Turbine blades and turbines

Abstract

To provide a turbine rotor blade capable of improving vibration control performance while securing physical strength, and a turbine.SOLUTION: A turbine rotor blade comprises: a rotor blade body having a blade root fixed to a rotational shaft extending along an axial line, a base part integrally provided radially outward of the blade root, a blade body integrally provided radially outward of the base, and a fin protruding from the axial end surface of the base part; and a damper piece provided across an inner peripheral region on the radially inner side of the fin on the axial end surface and a fin inner peripheral surface of the fin facing radially inward.SELECTED DRAWING: Figure 3

Description

[Technical field]

[0001] The present disclosure relates to turbine blades and turbines. [Background technology]

[0002] A turbine rotor blade is composed of a blade root attached to a rotating shaft, a base portion integrally formed radially outward of the blade root and consisting of a shank and a platform, and a blade body extending radially outward from the base portion. The base portion is provided with fins protruding from the base portion in the axial direction. The fins prevent the flow of combustion gas from entering between the turbine stator blade and the rotating shaft.

[0003] For example, Patent Document 1 discloses an example in which a damper is applied to a turbine rotor blade in a gas turbine in the aircraft field. When the turbine rotor blade rotates, the vibration of the turbine rotor blade is damped by the frictional force generated between the turbine rotor blade and the damper. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] JP 2000-161005 A Summary of the Invention [Problem to be solved by the invention]

[0005] In recent years, the weight and aspect ratio of turbine blades have been reduced, making it difficult to ensure the strength of the turbine blades themselves. In addition, in order to achieve higher performance and power output, it is necessary to further improve vibration damping.

[0006] The present disclosure has been made to solve the above-mentioned problems, and has an object to provide a turbine blade and a turbine that can improve vibration damping performance while ensuring physical strength. [Means for solving the problem]

[0007] In order to solve the above problems, the turbine rotor blade according to the present disclosure comprises a rotor blade main body having a blade root fixed to a rotating shaft extending along an axis, a base portion provided integrally with the blade root on the radially outer side, a blade body provided integrally with the base on the radially outer side, and a fin protruding from an axial end face of the base, and a damper piece provided across an inner peripheral region on the radially inner side of the fin at the axial end face and a fin inner peripheral surface facing radially inward of the fin. The damper piece has a first plate portion having a plate shape extending radially and circumferentially so as to abut against the inner peripheral region, and a second plate portion connected to the radially outer end of the first plate portion and extending axially and circumferentially so as to abut against the inner peripheral surface of the fin. The turbine rotor blade according to the present disclosure comprises a rotor blade main body having a blade root fixed to a rotating shaft extending along an axis, a base provided integrally with the radially outer side of the blade root, a blade body provided integrally with the radially outer side of the base, and a fin protruding from an axial end face of the base, and a damper piece which is L-shaped when viewed in the circumferential direction and thereby extends across an inner peripheral region on the radially inner side of the fin at the axial end face and a fin inner peripheral surface of the fin facing radially inward.

[0008] The turbine according to the present disclosure includes the rotating shaft and the above-mentioned turbine blades arranged circumferentially on the rotating shaft, and the damper piece is provided across the blade bodies adjacent to each other in the circumferential direction. Effect of the Invention

[0009] According to the present disclosure, it is possible to provide a turbine blade and a turbine that can improve vibration damping performance while ensuring physical strength. [Brief description of the drawings]

[0010] [Figure 1] FIG. 1 is a vertical cross-sectional view showing a schematic configuration of an aircraft gas turbine according to a first embodiment of the present disclosure. [Diagram 2] FIG. 1 is a perspective view of a turbine blade according to a first embodiment of the present disclosure; [Diagram 3] 1 is a longitudinal sectional view of a main portion of a turbine rotor blade according to a first embodiment of the present disclosure. FIG. [Figure 4] FIG. 2 is a view of a damper piece in the turbine rotor blade according to the first embodiment of the present disclosure, as viewed from the axial direction. [Diagram 5] FIG. 4 is a view showing a first modified example of a damper piece in the turbine rotor blade according to the first embodiment of the present disclosure, as viewed from the axial direction. [Figure 6] FIG. 4 is a view showing a second modified example of the damper piece in the turbine rotor blade according to the first embodiment of the present disclosure, as viewed from the axial direction. [Figure 7] FIG. 4 is a longitudinal sectional view of a main portion of a turbine rotor blade according to a second embodiment of the present disclosure. [Figure 8] FIG. 11 is a vertical cross-sectional view of a damper box of a turbine rotor blade according to a second embodiment of the present disclosure. [Figure 9] FIG. 11 is a vertical cross-sectional view of a damper box according to a modified example of a turbine rotor blade according to a second embodiment of the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0011] First Embodiment Hereinafter, a gas turbine 1 according to a first embodiment of the present invention will be described in detail with reference to FIGS.

