Aero-engine fan rotor-stator integrated dismounting device

Abstract

The application provides an aero-engine fan rotor-stator integrated dismounting device, and relates to the technical field of aero-engine component dismounting, which comprises a stator adapter structure, a stator adapter structure and an air inlet assembly bearing seat fixed connection; a rotor adapter structure, the bottom of which is fixed with a rotor front shaft neck; an axial limiting assembly, which comprises an axial limiting sleeve and an axial fastener, the axial limiting sleeve is fixed with the stator adapter structure, the axial fastener is sleeved at the top end of the axial limiting sleeve, and is fixed with the rotor adapter structure; a guide tool, which comprises a guide structure, a puller supporting cylinder and a force applying rod, the guide structure is arranged in the inner cavity of the rotor adapter structure, the bottom of the puller supporting cylinder is fixed with the rotor adapter structure, and the force applying rod is threadedly connected with the puller supporting cylinder, so that the puller supporting cylinder is driven to move upward by rotating the force applying rod, the rotor adapter structure and the stator adapter structure are driven to move together, and the aero-engine fan rotor-stator is synchronously pulled out. The application improves the aero-engine fan dismounting efficiency.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine component disassembly technology, specifically to an integrated disassembly device for aircraft engine fan rotor and stator. Background Technology

[0002] Assembly, as a crucial link in the product manufacturing process, is the core hub of aero-engine manufacturing. Product research and development, mass production, and maintenance all converge around assembly, which is closely linked to design, parts manufacturing, testing, operation, and maintenance. Aero-engine prototyping is even more inextricably linked to assembly; the efficiency and quality of the assembly process directly affect the entire product's development cycle and performance. In recent years, the prototyping process of new aero-engines has placed increasing emphasis on maintainability and replaceability design, which poses higher challenges to assembly process design. As an indispensable part of the aero-engine's air intake, how to achieve efficient and rapid disassembly of the fan component has become a problem that must be solved in engine assembly. Furthermore, the overall maintainability and replaceability of the fan component are being explored in various engine models.

[0003] The functions of fan components include compressing air, generating thrust, assisting cooling, and providing structural support and protection. Therefore, fan components fail much more frequently than other components. To meet this requirement, a certain type of aero-engine fan component (fan rotor, fan stator assembly, and intake assembly) adopts a modular design. Throughout its lifecycle, the fan component requires rapid maintenance and replacement. Disassembly of the fan component requires complete removal of the entire fan assembly, including the fan rotor, fan stator assembly, and intake assembly. Traditional disassembly methods involve gradually removing the intake assembly, fan stator, and fan rotor, a time-consuming process. However, the assembly requirements for the fan component do not necessitate disassembling these three components; only the fan component itself needs to be removed.

[0004] Therefore, an integrated disassembly device for the rotor and stator of an aircraft engine was invented. This device is of great significance for the rapid disassembly and replacement of aircraft engine fans. Summary of the Invention

[0005] In view of this, this application provides an integrated disassembly device for the fan rotor and stator of an aircraft engine, which aims to solve the problem of integrated disassembly of the fan rotor and stator of an aircraft engine, so as to improve the disassembly efficiency of the aircraft engine fan.

[0006] This application provides the following technical solution: an integrated disassembly device for the fan rotor and stator of an aircraft engine, comprising:

[0007] A fan stator adapter structure, wherein the stator adapter structure is a disc-shaped structure with a circular hole in the middle, and the stator adapter structure is fixedly connected to the bearing seat of the air intake assembly of the fan stator.

[0008] A fan rotor adapter structure is a cylindrical structure with an internal through-hole. The rotor adapter structure passes through a circular hole in the middle of the stator adapter structure and is fixedly connected to the front journal of the fan rotor at its bottom. A limiting boss is provided on the circumferential side of the outer wall of the rotor adapter structure.

[0009] An axial limiting assembly includes an axial limiting sleeve and an axial fastener, both of which are cylindrical structures. The axial limiting sleeve is sleeved between the outer wall of the rotor transition structure and the inner wall of the stator transition structure, and is fixedly connected to the stator transition structure. The bottom of the axial limiting sleeve abuts against the limiting boss. The axial fastener is sleeved on the top of the axial limiting sleeve, and the inner wall of the axial fastener is fixedly connected to the rotor transition structure, so as to tighten and fix the axial limiting sleeve against the limiting boss.

