JP2024024449A - Impellers, impeller manufacturing methods, and rotating machines - Google Patents

Abstract

The present invention suppresses deformation in the radial direction in an impeller, a method for manufacturing the impeller, and a rotating machine. [Solution] A hub having a cylindrical shape, a shroud having a cylindrical shape and disposed outside the hub, and a plurality of blades disposed at intervals in the circumferential direction between the hub and the shroud. , at least one of the hub and the shroud has a plurality of layers laminated in the thickness direction, each of the plurality of layers is made of a composite material in which fiber members are arranged along the circumferential direction, and the plurality of layers are , the outer side in the thickness direction has higher rigidity. [Selection diagram] Figure 3

Description

The present disclosure relates to an impeller, a method of manufacturing the impeller, and a rotating machine.

As a rotating machine, there is a centrifugal compressor that houses an impeller inside. Centrifugal compressors impart pressure and velocity energy to a fluid by rotating an impeller. As an impeller applied to a centrifugal compressor, there is a closed impeller in which a plurality of blades are arranged between a hub and a shroud. The rigidity of the closed impeller is improved by using a composite material made of fiber materials. Examples of impellers applied to centrifugal compressors and the like include those described in the following patent documents.

International Publication No. 2016/088451 Special Publication No. 2012-526230

In the conventional impeller described above, in the reinforcing ring made of a fiber-reinforced composite material fixed to the hub surface of the impeller main body, the fiber orientation direction is the circumferential direction of the impeller main body. Therefore, although the impeller has high rigidity in the circumferential direction, the impeller has low rigidity in the radial direction orthogonal to the fiber orientation direction. Therefore, it is conceivable to increase the thickness of the impeller in the radial direction, but in this case, the impeller becomes heavier and the rigidity in the radial direction becomes severe due to centrifugal force.

The present disclosure solves the above-mentioned problems, and aims to provide an impeller, an impeller manufacturing method, and a rotating machine that suppress deformation in the radial direction.

The impeller of the present disclosure for achieving the above object includes a hub having a cylindrical shape, a shroud having a cylindrical shape and disposed outside the hub, and a space between the hub and the shroud in the circumferential direction. a plurality of blades arranged at intervals, at least one of the hub and the shroud has a plurality of layers laminated in the thickness direction, and each of the plurality of layers has a fiber member arranged in a circumferential direction. The plurality of layers have higher rigidity toward the outside in the thickness direction.

Further, the impeller manufacturing method of the present disclosure includes a step of forming a hub having a cylindrical shape, and a plurality of blades are arranged at intervals in the circumferential direction between the supporting inner cylinder and the supporting outer cylinder. forming a blade assembly; forming a shroud having a cylindrical shape; and assembling the hub, the blade assembly, and the shroud; The member is formed of a composite material arranged along the circumferential direction, and forms a reinforcing layer composed of a plurality of layers whose rigidity is higher toward the outside.

Moreover, the rotating machine of this indication has the said impeller.

According to the impeller, impeller manufacturing method, and rotating machine of the present disclosure, deformation in the radial direction can be suppressed.

FIG. 1 is a sectional view showing a centrifugal compressor to which the impeller of this embodiment is applied. FIG. 2 is a front view showing the impeller of this embodiment. FIG. 3 is a sectional view taken along line III--III in FIG. 2, showing a cross section of the impeller. FIG. 4 is a table representing the materials applied to the hub and shroud. FIG. 5 is an explanatory diagram for explaining the impeller manufacturing method. FIG. 6 is a schematic diagram showing radial stress in a conventional impeller. FIG. 7 is a schematic diagram showing radial stress in the impeller of this embodiment.

Preferred embodiments of the present disclosure will be described in detail below with reference to the drawings. Note that the present disclosure is not limited to this embodiment, and if there are multiple embodiments, the present disclosure also includes a configuration in which each embodiment is combined. In addition, the components in the embodiments include those that can be easily imagined by those skilled in the art, those that are substantially the same, and those that are in the so-called equivalent range.