[0012] <Gas turbine configuration> The gas turbine 1 of this embodiment is used as an engine for an aircraft. The gas turbine 1 includes a compressor 4, a combustion chamber 10, and a turbine 11.

[0013] The compressor 4 generates high-pressure air by compressing air taken in through an intake duct 5. The compressor 4 includes a compressor casing 6, a compressor rotor shaft 7, a compressor rotor blade stage 8, and a compressor stator vane stage 9. The compressor casing 6 covers the compressor rotor shaft 7 from the outer periphery side, and extends in the direction in which an axis O extends (hereinafter referred to as the axis O direction).

[0014] A plurality of compressor rotor blade stages 8 are provided on the compressor rotor shaft 7. These compressor rotor blade stages 8 are arranged at intervals in the direction of the axis O. Each of the plurality of compressor rotor blade stages 8 includes a plurality of compressor rotor blades 8a. The compressor rotor blades 8a extend in a direction along the radius of an imaginary circle centered on the axis O (hereinafter referred to as the radial direction). The compressor rotor blades 8a of each compressor rotor blade stage 8 are arranged on the outer circumferential surface of the compressor rotor shaft 7 in a direction centered on the axis O (hereinafter referred to as the circumferential direction).

[0015] A plurality of compressor stator vane stages 9 are provided in the compressor casing 6. These compressor stator vane stages 9 are arranged at intervals in the direction of the axis O. The compressor stator vane stages 9 are arranged alternately with the compressor rotor blade stages 8 in the direction of the axis O. Each of the plurality of compressor stator vane stages 9 includes a plurality of compressor stator vanes 9a. The compressor stator vanes 9a of each compressor stator vane stage 9 are arranged in the circumferential direction on the inner circumferential surface of the compressor casing 6.

[0016] The combustion chamber 10 generates combustion gas G by mixing fuel F with the high-pressure air generated by the compressor 4 and burning the mixture. The combustion chamber 10 is provided between the compressor casing 6 and a turbine casing 13 of a turbine 11. The combustion gas G generated by the combustion chamber 10 is supplied to the turbine 11.

[0017] The turbine 11 is driven by high-temperature, high-pressure combustion gas G generated in the combustion chamber 10. More specifically, the turbine 11 expands the high-temperature, high-pressure combustion gas G to convert the thermal energy of the combustion gas G into rotational energy. The turbine 11 includes a turbine casing 13, a turbine rotor shaft (rotating shaft) 12, a turbine rotor blade stage 14, and a turbine stator vane stage 15.

[0018] The turbine casing 13 covers the turbine rotor shaft 12 from the outer periphery side. The turbine casing 13 and the above-mentioned compressor casing 6 are integrally connected along the axis O. The compressor casing 6 and the turbine casing 13 constitute a gas turbine casing 2.

[0019] The turbine rotor shaft 12 extends in the direction of the axis O. This turbine rotor shaft 12 and the above-mentioned compressor rotor shaft 7 are aligned in the direction of the axis O and are immovable relative to each other. The turbine rotor shaft 12 and the compressor rotor shaft 7 form a gas turbine rotor shaft 3. This gas turbine rotor shaft 3 is rotatable integrally around the axis O inside the gas turbine casing 2.

[0020] A plurality of turbine rotor blade stages 14 are provided at intervals in the direction of the axis O on the outer circumferential surface of the turbine rotor shaft 12. Each of the plurality of turbine rotor blade stages 14 has a plurality of turbine rotor blades 20 (described in detail below). The plurality of turbine rotor blades 20 included in one turbine rotor blade stage 14 are arranged side by side at equal pitch in the circumferential direction.

[0021] A plurality of turbine stator vane stages 15 are provided on the inner peripheral surface of the turbine casing 13 at intervals in the direction of the axis O. These plurality of turbine stator vane stages 15 are arranged alternately with the turbine rotor blade stages 14 in the direction of the axis O. Each of these turbine stator vane stages 15 includes a plurality of turbine stator vanes 15a. The turbine stator vanes 15a provided in each turbine stator vane stage 15 are arranged side by side at equal pitch in the circumferential direction on the inner peripheral surface of the turbine casing 13.

[0022] In operating the gas turbine 1 having the above-described configuration, first, the compressor rotor shaft 7 is rotationally driven by an external drive source. As the compressor rotor shaft 7 rotates, external air is successively compressed to generate high-pressure air. This high-pressure air is supplied into the combustion chamber 10 through the compressor casing 6. In the combustion chamber 10, the high-pressure air is mixed with fuel F and then combusted to generate high-temperature, high-pressure combustion gas G. The combustion gas G is supplied into the turbine 11 through the turbine casing 13. In the following, the side from which the combustion gas G flows of both sides in the direction of the axis O may be simply referred to as the "upstream side," and the opposite side may be simply referred to as the "downstream side."