[0010] The guiding fixture includes a cylindrical guiding structure, a puller support cylinder, and a force-applying rod. The guiding structure is disposed within the inner cavity of the rotor transfer structure, and its bottom end is fixed to the engine. The bottom of the puller support cylinder is fixedly connected to the rotor transfer structure. The force-applying rod has a threaded section, passes through the puller support cylinder, and is threadedly connected to the puller support cylinder through the threaded section. By rotating the force-applying rod, the puller support cylinder is moved upward on the force-applying rod, thereby causing the rotor transfer structure to move upward along the outer wall of the guiding structure, and thus causing the stator transfer structure to move together, so as to synchronously pull out the rotor and stator of the engine fan.

[0011] According to one embodiment of this application, the bottom of the rotor adapter structure is provided with a first external thread to be threadedly connected to the front journal of the fan rotor through the first external thread.

[0012] According to one embodiment of this application, the outer wall of the axial limiting sleeve is provided with an external thread so as to be threadedly connected to the stator adapter structure through the external thread.

[0013] According to one embodiment of this application, the inner wall of the axial fastener is provided with an internal thread, and the outer wall of the rotor adapter structure is provided with a second external thread adapted to the internal thread, so as to thread the axial fastener and the rotor adapter structure to tighten and fix the axial limiting sleeve on the limiting boss.

[0014] According to one embodiment of this application, the bottom of the puller support cylinder is provided with an internal thread, and the outer wall of the rotor adapter structure is provided with a third external thread adapted to the internal thread, so as to thread the puller support cylinder and the rotor adapter structure together.

[0015] According to one embodiment of this application, the top end of the guide structure has a groove for providing a force application support point, and the bottom end of the force application rod passes through the puller support cylinder and abuts against the groove.

[0016] According to one embodiment of this application, the outer wall of the guide structure and the inner wall of the rotor transfer structure are in clearance fit.

[0017] According to one embodiment of this application, the stator transition structure is a disc-shaped structure with a flange, and the stator transition structure is fixedly connected to the bearing seat of the fan stator intake assembly through the flange.

[0018] According to one embodiment of this application, the fan stator includes an intake assembly and fan stator guide vanes, the intake assembly and the fan stator guide vanes being fixedly connected by bolts and nuts.

[0019] According to one embodiment of this application, it further includes a force-applying extension rod, which is fixedly disposed at the top end of the force-applying rod, and the axis of the force-applying extension rod is perpendicular to the axis of the force-applying rod; a lifting eye screw is also provided at the top end of the force-applying rod.

[0020] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least:

[0021] (1) This invention provides an integrated disassembly device for the fan rotor and stator of an aero-engine. A rigid centering structure (stator transfer structure) is used to limit the position of the fan stator, and a rotor transfer structure is used to connect the fan rotor. To ensure controllable axial distance between the rotor and stator during disassembly, an axial limiting component is added. Furthermore, to ensure stability during the disassembly process, a guiding structure is designed to improve disassembly quality and reduce disassembly risks.

[0022] (2) The use of the aircraft engine fan stator disassembly device can greatly save the time of disassembling fan components and also provides a solution for the integrated and rapid replacement of fan components.

[0023] (3) The structure of this device is logically clear, with each part working together seamlessly, and the process of use is simple. Furthermore, the adapter dimensions can be modified to accommodate the integrated disassembly of the fan rotor and stator of different engines. Attached Figure Description

[0024] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a partial structural diagram of the disassembly device in an embodiment of the present invention;

[0026] Figure 2 This is a schematic diagram of the overall structure of the disassembly device in an embodiment of the present invention;

[0027] Figure 3 This is a schematic diagram of the stator transfer structure in an embodiment of the present invention;

[0028] Figure 4 This is a schematic diagram of the rotor transfer structure in an embodiment of the present invention;

[0029] Figure 5 This is a schematic diagram of the axial limiting sleeve structure in an embodiment of the present invention;

[0030] Among them, 1-stator transition structure, 2-axial limiting sleeve, 3-axial limiting nut, 4-rotor transition structure, 5-guide structure, 6-puller support cylinder, 7-force application rod, 8-lifting eye screw. Detailed Implementation

[0031] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0032] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0033] like Figures 1-5 As shown, this embodiment of the invention provides an integrated disassembly device for the fan rotor and stator of an aircraft engine, comprising:

[0034] The fan stator adapter structure 1 is a disc-shaped structure with a circular hole in the middle, and the stator adapter structure 1 is fixedly connected to the bearing seat of the air intake assembly of the fan stator.

