JP2013253522A - Blisk - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve durability of a blisk 1 to a high level by sufficiently and stably reducing vibration stress acting on the blisk 1 while achieving a reduction in weight of the blisk 1.SOLUTION: A locking peripheral groove 9 (21) is formed in a radial inner surface 5i of a platform 5. A cylindrical friction damper 11 (23) is pressed and provided by elastic force thereof to the radial inner surface 5i of the platform 5. The friction damper 11 (23) has a separation part 11f (23f) in a part in a circumferential direction. A locking flange 13 (25) lockable to the locking peripheral groove 9 (21) is formed at an axial end of the friction damper 11 (23).

Description

  The present invention relates to a blisk (integrated impeller) used as a component of a rotor such as a compressor rotor in a gas turbine engine such as an aircraft engine.

  In general, blisks are integrated at equal intervals along the circumferential direction on a circular disk that is rotatable around the rotor axis, an annular platform that is integrally formed on the outer periphery of the disk, and a radially outer surface of the platform. And a plurality of formed moving blades. In recent years, research and development on blisks has been actively conducted, and blisks having a damping function due to friction have already been developed (see Patent Document 1). And the structure of the characteristic part of the blisk which concerns on a prior art is as follows.

  The first blisk according to the prior art (in the case of the prior art 1) is characterized in that an insertion circumferential groove is formed on the radially inner side surface of the platform, and an annular friction damper is formed in the insertion circumferential groove of the platform. Is provided. Further, the friction damper is pressed against the bottom surface of the insertion circumferential groove of the platform by its elastic force, and has a dividing portion (abutting portion) in a part of the circumferential direction. As a result, during operation of the gas turbine engine, the friction damper is pressed against the bottom surface of the insertion circumferential groove of the platform by the centrifugal force caused by the rotation of the blisk, and the damping function by the friction between the friction damper and the platform is exhibited.

  As a feature of the second blisk according to the prior art (in the case of the prior art 2), an insertion circumferential groove is formed on the side surface in the axial direction of the platform, and a cylindrical friction damper is formed in the insertion circumferential groove of the platform. Is provided. Further, the friction damper is pressed against the inner wall surface on the radially outer side of the insertion circumferential groove of the platform by its elastic force, and has a dividing portion in a part in the circumferential direction. As a result, during operation of the gas turbine engine, the friction damper is pressed against the inner wall surface on the radially outer side of the circumferential groove of the platform by the centrifugal force generated by the blisk rotation, and the damping function by friction between the friction damper and the platform is exhibited. Let

JP 2009-197649 A

  By the way, in the case of the prior art 1, the friction damper is pressed against the bottom surface of the insertion groove of the platform by its elastic force, so that a sufficient contact area between the friction damper and the platform during operation of the gas turbine engine is ensured. Can not do it. For this reason, the vibration between the friction damper and the platform cannot sufficiently reduce the vibration of the rotor blade, and the vibration stress acting on the blisk becomes high, making it difficult to improve the durability of the blisk. There is.

  On the other hand, in the case of the prior art 2, the cylindrical friction damper is pressed against the radially outer wall surface of the insertion circumferential groove of the platform by its elastic force, and the friction damper and the platform during the operation of the gas turbine engine. However, because the insertion groove is formed on the side surface in the axial direction of the platform, the thickness of the platform increases by the width of the insertion groove of the platform, and the operation of the gas turbine engine Inside, the friction damper is easy to come off (easy to come off) from the platform. For this reason, one of the original purposes of adopting the blisk is to reduce the weight of the member, and the vibration of the rotor blades is stably reduced by the friction between the friction damper and the platform. There is a problem that it is difficult to improve the level to a high level.

  That is, in the case of the prior art 1 and the prior art 2, it is difficult to improve the durability of the blisk to a high level by reducing the vibration stress acting on the blisk sufficiently and stably while reducing the weight of the blisk. There is a problem that.

  Therefore, an object of the present invention is to provide a blisk having a novel configuration that can solve the above-described problems.

  A feature of the present invention is that in a blisk (integrated impeller) used as a component of a rotor in a gas turbine engine, a circular disk that can rotate around the axis of the rotor (axis of the blisk), and the disk An annular platform that is integrally formed on the outer peripheral edge and has a radially outer surface that is a flow path surface for gas (air or combustion gas), and a radially outer surface of the platform that is integrated at equal intervals along the circumferential direction. A plurality of rotor blades formed, a circumferential circumferential groove or a locking projection is formed on a radially inner side surface of the platform, and a cylindrical (band-shaped) friction damper is formed on the radially inner side surface of the platform. Is provided by being pressed by its elastic force, the friction damper has a dividing portion (abutting portion) in a part in the circumferential direction, and the locking circumferential groove or the front portion is provided at an axial end portion of the friction damper. And summarized in that lockable locking flange locking projection is formed.

