Auxiliary device for connecting and lossless assembling of rotor disc of gas compressor

Abstract

The utility model provides a compressor rotor disc connection lossless assembly auxiliary device, which comprises a plurality of disc bodies and an air bag, the adjacent disc bodies are circumferentially connected through fixing pieces, the air bag is placed in a disc cavity between two disc bodies corresponding to the fixing pieces, an inflation inlet is arranged on the air bag, and the inflation inlet is communicated with the air bag. And the whole disc cavity is expanded by the air bag. The soft air bag with the same shape as the disc cavity is ingeniously designed, enough pressure is supplied to the head of the bolt through inflation of the soft air bag, and enough anti-rotation friction force is generated. The assembling tool is rapidly evacuated through deflation of the soft air bag, structural damage to all structures in the disc cavity in the whole process is avoided, and the integrity of the rotor disc body is protected.

Description

Technical Field

[0001] The utility model relates to the field of aviation engines, in particular to an auxiliary device for connecting and non-destructive assembly of compressor rotor discs. Background Art

[0002] Figure 1 A schematic cross-sectional view of an aircraft engine high-pressure compressor unit. Figure 2 for Figure 1 Enlarged view of part A. Figure 3 for Figure 2 Schematic diagram of the local structure. Figure 4 for Figure 3 Schematic diagram of the observation along the R direction.

[0003] like Figure 1 As shown in the figure, the high-pressure compressor rotor disk of the aircraft engine is connected, and direction A is the axial direction of the aircraft engine. The high-pressure compressor rotor unit 1B is an important part of the aircraft engine. It is roughly composed of integral blades, rotor disks, rotor blades and other components. The rotors are connected between the disks by short bolts or welding. Figure 3 Taking the structure in as an example, the rotor disk 10 is centered in the circumferential direction by a stop structure and is connected axially by short bolts 11 and nuts 12, thereby achieving circumferential positioning.

[0004] like Figure 4 The figure shows the contact between the bolt and nut of the high-pressure compressor of an aircraft engine and the disc body during assembly. When the nut is tightened after the rotor disc is pressed, the rotation of the bolt cannot be controlled by inserting the bolt fixing device due to the small space inside the rotor disc body. Therefore, during the assembly process, the traditional method is to fix the bolt by contacting the bolt head with the disc body to prevent the bolt from rotating circumferentially, thereby completing the nut tightening work. Figure 4 It is shown in the figure that during the tightening process, the bolt head will form a linear contact with the disc body, which is very easy to produce indentations on the disc body, causing damage to the disc structure and thus affecting the structural strength.

[0005] The high-pressure compressor rotor is an important part of the aircraft engine. The rotor drum assembly consists of a multi-stage integral blade disk and a multi-stage drum. The drums are fixedly connected by multiple sets of short bolts, nuts and bolt collars (such as Figure 1 shown).

[0006] During assembly, the rotor disk is vertical to the ground, and the disk body is accumulated step by step from the first level, and the connection between the disk and the drum is fixed by a stopper. After the pressure plate is in place, the bolts and self-locking nuts are installed through the center hole of the disk through tools or by inserting hands into the disk cavity. In actual operation, it is necessary to pass through five to six levels of disks to achieve the installation of bolts and nuts. Since it is not visually accessible and the disk cavity space is extremely small, it is difficult for human hands and existing tools to directly reach the bolt head to fix the bolt. As a result, during the tightening of the self-locking nut, the bolt can only be fixed by clamping the disk body with the bolt head, thereby achieving the nut tightening work. The number of bolts required for the entire rotor assembly is large, and this process is time-consuming and labor-intensive. In addition, the compression between the bolts and the disk body can easily cause damage to the disk structure.

[0007] Most of the existing invention patents realize the functions of nut tightening and bolt locking by changing the rotor disc structure (such as using long bolts) or by manufacturing and using dozens of complex top tools. This makes the assembly process cumbersome and time-consuming, and will change the engine body structure, which is a loss of the big picture.

[0008] In view of this, the inventor of the present application has designed an auxiliary device for lossless assembly of compressor rotor disk connections in order to overcome the above-mentioned technical problems. Utility Model Content

[0009] The technical problem to be solved by the utility model is to overcome the defect in the prior art that during the tightening process of the bolts and nuts of the high-pressure compressor of an aircraft engine, the bolt head and the disk body are in linear contact with each other, which easily produces indentations on the disk body and causes damage to the disk body structure, and to provide an auxiliary device for the lossless assembly of the compressor rotor disk connection.

