A compressor rotor and an aircraft engine

Abstract

This disclosure relates to a compressor rotor and an aero-engine, wherein the compressor rotor includes: a multi-stage rotor disk; a support ring, fixedly connected to the rotor disk by fasteners, and having multiple radial through holes along its circumference; and a vortex damper, passing through the radial through holes and located axially between two adjacent stages of the rotor disk to form a radial channel for rotor air intake; the support ring also has a layered folding structure, which is located between the rotor disk and the vortex damper. The embodiments of this disclosure can effectively improve the overall natural frequency of the air intake structure within the rotor cavity, avoiding the risk of local resonance at the connection between the support ring and the rotor disk; simultaneously, it gives the support ring a good vibration damping effect, reducing the vibration load transmitted from the support ring to the rotor disk, thereby improving the service life of the rotor disk.

Description

Technical Field

[0001] This disclosure relates to the field of aero-engine manufacturing, and more particularly to a compressor rotor and an aero-engine. Background Technology

[0002] In a gas turbine engine, the compressor performs work on the air through high-speed rotating rotor blades. The rotor blades, as high-speed rotating components in the compressor, are usually combined with the long shaft or front and rear journals and multiple disks to form the rotor structure.

[0003] To meet bleed air requirements, current aero-engine high-pressure compressors typically have bleed air structures arranged inside the rotor cavity. To reduce bleed air losses, the bleed air structure inside the rotor cavity usually consists of bleed air anti-vortex tubes and support rings: several bleed air anti-vortex tubes are mounted on the support rings, which are then bolted to the rotor disk.

[0004] However, the applicant's research revealed the following problems with the existing rotor internal cavity air duct structure:

[0005] Firstly, the induced draft tube inevitably vibrates under the excitation of the induced draft in the inner cavity, causing the induced draft tube and the support ring to vibrate as a whole. As a result, the vibration load will be transmitted to the rotor disk through the support ring, which will have an adverse effect on the service life of the rotor disk.

[0006] Secondly, the complex vibration loads of the internal air bleed structure pose a risk of inducing local resonance at the connection between the support ring and the rotor disk, which is detrimental to the structural stability of the aero-engine. Summary of the Invention

[0007] In view of this, the present disclosure provides a compressor rotor and an aero-engine that can effectively improve the overall natural frequency of the air intake structure in the rotor cavity and avoid the risk of local resonance at the connection between the support ring and the rotor disk; at the same time, it enables the support ring to have a good vibration reduction effect, reducing the vibration load transmitted from the support ring to the rotor disk, thereby improving the service life of the rotor disk.

[0008] In one aspect of this disclosure, a compressor rotor is provided, comprising:

[0009] Multistage rotor disk;

[0010] A support ring, fixedly connected to the rotor disk by fasteners, and having multiple radial through holes along its circumference; and

[0011] The vortex reducer tube is inserted through the radial through hole and is located axially between two adjacent rotor disks to form a radial channel for rotor air intake.

[0012] The support ring is further provided with a layered folding structure, which is located between the rotor disk and the anti-vortex tube.

[0013] In some embodiments, the layered folding structure includes at least one bent segment, which is angular in a cross section perpendicular to the circumferential direction. The vertex of the angular segment corresponds to an annular edge of the bent segment, and the two sides of the angular segment correspond to two toroidal surfaces that meet at the same annular edge.

[0014] In some embodiments, the bent segment includes:

[0015] The radially bent segment forms a first angle in a cross-section perpendicular to the circumference, wherein the radial projections of the two sides of the first angle at least partially coincide; and / or

[0016] The axially bent section forms a second triangle on a cross section perpendicular to the circumferential direction, wherein the two sides of the second triangle at least partially overlap each other along the axial projection.

[0017] In some embodiments, the layered folding structure is configured such that, under a set vibration state, the common natural frequency of the support ring and the vortex reducer, determined by their own rigidity, does not resonate with the natural frequency of the rotor disk.

[0018] In some embodiments, the rigidity of the layered folding structure is determined by the number of the folded segments, the thickness of each folded segment, and the thickness distribution characteristics of each folded segment.

[0019] In some embodiments, an annular flange is provided on the inner end face of the rotor disk on the side axially away from the anti-vortex tube, and the support ring is attached to the radial inner side of the annular flange.

[0020] In some embodiments, the support ring has a radial mounting edge at one end near the rotor disk, and the fastener includes:

[0021] Bolts are inserted into coaxial axial mounting holes provided on the radial mounting edge and the annular flange to secure the support ring relative to the rotor disk.

[0022] In some embodiments, the support ring has an axial mounting edge, and the axial mounting edge has a plurality of radial studs distributed circumferentially on the side of the annular flange away from the vortex reducer, the fasteners comprising:

[0023] A nut is inserted through the radial stud and axially engaged with the annular flange on the side away from the anti-vortex tube.