  In the specification and claims of the present application, “rotor” means a compressor rotor, a fan roller, and a turbine rotor, and “axial direction” means the axial direction of the rotor, in other words, For example, it refers to the axial direction of the blisk.

  According to a feature of the invention, during operation of the gas turbine engine, the friction damper is pressed against the radially inner side surface of the platform by centrifugal force due to rotation of the blisk. Accordingly, when the moving blade vibrates and a relative displacement occurs between the friction damper and the platform, a damping function due to friction between the friction damper and the platform is exhibited, and the moving blade Vibration can be reduced.

  Here, since the cylindrical friction damper is press-fitted by the elastic force on the radially inner side surface of the platform, the contact area between the friction damper and the platform during operation of the gas turbine engine Can be sufficiently ensured, and it is not necessary to form a circumferential groove for attaching the friction damper on the side surface in the axial direction of the platform, so that the thickness of the platform can be suppressed. In addition, since the locking flange that can be locked to the locking circumferential groove or the locking protrusion is formed at the axial end of the friction damper, the friction damper is moved during the operation of the gas turbine engine. It can be prevented from coming off (disconnecting) from the platform.

  According to the present invention, while suppressing the increase in thickness of the platform, a sufficient contact area between the friction damper and the platform during operation of the gas turbine engine is ensured, and the operation during operation of the gas turbine engine is performed. Since it is possible to prevent the friction damper from coming off the platform, the vibration stress acting on the blisk is sufficiently and stably reduced while reducing the weight of the blisk, thereby improving the durability of the blisk to a high level. Can do.

Fig.1 (a) is sectional drawing which shows a part of blisk concerning 1st Embodiment of this invention, FIG.1 (b) is an enlarged view of the arrow IB in FIG.1 (a). 2A and 2B are schematic perspective views of friction dampers (first friction damper and second friction damper) in the blisk according to the first embodiment of the present invention. FIG. 3 is a perspective view showing a blisk according to the first embodiment of the present invention, in which a friction damper is omitted. 4A is a cross-sectional view showing a part of a blisk according to a modification of the first embodiment of the present invention, and FIG. 4B is an enlarged view of an arrow IVV in FIG. 4A. . 5A and 5B are schematic perspective views of a friction damper in a blisk according to a modification of the first embodiment of the present invention. Fig.6 (a) is sectional drawing which shows a part of blisk concerning 2nd Embodiment of this invention, FIG.6 (b) is an enlarged view of the arrow view part VIB in Fig.6 (a). FIGS. 7A and 7B are schematic perspective views of the friction damper in the blisk according to the second embodiment of the present invention. Fig.8 (a) is sectional drawing which shows a part of blisk concerning the modification of 2nd Embodiment of this invention, FIG.8 (b) is an enlarged view of the arrow VIIIB in Fig.8 (a). . FIGS. 9A and 9B are schematic perspective views of a friction damper in a blisk according to a modification of the second embodiment of the present invention.

(First embodiment)
A first embodiment of the present invention will be described with reference to FIGS. In the drawings, “F” indicates the forward direction (upstream direction), and “R” indicates the backward direction (downstream direction).

  As shown in FIGS. 1 (a) and 3, the blisk 1 according to the first embodiment of the present invention is used as a component of a compressor rotor (not shown) in an aircraft engine, and is a compressor rotor. A circular disk 3 that can rotate about the axis (the center of the blisk 1) SC is provided. An annular platform 5 is integrally formed on the outer peripheral edge of the disk 3, and a radially outer surface 5e of the platform 5 is an air flow path surface. A plurality of moving blades 7 are integrally formed on the radially outer side surface 5e of the platform 5 at equal intervals along the circumferential direction, and each moving blade 7 has an abdominal surface (positive pressure surface) on one side in the blade thickness direction. 7v, and a back surface (negative pressure surface) 7b on the other side in the blade thickness direction.