<Centrifugal compressor>
In this embodiment, a centrifugal compressor is applied as the rotating machine. However, the rotating machine is not limited to a centrifugal compressor, and may be, for example, a turbocharger, an uncooled supercharger (so-called MET supercharger), a turbo refrigerator, or the like.

FIG. 1 is a sectional view showing a centrifugal compressor to which the impeller of this embodiment is applied. In the following explanation, the axis of the center of rotation in the centrifugal compressor is referred to as the axis O, the direction of the axis O is the axial direction A, the radial direction of the centrifugal compressor with respect to the axis O is the radial direction D, and the axis The circumferential direction centered on O will be described as the circumferential direction R.

As shown in FIG. 1, the centrifugal compressor 11 includes a turbine 12, a compressor 13, and a rotating shaft 14, which are housed inside a housing 15.

The housing 15 has a hollow shape. Housing 15 includes a turbine housing 21, a compressor housing 22, and a bearing housing 23. A bearing housing 23 is disposed between the turbine housing 21 and the compressor housing 22, and are fastened together with bolts, for example. The turbine housing 21 accommodates the turbine 12 . The compressor housing 22 accommodates the compressor 13. The rotating shaft 14 is housed in the bearing housing 23 .

The rotating shaft 14 is arranged along the axis O. The rotating shaft 14 is rotatably supported by the compressor housing 22 by a pair of journal bearings 24 and 25, and movement in the radial direction D is restricted. Further, the rotating shaft 14 is rotatably supported by the compressor housing 22 by a thrust bearing 26, and movement in the axial direction A is restricted. The rotating shaft 14 is rotatably supported by the housing 15 by journal bearings 24 and 25 and a thrust bearing 26 about the axis O.

A turbine wheel 31 constituting the turbine 12 is fixed to one end of the rotating shaft 14 in the axial direction A. Turbine wheel 31 is housed inside turbine housing 21 . The turbine wheel 31 has a hub 32, a plurality of blades 33, and a shroud 34. That is, in the hub 32, a plurality of blades 33 are arranged on the outer circumference at equal intervals in the circumferential direction R, and a shroud 34 is arranged on the outer side of the plurality of blades 33. The turbine wheel 31 has a hub 32 fixed to one end of the rotating shaft 14 .

A compressor wheel 36 constituting the compressor 13 is fixed to the other end of the rotating shaft 14 in the axial direction A. Compressor wheel 36 is housed within compressor housing 22 . Compressor wheel 36 has a hub 37, a plurality of blades 38, and a shroud 39. That is, in the hub 37, a plurality of blades 38 are arranged at equal intervals in the circumferential direction R on the outer periphery, and a shroud 39 is arranged on the outer side of the plurality of blades 38. The compressor wheel 36 has a hub 37 fixed to the other end of the rotating shaft 14 .

The turbine housing 21 is provided with a first fluid inlet passage 41 and a first fluid outlet passage 42 with respect to the turbine wheel 31 . The turbine housing 21 is provided with a turbine nozzle 43 between the inlet passage 41 and the turbine wheel 31 . The turbine 12 is driven to rotate by guiding the first fluid, which is statically expanded by the turbine nozzle 43 and flows in the axial direction A, to the plurality of turbine wheels 31 .

The compressor housing 22 is provided with a suction port 44 and a discharge port 45 relative to the compressor wheel 36 . A diffuser 46 is provided in the compressor housing 22 between the compressor wheel 36 and the discharge port 45 . The compressor wheel 36 is driven to rotate by the rotational force of the turbine wheel 31 being transmitted via the rotating shaft 14 . When the compressor wheel 36 rotates, it draws in and compresses the second fluid, and the compressed second fluid is discharged to the outside through the diffuser 46 .

Therefore, in the centrifugal compressor 11, the turbine 12 is driven by the first fluid, the rotational force of the turbine 12 is transmitted to the rotating shaft 14 to drive the compressor 13, and the compressor 13 compresses the second fluid.

