Integrated dismounting device for rotor and stator of aero-engine fan

Abstract

The invention provides an aero-engine fan rotor and stator integrated dismounting device, and relates to the technical field of aero-engine component dismounting, and the aero-engine fan rotor and stator integrated dismounting device comprises a stator switching structure fixedly connected with an air inlet assembly bearing seat; the bottom of the rotor switching structure is fixed with the rotor front journal; the axial limiting assembly comprises an axial limiting sleeve and an axial fastening piece, the axial limiting sleeve is fixed to the stator switching structure, and the axial fastening piece is arranged at the top end of the axial limiting sleeve in a sleeving mode and fixed to the rotor switching structure; the guiding tool comprises a guiding structure, a puller supporting cylinder and a force application rod, the guiding structure is arranged in an inner cavity of the rotor switching structure, the bottom of the puller supporting cylinder is fixed to the rotor switching structure, and the force application rod is in threaded connection with the puller supporting cylinder so that the puller supporting cylinder can be driven to move upwards by rotating the force application rod; the rotor switching structure and the stator switching structure are driven to move together, and the rotor and the stator of the engine fan are pulled out synchronously. The disassembly efficiency of the aero-engine fan is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine component disassembly, and particularly to an integrated disassembly device for the fan rotor and stator of an aero-engine. Background Art

[0002] As one of the key links in the product manufacturing process, assembly is the core hub of aero-engine manufacturing. The research and development, mass production, and maintenance of products all converge on assembly, and assembly is closely related to operations such as design, part manufacturing, testing, and operation and maintenance. The trial production of aero-engines is even more closely related to assembly. The efficiency and quality of the assembly process directly affect the R & D cycle and performance of the entire product. In recent years, more and more attention has been paid to maintainability design and replaceability design in the trial production process of new aero-engines, which poses higher challenges to the assembly process design. As an indispensable part of the air intake of an aero-engine, how to achieve efficient and rapid disassembly of the fan component has also become a problem that must be solved in engine assembly. In addition, the overall maintainability and replaceability of the fan component have also begun to be explored on various types of engines.

[0003] The functions of the fan component include compressing air, generating thrust, assisting in cooling, providing structural support and protection. Therefore, the frequency of damage to the fan component is much higher than that of other components. Under this demand, a certain type of aero-engine fan component (fan rotor, fan stator assembly, air intake assembly) adopts a unitized design. During its life cycle, rapid repair and rapid replacement requirements are put forward for the fan component. When the fan component is disassembled, the entire fan component needs to be removed, that is, the fan rotor, fan stator assembly, and air intake assembly are removed as a whole. The traditional disassembly method is to gradually disassemble the air intake assembly, fan stator, and fan rotor. This process will take a lot of time. However, for the assembly requirements of the fan component, it is not necessary to disassemble the air intake assembly, fan stator, and fan rotor into three parts, and only the fan component needs to be removed.

[0004] Therefore, inventing an integrated disassembly device for the fan rotor and stator of an aero-engine is of great significance for the rapid disassembly and replacement of the aero-engine fan. Summary of the Invention

[0005] In view of this, the embodiments of the present application provide an integrated disassembly device for the fan rotor and stator of an aero-engine, aiming to solve the problem of integrated disassembly of the fan rotor and stator of an aero-engine, so as to achieve the purpose of improving the disassembly efficiency of the aero-engine fan.

[0006] The embodiments of the present application provide the following technical solutions: An integrated disassembly device for the fan rotor and stator of an aero-engine, comprising:

[0007] Fan stator adapter structure, 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 intake assembly of the fan stator;

[0008] Fan rotor adapter structure, the rotor adapter structure is a tubular structure with a through hole inside. The rotor adapter structure passes through the circular hole in the middle of the stator adapter structure, and the bottom is fixedly connected to the front journal of the fan rotor; a limiting boss is circumferentially arranged on the outer wall of the rotor adapter structure;

[0009] Axial limiting component, the axial limiting component includes an axial limiting sleeve and an axial fastener, both of which are tubular structures. The axial limiting sleeve is sleeved between the outer wall of the rotor adapter structure and the inner wall of the stator adapter structure, and is fixedly connected to the stator adapter 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 adapter structure to tightly fix the axial limiting sleeve against the limiting boss;

[0010] Guiding tooling, the guiding tooling includes a tubular guiding structure, an extractor support cylinder and a force application rod. The guiding structure is arranged in the inner cavity of the rotor adapter structure, and the bottom end of the guiding structure is used to be fixed on the engine. The bottom of the extractor support cylinder is fixedly connected to the rotor adapter structure. A threaded section is arranged on the force application rod. The force application rod passes through the extractor support cylinder and is threadedly connected to the extractor support cylinder through the threaded section. By rotating the force application rod, the extractor support cylinder is driven to move upward on the force application rod, thereby driving the rotor adapter structure to move upward along the outer wall of the guiding structure, thereby driving the stator adapter structure to move together, so as to synchronously extract the rotor and stator of the engine fan.