  As shown in FIGS. 1A and 1B and FIG. 2A, the axially one side portion (front side portion) of the outer peripheral edge of the disk 3 on the radially inner side surface 5i of the platform 5 has a pair of first portions. Locking circumferential grooves 9 are formed apart in the axial direction (front-rear direction). In addition, a cylindrical (band-shaped) first friction damper 11 has an elastic force (an elastic force of the first friction damper 11) on one axial side portion of the outer peripheral edge of the disk 3 on the radially inner side surface 5 i of the platform 5. ), And the first friction damper 11 has a dividing portion (joint portion) 11f in a part in the circumferential direction.

  At both ends in the axial direction (front end and rear end) of the first friction damper 11, annular locking outer flanges 13 protruding outward in the radial direction are formed, and each locking outer flange 13 corresponds to each other. The first locking circumferential groove 9 can be locked. Further, a wear-resistant coat 15 having wear resistance is provided at a portion between the pair of first locking circumferential grooves 9 on the radially inner side surface 5i of the platform (a portion in contact with the outer peripheral surface of the first friction damper 11). Is formed by discharge surface treatment using discharge energy, and the wear-resistant coat 15 is made of, for example, a stellite alloy. Furthermore, an abradable coat 17 having machinability is formed on the outer peripheral surface of the first friction damper 11 by a discharge surface treatment.

  Here, instead of forming the annular locking outer flanges 13 at both axial ends of the first friction damper 11, a plurality of locking outer flanges (not shown) are formed at intervals along the circumferential direction. It doesn't matter. Moreover, you may abbreviate | omit either one or both of the abrasion-resistant coat 15 and the abradable coat 17. Further, as shown in FIG. 2B, a plurality of slits 19 extending in the axial direction may be formed in the first friction damper 11 at intervals along the circumferential direction.

  Similarly, as shown in FIGS. 1A and 1B and FIG. 2A, the axially other side portion (rear side portion) of the outer peripheral edge of the disk 3 on the radially inner side surface 5i of the platform 5 includes: A pair of second locking circumferential grooves 21 are formed apart in the axial direction. A cylindrical (band-shaped) second friction damper 23 has an elastic force (elastic force of the second friction damper 23) on the other axial side portion of the outer peripheral edge of the disk 3 on the radially inner side surface 5 i of the platform 5. The second friction damper 23 has a dividing portion 23f in a part of the circumferential direction.

  At both ends in the axial direction of the second friction damper 23, annular locking outer flanges 25 protruding outward in the radial direction are formed, and each locking outer flange 25 corresponds to the corresponding second locking circumferential groove 21. Can be locked. In addition, the portion between the pair of second locking circumferential grooves 21 on the radially inner side surface 5i of the platform (the portion that contacts the outer peripheral surface of the second friction damper 23) has the same configuration as the wear-resistant coat 15. A wear-resistant coat 27 is formed by the discharge surface treatment, and an abradable coat 29 having the same configuration as the abradable coat 17 is formed on the outer peripheral surface of the second friction damper 23 by the discharge surface treatment. Yes.

  Here, instead of forming the annular locking outer flanges 13 at both axial ends of the second friction damper 23, a plurality of locking outer flanges (not shown) are formed at intervals along the circumferential direction. It doesn't matter. Further, either one or both of the wear resistant coat 27 and the abradable coat 29 may be omitted. Further, as shown in FIG. 2B, a plurality of slits 31 extending in the axial direction may be formed in the second friction damper 23 at intervals along the circumferential direction.

  Then, the effect | action and effect of 1st Embodiment of this invention are demonstrated.

  During operation of the aircraft engine, the first friction damper 11 and the second friction damper 23 are pressed against the radially inner side surface 5 i of the platform 5 by the centrifugal force generated by the rotation of the blisk 1. Thereby, when the moving blade 7 vibrates and relative displacement occurs between the first friction damper 11 and the platform 5 and between the second friction damper 23 and the platform 5, the first friction damper 11 and the platform 5 And the damping function by friction between the second friction damper 23 and the platform 5 is exhibited, and the vibration of the rotor blade 7 can be reduced.

  Here, since the cylindrical first friction damper 11 and the cylindrical second friction damper 23 are press-fitted by the elastic force on the radially inner side surface 5i of the platform 5, the aircraft engine is in operation. The contact area between the first friction damper 11 and the platform 5 and the contact area between the second friction damper 23 and the platform 5 can be sufficiently ensured, and the axial side surface (front side surface or rear side surface) of the platform 5 can be secured. In addition, it is not necessary to form a circumferential groove for mounting the first friction damper 11 or the second friction damper 23, and the thickness of the platform 5 can be suppressed. In particular, when a plurality of slits 19 (31) are formed at intervals along the circumferential direction in the first friction damper 11 and the second friction damper 23, the first friction damper 11 and the second friction damper 11 and the second friction damper 23 are formed. By increasing the flexibility of the friction damper 23, the contact area between the first friction damper 11 and the platform 5 and the contact area between the second friction damper 23 and the platform 5 during operation of the aircraft engine can be more sufficiently secured. it can.