[0035] The fan rotor adapter structure 4 is an internally through cylindrical structure. The rotor adapter structure 4 passes through the circular hole in the middle of the stator adapter structure 1, and its bottom is fixedly connected to the front journal of the fan rotor. The outer wall of the rotor adapter structure 4 is provided with a limiting boss in the circumferential direction.

[0036] An axial limiting assembly includes an axial limiting sleeve 2, both of which are cylindrical, and an axial fastener. The axial limiting sleeve 2 is sleeved between the outer wall of the rotor transition structure 4 and the inner wall of the stator transition structure 1, and is fixedly connected to the stator transition structure 1. The bottom of the axial limiting sleeve 2 abuts against the limiting boss. The axial fastener is sleeved on the top of the axial limiting sleeve 2, and the inner wall of the axial fastener is fixedly connected to the rotor transition structure 4, so as to tighten and fix the axial limiting sleeve 2 against the limiting boss.

[0037] The guiding fixture includes a cylindrical guiding structure 5, a puller support cylinder 6, and a force-applying rod 7. The guiding structure 5 is disposed in the inner cavity of the rotor transfer structure 4, and the bottom end of the guiding structure 5 is used to fix it to the engine. The bottom of the puller support cylinder 6 is fixedly connected to the rotor transfer structure 4. The force-applying rod 7 is provided with a threaded section. The force-applying rod 7 passes through the puller support cylinder 6 and is threadedly connected to the puller support cylinder 6 through the threaded section. By rotating the force-applying rod 7, the puller support cylinder 6 is driven to move upward on the force-applying rod 7, thereby driving the rotor transfer structure 4 to move upward along the outer wall of the guiding structure 5, thereby driving the stator transfer structure 1 to move together, so as to pull out the rotor and stator of the engine fan synchronously.

[0038] In this embodiment of the invention, with the aero-engine in a vertical position, a rigid stator adapter structure 1 is used to axially and radially position the fan stator, and a rotor adapter structure 4 is used to center the fan rotor. An axial limiting component adjusts the axial distance between the rotor and stator, maintaining the relative distance between the fan and stator. After these operations are completed, an upward axial force is applied to the fan rotor using a disassembly device. The disassembly device then pulls the fan rotor and stator together along a guide fixture, ultimately completing the integrated disassembly of the fan and stator.

[0039] To simplify the structure, facilitate operation, and reduce costs, in some embodiments of the invention, the rotor adapter structure 4 has a first external thread at its bottom for threaded connection with the front journal of the fan rotor. Specifically, the rotor adapter structure 4 employs a threaded connection structure, connecting to the front journal of the fan rotor via threads. Since the fan rotor and engine are interference-fitted, the interference fit is the primary point of resistance during disassembly of the fan rotor-stator. By applying an upward axial force to the fan rotor using the disassembly device, the resistance at the interference fit is overcome, and the disassembly device drives the fan rotor-stator upward, thus separating the fan rotor-stator from the engine.

[0040] In order to make the device simple in structure, easy to operate and low in cost, in some embodiments of the present invention, the outer wall of the axial limiting sleeve 2 is provided with external thread so as to be threadedly connected to the stator adapter structure 1 through the external thread.

[0041] To simplify the structure, facilitate operation, and reduce costs of the device, in some embodiments of the present invention, the inner wall of the axial fastener is provided with an internal thread, and the outer wall of the rotor adapter structure 4 is provided with a second external thread adapted to the internal thread, so as to thread the axial fastener and the rotor adapter structure 4 together, thereby securing the axial limiting sleeve 2 against the limiting boss. In specific implementations, the axial fastener is an axial limiting nut 3.