[0011] According to an embodiment of the present application, a first section of external thread is arranged at the bottom of the rotor adapter structure to be threadedly connected to the front journal of the fan rotor through the first section of external thread.

[0012] According to an embodiment of the present application, an external thread is arranged on the outer wall of the axial limiting sleeve to be threadedly connected to the stator adapter structure through the external thread.

[0013] According to an embodiment of the present application, an internal thread is arranged on the inner wall of the axial fastener, and a second section of external thread adapted to the internal thread is arranged on the outer wall of the rotor adapter structure to threadedly connect the axial fastener to the rotor adapter structure to tightly fix the axial limiting sleeve against the limiting boss.

[0014] According to an embodiment of the present application, an internal thread is provided at the bottom of the extractor support cylinder, and an external thread of a third section adapted to the internal thread is provided on the outer wall of the rotor adapter structure to threadedly connect the extractor support cylinder and the rotor adapter structure.

[0015] According to an embodiment of the present application, a groove for providing a force application support point is opened at the top end of the guiding structure, and the bottom end of the force application rod passes through the extractor support cylinder and abuts against the groove.

[0016] According to an embodiment of the present application, a clearance fit is provided between the outer wall of the guiding structure and the inner wall of the rotor adapter structure.

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

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

[0019] According to an embodiment of the present application, a force application extension rod is further included. The force application extension rod is fixedly provided at the top end of the force application rod, and the axis of the force application extension rod is perpendicular to the axis of the force application rod; a lifting eye screw is further provided at the top end of the force application rod.

[0020] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of the present specification at least include:

[0021] (1) The embodiments of the present invention provide a device for integrally disassembling the fan rotor and stator of an aeroengine. The fan stator is limited by a rigid centering structure (stator adapter structure), and the fan rotor is connected by a rotor adapter structure. In order to ensure that the axial distance between the rotor and stator is controllable when disassembling the fan rotor and stator, an axial limiting component is added. In addition, in order to ensure the stability of the process of disassembling the fan rotor and stator, a guiding structure is designed to improve the disassembly quality and reduce the disassembly risk.

[0022] (2) By using the device for disassembling the fan rotor and stator of an aeroengine, the time for disassembling the fan components can be greatly saved, and it also provides an idea for the rapid replacement of the fan components integrally.

[0023] (3) The structure of the present device is logically clear, and the various parts cooperate with each other, and the use process is simple. And it can meet the integral disassembly of the fan rotor and stator of different engines by modifying the adapter dimensions. Description of the Drawings

[0024] To more clearly illustrate the technical solutions of the embodiments of the present application, the accompanying drawings required for use in the embodiments will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other accompanying drawings can be obtained based on these drawings.

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

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

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

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

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

[0030] Among them, 1 - stator adapter structure, 2 - axial limiting sleeve, 3 - axial limiting nut, 4 - rotor adapter structure, 5 - guiding structure, 6 - extractor support cylinder, 7 - force application rod, 8 - lifting ring screw. Specific embodiments

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

[0032] The following illustrates the embodiments of the present application through specific examples. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of them. The present application can also be implemented or applied through other different specific embodiments. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts belong to the scope of protection of the present application.

[0033] As Figures 1 - 5 shown, the embodiment of the present invention provides an integrated disassembly device for the fan stator and rotor of an aeroengine, including:

[0034] Fan stator adapter structure. The 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 intake assembly of the fan stator;

[0035] Fan rotor adapter structure. The rotor adapter structure 4 is a tubular structure with a through hole inside. The rotor adapter structure 4 passes through the circular hole in the middle of the stator adapter structure 1, and the bottom is fixedly connected to the front journal of the fan rotor. A limiting boss is circumferentially arranged on the outer wall of the rotor adapter structure 4;

[0036] Axial limiting component. The axial limiting component includes an axial limiting sleeve 2 and an axial fastener, both of which are tubular structures. The axial limiting sleeve 2 is sleeved between the outer wall of the rotor adapter structure 4 and the inner wall of the stator adapter structure 1, and is fixedly connected to the stator adapter 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 adapter structure 4 to tightly fix the axial limiting sleeve 2 against the limiting boss;

[0037] Guiding tooling. The guiding tooling includes a tubular guiding structure 5, a puller support cylinder 6, and a force application rod 7. The guiding structure 5 is arranged in the inner cavity of the rotor adapter structure 4, and the bottom end of the guiding structure 5 is used to be fixed on the engine. The bottom of the puller support cylinder 6 is fixedly connected to the rotor adapter structure 4. A threaded section is arranged on the force application rod 7. The force application 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 application rod 7, the puller support cylinder 6 is driven to move upward on the force application rod 7, thereby driving the rotor adapter structure 4 to move upward along the outer wall of the guiding structure 5, and then driving the stator adapter structure 1 to move together to synchronously pull out the rotor and stator of the engine fan.