  Further, locking outer flanges 13 that can be locked in the first locking circumferential grooves 9 corresponding to both axial ends of the first friction damper 11 are formed, respectively, and correspond to both axial ends of the second friction damper 23. Since the locking outer flange 25 that can be locked in the second locking circumferential groove 21 is formed, the first friction damper 11 and the second friction damper 23 are prevented from coming off from the platform 5 during operation of the aircraft engine. it can.

  Further, a wear-resistant coat 15 is formed by a discharge surface treatment on a portion of the inner surface 5 i in the radial direction of the platform 5 that contacts the outer peripheral surface of the first friction damper 11, and an abradable coat 17 is formed on the outer peripheral surface of the first friction damper 11. Since the surface is formed by the discharge surface treatment, it is possible to suppress the wear of the portion in contact with the outer peripheral surface of the first friction damper 11 on the radially inner side surface 5 i of the platform 5. Similarly, a wear-resistant coat 27 is formed by a discharge surface treatment on a portion of the radially inner side surface 5i of the platform 5 that contacts the outer peripheral surface of the second friction damper 23, and an abradable coat is formed on the outer peripheral surface of the second friction damper 23. Since 29 is formed by the discharge surface treatment, it is possible to suppress the wear of the portion in contact with the outer peripheral surface of the second friction damper 23 on the radially inner side surface 5i of the platform.

  Therefore, according to the embodiment of the present invention, the contact area between the first friction damper 11 and the platform 5 and the second friction damper 23 and the platform 5 during the operation of the aircraft engine are suppressed while suppressing the increase in thickness of the platform 5. Each of the contact areas can be secured more sufficiently, and the first friction damper 11 and the second friction damper 23 can be prevented from coming off from the platform 5 during the operation of the aircraft engine. Therefore, the durability of the blisk 1 can be improved to a high level.

  In particular, the wear of the portion that contacts the outer peripheral surface of the first friction damper 11 on the radially inner side surface 5i of the platform 5 and the wear of the portion that contacts the outer peripheral surface of the second friction damper 23 on the radially inner side surface 5i of the platform 5 occur. Since each can be suppressed, the durability of the blisk 1 can be further improved by treating the first friction damper 11 and the second friction damper 23 as replacement parts.

(Modification of the first embodiment)
The modification of 1st Embodiment of this invention is demonstrated with reference to FIG.4 and FIG.5.

  As shown in FIGS. 4A and 4B and FIGS. 5A and 5B, the blisk 1A according to the modified example of the first embodiment of the present invention is the blisk 1 according to the first embodiment of the present invention ( 1 (a) and 1 (b)), and only the parts different from blisk 1 in the blisk 1A structure will be described. In addition, about the component corresponding to the component in Blisk 1 among several components in Blis 1A, the same number is attached | subjected in drawing.

  One first locking circumferential groove 9 is formed on one axial side portion (front side portion) of the outer peripheral edge of the disk 3 on the radially inner side surface 5 i of the platform 5, and the axial direction of the first friction damper 11 is formed. A locking outer flange 13 that can be locked to the first locking circumferential groove 9 is formed only at one end (front end). Here, the rear end portion of the first friction damper 11 may be in pressure contact with the front side surface of the disk 3.

  Similarly, one second locking circumferential groove 21 is formed in the other axial side portion (rear side portion) of the outer peripheral edge of the disk 3 on the radially inner side surface 5i of the platform 5, and a second friction damper is formed. A locking outer flange 25 that can be locked to the second locking circumferential groove 21 is formed only at one axial end portion (rear end portion) of 23. Here, the front end portion of the second friction damper 23 may be in pressure contact with the rear side surface of the disk 3.

  And also in the modification of 1st Embodiment of this invention, there exists an effect | action and effect similar to 1st Embodiment of this invention.

(Second Embodiment)
The modification of 2nd Embodiment of this invention is demonstrated with reference to FIG.6 and FIG.7.

