Blisk blade and rotary machine

Abstract

To provide a blisk blade that is further suppressed from vibrating, and a rotary machine.SOLUTION: A blisk blade has a disc-shaped disc part having its center on an axis, and a plurality of blade parts extending radially outward from an outer peripheral surface of the disc part and arrayed in a circumferential direction, wherein a detuning part which extends circumferentially around the axis is formed on a principal surface of the disc part which faces in the axial direction.SELECTED DRAWING: Figure 2

Description

Technical Field

[0001] The present disclosure relates to blisk blades and rotating machines.

Background Art

[0002] For example, rotating machines such as gas turbines, turbofan engines, and compressors mainly include a rotating shaft rotatable about an axis, a plurality of rotor blade rows attached to the rotating shaft, a casing that covers the rotor blade rows from the outer peripheral side, and a plurality of stator blade rows arranged on the inner peripheral surface of the casing so as to be alternately arranged in the axial direction with respect to the rotor blade rows. The rotor blade row and the stator blade row each have a disk-shaped disk attached to the rotating shaft and a plurality of blades extending radially outward from the outer peripheral surface of the disk. Conventionally, the disk and the blade have generally been manufactured as separate and independent components.

[0003] By the way, in recent years, due to the increase in the bore diameter of engines, that is, the increase in the length of blades, weight reduction of these members has been demanded. Therefore, attention has been focused on a technique called a blisk blade in which a disk and a blade are integrated (for example, Patent Document 1 below). On the other hand, in a blisk blade, there is a problem that vibration is likely to occur because structural friction damping generated between the disk and the blade cannot be obtained. For this reason, Patent Document 1 below proposes a technique of providing holes and grooves as a plurality of mistuning portions arranged at intervals in the circumferential direction in the disk portion of the blisk blade.

Prior Art Documents

Patent Documents

[0004]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0005] However, when a plurality of mistuning portions are provided at intervals in the circumferential direction as described above, there is a problem that vibration attenuation becomes difficult to obtain as the nodal diameter of vibration decreases.

[0006] The present disclosure has been made to solve the above problems, and an object thereof is to provide a blisk blade with further suppressed vibration and a rotating machine.

Means for Solving the Problems

[0007] In order to solve the above problems, a blisk blade according to the present disclosure is a blisk blade having a disk-shaped disk portion centered on an axis, and a plurality of blade portions extending radially outward from an outer peripheral surface of the disk portion and arranged in the circumferential direction, wherein a mistuning portion extending in the circumferential direction centered on the axis is formed on a main surface of the disk portion facing the axial direction.

[0008] A rotating machine according to the present disclosure includes the above-described blisk blade, a rotating shaft that is rotatable about the axis and supports the plurality of blisk blades, and a casing that covers the plurality of blisk blades from the outer peripheral side.

Effects of the Invention

[0009] According to the present disclosure, it is possible to provide a blisk blade with further suppressed vibration and a rotating machine.

Brief Description of the Drawings

[0010]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Figure 7

Figure 8

Mode for Carrying Out the Invention

[0011] <First Embodiment> (Configuration of Rotating Machine) Hereinafter, the blisk blade 5 according to the first embodiment of the present disclosure and the rotating machine will be described with reference to FIGS. 1 to 4. This blisk blade 5 is particularly preferably used as a moving blade of a rotating machine such as a gas turbine.

[0012] (Configuration of Aircraft Gas Turbine 100) As shown in FIG. 1, the aircraft gas turbine 100 as a rotating machine includes a compressor 1, a combustor 2, and a turbine 3.

[0013] The compressor 1 compresses the air sucked in from the intake duct 10 to generate high-pressure air. The compressor 1 includes a compressor rotor 11 (rotating shaft), a compressor casing 12, a compressor rotor blade row 13, and a compressor stator blade row 15. The compressor rotor 11 has a columnar shape extending along the axis Am and is rotatable around the axis Am. A plurality of compressor rotor blade rows 13 are arranged at intervals in the direction of the axis Am on the outer peripheral surface of the compressor rotor 11. Each compressor rotor blade row 13 has a plurality of compressor rotor blades 14 extending radially outward from the outer peripheral surface of the compressor rotor 11 and arranged in the circumferential direction. The compressor casing 12 has a cylindrical shape covering these compressor rotor blade rows 13 from the outer peripheral side. A plurality of compressor stator blade rows 15 are arranged on the inner peripheral surface of the compressor casing 12. The compressor stator blade rows 15 are arranged alternately with the compressor rotor blade rows 13 in the direction of the axis Am. Each compressor stator blade row 15 has a plurality of compressor stator blades 16 protruding radially inward from the inner peripheral surface of the compressor casing 12 and arranged in the circumferential direction.