[0024] In some embodiments, the support ring is further provided with a positioning stop, which is located on the side of the annular flange near the anti-vortex tube and engages with the annular flange in the radial and axial directions.

[0025] In some embodiments, the alloy material of the support ring has the same linear expansion coefficient as the alloy material of the rotor disk, and the positioning stop and the annular flange are in an interference fit in the radial direction.

[0026] In another aspect of this disclosure, an aircraft engine is provided, including a compressor rotor as described in any of the preceding embodiments.

[0027] Therefore, according to the embodiments of this disclosure, the overall natural frequency of the air duct structure in the rotor cavity can be effectively improved, avoiding the risk of local resonance at the connection between the support ring and the rotor disk; at the same time, the support ring has a good vibration reduction effect, reducing the vibration load transmitted from the support ring to the rotor disk, thereby improving the service life of the rotor disk. Attached Figure Description

[0028] The accompanying drawings, which form part of this specification, illustrate embodiments of this disclosure and, together with the specification, serve to explain the principles of this disclosure.

[0029] This disclosure will become clearer with reference to the accompanying drawings and the following detailed description, wherein:

[0030] Figure 1 This is a schematic diagram of a compressor rotor according to some embodiments of the present disclosure, in which the fasteners are nuts and the bent section is a radial bent section;

[0031] Figure 2 This is a schematic diagram of a compressor rotor according to some embodiments of the present disclosure, in which the fasteners are nuts and the bent section is an axial bent section;

[0032] Figure 3 This is a schematic diagram of a compressor rotor according to some embodiments of the present disclosure, in which the fasteners are bolts and the bent section is a radial bent section;

[0033] Figure 4 This is a schematic diagram of a compressor rotor according to some embodiments of the present disclosure, in which the fasteners are bolts and the bent section is an axially bent section;

[0034] In the picture:

[0035] 1. Vortex reducer; 2. Support ring; 21. Layered folding structure; 211. Radial bending section; 212. Axial bending section; 22. Radial mounting edge; 23. Axial mounting edge; 24. Positioning stop; 3. Fastener; 31. Bolt; 32. Nut; 4. Rotor disc; 41. Annular flange.

[0036] It should be understood that the dimensions of the various parts shown in the accompanying drawings are not drawn to actual scale. Furthermore, the same or similar reference numerals denote the same or similar components. Detailed Implementation

[0037] Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. The descriptions of the exemplary embodiments are merely illustrative and are in no way intended to limit the present disclosure or its application or use. The present disclosure may be implemented in many different forms and is not limited to the embodiments described herein. These embodiments are provided so that the present disclosure will be thorough and complete, and will fully express the scope of the disclosure to those skilled in the art. It should be noted that, unless specifically stated otherwise, the relative arrangement of components and steps, the composition of materials, numerical expressions, and values ​​set forth in these embodiments should be interpreted as exemplary only and not as limiting.

[0038] The terms "first," "second," and similar words used in this disclosure do not indicate any order, quantity, or importance, but are merely used to distinguish different parts. Words such as "including" or "contains" mean that the element preceding the word encompasses the element listed after it, and do not exclude the possibility of encompassing other elements as well. Terms such as "above," "below," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, this relative positional relationship may also change accordingly.

[0039] In this disclosure, when a specific device is described as being located between a first device and a second device, an intermediary device may or may not be present between the specific device and the first or second device. When a specific device is described as being connected to other devices, the specific device may be directly connected to the other devices without an intermediary device, or it may be not directly connected to the other devices but have an intermediary device.

[0040] All terms used in this disclosure (including technical or scientific terms) have the same meaning as understood by one of ordinary skill in the art to which this disclosure pertains, unless otherwise specifically defined. It should also be understood that terms defined in a general dictionary, such as a dictionary, should be interpreted as having a meaning consistent with their meaning in the context of the relevant art, and not as having an idealized or highly formalized meaning, unless expressly defined herein.

[0041] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0042] like Figures 1-4As shown, in one aspect of this disclosure, a compressor rotor is provided, including a multi-stage rotor disk 4, a support ring 2, and a vortex reducer 1. The support ring 2 is fixedly connected to the rotor disk 4 by fasteners 3 and has multiple radial through holes along its circumference; the vortex reducer 1 passes through the radial through holes and is located axially between two adjacent rotor disks 4 to form a radial channel for rotor air intake; the support ring 2 also has a layered folding structure 21, which is located between the rotor disk 4 and the vortex reducer 1.

[0043] The layered folding structure 21 can act as an "elastic element" to absorb the vibration energy from the internal air intake structure, which includes the overall structure composed of each vortex-reducing tube 1 and the support ring 2. This reduces the vibration load transmitted to the rotor disk 4, thereby reducing the overall load borne by the rotor disk 4 and ultimately extending the service life of the rotor disk 4.