[0042] In specific implementation, the axial limiting component is designed as a double-cylinder structure. One cylindrical structure, namely the axial limiting sleeve 2, is connected to the rigid stator adapter structure 1 through external threads. The other cylindrical structure, namely the axial limiting sleeve 2, is connected to the rotor adapter structure 4 through internal threads. The two cylindrical structures are designed with flange edges to adjust the axial distance.

[0043] In order to make the device simple in structure, easy to operate and low in cost, in some embodiments of the present invention, the bottom of the puller support cylinder 6 is provided with an internal thread, and the outer wall of the rotor adapter structure 4 is provided with a third external thread adapted to the internal thread, so as to thread the puller support cylinder 6 and the rotor adapter structure 4 together.

[0044] In some embodiments of the present invention, the top end of the guide structure 5 is provided with a groove for providing a force application support point, and the bottom end of the force application rod 7 passes through the puller support cylinder 6 and abuts against the groove.

[0045] In specific implementation, the outer wall of the guide structure 5 and the inner wall of the rotor transfer structure 4 are in clearance fit. The guide structure 5 is designed as a long shaft structure, with one end connected to the engine and the other end matched with the rotor transfer structure 4. The two are in clearance fit. The purpose of this design is twofold: (1) to withstand the clamping force during disassembly; (2) to guide disassembly and ensure that the disassembly process is stable and controllable.

[0046] In some embodiments of the present invention, the stator transition structure 1 is a disc-shaped structure with a flange, and the stator transition structure 1 is fixedly connected to the fan stator intake assembly bearing seat through the flange. Specifically, the rigid transition structure connecting the fan stator is a disc-shaped structure with a flange, which is connected to the fan stator through the intake assembly bearing seat. The fan stator includes an intake assembly and fan stator guide vanes, which are fastened together as a single unit by their own mounting bolts and nuts.

[0047] In some embodiments of the present invention, a force-applying extension rod is further included, which is fixedly disposed at the top end of the force-applying rod 7, and the axis of the force-applying extension rod is perpendicular to the axis of the force-applying rod 7; a lifting eye screw 8 is also provided at the top end of the force-applying rod 7. The force-applying extension rod facilitates hand gripping and rotation of the force-applying rod 7, thus facilitating hand operation.

[0048] The specific usage process of the integrated disassembly device for aircraft engine fan rotor and stator according to an embodiment of the present invention is as follows:

[0049] 1. First, disassemble the necessary components such as the intake cone to ensure that there are no obstructions in the disassembly path of the fan rotor and stator.

[0050] 2. The intake assembly and the fan stator adapter structure are connected together using mounting bolts and nuts. The intake assembly and stator adapter structure can be considered as a single unit. The stator adapter structure is designed as a disc with a flange. First, it is installed onto the bearing housing and tightened using a self-locking nut, thus connecting the fan stator to the disassembly device. During use, it is essential to ensure a reliable connection between the fan stator and the device.

[0051] 3. Screw the rotor adapter onto the front journal of the fan rotor using external threads to secure the fan rotor to the disassembly device.

[0052] 4. Install the axial limiting sleeve and axial limiting nut sequentially onto the rigid centering device (the rotor transfer structure). During this process, ensure that the axial limiting sleeve, which is rigidly connected to the fan stator, presses against the limiting boss of the rotor transfer structure to achieve axial limiting of the fan stator. Then, use another sleeve, namely the axial limiting nut, to press the rotor transfer structure tight, thereby achieving axial limiting of the rotor. At this point, all structures of the disassembly device are connected to the fan stator, ensuring that the fan stator is axially limited and will not detach.

[0053] 5. Install the bottom end of the guide cylinder of the guide structure onto the engine, and use its threads to maintain connection and centering with the engine. Then install the force-applying structure of the guide mechanism, namely the puller support cylinder and the force-applying rod, and slowly pull out the fan rotor and stator as a whole using static thread force. A lifting eye bolt 8 is designed at the top of the force-applying mechanism so that the fan rotor and stator can be directly lifted away by a crane.

[0054] This invention discloses an integrated disassembly device for an aero-engine fan rotor-stator. It utilizes a rigid centering structure (stator adapter structure) to limit the position of the fan stator and a rotor adapter structure to connect the fan rotor. To ensure controllable axial distance between the rotor and stator during disassembly, an axial limiting component is added. Furthermore, to ensure stability during the disassembly process, a guiding structure is designed to improve disassembly quality and reduce disassembly risks.