[0023] In the turbine 11, the combustion gas G collides sequentially with the turbine rotor blade stage 14 and the turbine stator vane stage 15, thereby providing a rotational driving force to the turbine rotor shaft 12. This rotational energy is mainly utilized to drive the compressor 4. The combustion gas G that has driven the turbine 11 has its flow velocity increased by the exhaust nozzle 16, becoming a jet that generates thrust, and is discharged to the outside from the injection port 17.

[0024] <Turbine blades> Next, the overall configuration of the rotor blade body 21 of the turbine rotor blade 20 will be described with reference to Fig. 2. The rotor blade body 21 of the turbine rotor blade 20 includes a blade root 30, a base 40, fins 70, a blade body 90, and a shroud 91.

[0025] <wing root> The blade root 30 is provided at the radially inner end of the rotor blade body 21. The blade root 30 fixes the rotor blade body 21 to the turbine rotor shaft 12. The blade root 30 has a so-called Christmas tree shape with unevenness formed on both circumferential sides. The blade root 30 has a uniform shape from one side in the direction of the axis O (the upstream side in the flow direction of the combustion gas G) to the other side in the direction of the axis O (the downstream side in the flow direction of the combustion gas G). The blade root 30 is inserted from the direction of the axis O into a groove formed in the turbine rotor shaft 12, whereby the rotor blade body 21 is fixed integrally to the turbine rotor shaft 12.

[0026] <Base> The base portion 40 is provided radially outward of the blade root 30. The base portion 40 has a shank 41 and a platform 50.

[0027] <Shank> The shank 41 is fixed integrally to the radially outer end of the blade root 30. A pair of surfaces of the shank 41 facing both circumferential sides are defined as shank end faces 42. The shank end faces 42 are flat surfaces extending in the radial direction and along the axis O direction. The circumferential distance between the pair of shank end faces 42 of the shank 41 is greater than the circumferential dimension of the blade root 30.

[0028] <Platform> The platform 50 is provided integrally with the shank 41. The platform 50 has a plate shape that covers one side of the shank 41 in the axis O direction, the radially outer side, and the other side in the axis O direction. The surface of the platform 50 facing radially outward is an outer circumferential end surface 51 that faces along the flow path of the combustion gas G.

[0029] A pair of surfaces of the platform 50 facing in the circumferential direction are each defined as a circumferential end face 52. The circumferential end face 52 is U-shaped with an open radially inward side when viewed in the circumferential direction. The pair of circumferential end faces 52 are located circumferentially outward (in a direction moving away from the circumferential center of the base 40 to one side and the other side in the circumferential direction) than the corresponding shank end faces 42 of the shank 41. The circumferential end faces 52 of the platforms 50 of adjacent rotor blade bodies 21 face each other in the circumferential direction. A gap is formed between the platforms 50 of adjacent rotor blade bodies 21.

[0030] A pair of surfaces of the platform 50 facing one side and the other side in the direction of the axis O are respectively set as axial end surfaces 53. The upper ends of the axial end surfaces 53 are connected to the end portions of the outer peripheral end surfaces 51 in the direction of the axis O. The lower ends of the axial end surfaces 53 extend to the lower end of the base portion 40.

[0031] <Finn> The fins 70 are formed so as to protrude in the direction of the axis O from the axial end surface 53 of the platform 50 of the base portion 40 .

[0032] In this embodiment, a pair of fins 70 are provided corresponding to the axial end face 53 on one side in the direction of the axis O and the axial end face 53 on the other side in the direction of the axis O. That is, the fins 70 are provided on both the upstream side and the downstream side of the turbine rotor blade 20. The pair of fins 70 are provided so as to protrude outward in the direction of the axis O (in a direction away from the center in the direction of the axis O of the rotor blade main body 21 in the direction of the axis O). That is, the fin 70 on one side in the direction of the axis O protrudes to one side in the direction of the axis O, and the fin 70 on the other side in the direction of the axis O protrudes to the other side in the direction of the axis O.

[0033] The fin 70 has a plate shape extending in the direction of the axis O and in the circumferential direction. The circumferential dimension of the fin 70 is the same as the circumferential dimension of the platform 50. Therefore, a pair of circumferential end faces 71a of the fin 70 facing in the circumferential direction are flush with the circumferential end face 52 of the platform 50.

[0034] <Wing body> The blade body 90 is fixed integrally to the outer peripheral end face 51 of the platform 50 and extends radially outward from the outer peripheral end face 51. The cross section of the blade body 90 perpendicular to the radial direction is airfoil-shaped. The surface of the blade body 90 facing one circumferential side is the ventral side, and the surface facing the other circumferential side is the suction side. The combustion gas G flowing from the upstream side to the downstream side hits the ventral side, causing the rotor blade main body 21 to rotate.