[0014] The combustor 2 mixes the fuel F with the high-pressure air generated by the compressor 1 and burns it to generate high-temperature and high-pressure combustion gas G. The combustor 2 is provided between the compressor casing 12 and the turbine casing 22. The combustion gas G generated by this combustor 2 is supplied to the turbine 3.

[0015] The turbine 3 has a turbine rotor 21, a turbine casing 22, a turbine moving blade row 23, and a turbine stationary blade row 25. The turbine rotor 21 has a columnar shape extending along the axis Am and is rotatable about the axis Am. A plurality of turbine moving blade rows 23 are arranged at intervals in the direction of the axis Am on the outer peripheral surface of the turbine rotor 21. Each turbine moving blade row 23 has a plurality of turbine moving blades 24 extending radially outward from the outer peripheral surface of the turbine rotor 21 and arranged in the circumferential direction. The turbine casing 22 has a cylindrical shape covering these turbine moving blade rows 23 from the outer peripheral side. A plurality of turbine stationary blade rows 25 are arranged on the inner peripheral surface of the turbine casing 22. The turbine stationary blade rows 25 are arranged so as to alternate with the turbine moving blade rows 23 in the direction of the axis Am. Each turbine stationary blade row 25 has a plurality of turbine stationary blades 26 protruding radially inward from the inner peripheral surface of the turbine casing 22 and arranged in the circumferential direction.

[0016] The compressor rotor 11 and the turbine rotor 21 are integrally connected in the direction of the axis Am to form a gas turbine rotor 91. The compressor casing 12 and the turbine casing 22 are integrally connected in the direction of the axis Am to form a gas turbine casing 92. That is, the gas turbine rotor 91 is rotatable about the axis Am inside the gas turbine casing 92.

[0017] When operating the aircraft gas turbine 100, first, the compressor rotor 11 (gas turbine rotor 91) is rotationally driven by an external drive source. As the compressor rotor 11 rotates, external air is sequentially compressed, and high-pressure air is generated. This high-pressure air is supplied to the combustor 2 through the compressor casing 12. In the combustor 2, fuel F is mixed with this high-pressure air and then burned to generate high-temperature and high-pressure combustion gas G. The combustion gas G is supplied into the turbine 3 through the turbine casing 22. In the turbine 3, as the combustion gas G sequentially collides with the turbine moving blade row 23 and the turbine stationary blade row 25, a rotational driving force is applied to the turbine rotor 21 (gas turbine rotor 91). This rotational energy is mainly used to drive the compressor 1. The combustion gas G that has driven the turbine 3 becomes a jet flow with an increased flow rate by the exhaust nozzle to generate thrust and is discharged to the outside from the injection port. In this embodiment, a single-shaft turbojet engine is described as an example of the aircraft gas turbine 100. However, it is not limited to a single-shaft turbojet engine, and any form of the aircraft gas turbine 100 may be used. In particular, it is suitable for the low-pressure turbine and turbofan of a multi-shaft turbofan engine.

[0018] (Configuration of the blisk blade 5) Next, the configuration of the above-described compressor moving blade row 13 will be described with reference to FIGS. 2 and 3. As shown in FIG. 2, this compressor moving blade row 13 includes a disk portion 51, a blade portion 52, and a parting portion 53. The disk portion 51 has a disk shape centered on the axis Am.

[0019] The blade portion 52 is provided on the outer peripheral side of the disk portion 51. The blade portion 52 extends radially outward from the outer peripheral surface of the disk portion 51 and is arranged in a plurality with intervals in the circumferential direction. These blade portions 52 correspond to the above-described compressor moving blades 14. The disk portion 51 and the blade portion 52 are integrally formed of one material. That is, this compressor moving blade row 13 constitutes a so-called blisk blade 5 in which the disk portion 51 and the blade portion 52 are integrated.