[0010] The utility model solves the above technical problems through the following technical solutions:

[0011] An auxiliary device for non-destructive assembly of compressor rotor disk connections is characterized in that the auxiliary device includes multiple disk bodies and air bags, adjacent disk bodies are circumferentially connected by fixings, the air bags are placed in a disk cavity between two disk bodies corresponding to where the fixings are located, and an inflation port is provided on the air bag so that the air bag can inflate the entire disk cavity.

[0012] According to an embodiment of the present invention, the disk body is a rotor disk.

[0013] According to an embodiment of the present invention, the rotor disk is vertical.

[0014] According to an embodiment of the utility model, a connection hole is provided at the connection point of two adjacent disk bodies, and the fixing member is inserted into the connection hole to fix the position of the disk body along the circumferential direction.

[0015] According to an embodiment of the present invention, the fixing member is a bolt.

[0016] According to an embodiment of the present utility model, the airbag is integrally formed by 3D printing.

[0017] According to an embodiment of the utility model, the airbag is made by using a wax congealing process.

[0018] According to an embodiment of the utility model, the shape of the airbag matches the shape of the disc cavity.

[0019] According to an embodiment of the present invention, the number of the disks is greater than or equal to two.

[0020] The positive and progressive effects of the utility model are:

[0021] The auxiliary device for connecting and assembling compressor rotor discs without loss of assembly has the following advantages:

[0022] 1. The soft airbag is cleverly designed with the same shape as the disc cavity. The airbag is inflated to give enough pressure to the bolt head, generating enough anti-rotation friction. The assembly tool can be quickly evacuated by deflation of the soft airbag, and the whole process will not cause structural damage to all structures in the disc cavity, thus protecting the integrity of the rotor disc.

[0023] Second, the production of soft airbags is quick, simple and low-cost. The existing production process is relatively mature and can also be applied to structures smaller than the disc cavity. It has strong applicability and high reuse rate.

[0024] 3. The auxiliary device does not require any adjustment to the main structure of the compressor, and there is no process of re-evaluating and iterating the structure and strength, thereby ensuring the safety and reliability of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] 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 the same reference numerals always represent the same features, wherein:

[0026] Figure 1 A schematic cross-sectional view of an aircraft engine high-pressure compressor unit.

[0027] Figure 2 for Figure 1 Enlarged view of part A.

[0028] Figure 3 for Figure 2 Schematic diagram of the local structure.

[0029] Figure 4 for Figure 3 Schematic diagram of the observation along the R direction.

[0030] Figure 5 The utility model is a schematic diagram of the structure of the auxiliary device for connecting the compressor rotor disk without loss of assembly.

[0031] Figure 6 The utility model is a schematic diagram of the working state of the auxiliary device for connecting the compressor rotor disk without loss of assembly.

[0032] Figure 7 The utility model is a flowchart for manufacturing an auxiliary device for connecting and non-destructive assembly of compressor rotor disks. DETAILED DESCRIPTION

[0033] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below with reference to the accompanying drawings.

[0034] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings.Preferred embodiments of the present invention will now be described in detail, examples of which are shown in the accompanying drawings.Where possible, the same reference numerals will be used throughout the drawings to represent the same or similar parts.

[0035] In addition, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the specification of the present invention may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this article.

[0036] Furthermore, it is required that the present invention be understood not only by the actual terms used but also by the meanings contained in each term.

[0037] Figure 5 The utility model is a schematic diagram of the structure of the auxiliary device for connecting the compressor rotor disk without loss of assembly. Figure 6 The utility model is a schematic diagram of the working state of the auxiliary device for connecting the compressor rotor disk without loss of assembly.

[0038] like Figure 5 and Figure 6 As shown, the utility model discloses an auxiliary device for connecting and assembling compressor rotor disks without loss, which includes a plurality of disk bodies 30 and airbags 40. Adjacent disk bodies 30 are connected circumferentially by fixing members 50, and the airbags are placed in a disk cavity 31 between two disk bodies 30 where the corresponding fixing members 50 are located. An inflation port is provided on the airbag 40, so that the airbag 40 inflates the entire disk cavity 31.