[0035] <Shroud> The shroud 91 is provided integrally with the radially outer end of the blade body 90. The shroud 91 has a shape that protrudes in the axis O direction and the circumferential direction beyond the radially outer end of the blade body 90. The shrouds 91 of adjacent rotor blade bodies 21 contact each other via their contact surfaces.

[0036] <Vibration control structure of rotor blade body> Next, the vibration damping structure of the turbine rotor blade 20 will be described in detail with reference to Fig. 3. The turbine rotor blade 20 further includes a damper piece 100 as a vibration damping member. The damper piece 100 is provided on the outer surface of the rotor blade body 21. The damper piece 100 is provided across the axial end face 53 of the platform 50 of the base 40 and the fin 70. In this embodiment, the damper pieces 100 are provided on both the upstream side and the downstream side of the turbine rotor blade 20.

[0037] <Detailed structure of the base> A pair of axial end faces 53 of the platform 50 of the base portion 40 described above are radially divided into two by the corresponding fins 70. The radially outer portions of the fins 70 at the axial end faces 53 are defined as outer circumferential region 54. The radially outer end of the outer circumferential region 54 is connected to the outer circumferential end face 51. The outer circumferential region 54 is inclined radially inward and outward in the direction of axis O.

[0038] <Inner area> A radially inner region of the fin 70 on the axial end face 53 is defined as an inner peripheral region 60. The inner peripheral region 60 is a surface facing the axis O and extends in the circumferential and radial directions. The radial dimension of the inner peripheral region 60 is longer than the radial dimension of the outer peripheral region 54. That is, the fin 70 is provided at a position on the axial end face 53 closer to the radially outer side.

[0039] The inner peripheral region 60 has an inner peripheral end face 63 and a first sliding contact surface 61 . The inner peripheral end surface 63 is a surface that forms the radially inner end portion of the axial end surface 53 . The first sliding contact surface 61 is a portion sandwiched between the inner circumferential end face 63 and the fin 70, and is positioned so as to retreat more inward in the axial O direction (toward the center of the rotor blade main body 21 in the axial O direction) than the inner circumferential end face 63. In other words, the first sliding contact surface 61 is a surface formed by cutting out a portion from the basic configuration of the base 40. The first sliding contact surface 61 has a planar shape extending in two directions, the circumferential direction and the axial O direction.

[0040] A first contact portion 62 is formed at a radially inner end of the first sliding contact surface 61, and protrudes outward in the direction of the axis O from the first sliding contact surface 61. The first contact portion 62 is formed at a step between the first sliding contact surface 61 and the inner peripheral end, and faces radially outward. The first contact portion 62 is provided in the circumferential direction. A fence portion 64 is provided at the end portion on the outer side in the direction of the axis O of the first contact portion 62 such that an inner peripheral end face 63 protrudes radially outward. The fence portion 64 is provided in the circumferential direction. In this manner, a groove-like structure extending in the circumferential direction is formed between the first sliding contact surfaces 61 by the first contact portions 62 and the fence portions 64. This groove is a damper insertion groove 65.

[0041] <Detailed structure of fins> The surface of the fin 70 facing radially outward is a fin outer circumferential surface 71 extending in the axial direction and the circumferential direction. An end portion of the fin outer circumferential surface 71 on the inner side in the axial direction O is connected to an end portion of the outer circumferential region 54 on the axial end face 53 on the inner side in the radial direction.

[0042] <Inner surface of fin> The surface of the fin 70 facing radially inward is a fin inner peripheral surface 80 that extends in the direction of the axis O and in the circumferential direction. The fin inner peripheral surface 80 has a second sliding contact surface 81 and a tip inner surface 83 .

[0043] The second sliding surface 81 is the part of the fin inner surface 80 on the inside in the direction of axis O, and extends in the circumferential and radial directions. The second sliding surface 81 may extend flatly in the circumferential direction, or may extend curvedly around the axis O as it extends in the circumferential direction.

[0044] An inner end of the second sliding contact surface 81 in the direction of the axis O is connected circumferentially to a radially outer end of the inner peripheral region 60 at the axial end face 53, i.e., a radially outer end of the first sliding contact surface 61. The first sliding contact surface 61 and the second sliding contact surface 81 are connected to be perpendicular to each other when viewed in the circumferential direction.

[0045] The tip inner surface 83 is a portion of the fin inner circumferential surface 80 on the outer side in the direction of the axis O, i.e., a portion on the tip side of the fin 70. The tip inner surface 83 is disposed so as to be adjacent to the outer side in the direction of the axis O of the second sliding contact surface 81. The tip inner surface 83 is provided so as to advance radially inwardly from the tip inner surface 83. In other words, the second sliding contact surface 81 is recessed so as to retreat radially outwardly from the tip inner surface 83. That is, the second sliding contact surface 81 is a surface formed by cutting out a portion of the fin inner circumferential surface 80 of the fin 70.

