealing with a problem related to cooling of a portion in the vicinity of the tip 4 a in the rotation direction of the chip shroud 4.

  In the tip shroud 4 of FIG. 11, at least one of the cooling air holes 6 (cooling air hole indicated by reference numeral 6 b in FIG. 11) is a position where the cooling air 7 from the airfoil 3 is supplied (FIG. 11). Then, the gas turbine blade 1 extends in a direction having a component in the rotation direction of the gas turbine blade 1 to reach a specific position, and further, from the specific position, the direction opposite to the rotation direction of the gas turbine blade 1 The structure is such that it reaches the opening through which the cooling air 7 is discharged by extending so as to have the following components. In such a structure, a structure in which a large proportion (most simply, all) of the cooling air 7 supplied to the chip shroud 4 is discharged so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade 1. Even so, the portion in the vicinity of the tip 4a in the rotation direction of the tip shroud 4 can be sufficiently cooled.

  The structure of the cooling air hole 6 of the chip shroud 4 as described above can make the manufacturing process complicated. The cooling air hole 6 of the chip shroud 4 can be formed by electric discharge machining. Electric discharge machining is the most typical method of providing a through hole in a metal structure. However, when the cooling air hole 6 is manufactured by this electric discharge machining, it is difficult to accurately manufacture the cooling air hole 6 that does not penetrate the chip shroud 4 as shown in FIGS. 4A and 4B. There is a case. The bent cooling air holes 6 as shown in FIG. 11 are more difficult to manufacture. Below, the manufacturing process for manufacturing the cooling air hole 6 which has not penetrated and the cooling air hole 6 of the bent shape is described.

  12A and 12B are plan views showing a manufacturing process of the cooling air hole 6 in one embodiment of the present invention. First, as shown in FIG. 12A, a through hole 21 penetrating the chip shroud 4 is formed. The through hole 21 is easily formed by, for example, electric discharge machining. Here, in a later step, the gas turbine blade 1 extends from the position where the cooling air 7 from the airfoil 3 is supplied in a direction having a component in the rotational direction of the gas turbine rotor blade 1 and reaches a specific position. A through hole that is formed into a cooling air hole 6 that has a structure that extends from the position so as to have a component in the direction opposite to the rotation direction of the gas turbine rotor blade 1 and reaches the opening that discharges the cooling air 7. With respect to 21, a communication portion 22 that connects adjacent through holes 21 is formed, and the through hole 21 is formed so as to be connected to the communication portion 22. The communication part 22 is formed as an opening provided in the chip shroud 4. When the discharge electrode used for electric discharge machining of the through hole 21 is composed of a plurality of discharge rods and a root portion that supports the discharge rod, such a communication portion 22 extends to the root portion of the discharge electrode. It can be easily formed by inserting it into the chip shroud 4.

  Subsequently, as shown in FIG. 12B, unnecessary openings of the through hole 21 and the communication portion 22 are closed, and the manufacture of the cooling air hole 6 is completed. In the present embodiment, the cooling air hole 6 is formed by closing the opening of the through hole 21 and the communication portion 22 on the front side in the rotational direction of the gas turbine rotor blade 1. The opening may be closed by, for example, welding the closing plate 23 to the chip shroud 4 or filling the metal brazing 24 near the opening of the through hole 21 by brazing. What is important at this time is that from the tip shroud 4 so that the cooling air 7 having a flow rate higher than 50% of the total amount of the cooling air 7 supplied to the tip shroud 4 has a velocity component in the direction opposite to the rotation direction. Realizing a structure that is discharged or discharged from the tip shroud 4 so that the entire amount of the cooling air 7 supplied to the tip shroud 4 has a velocity component in a direction opposite to the rotation direction of the gas turbine rotor blade 1. It is.

  In the structure shown in FIGS. 4A, 4B, and 5, the side surface of the tip shroud 4 (that is, the inner peripheral surface 4b to which the airfoil portion 3 is bonded and the outer peripheral surface 4c to which the fin 5 is bonded) The cooling air hole 6 is opened on the surface connecting the two. However, the cooling air holes 6 may be opened on the outer peripheral surface 4c to which the fins 5 are joined.

  13 is a plan view showing the structure of the tip shroud 4 in which the cooling air holes 6 are provided on the outer peripheral surface 4c, and FIG. 14 is a sectional view showing the structure of the tip shroud 4 in the KK section of FIG. is there. Whether the cooling air hole 6 is open on the side surface of the tip shroud 4 or the outer peripheral surface 4c is essentially not important from the viewpoint of improving the output and / or energy efficiency of the gas turbine. As described above, what is important is that the tip shroud is such that the cooling air 7 having a flow rate higher than 50% of the total amount of the cooling air 7 supplied to the tip shroud 4 has a velocity component opposite to the rotational direction. 4 or a structure in which the entire amount of the cooling air 7 supplied to the tip shroud 4 is released from the tip shroud 4 so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade 1 is realized. It is to be.

