Rotor, gas compressor and aero-engine

Abstract

The utility model provides a rotor, compressor and aero-engine, rotor includes at least two rotor discs and a plurality of rotor blades, each rotor disc is provided with a plurality of mounting grooves along its outer circumference, each rotor blade is provided with a tenon, and the tenon is clamped in the mounting groove; and the rotor discs of different stages are provided with mistake-proof mechanisms in the mounting grooves and / or the rotor blades of different stages are provided with mistake-proof mechanisms on the tenons. According to the rotor, the mistake-proof mechanisms are arranged in the mounting grooves of the rotor discs of different stages and / or on the tenons of the rotor blades of different stages, and the mistake-proof mechanisms are arranged, so that the situation that the rotor blades are easily mounted mistakenly under the condition that the structures of the rotor blades are consistent can be avoided, the mounting efficiency of the rotor blades is improved, and a gas compressor test is facilitated.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engine assembly, in particular to a rotor, a compressor and an aviation engine. Background Art

[0002] During the operation of the aircraft engine compressor, a large amount of outside air is sucked into the aircraft engine, and the multi-stage compressor rotor blades rotate at high speed to do work on the inhaled gas and increase the gas pressure.

[0003] During the compressor assembly process, due to the consistent structure of the rotor blade tenons, it is difficult to distinguish blades of different stages with the naked eye, and it is very easy to install them incorrectly, resulting in the compressor not being in the designed state during testing, which has a great impact on the compressor performance and safety.

[0004] Based on this, the utility model of the present application proposes a rotor, a compressor and an aircraft engine in order to solve the above-mentioned technical problems. Utility Model Content

[0005] The technical problem to be solved by the utility model is to overcome the defect that rotor blades are easily installed incorrectly in the prior art, and to provide a rotor, a compressor and an aero-engine.

[0006] The utility model solves the above technical problems through the following technical solutions:

[0007] The utility model provides a rotor, which is characterized by comprising:

[0008] At least two rotor disks, each of which has a plurality of mounting grooves along its outer circumference;

[0009] A plurality of rotor blades, each of which is provided with a tenon, and the tenon is clamped in the mounting groove; wherein,

[0010] The rotor disks of different stages are provided in the installation grooves and / or the rotor blades of different stages are provided on the tenons with the anti-error mechanism.

[0011] According to an embodiment of the present utility model, the error prevention mechanism is arranged on the rotor disk or the rotor blade.

[0012] According to an embodiment of the utility model, the tenon forms a fitting gap with the rotor blade in the installation groove along the chord direction of the rotor blade;

[0013] The length of the anti-error mechanism along the chord direction of the rotor blade is at least greater than half of the length of the fitting clearance along the chord direction of the rotor blade and is less than the length of the fitting clearance along the chord direction of the rotor blade.

[0014] According to an embodiment of the utility model, the anti-error mechanism is an anti-error boss, and the anti-error boss is integrally arranged with the tenon or the rotor disk.

[0015] According to an embodiment of the utility model, the anti-error boss is in the form of a rectangular parallelepiped, and is provided with rounded corners at the edge and corner areas.

[0016] According to an embodiment of the utility model, one of the adjacent rotor disks is provided with the anti-error mechanism, and the corresponding rotor blade of the other one is provided with the anti-error mechanism.

[0017] According to an embodiment of the utility model, an installation gap is formed between one end of the anti-error mechanism and the bottom of the installation groove or between one end of the anti-error mechanism and the outer end surface of the tenon.

[0018] According to an embodiment of the present utility model, the length of the installation gap along the chord direction of the rotor blade is smaller than the length of the error prevention mechanism along the chord direction of the rotor blade.

[0019] The utility model also provides a compressor, which is characterized in that it comprises the rotor as described above.

[0020] The utility model also provides an aeroengine, comprising the above-mentioned compressor.

[0021] The positive and progressive effects of the utility model are:

[0022] In the rotor of the utility model, rotor disks of different stages are provided with the anti-error mechanism in the installation grooves and / or rotor blades of different stages are provided with the tenon. The provision of the anti-error mechanism can avoid the situation where the rotor blades are easily installed incorrectly when the structures are consistent, which is beneficial to improving the installation efficiency of the rotor blades and facilitating the compressor test. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0024] Figure 1 It is a schematic diagram of the structure of the rotor of the utility model.

[0025] 1. Rotor disk; 11. Mounting slot;

[0026] 2. rotor blade; 21. tenon; 22. fitting clearance;

[0027] 3. Anti-error mechanism; 31. Installation clearance. DETAILED DESCRIPTION

[0028] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0029] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0030] Reference Figure 1 The utility model provides a rotor, which includes at least two rotor disks 1 and a plurality of rotor blades 2. Each rotor disk 1 is provided with a plurality of mounting grooves 11 along its outer circumference, and each rotor blade 2 is provided with a tenon 21, which is clamped in the mounting groove 11. Among them, the rotor disks 1 of different levels are provided with an anti-mistake mechanism 3 in the mounting groove 11 and / or the rotor blades 2 of different levels are provided with an tenon 21.