[0046] A step surface between the second sliding contact surface 81 and the tip inner surface 83 serves as a second abutment portion 82 facing inward in the direction of the axis O. The second abutment portion 82 extends in the circumferential direction.

[0047] A recess 84 is formed in a part of the second sliding contact surface 81 in the direction of the axis O. The recess 84 is recessed radially outward from the second sliding contact surface 81 and extends in the circumferential direction. The recess 84 is formed in a position spaced apart from an end portion of the second sliding contact surface 81 on the outer side in the direction of the axis O and an end portion of the second sliding contact surface 81 on the inner side in the direction of the axis O, i.e., in a middle portion of the second sliding contact surface 81 in the direction of the axis O.

[0048] <Damper Piece> The damper piece 100 is made of a metal such as a Ni-based alloy or titanium. Note that a high damping metal may be used as the damper piece 100 if the temperature of the environment in which it is used is appropriate. The damper piece 100 has a first plate portion 110 and a second plate portion 120. The thickness of the first plate portion 110 and the second plate portion 120 is set to, for example, 2 to 10 mm.

[0049] <First plate part> The first plate portion 110 has a rectangular plate shape extending in the circumferential direction and the radial direction. That is, the sides of the first plate portion 110 extend so as to coincide with each other in the circumferential direction and the radial direction. The surface of the first plate portion 110 facing inward in the direction of the axis O is in surface contact with the first sliding contact surface 61 of the base portion 40. The radially inner end portion of the first plate portion 110 abuts against the first abutment portion 62 from the radial direction. The radially inner end portion of the first plate portion 110 is covered from the outside in the direction of the axis O by the fence portion 64. In other words, the radially inner end portion of the first plate portion 110 is inserted into a damper insertion groove 65 defined by the first abutment portion 62 and the fence portion 64.

[0050] <Second plate part> The second plate portion 120 has a plate shape extending in the circumferential direction and in the axial direction O. That is, the sides of the second plate portion 120 extend so as to coincide with the circumferential direction and the axial direction O. An end portion of the second plate portion 120 on the inner side in the axial direction O is connected to an end portion of the first plate portion 110 on the radially outer side over the circumferential direction. This gives the damper piece 100 an L-shape when viewed in the circumferential direction.

[0051] The surface of the second plate portion 120 facing outward in the direction of the axis O is in surface contact with the second sliding contact surface 81 of the fin 70. The second plate portion 120 may be in the shape of a flat plate or in the shape of a plate curved around the axis O, depending on the shape of the second sliding contact surface 81. The end portion of the second plate portion 120 on the outer side in the direction of the axis O abuts against the second abutment portion 82 from inside in the direction of the axis O.

[0052] The damper piece 100 further has a protrusion 122 that protrudes radially outward from a portion of the surface facing radially outward of the second plate portion 120 and extends circumferentially. The protrusion 122 has a shape corresponding to the recess 84 of the fin inner circumferential surface 80 at a position corresponding to the recess 84. As a result, when the damper piece 100 is attached to the rotor blade main body 21, the protrusion 122 of the damper piece 100 is fitted into the recess 84.

[0053] 4, the above-described damper piece 100 has a divided structure in which a plurality of damper pieces 100 are arranged in the circumferential direction of the entire turbine rotor blade stage 14. Each damper piece 100 is provided across the rotor blade bodies 21 of adjacent turbine rotor blades 20. <Action and effect> In the gas turbine 1 configured as described above, when an exciting force acts on the turbine rotor blade 20 while the turbine rotor blade 20 is rotating, the exciting force is suppressed by the damper piece 100. That is, when an exciting force acts on the turbine rotor blade 20 and the turbine rotor blade 20 vibrates, the damper piece 100, which abuts against the first sliding contact surface 61 and the second sliding contact surface 81 of the rotor blade main body 21, slides against the first sliding contact surface 61 and the second sliding contact surface 81. This generates a frictional force between the damper piece 100 and the rotor blade main body 21, and the vibration energy can be dissipated by this frictional force. Therefore, the damper piece 100 can provide a vibration damping effect on the turbine rotor blade 20 as a whole.

[0054] Particularly in this embodiment, the damper piece 100 is L-shaped in the circumferential direction and is made up of a first plate portion 110 and a second plate portion 120, and is configured to generate frictional forces between the first plate portion 110 and the second plate portion 120 and both the first sliding contact surface 61 of the base portion 40 and the second sliding contact surface 81 of the fin 70. That is, frictional forces that contribute to vibration damping can be generated not only between the first plate portion 110 and the second plate portion 120 and the base portion 40 but also between the first plate portion 110 and the second plate portion 120 and the fin 70. Therefore, a large vibration damping effect can be obtained for the turbine rotor blade 20 as a whole.