  In addition, in the structure in which the cooling air hole 6 is provided in the outer peripheral surface 4c as shown in FIG. 13, the degree of freedom of the shape of the cooling air hole 6 is increased, and the total amount of the cooling air 7 supplied to the chip shroud 4 is The emitted rate can be increased to have a velocity component in the direction opposite to the rotational direction. For example, consider the cooling air hole 6c connected to the cooling flow path 13 closest to the tip 4a of the tip shroud 4 in FIG. The cooling air hole 6c includes a flow path portion 6d extending in a direction having a component in the rotation direction and a flow path portion 6e extending in a direction having a component opposite to the rotation direction. As shown in FIG. 14, the flow path portion 6 e has an opening (6 f) in the outer peripheral surface 4 c of the chip shroud 4. In such a structure, the portion near the tip 4a of the tip shroud 4 can be sufficiently cooled. On the other hand, in the structure in which the cooling air holes 6 are opened in the side surface of the chip shroud 4, it is difficult to realize the cooling air holes 6c arranged as shown in FIG.

  In the above description, the embodiment in which the cooling air hole 6 is configured as a flow path extending from the cooling flow path 13 (or the cavity 16) of the airfoil 3 has been described. However, the cooling structure of the chip shroud 4 and the chip are described. The structure for discharging the cooling air 7 from the shroud 4 is not limited to this. Of the total amount of the cooling air 7 supplied to the chip shroud 4, the cooling air 7 having a flow rate higher than 50% is discharged from the chip shroud 4 so as to have a velocity component in the direction opposite to the rotation direction, or the chip The structure discharged from the tip shroud 4 so that the entire amount of the cooling air 7 supplied to the shroud 4 has a velocity component in the direction opposite to the rotation direction of the gas turbine rotor blade 1 can be realized in various structures. For example, as shown in FIGS. 15 to 18, the present invention is also applicable to a chip shroud 4 that employs a cooling structure in which a cavity 30 is provided inside.

  Specifically, in the structure of the tip shroud 4 shown in FIG. 15, the cooling flow path 13 of the airfoil 3 communicates with the cavity 30 of the tip shroud 4, and the cooling air 7 is discharged from the cooling flow path 13. It is introduced inside the cavity 30. A pin fin 31 is provided in the cavity 30, and the chip shroud 4 is cooled by the cooling air 7 coming into contact with the pin fin 31. The cooling air 7 introduced into the cavity 30 inside the chip shroud 4 is discharged from an opening 33 provided at the end of the chip shroud 4. Here, in the structure of the chip shroud 4 shown in FIG. 15, the cooling air 7 is rectified by the partition wall 32 provided in the vicinity of the opening 33, whereby the total amount of the cooling air 7 supplied to the chip shroud 4. Is discharged from the tip shroud 4 so as to have a velocity component in the direction opposite to the rotation direction of the gas turbine blade 1.

  In the structure of the tip shroud 4 shown in FIGS. 16 to 18, the cavity 16 provided inside the airfoil 3 communicates with the cavity 30 of the tip shroud 4, and the cooling air 7 is discharged from the cavity 16. It is introduced inside the cavity 30. A pin fin 31 is provided inside the cavity 30, and the tip shroud 4 is effectively cooled by disturbing the flow of the cooling air 7 by the pin fin 31. The cooling air 7 used for cooling the chip shroud 4 is discharged from an opening 33 (see FIG. 17) provided at the end of the chip shroud 4 and communicates from the cavity 30 to the outer peripheral surface 4 c of the chip shroud 4. It discharges | emits from the slit 34 provided in (refer FIG.16 and FIG.18). As shown in FIG. 18 which is a cross-sectional view showing the structure of the chip shroud 4 in the LL cross section of FIGS. 16 and 17, the slit 34 has a total amount of the cooling air 7 supplied to the chip shroud 4 as a gas. The turbine blade 1 has a structure that is discharged from the tip shroud 4 so as to have a velocity component in a direction opposite to the rotational direction of the turbine blade 1.

  Although the embodiments of the present invention have been specifically described above, the present invention should not be construed as being limited to the above-described embodiments, and various modifications obvious to those skilled in the art have been made. Can be implemented. In addition, it should be noted that a plurality of the above embodiments may be implemented in combination as long as there is no technical conflict.