[0039] Preferably, in this embodiment, the disk body 30 is configured as a rotor disk. The rotor disk is vertical.

[0040] A connection hole is provided at the connection of two adjacent disc bodies 30, and a fixing member 50 is inserted into the connection hole to fix the position of the disc body 30 along the circumferential direction. The fixing member 50 is preferably a bolt.

[0041] In this embodiment, the airbag 40 is preferably formed in one piece by 3D printing, or is made by a wax solidification process. The shape of the airbag 40 matches the shape of the disc cavity 31 .

[0042] In addition, in the present application, the airbag 40 is preferably a soft airbag that can realize the functions of inflation and deflation.

[0043] Two different airbag production schemes can be used in this application:

[0044] The first method is relatively expensive. It uses engineering software to obtain the precise shape and size of the space contour within the disc cavity, and then produces the airbag through 3D printing integrated molding. The wall thickness of the rubber airbag can be completed through the shell setting of 3D printing, which is highly accurate and reliable.

[0045] The second method is low-cost and uses the traditional wax coagulation process, that is, the entire disc cavity is filled with wax in a low temperature environment, and the wax block with the shape of the disc cavity is taken out after the wax coagulates. Then, the surface of the wax block is wrapped and bonded with a material with a certain toughness and elasticity, and the airbag connection needs to be bonded with strong glue to strictly ensure its airtightness. Finally, an air port needs to be left to facilitate the heating of the airbag to remove the wax liquid, and at the same time realize the inflation and deflation functions. The production plan of the soft airbag can be flexibly selected according to the process conditions on the assembly site.

[0046] Both of the above methods are feasible to a certain extent and the processes are relatively mature.

[0047] For the first time, a soft airbag is used as a top tool for bolt and nut assembly, which is applicable to bolt and nut assembly in similar closed and narrow spaces. In the prior art, most of them are to design new self-locking nuts or adjust the compressor rotor disk structure, design bolts and nuts that run through the entire compressor rotor, etc., which face the re-iterative evaluation of structure, strength and materials, which is time-consuming and costly. However, the utility model does not require any adjustment to the main structure of the compressor, the method is simple and easy, which greatly saves time and cost from design to implementation, and effectively ensures the safety and reliability of aircraft engines.

[0048] In this embodiment, the number of the disks 30 is preferably greater than or equal to two.

[0049] According to the above structural description, the auxiliary device for connecting the compressor rotor disk without loss of assembly of the utility model uses the static friction formula f = μ × F n , the soft airbag top is filled with gas and expands in the disc cavity space, giving the bolt head enough pressure F nIt contacts the pressure surface of the disc body, increases the resistance to bolt rotation, ensures that the bolt can be fixed during the tightening process of the nut, blocks the risk of linear contact between the bolt and the disc body, and can effectively avoid damage to the disc body structure.

[0050] The soft airbag is easy to manufacture, has low cost, and will not cause any structural damage to all structures in the disc cavity, nor will it cause any damage to the pressure surface of the bolt head, and can effectively protect the integrity of the disc cavity space structure and materials.

[0051] The process of the soft airbag extending into the cavity to inflate and evacuate the cavity is quick and easy to operate, and the top tool can be put in place and removed within five seconds. The process of the airbag inflation and expansion can adapt to the structure. Compared with other methods of supporting the bolts with hard top tools, it reduces the time for adjusting the position and strength of the fixture, greatly improves the assembly efficiency, and reduces the labor intensity of the operator.

[0052] Figure 7 The utility model is a flowchart for manufacturing an auxiliary device for connecting and non-destructive assembly of compressor rotor disks.

[0053] like Figure 7 As shown, the auxiliary device for connecting the compressor rotor disc without loss of assembly of the utility model is used to realize the bolt fixing method as follows:

[0054] First, a soft airbag (i.e., airbag 40) is made to fit the disc cavity structure and can realize the functions of inflation and deflation (e.g., Figure 5 shown).

[0055] Next, the rotor disk is placed vertically in the direction Figure 6 As shown, after the plate is pressed, all the rotor bolts (i.e., the fixing members 50) of this stage are passed through the plate body 30 and placed into the bolt holes corresponding to the plate body 30.

[0056] Then, if Figure 6 As shown, first put the uninflated soft airbag (i.e., airbag 40) into the disc cavity 31 where the bolt head is located, and after roughly spreading it out, use the inflating device to align the inflating port to inflate until the soft airbag expands and fills the entire disc cavity, and keep the soft airbag in a state of being inflated. At this time, the bolt has been applied with sufficient static pressure F n .