[0038] In the embodiment of the present invention, when the aeroengine is in a vertical state, the rigid stator adapter structure 1 is used to axially and radially position the fan stator, the rotor adapter structure 4 is used to center the fan rotor, and the axial distance between the rotor and stator is adjusted through the axial limiting component, and the relative distance between the fan rotor and stator is maintained. After the above operations are completed, an upward axial force is applied to the fan rotor through the disassembly device, and then the disassembly device drives the fan rotor and stator to be pulled out along the guiding tooling together, and finally the integral disassembly of the fan rotor and stator is completed.

[0039] In order to make the structure of the device simple, easy to operate, and low in cost, in some embodiments of the present invention, the bottom of the rotor adapter structure 4 is provided with a first external thread to be threadedly connected to the front journal of the fan rotor through the first external thread. Specifically in implementation, the rotor adapter structure 4 adopts a threaded connection structure, which is connected to the front journal of the fan rotor through threads. Since the fan rotor and the engine are in interference fit, when disassembling the fan rotor stator, the interference fit part of the fan rotor is the main position where the disassembly resistance is generated. By applying an upward axial force to the fan rotor through the disassembly device, the resistance at the interference fit part is overcome, and the disassembly device drives the fan rotor stator to move upward to separate the fan rotor stator from the engine.

[0040] In order to make the structure of the device simple, 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 an external thread to be threadedly connected to the stator adapter structure 1 through the external thread.

[0041] In order to make the structure of the device simple, easy to operate, and low in cost, 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 to threadedly connect the axial fastener to the rotor adapter structure 4 to tightly fix the axial limiting sleeve 2 against the limiting boss. Specifically in implementation, the axial fastener adopts an axial limiting nut 3.

[0042] Specifically in implementation, the axial limiting component is designed as a double-barrel structure. One barrel structure, that is, the axial limiting sleeve 2, is connected to the rigid stator adapter structure 1 through an external thread, and the other barrel structure, that is, the axial limiting sleeve 2, is connected to the rotor adapter structure 4 through an internal thread. The two barrel structures are designed with flange edges to adjust the axial distance.

[0043] In order to make the structure of the device simple, easy to operate, and low in cost, in some embodiments of the present invention, the bottom of the extractor 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 to threadedly connect the extractor support cylinder 6 to the rotor adapter structure 4.

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

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

[0046] In some embodiments of the present invention, the stator transfer structure 1 is a disc-shaped structure with a flange, and the stator transfer structure 1 is fixedly connected to the fan stator air intake assembly bearing seat through the flange. In specific implementation, the rigid transfer structure connected to the fan stator is a disc-shaped structure with a flange, which is connected to the fan stator through the air intake assembly bearing seat. The fan stator includes an air intake assembly and a fan stator guide blade, which are fastened by their own mounting side bolts and nuts and connected as a whole.

[0047] In some embodiments of the present invention, a force extension rod is further included, which is fixedly arranged at the top of the force application rod 7, and the axis of the force extension rod is perpendicular to the axis of the force application rod 7; a lifting eye screw 8 is also arranged at the top of the force application rod 7. The force extension rod is convenient for the hand to hold the extension rod tightly so as to rotate the force application rod 7, which is convenient for hand operation.

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

[0049] 1. First disassemble the necessary components such as the air intake cone so that there are no interferences on the fan rotor and stator disassembly path.

[0050] 2. The air intake assembly and the fan stator transfer structure are connected together by mounting side bolts and nuts. The air intake assembly and the stator transfer structure can be regarded as one piece. The stator transfer structure is designed as a disc with a flange edge. First, install it on the bearing seat and tighten it with a self-locking nut to connect the fan stator to the disassembly device. During use, the fan stator connection must be reliable.

[0051] 3. Screw the rotor adapter structure onto the front shaft neck of the fan rotor through the external thread to achieve the connection and tightening of the fan rotor and the disassembly device.

[0052] 4. Install the axial limit sleeve and the axial limit nut on the rigid centering device (the rotor adapter structure) in sequence. During this process, it is necessary to ensure that the axial limit sleeve body rigidly connected to the fan stator is pressed against the limit boss of the rotor adapter structure to achieve the axial limit of the fan rotor. Then use another cylinder, that is, the axial limit nut, to press the rotor adapter structure to achieve the axial limit of the rotor. At this point, the various structures of the disassembly device are connected to the fan rotor and stator to ensure the axial limit of the fan rotor and stator and prevent it from detaching.