[0031] Since the tenons 21 of the rotor blades 2 have the same structural form, in order to avoid incorrect installation, the rotor disks 1 of different stages are provided with anti-error mechanisms 3 in the installation grooves 11 and / or the rotor blades 2 are provided on the tenons 21. The anti-error mechanisms 3 are used as restrictions to prevent installation errors between the rotor disks 1 and rotor blades 2 of different stages. In this way, it can be ensured that the rotor disks 1 and rotor blades 2 of different stages are in the design state during the compressor test, thereby improving the test efficiency and safety.

[0032] For example, the first-stage rotor disk 1 is provided with an anti-error mechanism 3, while the rotor blade 2 is not provided with an anti-error mechanism 3 and is installed in a matching manner. Meanwhile, the rotor disk 1 of another stage is not provided with an anti-error mechanism 3, and is installed in a matching manner with the rotor blade 2 provided with an anti-error mechanism 3.

[0033] Based on this, if both the rotor disk 1 and the rotor blade 2 are provided with the anti-error mechanism 3, the two cannot be installed in a matching manner, and if neither the rotor disk 1 nor the rotor blade 2 is provided with the anti-error mechanism 3, the two cannot be installed in a matching manner. Thus, the rotor disk 1 and the rotor blade 2 are matched with each other, and assembly errors between different stages can be avoided.

[0034] In one embodiment, the error prevention mechanism 3 is provided on the rotor disk 1 or the rotor blade 2 .

[0035] That is, the anti-error mechanism 3 is provided on the rotor disk 1 or the rotor blade 2 .

[0036] In some other embodiments, the anti-error mechanism 3 may be provided on both the rotor disk 1 and the rotor blade 2 , and the installation method of the anti-error mechanism 3 is not limited herein.

[0037] Specifically, the tenon 21 forms a fitting gap 22 with the rotor blade 2 along the chord direction of the rotor blade 2 in the installation groove 11; the length of the anti-error mechanism 3 along the chord direction of the rotor blade 2 is at least greater than half of the length of the fitting gap 22 along the chord direction of the rotor blade 2 and is less than the length of the fitting gap 22 along the chord direction of the rotor blade 2.

[0038] That is, when the rotor disk 1 and the rotor blades 2 are installed, there is only one way to install the rotor blades 2 and the rotor disk 1, thereby avoiding installation errors.

[0039] For example, when an anti-error mechanism 3 is provided on the primary rotor disk 1, the rotor blades 2 without the anti-error mechanism 3 can be installed therewith, while the rotor blades 2 with the anti-error mechanism 3 cannot be installed therewith because the length of the two anti-error mechanisms 3 is greater than the fitting clearance 22, thereby playing an anti-error role.

[0040] In one embodiment, the anti-error mechanism 3 is an anti-error boss, and the anti-error boss is integrally provided with the tenon 21 or the rotor disk 1 .

[0041] That is, the anti-misalignment boss and the tenon 21 or the rotor disk 1 are integrally formed, thereby saving processing costs.

[0042] In some other implementations, the anti-error boss, the tenon 21 and the rotor disk 1 may also be connected by bonding, welding or the like, which is not limited here.

[0043] As for the anti-error boss, the anti-error boss is in the shape of a rectangular parallelepiped, and is rounded at the corner area.

[0044] The side of the anti-error boss and the original wall surface are smoothly transitioned by chamfering. During the machining process of the anti-error boss, the anti-error boss can be made by milling, which has better processing accessibility and processability.

[0045] In some other implementations, the anti-error boss may also be in the form of a cube, a sphere, or other shapes, which are not limited here.

[0046] Specifically, one of the adjacent rotor disks 1 is provided with an anti-error mechanism 3 , and the other corresponding rotor blade 2 is provided with an anti-error mechanism 3 .

[0047] That is, the rotor disk 1 and the rotor blade 2 of the same stage are installed in one way, and the rotor disk 1 and the rotor blade 2 of another stage are installed in another way, so as to distinguish them and avoid wrong installation.

[0048] For example, if the first-stage rotor disk 1 is provided with an anti-error mechanism 3, the rotor blades 2 without the anti-error mechanism 3 will not interfere with it when matched with it, thereby satisfying the first installation method.

[0049] The rotor disc 1 of another stage is not provided with the anti-error mechanism 3, and the rotor blade 2 provided with the anti-error mechanism 3 cooperates with it. In this way, the installation method of the rotor discs 1 and rotor blades 2 of different stages is unique, thereby avoiding the occurrence of installation errors.

[0050] In one embodiment, an installation gap 31 is formed between one end of the anti-error mechanism 3 and the bottom of the installation groove 11 or between one end of the anti-error mechanism 3 and the outer end surface of the tenon 21 .