[0055] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A device for disassembling an integrated fan rotor and stator of an aircraft engine, characterized in that, include: A fan stator adapter structure, wherein the stator adapter structure is a disc-shaped structure with a circular hole in the middle, and the stator adapter structure is fixedly connected to the bearing seat of the air intake assembly of the fan stator. A fan rotor adapter structure is a cylindrical structure with an internal through-hole. The rotor adapter structure passes through a circular hole in the middle of the stator adapter structure and is fixedly connected to the front journal of the fan rotor at its bottom. A limiting boss is provided on the circumferential side of the outer wall of the rotor adapter structure. An axial limiting assembly includes an axial limiting sleeve and an axial fastener, both of which are cylindrical structures. The axial limiting sleeve is sleeved between the outer wall of the rotor transition structure and the inner wall of the stator transition structure, and is fixedly connected to the stator transition structure. The bottom of the axial limiting sleeve abuts against the limiting boss. The axial fastener is sleeved on the top of the axial limiting sleeve, and the inner wall of the axial fastener is fixedly connected to the rotor transition structure, so as to tighten and fix the axial limiting sleeve against the limiting boss. The guiding fixture includes a cylindrical guiding structure, a puller support cylinder, and a force-applying rod. The guiding structure is disposed within the inner cavity of the rotor transfer structure, and its bottom end is fixed to the engine. The bottom of the puller support cylinder is fixedly connected to the rotor transfer structure. The force-applying rod has a threaded section, passes through the puller support cylinder, and is threadedly connected to the puller support cylinder through the threaded section. By rotating the force-applying rod, the puller support cylinder is moved upward on the force-applying rod, thereby causing the rotor transfer structure to move upward along the outer wall of the guiding structure, and thus causing the stator transfer structure to move together, so as to synchronously pull out the rotor and stator of the engine fan.

2. The integrated disassembly device for the aero-engine fan rotor and stator according to claim 1, characterized in that, The rotor adapter structure is provided with a first external thread at the bottom, so as to connect with the front journal thread of the fan rotor through the first external thread.

3. The integrated disassembly device for the aero-engine fan rotor and stator according to claim 1, characterized in that, The outer wall of the axial limiting sleeve is provided with an external thread so as to be threadedly connected to the stator adapter structure through the external thread.

4. The integrated disassembly device for the aero-engine fan rotor and stator according to claim 1, characterized in that, The inner wall of the axial fastener is provided with an internal thread, and the outer wall of the rotor adapter structure is provided with a second external thread that matches the internal thread, so as to thread the axial fastener and the rotor adapter structure to tighten and fix the axial limiting sleeve on the limiting boss.

5. The integrated disassembly device for the aero-engine fan rotor and stator according to claim 1, characterized in that, The bottom of the puller support cylinder is provided with an internal thread, and the outer wall of the rotor adapter structure is provided with a third external thread that matches the internal thread, so as to thread the puller support cylinder and the rotor adapter structure together.

6. The integrated disassembly device for the aero-engine fan rotor and stator according to claim 1, characterized in that, The top of the guide structure has a groove for providing a force application support point, and the bottom end of the force application rod passes through the puller support cylinder and abuts against the groove.

7. The integrated disassembly device for the aero-engine fan rotor and stator according to claim 1, characterized in that, The outer wall of the guide structure and the inner wall of the rotor transfer structure are fitted with a clearance.

8. The integrated disassembly device for the aero-engine fan rotor and stator according to claim 1, characterized in that, The stator transition structure is a disc-shaped structure with a flange, and the stator transition structure is fixedly connected to the bearing housing of the fan stator intake assembly through the flange.

9. The integrated disassembly device for the fan rotor and stator of an aircraft engine according to claim 1, characterized in that, The fan stator includes an intake assembly and fan stator guide vanes, which are fixedly connected by bolts and nuts.

10. The integrated disassembly device for the fan rotor and stator of an aircraft engine according to claim 1, characterized in that, It also includes a force-applying extension rod, which is fixedly installed at the top of the force-applying rod, and the axis of the force-applying extension rod is perpendicular to the axis of the force-applying rod; a lifting eye screw is also provided at the top of the force-applying rod.

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