Detachable gear shaft structure of aero-engine and assembly method

Abstract

The invention provides an aero-engine detachable gear shaft structure which comprises a gear shaft body, a gear ring, a positioning piece and a locking piece, the gear ring is installed on the gear shaft body through the positioning piece and the locking piece, and the aero-engine detachable gear shaft structure has the same torque transmission function as an integrally-designed gear shaft. The invention discloses an assembling and repairing method for a detachable gear shaft structure of an aero-engine. The assembling method for the detachable gear shaft structure of the aero-engine comprises the following steps that a gear ring and a gear shaft body are combined in an interference fit mode; the assembly is disassembled, the locking piece and the positioning piece are disassembled, and the gear ring is disassembled from the gear shaft body; and after the combined part is formed through repairing, the gear shaft body is used as a reference, and tooth shape and tooth direction parameter detection, machining and shape modification of the gear ring part are carried out. The method has the advantages that non-serious or destructive gear abrasion can be replaced and repaired by replacing the gear ring or the shaft part of the gear, the maintenance cost is effectively reduced, and high economic benefits are achieved.

Description

Technical Field

[0001] This invention relates to the field of gear shaft design technology for aero-engine transmission systems. It applies to aero-engines, gas turbines, and civil engines, and provides a detachable gear shaft structure for aero-engines. This structure has the same torque transmission function and role as an integrated gear shaft. The invention also provides a detachable gear shaft structure and assembly method for aero-engines. Background Technology

[0002] Gear shafts are a crucial core component of aero-engine transmission systems, and their main functions include the following: Power transmission: Transmitting the power of the main engine to the relevant accessories or components of the aircraft and engine to achieve the distribution of different power.

[0003] Torque transmission: During the power transmission process, the torque transmission is controlled according to the ratio of parameters such as the number of gear teeth to meet the load requirements of different accessories.

[0004] Adjusting the speed: By changing the transmission ratio between gear pairs, the speed of the gear shaft is changed to ensure that each accessory works at its optimal speed, thereby improving efficiency.

[0005] Structural support: As a supporting structure for rotating parts, it ensures the stable operation of rotating parts such as gears and bearings, and maintains the concentricity and stability of rotation.

[0006] Existing aero-engine transmission system gear shafts generally adopt an integral or welded design structure. However, as rotating components, gear shafts often suffer damage such as impacts, chipping, and wear on the gear teeth or shaft portion during post-use troubleshooting. Currently, there is no effective additive manufacturing repair method for this type of damage; the only option is to scrap and replace the entire gear shaft, resulting in high maintenance costs. Therefore, reducing maintenance costs has become a pressing problem to be solved. Summary of the Invention

[0007] The purpose of this invention is to reduce maintenance costs by designing a detachable gear shaft structure for aero engines, applicable to the transmission systems of aero engines, gas turbines, and civil engines. The detachable gear shaft structure manufactured using this design concept allows for partial repairs during maintenance, by replacing the gear ring or shaft portion depending on the damaged area. This effectively reduces the likelihood of the entire gear shaft being scrapped due to excessive damage to the gear ring or shaft, demonstrating its versatility and promising application prospects.

[0008] To avoid the cost waste caused by the complete scrapping of the gear shaft during maintenance of the integrated design of the aero-engine, a detachable gear shaft structure for aero-engines has been invented and designed. The design concept of this mechanism is mainly based on the fact that during maintenance, partial parts can be replaced by replacing the gear ring or shaft part according to the damaged part to reduce costs.

[0009] A detachable gear shaft structure for an aircraft engine comprises four parts: a gear shaft body, a gear ring, a positioning component, and a locking component. The gear ring is mounted on the gear shaft body via the positioning component and the locking component, and has the same torque transmission function as an integrated gear shaft design.

[0010] The positioning component is a pin.

[0011] The locking component is a plug structure.

[0012] A method for assembling and repairing a detachable gear shaft structure for an aircraft engine. The assembly method for the detachable gear shaft structure for an aircraft engine is as follows: The gear ring and gear shaft are combined using an interference fit. The three positioning holes are machined first using a combination and post-processing method, and then the three positioning components are installed. The same combination and post-processing method is used to process three locking holes and install three locking parts. The locking part plugs have threaded outer diameters to activate the locking function. After installing the locking parts, a three-point punch lock process is performed. After the assembly is formed, the gear shaft is used as a reference to carry out the detection, machining and shaping of parameters such as tooth profile and tooth direction of the gear ring.

[0013] Repair method: Disassemble the assembly, remove the locking and positioning parts, and separate the gear ring from the gear shaft; Replace the damaged gear ring or gear shaft, and carry out the component assembly process according to the assembly method of the new component assembly. Among them, the locking parts and positioning parts are selected and matched according to the actual situation by enlarging the repair group to ensure the original fit requirements. After the repair is completed and the assembly is formed, the tooth profile and tooth direction parameters of the gear ring are detected, processed and modified, using the gear shaft as a reference.