That is, the first fluid passes through the inlet passage 41 and is statically expanded by the turbine nozzle 43, and the first fluid flowing in the axial direction A is guided to the plurality of blades 33, thereby driving and rotating the turbine wheel 31. The first fluid that has driven the turbine wheel 31 is discharged from the outlet passage 42 to the outside. On the other hand, when the rotating shaft 14 is rotated by the turbine wheel 31, the compressor wheel 36, which is integrated with the rotating shaft 14, is driven to rotate. Then, the second fluid is sucked in through the suction port 44, and is pressurized and compressed by the compressor wheel 36. The compressed second fluid passes through the diffuser 46 and is discharged from the discharge port 45 to the outside.

<Impeller>
FIG. 2 is a front view showing the impeller of this embodiment, and FIG. 3 is a sectional view taken along line III--III in FIG. 2 showing a cross section of the impeller.

As shown in FIGS. 2 and 3, the impeller 50 of this embodiment is applied to the compressor wheel 36 of the centrifugal compressor 11 described above.

The impeller 50 is a closed impeller including a hub 51, a shroud 52, and a plurality of blades 53. However, the impeller 50 may be an open impeller.

The impeller 50 is configured such that a plurality of blades 53 are arranged between a hub 51 and a shroud 52 at intervals (preferably at equal intervals) in the circumferential direction R. The plurality of blades 53 are fixed to the hub 51 on one side in the axial direction A and the radial direction D, and fixed to the shroud 52 on the other side. The impeller 50 is provided with a plurality of impeller passages 54 surrounded by a hub 51, a shroud 52, and a plurality of blades 53. The impeller flow path 54 is bent approximately 90 degrees from one side in the axial direction A to the outer side in the radial direction D, and is arranged in a spiral shape centered on the axis O.

The hub 51 has a cylindrical shape and a disk shape centered on the axis O. That is, the hub 51 gradually expands in diameter outward in the radial direction D from one side in the axial direction A (upper side in FIG. 3) to the other side (lower side in FIG. 3). The hub 51 includes a cylindrical portion 61, a disk portion 62, and a reinforcing layer (hub reinforcing layer) 63.

A circular through hole 61a is formed in the cylindrical portion 61 at the position of the axis O and extends in the axial direction A. The hub 51 is integrally fixed to the rotating shaft with the inner circumferential surface of the through hole 61a of the cylindrical portion 61 fitting into the outer circumferential surface of the rotating shaft (the rotating shaft 14 shown in FIG. 1). Note that the hub 51 may be rotatably supported with respect to the rotating shaft with the inner circumferential surface of the through hole 61a of the cylindrical portion 61 fitting into the outer circumferential surface of the rotating shaft. The inner circumferential portion of the disc portion 62 is integrally fixed to the cylindrical portion 61 at an intermediate position in the axial direction A. The disc portion 62 has a hollow truncated conical shape extending outward in the radial direction D and in the other direction in the axial direction A (downward in FIG. 3) from the inner circumference toward the outer circumference. The disk portion 62 has a mounting surface 62a having a concavely curved outer peripheral surface. The cylindrical portion 61 and the disk portion 62 are formed, for example, by injection molding of resin.

The reinforcing layer 63 is arranged between the cylindrical portion 61 and the disk portion 62. The reinforcing layer 63 includes a first layer 63a, a second layer 63b, and a third layer 63c. The first layer 63a, second layer 63b, and third layer 63c that constitute the reinforcing layer 63 are laminated in the thickness direction of the hub 51. The first layer 63a, the second layer 63b, and the third layer 63c are each made of a composite material in which fiber members are continuously arranged along the circumferential direction. The first layer 63a, the second layer 63b, and the third layer 63c have higher rigidity toward the outer side in the thickness direction. That is, the second layer 63b has a higher rigidity than the first layer 63a, and the third layer 63c has a higher rigidity than the second layer 63b.