  As shown in FIGS. 6A and 6B and FIG. 7A, the blisk 33 according to the second embodiment of the present invention is the blisk 1 according to the first embodiment of the present invention (FIG. 1 (a) ( b) has substantially the same configuration as the reference), and only the portion different from the blisk 1 in the blisk 33 will be described. Of the plurality of components in blisk 33, those corresponding to the components in blisk 1 are given the same numbers in the drawing.

  A pair of annular first locking protrusions 35 are formed in the axial direction on one side portion (front side portion) of the outer peripheral edge of the disk 3 on the radially inner side surface 5i of the platform 5 so as to be separated in the axial direction. A cylindrical (band-shaped) first friction damper 37 has an elastic force (an elastic force of the first friction damper 37) on one axial side portion of the outer peripheral edge of the disk 3 on the radially inner side surface 5 i of the platform 5. The first friction damper 37 has a dividing portion 37f in a part in the circumferential direction.

  An annular locking inner flange 39 protruding inward in the radial direction is formed at both axial end portions (front end portion and rear end portion) of the first friction damper 37, and each locking inner flange 39 corresponds to each other. The first locking projection 35 can be locked. Further, the wear-resistant coat 15 (FIG. 1 (b)) is provided on a portion between the pair of first locking projections 35 on the radially inner side surface 5i of the platform (a portion that contacts the outer peripheral surface of the first friction damper 37). The wear-resistant coat 41 having the same configuration as that of the reference coat) is formed by the discharge surface treatment, and the same configuration as the abradable coat 17 (see FIG. 1B) is formed on the outer peripheral surface of the first friction damper 37. An abradable coat 43 made of is formed by a discharge surface treatment.

  Here, instead of forming the annular first locking projections 35 on the radially inner side surface 5i of the platform 5, a plurality of first locking projections (not shown) are formed at intervals along the circumferential direction. Of course, a balance land (not shown) or a balance weight (not shown) provided on the radially inner side surface 5i of the platform 5 is used as the annular first locking protrusion 35 or the plurality of first locking protrusions. It doesn't matter. Further, instead of forming the annular locking inner flanges 39 at both axial ends of the first friction damper 37, a plurality of locking inner flanges (not shown) are formed at intervals along the circumferential direction. Any one or both of the wear-resistant coat 41 and the abradable coat 43 may be omitted. Further, as shown in FIG. 7B, the first friction damper 37 may be formed with a plurality of slits 45 extending in the axial direction at intervals along the circumferential direction.

  Similarly, as shown in FIGS. 6A and 6B and FIG. 7A, the axially other side portion (rear side portion) of the outer peripheral edge of the disk 3 on the radially inner side surface 5i of the platform 5 includes: A pair of annular second locking projections 47 are formed apart in the axial direction. In addition, a cylindrical second friction damper 49 is pressed against the other axial portion of the outer peripheral edge of the disk 3 on the radially inner side surface 5i of the platform 5 by its elastic force (elastic force of the second friction damper 49). The second friction damper 49 has a dividing portion 49f in a part in the circumferential direction.

  An annular locking inner flange 51 projecting inward in the radial direction is formed at both axial end portions (front end portion and rear end portion) of the second friction damper 49, and each locking inner flange 51 corresponds to each other. The second locking projection 47 can be locked. In addition, the portion between the pair of second locking projections 47 on the radially inner side surface 5i of the platform 5 (the portion in contact with the outer peripheral surface of the second friction damper 49) has the same configuration as the wear-resistant coat 41. A wear-resistant coat 53 is formed by the discharge surface treatment, and an abradable coat 55 having the same configuration as the abradable coat 43 is formed on the outer peripheral surface of the second friction damper 49 by the discharge surface treatment. Yes.

  Here, instead of the annular second locking projection 47 being formed on the radially inner side surface 5i of the platform 5, a plurality of second locking projections (not shown) are formed at intervals along the circumferential direction. Alternatively, a balance land or a balance weight may be used as the annular second locking protrusion 47 or the plurality of second locking protrusions. Further, instead of forming the annular locking inner flanges 51 at both axial ends of the second friction damper 49, a plurality of locking inner flanges (not shown) may be formed at intervals along the circumferential direction. Any one or both of the wear-resistant coat 53 and the abradable coat 55 may be omitted. Further, as shown in FIG. 7B, the second friction damper 49 may be formed with a plurality of slits 57 extending in the axial direction at intervals along the circumferential direction.

  And also in 2nd Embodiment of this invention, there exists an effect | action and effect similar to 1st Embodiment of this invention. Further, by using a balance land or a balance weight as the annular first locking projection 35 or the plurality of arc-shaped first locking projections, the configuration of the blisk 33 can be simplified.