[0057] Then, the nuts 51 are assembled and tightened one by one. During the tightening process, the bolt head (i.e., the fixing member 50) exerts sufficient static pressure F n Therefore, sufficient static friction is generated during the assembly process, the bolt (ie, the fixing member 50) is circumferentially fixed, and the nut 51 is assembled smoothly.

[0058] Then, the soft airbag is removed and deflated through the inflation port 41 until there is no gas in the soft airbag, and the soft airbag is taken out after being in a soft couch state, and the assembly process ends.

[0059] Combination Figure 7 , the entire rotor bolt assembly process is explained: First, a soft airbag suitable for the disc cavity structure is made by 3D integrated molding or traditional wax solidification to complete the soft airbag. Due to the strong adaptability of the soft airbag structure, it can be applied to disc cavity structures of various sizes. Then, after the rotor disc is vertically pressed into place, all the bolts of this level are placed. Then, the soft airbag is inflated to fill the disc cavity and press the bolts. Tighten the nut and deflate the soft airbag. Take out the soft airbag and continue the subsequent assembly work.

[0060] The utility model is suitable for the auxiliary device of compressor rotor disk connection non-destructive assembly in the field of aircraft engines and gas turbines, and is also suitable for structures with narrow assembly space and difficult bolt assembly. It can realize the rapid installation of bolts and nuts in a narrow space, will not cause irreversible structural damage to the disk body, and will not affect the engine rotor body structure, thus ensuring the safety and reliability of the aircraft engine.

[0061] The auxiliary device for connecting the compressor rotor disk with non-destructive assembly realizes the circumferential fixation of the bolts during the assembly of the rotor disk body, and the bolt heads do not contact the disk body, so that no irreversible structural damage will be caused to the disk body. It can realize non-destructive assembly, improve assembly efficiency, and protect the engine body structure.

[0062] For those skilled in the art, the above invention disclosure is only used as an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary implementation of the present application.

[0063] At the same time, 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 more 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.

[0064] Similarly, it should be noted that in order to simplify the description of the disclosure of this application and thus facilitate the understanding of one or more embodiments of the invention, in the foregoing description of the embodiments of this application, multiple features are sometimes grouped into one embodiment, drawing, or description thereof. However, this disclosure method does not mean that the subject matter of this application requires more features than those mentioned in the claims. In fact, the features of an embodiment are less than all the features of a single embodiment disclosed above.

[0065] Although the specific embodiments of the present invention are described above, those skilled in the art should understand that these are only examples, and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principle and essence of the present invention, but these changes and modifications fall within the protection scope of the present invention.

Claims

1. An auxiliary device for non-destructive assembly of compressor rotor disks, characterized in that: The auxiliary device includes a plurality of discs and airbags. Adjacent discs are circumferentially connected by fixings. The airbag is placed in a disc cavity between two discs corresponding to the fixings. An inflation port is provided on the airbag so that the airbag inflates the entire disc cavity.

2. The auxiliary device for non-destructive assembly of compressor rotor disks according to claim 1, characterized in that: The disk body is a rotor disk.

3. The auxiliary device for non-destructive assembly of compressor rotor disks according to claim 2, characterized in that: The rotor disk is vertical.

4. The auxiliary device for non-destructive assembly of compressor rotor disks according to claim 3, characterized in that: A connection hole is provided at the connection point of two adjacent disk bodies, and the fixing member is inserted into the connection hole to fix the position of the disk body along the circumferential direction.

5. The auxiliary device for non-destructive assembly of compressor rotor disks according to claim 1, characterized in that: The fixing member is a bolt.

6. The auxiliary device for non-destructive assembly of compressor rotor disks according to claim 1, characterized in that: The airbag is integrally formed by 3D printing.

7. The auxiliary device for non-destructive assembly of compressor rotor disks according to claim 1, characterized in that: The airbag is made by adopting the wax congealing process.

8. The auxiliary device for non-destructive assembly of compressor rotor disks according to claim 1, characterized in that: The shape of the airbag matches the shape of the disc cavity.

9. The auxiliary device for non-destructive assembly of compressor rotor disks according to claim 1, characterized in that: The number of the disks is greater than or equal to two.

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