[0020] On the surface (main surface 51a) facing the axial direction Am of the disk portion 51, a detuning portion 53 is provided. The detuning portion 53 is a structure for changing the vibration mode of the disk portion 51 to avoid resonance and coupled vibration. Specifically, the detuning portion 53 has a groove portion 61. The groove portion 61 forms a continuous single annular shape centered on the axis Am and is a groove recessed in the direction of the axis Am from the main surface 51a. As an example, the cross-sectional shape of the groove portion 61 is rectangular as shown in FIG. 3. Note that the cross-sectional shape of the groove portion 61 may be semicircular or trapezoidal. Further, the groove portion 61 as the detuning portion 53 is provided at an intermediate position in the radial direction of the disk portion 51. Note that the groove portion 61 may be biased more toward the inner side or the outer side in the radial direction.

[0021] (Function and effect) In recent years, due to the increase in the diameter of the aircraft gas turbine 100, that is, the increase in the length of the blades, weight reduction of these members has been demanded. Therefore, attention has been focused on the blisk blade 5 in which the disk and the blade are integrated. On the other hand, in the blisk blade 5, there is a problem that vibration is likely to occur because structural friction damping generated between the disk and the blade cannot be obtained. To solve this problem, each of the above-described configurations is adopted in the present embodiment.

[0022] According to the above configuration, a tuning-out portion 53 extending in the circumferential direction is provided on the main surface 51a of the disk portion 51. Therefore, the rigidity of the disk portion 51 changes. By changing the rigidity in this way, the vibration frequency when the entire blisk 5 is excited can be arbitrarily controlled. Specifically, as shown by the one-dot chain line and the two-dot chain line in the graph of FIG. 4, particularly in the primary vibration mode with a small nodal diameter (the nodal diameter is about 0 to 3), the influence of the change in rigidity on the vibration frequency is greater than that in the mode with a large nodal diameter. According to the above configuration, the vibration characteristics (vibration frequency) of the blisk 5 in such a low nodal diameter mode can be optimized, and fatigue failure and the like of the blisk 5 can be avoided. Specifically, it is possible to avoid a state where the "constant rotation speed line" of the broken line shown in FIG. 4 coincides with the value of the vibration frequency. It is known that when this constant rotation speed line and the vibration frequency coincide, there is a risk of resonance or coupled vibration. According to the above configuration, since such a coincidence of vibration frequencies can be avoided, the possibility of resonance or coupled vibration occurring can be significantly reduced. Therefore, it becomes possible to continuously maintain the stable operation of the rotating machine to which the blisk 5 is applied for a long time. Here, the "nodal diameter mode" refers to a unique vibration mode similar to the vibration mode of a disk, and like the vibration mode of a disk, nodes exist at several diameter positions where there is one wavelength, two wavelengths, etc. over the circumferential direction. These wavelengths, that is, the number of "nodes" are called "nodal diameters".

[0023] According to the above configuration, the tuning-out portion 53 has a groove portion 61 provided on the main surface 51a. By providing this groove, the rigidity of the disk portion 51 decreases. Then, the vibration frequency of the blisk 5 when excited becomes lower (see the one-dot chain line in FIG. 4). Thereby, the vibration characteristics in the low nodal diameter mode can be optimized. Thereby, fatigue failure and the like of the blisk 5 can be avoided. Therefore, it becomes possible to continuously maintain the stable operation of the rotating machine to which the blisk 5 is applied for a long time.

[0024] According to the above configuration, since the detuning portion 53 forms an annular shape that is continuous in the circumferential direction, vibration in the nodal diameter mode can be suppressed over the entire circumferential direction. Further, a mistuning state in the radial direction can be created over the entire circumferential direction. Thereby, it becomes possible to further reduce the possibility of coupled vibration and resonance occurring.

[0025] The first embodiment of the present disclosure has been described above. Note that various changes and modifications can be made to the above configuration without departing from the gist of the present disclosure.

[0026] <Second Embodiment> Next, a second embodiment of the present disclosure will be described with reference to FIGS. 5 and 6. Note that the same components as those in the first embodiment described above are denoted by the same reference numerals, and detailed descriptions thereof are omitted.