In this embodiment, the reinforcing layer 63 is arranged between the cylindrical portion 61 and the disk portion 62, but the structure is not limited to this. For example, the disk portion 62 may be omitted and the reinforcing layer 63 may be placed on the outer periphery of the cylindrical portion 61. Further, the first layer 63a, the second layer 63b, and the third layer 63c are laminated in the thickness direction of the hub 51, here, along the radial direction D, but they are also laminated at a predetermined inclination in the axial direction A with respect to the radial direction D. They may be laminated along a direction that is inclined by an angle. Further, the thicknesses of the first layer 63a, the second layer 63b, and the third layer 63c may be the same or different, and may be set as appropriate. Furthermore, although the reinforcing layer 63 is composed of three layers, the first layer 63a, the second layer 63b, and the third layer 63c, it may be composed of two layers or four or more layers.

The shroud 52 has a cylindrical shape centered on the axis O. The shroud 52 has a reinforcement layer (shroud reinforcement layer) 64.

Shroud 52 is comprised of a reinforcing layer 64. The reinforcing layer 64 has a first layer 64a, a second layer 64b, and a third layer 64c. A first layer 64a, a second layer 64b, and a third layer 64c constituting the reinforcing layer 64 are laminated in the thickness direction of the shroud 52. The first layer 64a, the second layer 64b, and the third layer 64c are each made of a composite material in which fiber members are continuously arranged along the circumferential direction. The first layer 64a, the second layer 64b, and the third layer 64c have higher rigidity toward the outer side in the thickness direction. That is, the second layer 64b has a higher rigidity than the first layer 64a, and the third layer 64c has a higher rigidity than the second layer 64b. Although the reinforcing layer 64 is composed of three layers, a first layer 64a, a second layer 64b, and a third layer 64c, it may have two layers or four or more layers.

In this embodiment, the shroud 52 is configured by the reinforcing layer 64, but the configuration is not limited to this. For example, a cylindrical portion made of resin may be provided, and the reinforcing layer 64 may be placed on the outer periphery of the cylindrical portion. Further, the first layer 64a, the second layer 64b, and the third layer 64c are laminated in the thickness direction of the shroud 52, here, along the radial direction D. They may be laminated along a direction that is inclined by an angle. Further, the thicknesses of the first layer 64a, the second layer 64b, and the third layer 64c may be the same or different, and may be set as appropriate. Furthermore, although the reinforcing layer 64 is composed of three layers, the first layer 64a, the second layer 64b, and the third layer 64c, it may be composed of two layers or four or more layers.

The shroud 52 is disposed outwardly in the radial direction D from the hub 51 by a predetermined distance. The reinforcing layer 64 has a mounting surface 64d having a convexly curved inner peripheral surface. The mounting surface 62a of the disk portion 62 on the hub 51 and the mounting surface 64d of the reinforcing layer 64 on the shroud 52 face each other.

A plurality of blades 53 connect hub 51 and shroud 52. One side of the plurality of blades 53 in the radial direction D is fixed to the mounting surface 62a of the disk portion 62 on the hub 51, and the other side of the plurality of blades 53 in the radial direction D is fixed to the mounting surface 64d of the reinforcing layer 64 on the shroud 52. The plurality of blades 53 extend curvedly from one side in the axial direction A toward the outer side in the radial direction D. The plurality of blades 53 are arranged at intervals in the circumferential direction R. The plurality of blades 53 are arranged radially outward in the radial direction D with the axis O as the center. The blade 53 is formed by injection molding, cutting, or the like.

The impeller flow path 54 is formed between the hub 51 and the shroud 52 by being divided into a plurality of sections in the circumferential direction R by a plurality of blades 53. The impeller flow path 54 extends while curving from the inner side to the outer side in the radial direction D as it goes from one side to the other side in the axial direction A. The impeller flow path 54 has an inlet 54a that opens on the inner side in the radial direction D and on one side in the axial direction A. Further, the impeller flow path 54 has an outlet 54b that opens on the outer side in the radial direction D and on the other side in the axial direction A.