(Modification of the second embodiment)
A modification of the second embodiment of the present invention will be described with reference to FIGS.

  As shown in FIGS. 8A and 8B and FIGS. 9A and 9B, the blisk 33A according to the modification of the second embodiment of the present invention is the blisk 33 ( 6 (a) and 6 (b)), and only the portions different from the blisk 33 in the blisk 33A will be described. Of the plurality of components in the blisk 33A, those corresponding to the components in the blisk 33 are given the same numbers in the drawing.

  One first locking projection 35 is formed on one axial side portion (front side portion) of the outer peripheral edge of the disk 3 on the radially inner side surface 5 i of the platform 5, and one axial end of the first friction damper 37 is formed. A locking inner flange 39 that can be locked to the first locking projection 35 is formed only on the portion (front end). Here, the rear end portion of the first friction damper 37 may be in pressure contact with the front side surface of the disk 3.

  Similarly, one second locking protrusion 47 is formed on the other axial side portion (rear side portion) of the outer peripheral edge of the disk 3 on the radially inner side surface 5 i of the platform 5, and the second friction damper 49. A locking inner flange 51 that can be locked to the second locking projection 47 is formed only at one end (rear end) in the axial direction. Here, the front end portion of the second friction damper 49 may be in pressure contact with the rear side surface of the disk 3.

  And also in the modification of 2nd Embodiment of this invention, there exists an effect | action and effect similar to 2nd Embodiment of this invention.

  The present invention is not limited to the description of the above-described embodiment, and can be implemented in various aspects as follows, for example. That is, any of the friction dampers 11 or 23 may be omitted from the blisk 1 according to the first embodiment of the present invention or the blisk 1A according to the modification of the first embodiment of the present invention. Further, any friction damper 37 or 49 may be omitted from the blisk 33 according to the second embodiment of the present invention or the blisk 33A according to the modification of the second embodiment of the present invention. Furthermore, the technology applied to Blisk 1 (1A, 33, 33A) is applied to another blisk (not shown) used as a component part of a fan rotor (not shown) or a turbine rotor (not shown) in an aircraft engine. Is also possible. Further, the abrasion-resistant coat 15 and the abradable coat 17 may be formed by a method other than the discharge surface treatment such as thermal spraying. The scope of rights encompassed by the present invention is not limited to these embodiments.

DESCRIPTION OF SYMBOLS 1 Blisk 1A Blisk 3 Disc 5 Platform 5e Radial outer side surface 5i Radial inner side surface 7 Rotor blade 9 First locking circumferential groove 11 First friction damper 11f Dividing part 13 Locking outer flange 15 Wear-resistant coating 17 Abradable coating 19 slit 21 second locking circumferential groove 23 second friction damper 23f dividing portion 25 locking outer flange 27 wear-resistant coat 29 abradable coating 31 slit 33 blisk 33A blisk 35 first locking projection 37 first friction damper 37f cutting Portion 39 Locking inner flange 41 Wear-resistant coating 43 Abradable coating 45 Slit 47 Second locking projection 49 Second friction damper 49f Dividing portion 51 Locking inner flange 53 Wear-resistant coating 55 Abradable coating 57 Slit

Claims (5)

In a blisk used as a rotor component in a gas turbine engine,
A circular disc rotatable around the axis of the rotor;
An annular platform formed integrally with the outer peripheral edge of the disk, the radially outer surface of which is a gas flow path surface;
A plurality of rotor blades integrally formed at equal intervals along the circumferential direction on the radially outer surface of the platform,
A locking circumferential groove or a locking projection is formed on the radially inner side surface of the platform, and a cylindrical friction damper is press-fitted by the elastic force on the radially inner side surface of the platform. A blisk having a dividing part in a part of the direction, and a locking flange that can be locked to the locking circumferential groove or the locking projection is formed at an axial end of the friction damper.   The blisk according to claim 1, wherein a plurality of slits extending in the axial direction are formed in the friction damper at intervals along the circumferential direction.   The blisk according to claim 1, wherein the locking protrusion is a balance land or a balance weight provided on a radially inner side surface of the platform.   The wear-resistant coat is formed in the site | part which contacts the outer peripheral surface of the said friction damper in the radial direction inner surface of the said platform, The Claim in any one of Claims 1-3 characterized by the above-mentioned. Blisk.   The blisk according to any one of claims 1 to 4, wherein an abradable coat is formed on an outer peripheral surface of the friction damper.

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