1: Gas turbine rotor blade 2: Blade root portion 3: Airfoil portion 4: Tip shroud 4a: Tip 4b: Inner peripheral surface 4c: Outer peripheral surface 5: Fins 6, 6a, 6b, 6c: Cooling air holes 6d, 6e: Flow 6f: Opening 7: Cooling air 8: Cavity 11: Cavity 12: Pin fin 13: Cooling flow path 14: Core support rib 15: Inclined turbulator 16: Cavity 21: Through hole 22: Communication part 23: Closing plate 24: Metal Wax 30: cavity 31: pin fin 32: partition wall 33: opening 34: slit 35: flow path

Claims (11)

A gas turbine rotor blade that receives a high-temperature gas and rotates in a specific rotation direction,
An airfoil with a wing surface formed;
An inner peripheral surface joined to the tip of the airfoil, and a tip shroud having an outer peripheral surface facing the inner peripheral surface,
The airfoil is configured to supply cooling air to the tip shroud;
The tip shroud is configured to discharge the supplied cooling air to the outside of the tip shroud through its internal space.
The chip shroud discharges a part of the supplied cooling air so as to have a velocity component in the rotation direction, and discharges the rest so as to have a velocity component in a direction opposite to the rotation direction. A gas turbine blade configured and configured to discharge the cooling air having a flow rate greater than 70 % so as to have a velocity component in a direction opposite to the rotational direction. The gas turbine rotor blade according to claim 1,
The chip shroud has cooling air holes that discharge the cooling air so as to have a velocity component in the upstream direction of the hot gas.
Gas turbine blade. The gas turbine rotor blade according to claim 1,
The tip shroud has a cooling air hole for cooling the tip shroud in the vicinity of the tip in the rotational direction and discharging the cooling air so as to have a velocity component in the rotational direction.
Gas turbine blade. A gas turbine rotor blade according to any one of claims 1 to 3,
The airfoil has a cooling passage for supplying the cooling air to the tip shroud,
The tip shroud has a cooling air hole for discharging the cooling air supplied from the cooling passage. A gas turbine rotor blade according to any one of claims 1 to 3,
The airfoil has a cavity for supplying the cooling air to the tip shroud;
The tip shroud has a plurality of cooling air holes for discharging the cooling air supplied from the cavity. A gas turbine rotor blade according to any one of claims 1 to 3,
The airfoil has a plurality of cooling passages for supplying the cooling air to the tip shroud,
The tip shroud includes a cavity that communicates with the plurality of cooling passages, and a cooling air hole that is connected to the cavity and discharges the cooling air. A gas turbine rotor blade that receives a high-temperature gas and rotates in a specific rotation direction,
An airfoil with a wing surface formed;
A tip shroud having an inner peripheral surface joined to the tip of the airfoil and an outer peripheral surface facing the inner peripheral surface
And
The airfoil is configured to supply cooling air to the tip shroud;
The tip shroud is configured to discharge the supplied cooling air to the outside of the tip shroud through its internal space.
The chip shroud is configured to discharge the cooling air having a flow rate of more than 50% of the total amount of the supplied cooling air so as to have a velocity component in a direction opposite to the rotation direction;
The tip shroud extends from the position supplied from the airfoil in a direction having a component in the rotational direction to reach a specific position, and has a component in the direction opposite to the rotational direction from the specific position. A gas turbine blade having a flow path that reaches an opening that extends and discharges cooling air. A gas turbine rotor blade that receives a high-temperature gas and rotates in a specific rotation direction,
An airfoil with a wing surface formed;
A tip shroud having an inner peripheral surface joined to the tip of the airfoil and an outer peripheral surface facing the inner peripheral surface
And
The airfoil is configured to supply cooling air to the tip shroud;
The tip shroud is configured to discharge the supplied cooling air to the outside of the tip shroud through its internal space.
The chip shroud is configured to discharge the entire amount of the supplied cooling air so as to have a velocity component in a direction opposite to a rotation direction;
The tip shroud extends from the position supplied from the airfoil in a direction having a component in the rotational direction to reach a specific position, and has a component in the direction opposite to the rotational direction from the specific position. It has a flow path that reaches an opening that extends and discharges cooling air
Gas turbine blade. A manufacturing method for manufacturing the gas turbine rotor blade according to claim 4 or 5,
Producing a through hole penetrating the chip shroud;
And a step of closing the opening on the front side in the rotational direction of the through hole to form the cooling air hole. A manufacturing method for manufacturing the gas turbine rotor blade according to claim 7 or 8 ,
Forming a plurality of through holes penetrating the chip shroud and a communicating portion communicating with the through holes;
And a step of closing the opening on the front side in the rotational direction of the communication portion to form the flow path . It is a manufacturing method of Claim 10 , Comprising:
The method of manufacturing a gas turbine rotor blade, wherein the through hole and the communication portion are formed by inserting a discharge electrode configured of a plurality of discharge rods and a root portion supporting the discharge rod into the tip shroud.

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