Therefore, when the impeller 50 rotates, when the fluid F1 is sucked into the impeller channel 54 from the inlet 54a, it is pressurized and compressed by the plurality of blades 53. The compressed fluid F2 is discharged from the outlet 54b.

<Specific example of reinforcement layer>
FIG. 4 is a table representing the materials applied to the hub and shroud. Here, in the elastic modulus E, shear modulus G, Poisson's ratio v, and tensile strength F, the subscript 1 is for the fiber direction, 2 is for the direction perpendicular to the fibers, 3 is for the lamination direction, and t represents tension.

As shown in FIGS. 3 and 4, in the reinforcing layers 63, 64 in the hub 51 and shroud 52, the first layers 63a, 64a, the second layers 63b, 64b, and the third layers 63c, 64c are made of different materials, respectively. configured. In the reinforcing layer 63 of the hub 51, for example, the first layer 63a is formed of T300/EP#3631 (fiber/resin), and the second layer 63b is formed of T800H/EP#3631 (fiber/resin). , the third layer 63c is formed of M40J/EP#3631 (fiber/resin). Further, in the reinforcing layer 64 of the shroud 52, for example, the first layer 64a is formed of T300/EP#3631 (fiber/resin), and the second layer 64b is formed of T800H/EP#3631 (fiber/resin). The third layer 64c is made of M40J/EP#3631 (fiber/resin).

The first layer 63a, 64a (T300/EP#3631), the second layer 63b, 64b (T800H/EP#3631), and the third layer 63c, 64c (M40J/EP#3631) have a longitudinal elastic modulus corresponding to the stiffness. E1 is 130000Mpa, 165000Mpa, and 212000Mpa. Therefore, the stiffness of the reinforcing layers 63 and 64 increases toward the outer side of the hub 51 and the shroud 52 in the thickness direction (radial direction D). Note that the combinations of materials for the first layers 63a, 64a, the second layers 63b, 64b, and the third layers 63c, 64c are not limited to those described above, and may be appropriately selected based on the table in FIG. 4, for example. It is something.

In addition, T300, T800H, M40J, etc. are high-performance carbon fibers made from polyacrylonitrile manufactured by Toray Industries, Inc. under the trade name of Torayca (registered trademark). However, the first layers 63a, 64a, the second layers 63b, 64b, and the third layers 63c, 64c are not limited to these materials, and other composite materials may be used.

In the embodiment described above, the reinforcing layers 63 and 64 were provided on both the hub 51 and the shroud 52, but the reinforcing layers 63 and 64 may be provided on at least one of the hub 51 and the shroud 52.

<Impeller manufacturing method>
FIG. 5 is an explanatory diagram for explaining the impeller manufacturing method.

As shown in FIG. 5, the impeller manufacturing method of this embodiment includes a step of forming a cylindrical hub 51, and forming a support inner cylinder 71 and a support outer cylinder 72 that are spaced apart in the circumferential direction. The method includes a step of forming a blade assembly 53A in which a plurality of blades 53 are arranged, a step of forming a shroud 52 having a cylindrical shape, and a step of assembling the hub 51, the blade assembly 53A, and the shroud 52. , reinforcing layers 63 and 64 are formed on at least one of the hub 51 and the shroud 52, and are made of a composite material in which fiber members are arranged along the circumferential direction, and are composed of a plurality of layers whose rigidity is higher toward the outside. .

That is, the hub 51, the shroud 52, and the plurality of blades 53 are formed separately, and the hub 51, the shroud 52, and the plurality of blades 53 are integrally formed by bonding.

In the hub 51, for example, a cylindrical part 61 and a disc part 62 are formed by injection molding of resin, and a reinforcing layer 63 is disposed between the cylindrical part 61 and the disc part 62, and the reinforcing layer 63 is formed by, for example, adhesion. Fixed. In this case, the reinforcing layer 63 is composed of a first layer 63a, a second layer 63b, and a third layer 63c, which have higher rigidity toward the outer side in the thickness direction.