[0014] Advantages of this invention: This invention describes a design concept for a detachable gear shaft structure for aero engines, which is currently only used in a few engines and has not been widely adopted or expanded in the fields of aero engines and gas turbines. This invention is beneficial for optimizing design and reducing maintenance costs.

[0015] The detachable gear shaft structure of this invention does not change the function of the original integrated gear shaft structure, and still has the functions and roles of transmitting power, transmitting torque, regulating speed, and providing structural support. With the gear shaft structure of this invention, for non-severe or destructive gear wear, repairs can be carried out by replacing the gear ring or shaft portion, avoiding the situation where partial damage, chipping, or wear of some gears leads to the complete scrapping of the gear shaft, effectively reducing maintenance costs and achieving high economic benefits. Attached Figure Description

[0016] Figure 1 Gear shaft; Figure 2 Gear ring; Figure 3 Schematic diagram of the detachable gear shaft assembly. Detailed Implementation

[0017] The present invention will be further explained below with reference to specific implementation schemes, but it is not limited to the present invention. The structures, proportions, sizes, etc. shown in the accompanying drawings are only used to complement the content disclosed in the specification, so as to enable those skilled in the art to understand and read, and are not intended to limit the conditions under which the present invention can be implemented. Therefore, they have no substantial technical significance. Any modification of the structure, change of the proportion relationship or adjustment of the size, without affecting the effect and purpose that the present invention can produce, should still fall within the scope of the technical content disclosed in the present invention.

[0018] The aforementioned detachable gear shaft structure for aero engines comprises four parts: a gear shaft body, a gear ring, a positioning component, and a locking component. It possesses the same torque transmission function as an integrated gear shaft. A schematic diagram of the design structure is shown below. Figure 1 , 2 、3 shows.

[0019] Among them: the positioning part is a pin, and the locking part is a plug structure.

[0020] Assembly Method: The implementation methods of the detachable gear shaft structure for aero-engines of the present invention are introduced through two process routes: new assembly and repair. The assembly method and process route of the new assembly are as follows: The gear ring and gear shaft are combined using an interference fit. The three positioning holes are machined first using a combination and post-processing method, and then three pins are installed. The same combination and post-processing method is used to process three locking holes and install three plugs. The locking plugs have threaded outer diameters and can activate the locking function. After installing the locking parts, a three-point punch lock process is performed. After the assembly is formed, the gear shaft is used as a reference to carry out the detection, machining and shaping of parameters such as tooth profile and tooth direction of the gear ring.

[0021] Repair method: Disassemble the assembly, remove the locking and positioning parts, and separate the gear ring from the gear shaft; Replace the damaged gear ring or gear shaft, and carry out the component assembly process according to the assembly method of the new assembly. Among them, the locking parts and positioning parts are selected and matched by enlarging the repair group according to the actual situation to ensure the original fit requirements.

[0022] After the repair is completed and the assembly is formed, the gear shaft is used as a reference to carry out the detection, machining and shaping of parameters such as tooth profile and tooth direction of the gear ring.

[0023] Matters not covered in this invention are common knowledge.

[0024] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A split gear shaft structure for an aeroengine, characterized by: The aviation engine split gear shaft structure contains gear shaft body, gear ring, positioning member and locking member, the gear ring is installed on the gear shaft body through the positioning member and the locking member, and has the same torque transmission function as the integrated design gear shaft.

2. The aerospace engine split gear shaft structure of claim 1, wherein: The positioning member is a pin.

3. The aerospace engine split gear shaft structure of claim 1, wherein: The locking member is a plug structure member.

4. A method of assembling and repairing a split gear shaft structure of an aeroengine as claimed in claim 1, characterized in that: The assembly method of the aviation engine split gear shaft structure is as follows: The gear ring and the gear shaft body are combined in an interference fit mode; Three positioning holes are processed in a combined post-processing mode, and three positioning members are installed; Three locking holes are processed in the same combined post-processing mode, and three locking members are installed, the locking member plug has a threaded outer diameter, and plays a starting locking role, three-point locking treatment is performed after the locking member is installed; After the combined part is formed, the gear ring part is detected, processed and shaped according to the parameters such as tooth shape and tooth direction of the gear shaft body; Repair method: Split the combined part, remove the locking member and the positioning member, and disassemble the gear ring from the gear shaft body; Replace the damaged gear ring or gear shaft, and carry out the assembly process according to the assembly mode of the new part combined part, wherein the locking member and the positioning member are selected according to the actual situation to carry out the enlarged repair group mode, so as to ensure the original matching requirements; After the repair combined part is formed, the gear ring part is detected, processed and shaped according to the parameters such as tooth shape and tooth direction of the gear shaft body.

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