[0027] As shown in FIG. 5 or FIG. 6, in the present embodiment, the detuning portion 53 has a protrusion portion 62 instead of the groove portion 61. The protrusion portion 62 protrudes from the main surface 51a of the disk portion 51 in the direction of the axis Am and forms a continuous single annular shape centered on the axis Am. As shown in FIG. 5, the cross-sectional shape of the protrusion portion 62 is, for example, rectangular. Note that the cross-sectional shape of the protrusion portion 62 may be semicircular or trapezoidal. Further, the protrusion portion 62 is provided at an intermediate position in the radial direction of the disk portion 51. Note that the protrusion portion 62 may be biased more toward the inner side in the radial direction or may be biased toward the outer side.

[0028] (Function and Effect) According to the above configuration, the detuning portion 53 has the protrusion portion 62 provided on the main surface 51a. By providing this protrusion portion 62, the rigidity of the disk portion 51 increases. Then, the vibration frequency of the blisk blade 5 when excited also increases (see the two-dot chain line in FIG. 4). Thereby, the vibration characteristics in the low nodal diameter mode can be optimized. For this reason, fatigue failure and the like of the blisk blade 5 can be avoided. Therefore, it becomes possible to continuously maintain stable operation of the rotating machine to which the blisk blade 5 is applied for a long time.

[0029] According to the above configuration, since the out-of-tune portion 53 forms an annular shape that is continuous in the circumferential direction, vibration in the nodal diameter mode can be suppressed over the entire circumferential direction. Further, a mistuned state in the radial direction can be created over the entire circumferential direction. Thereby, it becomes possible to further reduce the possibility of coupled vibration or resonance occurring.

[0030] The second embodiment of the present disclosure has been described above. Note that various changes and modifications can be made to the above configuration without departing from the gist of the present disclosure.

[0031] <Third Embodiment> Next, a third embodiment of the present disclosure will be described with reference to FIG. 7. Note that the same reference numerals are given to the same configurations as those in the above embodiments, and detailed descriptions thereof are omitted.

[0032] As shown in FIG. 7, in the present embodiment, the out-of-tune portion 53 has small grooves 63 in addition to the grooves 61. The small grooves 63 are provided in addition to the grooves 61. That is, the small grooves 63 are integrally formed on the outer peripheral side of the grooves 61. The small grooves 63 are recessed from the main surface 51a of the disk portion 51 in the direction of the axis Am, and a plurality (five in one example) are provided at intervals in the circumferential direction. The small grooves 63 have a rectangular shape when viewed from the direction of the axis Am. Note that the number of small grooves 63 provided may be any number as long as the greatest common divisor of the number does not match the nodal diameter.

[0033] (Function and Effect) According to the above configuration, in addition to the grooves 61, a plurality of small grooves 63 are provided. Thereby, not only the vibration mode in the radial direction of the disk portion 51 but also the vibration mode in the circumferential direction can be made into a mistuned state. Therefore, it becomes possible to minimize the possibility of coupled vibration in which various vibration modes are coupled and resonance occurring.

[0034] The third embodiment of the present disclosure has been described above. Note that various changes and modifications can be made to the above configuration without departing from the gist of the present disclosure.

[0035] For example, instead of the groove portion 61 and the small groove portion 63 described in the third embodiment, it is also possible to adopt a configuration including the ridge portion 62 and the small ridge portion described in the second embodiment. Here, the small ridge portion is a member that protrudes from the main surface 51a of the disk portion 51 in the direction of the axis Am and is arranged in a plurality at intervals in the circumferential direction. The small ridge portion is integrally formed on the outer peripheral side of the ridge portion 62. It is desirable that the number of small ridge portions be determined according to the same criterion as the number of small groove portions 63.

[0036] According to the above configuration, in addition to the ridge portion 62, it has a plurality of small ridge portions. Thereby, not only the vibration mode in the radial direction of the disk portion 51 but also the vibration mode in the circumferential direction can be made into a mistuned state. Therefore, it is possible to minimize the possibility of the occurrence of coupled vibrations in which various vibration modes are coupled and resonance.

[0037] (Other Embodiments) As described above, the embodiments of the present disclosure have been described in detail with reference to the drawings, but the specific configuration is not limited to this embodiment, and design changes and the like within the scope not departing from the gist of the present disclosure are also included.