Shroud 52 is configured as a reinforcement layer 64. In this case, the reinforcing layer 64 is composed of a first layer 64a, a second layer 64b, and a third layer 64c, which have higher rigidity toward the outer side in the thickness direction.

The plurality of blades 53 are arranged at intervals in the circumferential direction. The plurality of blades 53 arranged at intervals in the circumferential direction are supported on one side in the radial direction D by the support inner cylinder 71 and on the other side in the radial direction D by the support outer cylinder 72. A blade assembly 53A is formed by supporting the plurality of blades 53 by the support inner cylinder 71 and the support outer cylinder 72.

The support inner cylinder 71 is preferably formed of the same material as the mounting surface 62a of the disk portion 62 on the hub 51. The support outer cylinder 72 is preferably formed of the same material as the mounting surface 64d of the reinforcing layer 64 in the shroud 52. That is, it is preferable that the support inner cylinder 71 is formed of the same material as the disk portion 62 of the hub 51, and the support outer cylinder 72 is formed of the same material as the first layer 64a of the reinforcing layer 64 in the shroud 52.

Note that the hub 51 and the shroud 52 are preferably formed by a combination of filament winding using a thermosetting resin and resin impregnation, a combination of pipe molding and machining, or the like. Since the blade 53 has a complex structure including a curved surface, injection molding of a composite material reinforced with short fibers using thermoplastic resin or molding using SMC (sheet mold compound) using thermosetting resin and short fiber mat can be applied. It is.

A hub 51 is placed inside the blade assembly 53A, and a shroud 52 is placed outside the blade assembly 53A. The hub 51, blade assembly 53A, and shroud 52 are fixed to each other by adhesive.

The composite material has high tensile strength in the fiber direction (circumferential direction R of the impeller 50), but low tensile strength in the direction perpendicular to the fibers (radial direction D of the impeller 50). As shown in FIG. 3, when the impeller 50 rotates, centrifugal force (radial stress) acts. When centrifugal force acts on the impeller 50, tensile stress in the circumferential direction R and tensile stress in the radial direction D are generated in the composite material.

For example, if the shroud is made of one layer of composite material in the thickness direction, as in a conventional impeller, the tensile stress in the radial direction D will be maximum near the center of the thickness of the composite material in the radial direction D. As a result, the composite material breaks as if torn from this point.

On the other hand, in the impeller 50 of this embodiment, the reinforcing layer 64 of the shroud 52 is composed of a first layer 64a, a second layer 64b, and a third layer 64c, which have higher rigidity toward the outer side in the thickness direction. That is, the impeller 50 divides the composite material in the radial direction D, and makes the inner side have low rigidity and the outer side has high rigidity. The outer third layer 64c has high rigidity, so deformation of the impeller 50 as a whole is suppressed, and the inner first layer 64a has low rigidity, so it is pressed against the outer third layer 64c. Then, a compressive stress field in the radial direction D is generated at each boundary of the divided first layer 64a, second layer 64b, and third layer 64c, and the tensile stress in the radial direction D is reduced.

<Radial stress of impeller>
FIG. 6 is a schematic diagram showing radial stress in a conventional impeller, and FIG. 7 is a schematic diagram showing radial stress in the impeller of this embodiment.

6 and 7 show the results of FEM (finite element method) analysis of the conventional impeller 100 and the impeller 50 of this embodiment. Here, the conventional impeller 100 has a plurality of blades 103 arranged between a hub 101 reinforced with a fiber-reinforced composite material and a shroud 102 reinforced with a fiber-reinforced composite material. On the other hand, the impeller 50 of this embodiment has a plurality of blades between a hub 51 having a reinforcing layer 63 whose rigidity is higher toward the outer side in the thickness direction and a shroud 52 having a reinforcing layer 64 whose rigidity is higher toward the outer side in the thickness direction. 53 are arranged.

Although the conventional impeller 100 has a leading edge sweep on the blade 103, the impeller 50 of this embodiment has a leading edge sweep in order to reduce the radial D stress at the joint between the hub 51 and the blade 53. Eliminates sweep.