[0051] In order to avoid interference between the rotor blades 2 and the rotor disk 1 during installation, an installation gap 31 is formed between the rotor blades 2 and the rotor disk 1. The existence of the installation gap 31 not only meets the requirements of the installation of the rotor blades 2 and the rotor disk 1, but also meets the requirements of preventing error installation in case of interference between the rotor disk 1 and the rotor blades 2, both of which are provided with the anti-error mechanism 3.

[0052] For details, please refer to Figure 1 When the rotor blade 2 on the right is matched with the rotor disk 1 on the left for installation, interference will occur between the rotor blade 2 and the rotor disk 1, and the installation cannot be completed. Then, the error-proofing mechanism 3 is set so that the rotor disks 1 on the left and right sides are installed correspondingly with the corresponding rotor blades 2 without making any mistakes, thereby achieving the effect of error-proofing installation.

[0053] Correspondingly, the length of the installation gap 31 along the chord direction of the rotor blade 2 is smaller than the length of the anti-error mechanism 3 along the chord direction of the rotor blade 2 .

[0054] In summary, in the rotor of the utility model, rotor disks 1 of different stages are provided with anti-error mechanisms 3 in the installation grooves 11 and / or rotor blades 2 of different stages are provided with anti-error mechanisms 3 on the tenons 21. The setting of the anti-error mechanisms 3 can avoid the situation where the rotor blades 2 are easily installed incorrectly when the structures are consistent, which is beneficial to improving the installation efficiency of the rotor blades 2 and facilitating the compressor test.

[0055] The utility model also proposes a compressor, which includes the above-mentioned rotor, and thus has all the beneficial effects of the rotor, which will not be described in detail here.

[0056] The utility model also provides an aircraft engine, including the above-mentioned compressor, which similarly has all the beneficial effects of the rotor and will not be described in detail here.

[0057] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "install", "connect", "connect", "fixed" and the like should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can also be a mechanical connection. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0058] The present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or multiple times in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0059] Similarly, it should be noted that in order to simplify the description of the disclosure of this application and thus help understand one or more utility model embodiments, in the above description of the embodiments of this application, multiple features are sometimes combined into one embodiment, drawing or description thereof. However, this disclosure method does not mean that the features required by the object of this application are more than the features mentioned in the claims. In fact, the features of the embodiments are less than all the features of the single embodiment disclosed above.

[0060] In some embodiments, numbers describing the number of components and attributes are used. It should be understood that such numbers used in the description of the embodiments are modified by the modifiers "about", "approximately" or "substantially" in some examples. Unless otherwise specified, "about", "approximately" or "substantially" indicate that the numbers are allowed to vary by ±20%. Accordingly, in some embodiments, the numerical parameters used in the specification and claims are approximate values, which may change according to the required features of individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and adopt the general method of retaining digits. Although the numerical domains and parameters used to confirm the breadth of their range in some embodiments of the present application are approximate values, in specific embodiments, the setting of such numerical values ​​is as accurate as possible within the feasible range.

[0061] Although the utility model is disclosed as above with preferred embodiments, it is not intended to limit the utility model. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the utility model. Therefore, any modification, equivalent change and modification made to the above embodiments based on the technical essence of the utility model without departing from the content of the technical solution of the utility model shall fall within the protection scope defined by the claims of the utility model.

Claims

1. A rotor, characterized in that: include: At least two rotor disks, each of which has a plurality of mounting grooves along its outer circumference; A plurality of rotor blades, each of which is provided with a tenon, and the tenon is clamped in the mounting groove; wherein, One of the adjacent rotor disks is provided with an anti-error mechanism, and the corresponding rotor blade of the other one is provided with the anti-error mechanism.

2. The rotor according to claim 1, characterized in that The tenon forms a fitting gap with the rotor blade in the installation groove along the chord direction of the rotor blade; The length of the anti-error mechanism along the chord direction of the rotor blade is at least greater than half of the length of the fitting clearance along the chord direction of the rotor blade and is less than the length of the fitting clearance along the chord direction of the rotor blade.

3. The rotor according to claim 1, characterized in that The anti-error mechanism is an anti-error boss, and the anti-error boss is integrally arranged with the tenon or the rotor disk.

4. The rotor according to claim 3, characterized in that The anti-error boss is in the shape of a rectangular parallelepiped and is rounded at the corners.

5. The rotor according to claim 1, characterized in that An installation gap is formed between one end of the anti-error mechanism and the bottom of the installation groove or between one end of the anti-error mechanism and the outer end surface of the tenon.

6. The rotor according to claim 5, characterized in that A length of the installation gap along the chord direction of the rotor blade is smaller than a length of the anti-error mechanism along the chord direction of the rotor blade.

7. A compressor, characterized in that: Comprising a rotor as described in any one of claims 1-6.

8. An aircraft engine, characterized in that: Comprising the compressor as claimed in claim 7.

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