[0038] For example, as a modification common to each embodiment, it is possible to adopt the configuration shown in FIG. 8. In the example of the figure, the groove portion 61 or the ridge portion 62 of the detuning portion 53 is not in a continuous annular shape but in a divided arc shape and is arranged in a plurality at intervals in the circumferential direction. It is also possible to combine the configuration in which the groove portion 61 or the ridge portion 62 is divided in this way with the configuration having the small groove portion 63 and the small ridge portion described in the third embodiment above.

[0039] According to the above configuration, since a plurality of the off-tuning portions 53 are arranged at intervals in the circumferential direction, the rigidity can be increased in a part of the circumferential region where the off-tuning portions 53 are not provided. As a result, the vibration frequency of the entire blisk blade 5 when excited becomes higher. As a result, it is possible to optimize the vibration frequency particularly in the low nodal diameter mode. Further, since a plurality of the off-tuning portions 53 are provided in the circumferential direction, it is also possible to create a mistuning state in the circumferential direction. Thereby, it is possible to further reduce the possibility of occurrence of coupled vibration and resonance.

[0040] Further, although not shown, as long as the rigidity of the disk portion 51 can be ensured to the minimum, it is also possible to adopt a configuration in which a plurality of groove portions 61 or rib portions 62 are arranged at intervals in the radial direction. Also with this configuration, the same operational effects as those described above can be obtained.

[0041] Furthermore, the small groove portion 63 or the small rib portion described in the third embodiment may be provided on the inner peripheral side instead of the outer peripheral side of the groove portion 61 or the rib portion 62. It is also possible to adopt a configuration in which the small groove portion 63 or the small rib portion is provided on the inner peripheral side and the outer peripheral side, respectively. Further, in this case, it is also possible to arrange the small groove portion 63 or the small rib portion at different circumferential positions on the inner peripheral side and the outer peripheral side. According to this configuration, it is possible to more precisely control the mistuning state described above.

[0042] <Supplementary Note> The blisk blade 5 and the rotating machine described in each embodiment are grasped as follows, for example.

[0043] (1) The blisk blade 5 according to the first aspect is a blisk blade 5 having a disk-shaped disk portion 51 centered on the axis Am and a plurality of blade portions 52 extending radially outward from the outer peripheral surface of the disk portion 51 and arranged in the circumferential direction, wherein a main surface 51a of the disk portion 51 facing the direction of the axis Am has an off-tuning portion 53 formed thereon that extends in the circumferential direction around the axis Am.

[0044] According to the above configuration, a detuning portion 53 extending in the circumferential direction is provided on the main surface 51a of the disk portion 51. Therefore, the rigidity of the disk portion 51 changes. By changing the rigidity in this way, the frequency when the entire blisk blade 5 is excited can be arbitrarily controlled.

[0045] (2) The blisk blade 5 according to the second aspect is the blisk blade 5 of (1), and the detuning portion 53 has a groove portion 61 that is recessed from the main surface 51a in the direction of the axis Am.

[0046] According to the above configuration, the detuning portion 53 has a groove portion 61 provided on the main surface 51a. By providing this groove, the rigidity of the disk portion 51 decreases. Then, the frequency of the blisk blade 5 when excited becomes lower. Thereby, the vibration characteristics in the low nodal diameter mode can be optimized.

[0047] (3) The blisk blade 5 according to the third aspect is the blisk blade 5 of (2), and the detuning portion 53 is provided in the groove portion 61 and further has a plurality of small groove portions 63 that are recessed from the main surface 51a in the direction of the axis Am and arranged at intervals in the circumferential direction.

[0048] According to the above configuration, in addition to the groove portion 61, a plurality of small groove portions 63 are provided. Thereby, not only the vibration mode in the radial direction of the disk portion 51 but also the vibration mode in the circumferential direction can be made into a mistuned state.

[0049] (4) The blisk blade 5 according to the fourth aspect is the blisk blade 5 of (1), and the detuning portion 53 has a ridge portion 62 that protrudes from the main surface 51a in the direction of the axis Am.

[0050] According to the above configuration, the detuning portion 53 has a ridge portion 62 provided on the main surface 51a. By providing this ridge portion 62, the rigidity of the disk portion 51 increases. Then, the frequency of the blisk blade 5 when excited also increases. Thereby, the vibration characteristics in the low nodal diameter mode can be optimized.