[0055] Furthermore, by installing the damper piece 100 having such a first plate portion 110 and a second plate portion 120, it is possible to reinforce not only the base portion 40 but also the physical size of the fin 70, which is relatively thin and has low strength. Therefore, the physical strength of the turbine rotor blade 20 as a whole can be ensured.

[0056] On the other hand, the first sliding contact surface 61 and the second sliding contact surface 81 with which the first plate portion 110 and the second plate portion 120 come into contact are surfaces formed by cutting out a portion from the original shape of the rotor blade main body 21. In other words, the first plate portion 110 and the second plate portion 120 are configured to be installed in the cut-out portion. Therefore, while ensuring high damping by the first plate portion 110 and the second plate portion 120, it is possible to prevent the weight of the turbine rotor blade 20 as a whole from increasing inadvertently. This allows for further performance improvement and reliability improvement by expanding the degree of freedom in design.

[0057] Furthermore, in this embodiment, the damper piece 100 abuts against the first abutment portion 62 and the second abutment portion 82, so that the damper piece 100 can be appropriately positioned and held relative to the rotor blade body. That is, the damper piece 100 is provided so as to be stretched between the first abutment portion 62 and the second abutment portion 82, so that the damper piece 100 can be configured to slide in response to vibration while being appropriately fixed.

[0058] Furthermore, the radially inner end of the first plate portion 110 is configured to be covered from the direction of the axis O by the fence portion 64 of the base 40. That is, since the radially inner end of the first plate portion 110 is configured to be inserted into the damper insertion groove 65, the damper piece 100 can be securely held relative to the base 40 and the damper piece 100 can be easily attached to the base 40.

[0059] Furthermore, since the convex portion 122 provided on the second plate portion 120 of the damper piece 100 is configured to fit into the concave portion 84 of the fin inner peripheral surface 80, the second plate portion 120 can be positioned and attached more appropriately.

[0060] Furthermore, in this embodiment, each of the damper pieces 100 is provided across adjacent turbine rotor blades 20. This makes it possible to seal the gap between the platforms 50 of the adjacent turbine rotor blades 20, thereby preventing the combustion gas G from passing through the gap. As a result, the performance of the gas turbine 1 can be improved.

[0061] <First Modification of First Embodiment> Note that the damper piece 100 may be configured to be provided across a plurality of rotor blade bodies 21 arranged in the circumferential direction, as shown in Fig. 5, for example. In this case, the first plate portion 110 and the second plate portion 120 of the damper piece 100 have a shape that extends in the circumferential direction more than the configuration of the first embodiment, for example, a shape that extends across the entire upper half of the gas turbine 1. This also makes it possible to obtain the damping performance of the damper piece 100 while suppressing the combustion gas G from leaking out between the base portions 40 of adjacent turbine rotor blades 20.

[0062] <Second Modification of First Embodiment> Furthermore, the damper piece 100 may have a configuration that has been subjected to topology optimization, for example, as shown in Fig. 6. That is, for example, a vibration analysis using the finite element method may be performed on the turbine rotor blade 20, and the shape of the damper piece 100 itself may be optimized so as to minimize vibration. In the example of Fig. 6, a concave-convex structure is formed by removing a part of the tip of the second plate portion 120. This not only optimizes the vibration damping effect, but also reduces the weight. It should be noted that the damper piece 100 may be manufactured using a three-dimensional additive manufacturing method based on the result of the topology optimization. In this case, the damper piece 100 may be formed in a three-dimensional lattice shape.

[0063] Second Embodiment Next, a second embodiment of the present invention will be described with reference to Figs. 7 and 8. In Figs. 7 and 8, components similar to those in the first embodiment are given the same reference numerals and detailed description thereof will be omitted.

[0064] As shown in FIG. 7, the turbine rotor blade 20 of the second embodiment has a damper box 140 in addition to the configuration of the first embodiment. The damper box 140 is provided integrally with the damper piece 100. As shown in Fig. 8, the damper box 140 has a box body 141 and a spherical damper 142 serving as a moving damper.

[0065] The box body 141 has a rectangular box shape and is made of the same material as the damper piece 100 or another steel material. Two of the outer surfaces of the box body 141 are fixed integrally to the first plate portion 110 and the second plate portion 120 of the damper piece 100. A space is formed inside the box body 141.

[0066] The spherical damper 142 is a sphere made of the same material as the damper piece 100 or the same material as the box body 141. A plurality of the spherical dampers 142 are provided in the space within the box body 141. The spherical dampers 142 are provided so as to be able to move freely within the space within the box body 141.