[0053] 5. Install the bottom end of the guide cylinder of the guiding structure onto the engine, and use the threads thereon to keep the connection centered with the engine. Then install the force-applying structure of the guiding mechanism, namely the extractor support cylinder and the force-applying rod, and slowly pull out the fan rotor-stator assembly integrally by using the static thread force. A lifting eye screw 8 is designed at the top of the force-applying mechanism, and the fan rotor-stator can be directly lifted away by using a crane.

[0054] An integrated disassembly device for an aero-engine fan rotor-stator according to an embodiment of the present invention uses a rigid centering structure (stator adapter structure) to limit the fan stator and uses a rotor adapter structure to connect the fan rotor. To ensure that the axial distance between the rotor and the stator is controllable when disassembling the fan rotor-stator, an axial limiting component is added. In addition, to ensure the stability of the process of disassembling the fan rotor-stator, a guiding structure is designed to improve the disassembly quality and reduce the disassembly risk.

[0055] As described above, only the specific embodiments of the present application are provided, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the technical field of the present application within the technical scope disclosed by the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An integrated disassembly device for a 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 a bearing seat of an air intake assembly of the fan stator; The fan rotor transfer structure is a cylindrical structure with a through hole inside. The rotor transfer structure passes through the circular hole in the middle of the stator transfer structure, and the bottom is fixedly connected to the front journal of the fan rotor. A limiting boss is circumferentially arranged on the outer wall of the rotor transfer structure. An axial limit assembly, wherein the axial limit assembly comprises an axial limit sleeve and an axial fastener, both of which are cylindrical structures; the axial limit sleeve is sleeved between the outer wall of the rotor adapter structure and the inner wall of the stator adapter structure, and is fixedly connected to the stator adapter structure; the bottom of the axial limit sleeve abuts against the limit boss; the axial fastener is sleeved on the top of the axial limit sleeve, and the inner wall of the axial fastener is fixedly connected to the rotor adapter structure, so as to tightly and fix the axial limit sleeve on the limit boss; The guiding tool comprises a cylindrical guiding structure, a puller supporting cylinder and a force applying rod, wherein the guiding structure is arranged in the inner cavity of the rotor adapter structure, and the bottom end of the guiding structure is used to be fixed on the engine, the bottom of the puller supporting cylinder is fixedly connected to the rotor adapter structure, and a threaded section is arranged on the force applying rod, the force applying rod passes through the puller supporting cylinder, and is threadedly connected to the puller supporting cylinder through the threaded section, so that by rotating the force applying rod, the puller supporting cylinder is driven to move upward on the force applying rod, thereby driving the rotor adapter structure to move upward along the outer wall of the guiding structure, thereby driving the stator adapter structure to move together, so as to synchronously pull out the rotor and stator of the engine fan.

2. The aircraft engine fan rotor and stator integrated disassembly device according to claim 1, characterized in that: A first section of external threads is provided at the bottom of the rotor adapter structure so as to be threadedly connected to the front journal of the fan rotor through the first section of external threads.

3. The aircraft engine fan rotor and stator integrated disassembly device 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 with the stator adapter structure through the external thread.

4. The aircraft engine fan rotor and stator integrated disassembly device 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 section of external thread adapted to the internal thread, so as to threadably connect the axial fastener with the rotor adapter structure, so as to tighten and fix the axial limiting sleeve on the limiting boss.

5. The integrated disassembly device for the rotor and stator of an aircraft engine fan 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 section of external thread adapted to the internal thread, so as to threadably connect the puller support cylinder with the rotor adapter structure.

6. The aircraft engine fan rotor and stator integrated disassembly device according to claim 1, characterized in that: A groove for providing a force application support point is formed at the top of the guide structure, and the bottom end of the force application rod passes through the puller support tube and abuts against the groove.

7. The aircraft engine fan rotor and stator integrated disassembly device according to claim 1, characterized in that: There is a clearance fit between the outer wall of the guide structure and the inner wall of the rotor adapter structure.

8. The integrated disassembly device for the rotor and stator of an aircraft engine fan according to claim 1, characterized in that: The stator transfer structure is a disc-shaped structure with a flange edge, and the stator transfer structure is fixedly connected to the bearing seat of the fan stator air inlet assembly through the flange edge.

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

10. The aircraft engine fan rotor and stator integrated disassembly device according to claim 1, characterized in that: It also includes a force extension rod, which is fixedly arranged on the top end of the force rod, and the axis of the force extension rod is perpendicular to the axis of the force rod; and a lifting eye screw is also arranged on the top end of the force rod.

Images