[0051] (5) The blisk blade 5 according to the fifth aspect is the blisk blade 5 of (4), wherein the detuning portion 53 is provided in parallel with the ridge portion 62 and further has a plurality of small ridge portions that protrude in the direction of the axis Am from the main surface 51a and are arranged at intervals in the circumferential direction.

[0052] According to the above configuration, in addition to the ridge portion 62, it has a plurality of small ridge portions 62. Thereby, not only the vibration mode in the radial direction of the disk portion 51 but also the vibration mode in the circumferential direction can be made into a mistuned state.

[0053] (6) The blisk blade 5 according to the sixth aspect is the blisk blade 5 according to any one of the aspects (1) to (5), wherein the detuning portion 53 forms an annular shape that is continuous in the circumferential direction.

[0054] According to the above configuration, since the detuning portion 53 forms an annular shape that is continuous in the circumferential direction, vibration in the nodal diameter mode can be suppressed over the entire circumferential direction.

[0055] (7) The blisk blade 5 according to the seventh aspect is the blisk blade 5 according to any one of the aspects (1) to (5), wherein a plurality of the detuning portions 53 are arranged at intervals in the circumferential direction.

[0056] According to the above configuration, since a plurality of the detuning portions 53 are arranged at intervals in the circumferential direction, the rigidity can be increased in a partial region in the circumferential direction where the detuning portion 53 is not provided. As a result, the vibration frequency of the entire blisk blade 5 when excited becomes higher. As a result, the vibration frequency in particular in the low nodal diameter mode can be optimized.

[0057] (8) The rotary machine according to the eighth aspect includes the blisk blade 5 according to any one of the aspects (1) to (7), a rotary shaft that is rotatable about the axis Am and supports the plurality of blisk blades 5, and a casing that covers the plurality of blisk blades 5 from the outer peripheral side.

[0058] According to the above configuration, by suppressing the coupled vibration and resonance of the blisk blade 5, a rotating machine that can be stably operated over a long period can be provided.

Explanation of Signs

[0059] 1…Compressor 2…Combustor 3…Turbine 5…Blisk blade 10…Intake duct 11…Compressor rotor 12…Compressor casing 13…Compressor rotor blade row 14…Compressor rotor blade 15…Compressor stator blade row 16…Compressor stator blade 21…Turbine rotor 22…Turbine casing 23…Turbine rotor blade row 24…Turbine rotor blade 25…Turbine stator blade row 26…Turbine stator blade 51…Disk part 51a…Main surface 52…Blade part 53…Detuning part 61…Groove part 62…Ridge part 63…Small groove part 91…Gas turbine rotor 92…Gas turbine casing 100…Aircraft gas turbine Am…Axis F…Fuel G…Combustion gas

Claims

1. A blisk blade having a disk portion in the shape of a disk centered on an axis, and a plurality of blade portions extending radially outward from the outer peripheral surface of the disk portion and arranged in the circumferential direction, wherein a detuning portion extending in the circumferential direction centered on the axis is formed on the main surface of the disk portion facing the axial direction.

2. The blisk blade according to claim 1, wherein the detuning portion has a groove portion recessed from the main surface in the axial direction.

3. The blisk blade according to claim 2, wherein the detuning portion is provided in the groove portion and further has a plurality of small groove portions recessed from the main surface in the axial direction and arranged at intervals in the circumferential direction.

4. The blisk blade according to claim 1, wherein the detuning portion has a ridge portion protruding from the main surface in the axial direction.

5. The blisk blade according to claim 4, wherein the detuning portion is provided in the ridge portion and further has a plurality of small ridge portions protruding from the main surface in the axial direction and arranged at intervals in the circumferential direction.

6. The blisk blade according to any one of claims 1 to 5, wherein the detuning portion forms an annular shape continuous in the circumferential direction.

7. The blisk blade according to any one of claims 1 to 5, wherein a plurality of the detuning portions are arranged at intervals in the circumferential direction.

8. The blisk blade according to any one of claims 1 to 5, a rotating shaft that is rotatable about the axis and supports the plurality of blisk blades, and a casing that covers the plurality of blisk blades from the outer peripheral side, A rotating machine comprising.

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