[0067] <Action and effect> According to the turbine rotor blade 20 of the second embodiment, in addition to the advantageous effects of the first embodiment, a vibration damping effect due to the damper box 140 can be obtained. That is, when an exciting force acts on the turbine rotor blades 20 and vibration occurs, the spherical damper 142 in the box body 141 collides with and slides against the inner surface of the box body 141. This makes it possible to dissipate the vibration of the turbine rotor blades 20 as collision energy or friction energy. Therefore, it is possible to obtain the effect of damping the vibration of the turbine rotor blades 20. Furthermore, by using the damper piece 100 and the damper box 140 together, the vibration damping effect of the turbine rotor blade 20 as a whole can be improved.

[0068] <Modification of the second embodiment> As the moving damper housed in the box body 141 of the damper box 140, for example, as shown in Fig. 9, a plate-shaped damper 143 movable within the box body 141 may be used. The plate-shaped damper 143 is housed in the box body 141 with each outer surface facing each inner surface of the box body 141. When the turbine rotor blades 20 vibrate, the plate-shaped damper 143 collides with and slides against the inner surface of the box body 141. This also makes it possible to obtain a high vibration damping effect, similar to the above. As the moving damper, not only the spherical damper 142 and the plate-shaped damper 143 but also various shapes can be used.

[0069] <Other embodiments> Although the embodiment of the present invention has been described above, the present invention is not limited to this, and can be modified as appropriate without departing from the technical concept of the invention.

[0070] For example, in the embodiment, a pair of fins 70 are provided on the upstream side and downstream side, and the damper pieces 100 are provided on both the upstream side and downstream side corresponding to these fins 70, but the present invention is not limited to this. The damper piece 100 may be provided only on at least one of the upstream side and downstream side.

[0071] Furthermore, in the second embodiment, an example has been described in which a pair of damper boxes 140 are provided corresponding to a pair of damper pieces 100, but the damper box 140 may be provided for only one of the damper pieces 100.

[0072] <Additional Notes> The turbine rotor blades 20 and the turbine 11 described in each embodiment can be understood, for example, as follows.

[0073] (1) A turbine rotor blade 20 according to a first embodiment comprises a rotor blade main body 21 having a blade root 30 fixed to a rotating shaft extending along an axis O, a base 40 integrally formed radially outward of the blade root 30, a blade body 90 integrally formed radially outward of the base 40, and a fin 70 protruding from an axial end face 53 of the base 40, and a damper piece 100 provided across an inner circumferential region 60 on the radial inside of the fin 70 at the axial end face 53 and a fin inner circumferential surface 80 facing radially inward of the fin 70.

[0074] With the above-mentioned configuration, when an exciting force acts on the turbine rotor blade 20 while the turbine rotor blade 20 is rotating, the damper piece 100, which is in contact with the inner circumferential region 60 of the base 40 of the turbine rotor blade 20 and the fin inner circumferential surface 80 of the fin 70, slides against the inner circumferential region 60 and the fin inner circumferential surface 80, generating a frictional force. This makes it possible to obtain a vibration damping effect due to the frictional force. In other words, since the frictional force can be obtained over a wide region, such as the inner circumferential region 60 and the fin inner circumferential surface 80, a large damping effect can be obtained for the turbine rotor blade 20 as a whole. Furthermore, since the damper piece 100 ensures the size of the base 40 and the fins 70, the strength of the turbine rotor blade 20 as a whole can be improved.

[0075] (2) The turbine blade 20 according to the second aspect is the first aspect, wherein the damper piece 100 has a first plate portion 110 having a plate shape extending radially and circumferentially so as to abut against the inner peripheral region 60, and a second plate portion 120 connected to a radially outer end portion of the first plate portion 110 and extending in the axial direction O and circumferentially so as to abut against the fin inner peripheral surface 80.

[0076] Since the first plate portion 110 abuts against the inner peripheral region 60 of the base portion 40 and the second plate portion 120 abuts against the fin inner peripheral surface 80, the exciting force acting on the turbine rotor blade 20 can be appropriately damped. Furthermore, the first plate portion 110 and the second plate portion 120 can ensure the size of the base portion 40 and the fins 70 .

[0077] (3) In the third aspect, in the turbine rotor blade 20 of the second aspect, the base 40 has a first abutment portion 62 against which the radially inner end portion of the first plate portion 110 abuts, and the fin 70 has a second abutment portion 82 against which the tip of the second plate portion 120 in the axis O direction abuts.

[0078] The damper piece 100 abuts against the first abutment portion 62 and the second abutment portion 82, so that the damper piece 100 can be appropriately positioned and held relative to the base portion 40.

[0079] (4) A fourth aspect of the turbine rotor blade 20 is the third aspect, wherein the base 40 further has a fence portion 64 extending circumferentially so as to cover the radially inner end of the first plate portion 110 from the direction of the axis O.

[0080] This allows the damper piece 100 to be securely held on the base 40 , and also allows the damper piece 100 to be easily attached to the base 40 .