As shown in FIG. 6, in the conventional impeller 100, the radial stress is 1413 MPa at the joint P between the hub 101 and the blade 103 on the inner side of the leading edge, where the strength is most severe. On the other hand, in the impeller 50 of this embodiment, the radial stress is 451 MPa at the joint P between the hub 51 and the blade 53 on the inner side of the leading edge, which is the most severe in terms of strength, and the radial stress is approximately 1/ Reduced to 3.1. Furthermore, since the circumferential speed of the impeller 50 of this embodiment is proportional to the square root of the centrifugal force, the circumferential speed is approximately 1.8 times higher than that of the conventional impeller 100.

[Actions and effects of this embodiment]
The impeller according to the first aspect includes a hub 51 having a cylindrical shape, a shroud 52 having a cylindrical shape and disposed outside the hub 51, and a space between the hub 51 and the shroud 52 in the circumferential direction. At least one of the hub 51 and the shroud 52 has a plurality of layers 63a, 63b, 63c, 64a, 64b, 64c laminated in the thickness direction, and the plurality of layers 63a , 63b, 63c, 64a, 64b, and 64c are each made of a composite material in which fiber members are arranged along the circumferential direction. The outer side is more rigid.

According to the impeller according to the first aspect, when the impeller 50 rotates, centrifugal force acts, but at least one of the hub 51 and the shroud 52 has a plurality of layers 63a, 63b, 63c, 64a, which are more rigid toward the outside. 64b and 64c. Then, since the outer third layers 63c, 64c have high rigidity, deformation of the impeller 50 as a whole is suppressed, and the inner first layers 63a, 64a have low rigidity, so the outer third layer 64c A compressive stress field in the radial direction D is generated at each boundary of the divided first layers 63a, 64a, second layers 63b, 64b, and third layers 63c, 64c, and the tensile stress in the radial direction D is reduced. be done. Therefore, radial stress due to centrifugal force is reduced in at least one of the hub 51 and the shroud 52, and deformation in the radial direction D can be suppressed.

The impeller according to the second aspect is the impeller according to the first aspect, and further, the shroud 52 has a reinforcement layer (shroud reinforcement layer) 64 consisting of a plurality of layers 64a, 64b, 64c, and the reinforcement layer 64 is made of a composite material in which fiber members are arranged along the circumferential direction, and the outer side in the thickness direction has higher rigidity. As a result, when centrifugal force is generated due to rotation of the impeller 50, a compressive stress field in the radial direction D is generated at each boundary of the divided first layer 64a, second layer 64b, and third layer 64c, and the radial direction D The tensile stress of is reduced, and deformation in the radial direction D can be effectively suppressed.

The impeller according to the third aspect is the impeller according to the second aspect, and further, the hub 51 has a reinforcing layer (hub reinforcing layer) 63 consisting of a plurality of layers 63a, 63b, 63c, and the reinforcing layer 63 is made of a composite material in which fiber members are arranged along the circumferential direction, and the outer side in the thickness direction has higher rigidity. As a result, when centrifugal force is generated due to the rotation of the impeller 50, a compressive stress field in the radial direction D is generated at each boundary of the divided first layer 63a, second layer 63b, and third layer 63c, and the radial direction D The tensile stress of is reduced, and deformation in the radial direction D can be effectively suppressed.

The impeller according to the fourth aspect is the impeller according to any one of the first to third aspects, and further, the plurality of layers 63a, 63b, 63c, 64a, 64b, 64c are three layers. The above is provided. Thereby, the tensile stress exerted by the centrifugal force of the impeller 50 can be effectively reduced.

The impeller according to the fifth aspect is the impeller according to any one of the first to fourth aspects, and further, the plurality of layers 63a, 63b, 63c, 64a, 64b, and 64c are made of different materials. Consisted of. Thereby, it is possible to easily form a plurality of layers 63a, 63b, 63c, 64a, 64b, 64c whose rigidity is higher toward the outer side.