[0044] In addition, the layered folding structure 21 is located between the connecting support ring 2 and the rotor disk 4, which can effectively improve the overall natural frequency of the internal cavity air intake structure, reduce the risk of local resonance at the connection between the connecting ring and the rotor disk 4, and help improve the service life of the rotor disk 4.

[0045] Furthermore, in some embodiments, the layered foldback structure 21 includes at least one bent segment, which is angular in a cross-section perpendicular to the circumferential direction. The vertex of the angular segment corresponds to an annular edge of the bent segment, and the two sides of the angular segment correspond to two annular surfaces that meet at the same annular edge. Thus, the bent segment can include two forms: a radial bent segment 211 and an axial bent segment 212.

[0046] The radially bent segment 211 is a first triangle in a cross section perpendicular to the circumference, and the two sides of the first triangle are at least partially overlapped by radial projections; while the axially bent segment 212 is a second triangle in a cross section perpendicular to the circumference, and the two sides of the second triangle are at least partially overlapped by axial projections.

[0047] In fact, considering that the principle of the layered folding structure 21 absorbing vibration loads is similar to that of a spring absorbing energy, for example, for axial vibration loads, the axial compression and expansion of the axial bending section 212 can better absorb the energy of the axial vibration load. Therefore, considering the vibration characteristics of the compressor rotor's internal air intake structure, the shape of the bending section is not limited to the radial bending section 211 and the axial bending section 212, but can be flexibly arranged according to the direction of the vibration load to obtain a better absorption effect.

[0048] To address the function of the layered folding structure 21 in altering the resonant frequency of the rotor's internal air intake structure, the layered folding structure 21 is constructed such that, under a set vibration state, the common natural frequency of the support ring 2 and the vortex reducer 1, determined by their own rigidity, does not resonate with the natural frequency of the rotor disk 4. Furthermore, the rigidity of the layered folding structure 21 is determined by the number of bending segments, the thickness of each bending segment, and the thickness distribution characteristics of each bending segment.

[0049] Therefore, based on the layered folding structure 21 provided in this disclosure, the natural frequency of the rotor's internal air intake structure can be adjusted by changing the number, thickness, and thickness characteristics of the bending sections, or by adjusting the angle and shape of the bending sections, so that the common natural frequency of the support ring 2 and the vortex reducer 1 avoids the resonance frequency range, thereby reducing the risk of resonance.

[0050] To achieve a fixed connection between the support ring 2 and the rotor disk 4, in some embodiments, an annular flange 41 is provided on the inner end face of the rotor disk 4 along the axial direction away from the vortex reducer 1, and the support ring 2 is attached to the radial inner side of the annular flange 41. Thus, the support ring 2 can transmit radial loads to the rotor disk 4. Especially after the compressor rotor starts rotating, under the influence of centrifugal force, the support ring 2 will be tightly attached to the inner side of the rotor disk 4, thereby achieving radial limiting of the support ring 2.

[0051] In order to achieve axial positioning of the support ring 2, in some embodiments, the end of the support ring 2 near the rotor disk 4 is provided with a radial mounting edge 22, and the fastener 3 includes a bolt 31, which passes through a coaxial axial mounting hole provided on the radial mounting edge 22 and the annular flange 41, so as to achieve fastening of the support ring 2 relative to the rotor disk 4.

[0052] The support ring 2 and rotor disk 4 connected by studs can transfer axial loads to each other. Especially for the compressor rotor, when it applies aerodynamic force to the airflow in the working state, it will be subjected to a forward thrust from the airflow under the influence of action and reaction forces. At this time, the support ring 2, through the radial mounting edge 22 and bolt 31, jointly bears the forward axial load of the rotor disk 4, thereby ensuring the connection stability between the support ring 2 and the rotor disk 4.

[0053] Similarly, to achieve axial positioning of the support ring 2, in some embodiments, the support ring 2 may also be provided with an axial mounting edge 23. The axial mounting edge 23 has multiple radial studs distributed circumferentially on the side of the annular flange 41 away from the anti-vortex tube 1. Fasteners 3 include nuts 32, which pass through the radial studs and are axially engaged on the side of the annular flange 41 away from the anti-vortex tube 1. Furthermore, to coordinate with the nut 32 in limiting the radial position of the support ring 2, in some embodiments, the support ring 2 is also provided with a positioning stop 24. The positioning stop 24 is located on the side of the annular flange 41 near the anti-vortex tube 1 and engages with the annular flange 41 radially and axially.

[0054] Therefore, for the annular flange 41 of the rotor disk 4, the support ring 2 is axially limited on both sides of the annular flange 41 by the positioning stop 24 and the nut 32, thereby completing the stable connection between the support ring 2 and the rotor disk 4.