[0081] (5) In the turbine blade 20 of the fifth aspect, in any one of the second to third aspects, a recess 84 recessed radially inward is formed in a portion of the fin inner surface 80, and a protrusion 122 that fits into the recess 84 is formed on the radially outward surface of the second plate portion 120 of the damper piece 100.

[0082] This makes it possible to more appropriately position and attach the second plate portion 120 of the damper piece 100 to the fin inner peripheral surface 80 .

[0083] (6) The turbine rotor blade 20 according to the sixth aspect, in any one of the first to fifth aspects, has a box body 141 fixed to the damper piece 100, and a movable damper movably arranged within the box body 141.

[0084] When an exciting force acts on the turbine rotor blade 20, the moving damper in the damper box 140 collides or slides against the inner surface of the damper box 140. This makes it possible to more appropriately reduce the exciting force.

[0085] (7) A turbine 11 according to a seventh aspect includes the rotating shaft and any one of first to sixth turbine blades 20 arranged circumferentially on the rotating shaft, and the damper piece 100 is provided across adjacent blade bodies in the circumferential direction.

[0086] The damper piece 100 can seal the gap between the adjacent turbine rotor blades 20. As a result, the performance of the gas turbine 1 can be improved. [Explanation of symbols]

[0087] 1...gas turbine 2...gas turbine casing 3...gas turbine rotor shaft 4...compressor 5...intake duct 6...compressor casing 7...compressor rotor shaft 8...compressor rotor blade stage 8a...compressor rotor blade 9...compressor stator vane stage 9a...compressor stator vane 10...combustion chamber 11...turbine 12...turbine rotor shaft (rotating shaft) 13...turbine casing 14...turbine rotor blade stage 15...turbine stator vane stage 15a...turbine stator vane stage 16...exhaust nozzle 17...injection port 20...turbine rotor blade 21...rotor blade body 30...blade root 40...base 41...shank 42...shank end face 50...platform 51...outer peripheral end face 52...circumferential end face 53...axial end face 54...outer peripheral region 60...inner peripheral region 61...first sliding contact surface 62...first contact portion 63...inner peripheral end face 64...fence portion 65...damper insertion groove 70...fin 71a...fin circumferential end face 71...fin outer peripheral surface 80...fin inner peripheral surface 81...second sliding contact surface 82...second contact portion 83...tip inner surface 84...recess 90...wing body 91...shroud 100...damper piece 110...first plate portion 111...inner peripheral end portion 120...second plate portion 121...axial tip portion 122...projection portion 140...damper box 141...box body 142...spherical damper (moving damper) 143...plate damper (moving damper) F...fuel G...combustion gas O...axis

Claims

1. a rotor blade main body having a blade root fixed to a rotating shaft extending along an axis, a base portion provided integrally with the blade root on the radially outer side, a blade body provided integrally with the base portion on the radially outer side, and a fin protruding from an axial end surface of the base portion; a damper piece provided across an inner circumferential region on a radially inner side of the fin at the axial end surface and a fin inner circumferential surface facing radially inward of the fin; Equipped with The damper piece is a first plate portion extending in a radial direction and a circumferential direction so as to abut against the inner peripheral region; A second plate portion connected to a radially outer end of the first plate portion and extending in the axial and circumferential directions so as to abut against the fin inner peripheral surface; A turbine blade having a

2. The base portion has a first abutment portion against which a radially inner end portion of the first plate portion abuts, The turbine rotor blade according to claim 1 , wherein the fin has a second abutment portion against which an axial tip of the second plate portion abuts.

3. The turbine rotor blade according to claim 2 , wherein the base portion further includes a fence portion extending in a circumferential direction so as to cover a radially inner end portion of the first plate portion from the axial direction.

4. A recess is formed in a part of the inner peripheral surface of the fin, the recess being recessed radially inward, The turbine rotor blade according to claim 1 , wherein a convex portion that fits into the concave portion is formed on a radially outward surface of the second plate portion of the damper piece.

5. A rotor blade body having a blade root fixed to a rotating shaft extending along an axis, a base integrally provided radially outward from the blade root, a blade body integrally provided radially outward from the base, and a fin protruding from an axial end face of the base; a damper piece that is L-shaped when viewed in the circumferential direction and is provided across an inner circumferential region on the radially inner side of the fin at the axial end face and a fin inner circumferential surface of the fin that faces the radially inner side; A turbine blade comprising:

6. 6. The turbine rotor blade according to claim 1, further comprising: a box body fixed to the damper piece; and a moving damper provided movably within the box body.

7. The rotation shaft; The turbine rotor blade according to any one of claims 1 to 6, which is arranged in a circumferential direction on the rotating shaft; Equipped with The damper pieces are provided across adjacent rotor blade bodies in the circumferential direction.

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