The impeller according to the sixth aspect is the impeller according to any one of the first to fifth aspects, and further, the hub 51, the shroud 52, and the plurality of blades 53 are formed individually and bonded together. It is integrally formed by Thereby, the impeller 50 having a plurality of layers 63a, 63b, 63c, 64a, 64b, and 64c whose rigidity is higher toward the outer side can be easily formed.

The impeller manufacturing method according to the seventh aspect includes a step of forming a hub 51 having a cylindrical shape, and a plurality of blades arranged at intervals in the circumferential direction between an inner supporting cylinder 71 and an outer supporting cylinder 72. 53, a step of forming a cylindrical shroud 52, and a step of assembling the hub 51, the blade assembly 53A, and the shroud 52. Reinforcement layers 63 and 64 are formed on at least one of the layers 52 and are made of a composite material in which fiber members are arranged along the circumferential direction, and are composed of a plurality of layers whose rigidity is higher toward the outside.

According to the impeller manufacturing method according to the seventh aspect, the impeller 50 having a plurality of layers 63a, 63b, 63c, 64a, 64b, 64c, which are more rigid toward the outer side on at least one of the hub 51 and the shroud 52, can be easily manufactured. can be manufactured.

The rotating machine according to the eighth aspect includes an impeller 50. Thereby, for example, deformation of the compressor wheel 36 in the centrifugal compressor 11 as a rotating machine can be suppressed and efficiency can be improved.

11 Centrifugal compressor 12 Turbine 13 Compressor 14 Rotating shaft 15 Housing 21 Turbine housing 31 Turbine wheel (impeller)
32 Hub 33 Blade 34 Shroud 36 Compressor wheel (impeller)
37 Hub 38 Blade 39 Shroud 50 Impeller 51 Hub 52 Shroud 53 Blade 54 Impeller channel 61 Cylindrical portion 62 Disc portion 63 Reinforcement layer (hub reinforcement layer)
63a 1st layer 63b 2nd layer 63c 3rd layer 64 Reinforcement layer (shroud reinforcement layer)
64a 1st layer 64b 2nd layer 64c 3rd layer A Axial direction D Radial direction R Circumferential direction

Claims (8)

A cylindrical hub,
a shroud having a cylindrical shape and disposed outside the hub;
a plurality of blades circumferentially spaced between the hub and the shroud;
Equipped with
At least one of the hub and the shroud has a plurality of layers stacked in the thickness direction, each of the plurality of layers is made of a composite material in which fiber members are arranged along the circumferential direction, and the plurality of layers are each made of a composite material in which fiber members are arranged along the circumferential direction. The outer layer in the thickness direction is more rigid,
impeller. The shroud has a shroud reinforcing layer made up of the plurality of layers, and the shroud reinforcing layer is made of a composite material in which fiber members are arranged along the circumferential direction, and the outer side in the thickness direction is higher in rigidity.
The impeller according to claim 1. The hub has a hub reinforcing layer made up of the plurality of layers, and the hub reinforcing layer is made of a composite material in which fiber members are arranged along the circumferential direction, and the outer side in the thickness direction has higher rigidity.
The impeller according to claim 2. The plurality of layers are provided with three or more layers,
The impeller according to any one of claims 1 to 3. The plurality of layers are made of different materials,
The impeller according to claim 1. The hub, the shroud, and the plurality of blades are formed individually and integrally formed by adhesive.
The impeller according to claim 1. a step of forming a hub having a cylindrical shape;
forming a blade assembly having a plurality of circumferentially spaced blades disposed between an inner support cylinder and an outer support cylinder;
forming a shroud having a cylindrical shape;
assembling the hub and blade assembly and the shroud;
has
forming a reinforcing layer on at least one of the hub and the shroud, which is made of a composite material in which fiber members are arranged along the circumferential direction, and is composed of a plurality of layers whose rigidity is higher toward the outside;
Impeller manufacturing method. A rotating machine comprising the impeller according to claim 1.

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