[0055] In some embodiments, the alloy material of the support ring 2 and the alloy material of the rotor disk 4 have the same coefficient of linear expansion, and the positioning stop 24 and the annular flange 41 are in an interference fit in the radial direction. Of course, the parts on both sides connected by the centering stop on the layered folding structure 21 can also be made of alloys with different coefficients of linear expansion, but a suitable fit relationship needs to be selected through calculation to avoid affecting reliable centering due to deformation incoordination caused by thermal expansion during operation.

[0056] In another aspect of this disclosure, an aircraft engine is provided, including a compressor rotor as described in any of the embodiments above.

[0057] Therefore, according to the embodiments of this disclosure, the overall natural frequency of the air intake structure in the rotor cavity can be effectively improved, avoiding the risk of local resonance at the connection between the support ring 2 and the rotor disk 4; at the same time, the support ring 2 has a good vibration reduction effect, reducing the vibration load transmitted from the support ring 2 to the rotor disk 4, thereby improving the service life of the rotor disk 4.

[0058] The embodiments of this disclosure have now been described in detail. To avoid obscuring the concept of this disclosure, some details known in the art have not been described. Those skilled in the art can fully understand how to implement the technical solutions disclosed herein based on the above description.

[0059] While specific embodiments of this disclosure have been described in detail by way of examples, those skilled in the art should understand that the examples are for illustrative purposes only and not intended to limit the scope of this disclosure. Those skilled in the art should understand that modifications can be made to the above embodiments or equivalent substitutions can be made to some technical features without departing from the scope and spirit of this disclosure. The scope of this disclosure is defined by the appended claims.

Claims

1. A compressor rotor, characterized in that, include: Multistage rotor disk (4); The support ring (2) is fixedly connected to the rotor disk (4) by fasteners (3) and has multiple radial through holes along the circumference; and The vortex reducer (1) is inserted through the radial through hole and is located axially between two adjacent rotor disks (4) to form a radial channel for rotor air intake; The support ring (2) is further provided with a layered folding structure (21). The layered folding structure (21) is located between the rotor disk (4) and the vortex reducer (1). The layered folding structure (21) includes at least one bending segment. The bending segment is angular in a cross section perpendicular to the circumferential direction. The vertex of the angular segment corresponds to an annular edge of the bending segment, and the two sides of the angular segment correspond to two annular surfaces that meet at the same annular edge.

2. The compressor rotor according to claim 1, characterized in that, The bending segment includes: The radially bent segment (211) forms a first angle in a cross-section perpendicular to the circumference, wherein the radial projections of the two sides of the first angle at least partially coincide; and / or The axially bent segment (212) is a second triangle in a cross section perpendicular to the circumferential direction, wherein the two sides of the second triangle at least partially overlap each other in the axial projection.

3. The compressor rotor according to claim 1, characterized in that, The layered folding structure (21) is constructed such that, under a set vibration state, the common natural frequency of the support ring (2) and the vortex reducer (1), determined by their own rigidity, does not resonate with the natural frequency of the rotor disk (4).

4. The compressor rotor according to claim 3, characterized in that, The rigidity of the layered folding structure (21) is determined by the number of the bending segments, the thickness of each bending segment, and the thickness distribution characteristics of each bending segment.

5. The compressor rotor according to claim 1, characterized in that, An annular flange (41) is provided on the inner end face of the rotor disk (4) on the side away from the vortex reducer (1) along the axial direction, and the support ring (2) is attached to the radial inner side of the annular flange (41).

6. The compressor rotor according to claim 5, characterized in that, The support ring (2) has a radial mounting edge (22) at one end near the rotor disk (4), and the fastener (3) includes: Bolts (31) are inserted into coaxial axial mounting holes provided on the radial mounting edge (22) and the annular flange (41) to fasten the support ring (2) relative to the rotor disk (4).

7. The compressor rotor according to claim 5, characterized in that, The support ring (2) is provided with an axial mounting edge (23), and the axial mounting edge (23) has a plurality of radial studs distributed circumferentially on the side of the annular flange (41) away from the anti-vortex tube (1). The fastener (3) includes: Nut (32) is inserted through the radial stud and is axially engaged on the side of the annular flange (41) away from the vortex reducer (1).

8. The compressor rotor according to claim 7, characterized in that, The support ring (2) is also provided with a positioning stop (24), which is located on the side of the annular flange (41) close to the vortex reducer (1) and cooperates with the annular flange (41) in the radial and axial directions.

9. The compressor rotor according to claim 8, characterized in that, The alloy material of the support ring (2) has the same linear expansion coefficient as the alloy material of the rotor disk (4), and the positioning stop (24) and the annular flange (41) are in an interference fit in the radial direction.

10. An aircraft engine, characterized in that, Includes the compressor rotor as described in any one of claims 1 to 9.

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