CN-121997621-A - Aviation spiral bevel gear dynamic impression analysis method

CN121997621ACN 121997621 ACN121997621 ACN 121997621ACN-121997621-A

Abstract

The embodiment of the invention provides a dynamic impression analysis method for an aviation spiral bevel gear, and relates to the field of aviation spiral bevel gear impression analysis. The method aims to solve the problem that the consistency of the dynamic contact mark and the actual measurement mark obtained by simulation analysis of the aerial bevel gear mark of the large-clearance bearing is poor. The aviation spiral bevel gear dynamic impression analysis method comprises the steps of establishing a spiral bevel gear system analysis model containing accurate tooth surfaces based on gear design parameters of the spiral bevel gear, applying load, adjusting the tooth surface design parameters, respectively performing machining state impression LTCA analysis and assembly state impression LTCA analysis until the impression requirements are met, applying load, adjusting EPG parameters, and performing dynamic impression LTCA analysis until the impression requirements are met. After a simulation analysis model is established, LTCA analysis from the half clearance to the full clearance is carried out, finally, a simulation impression meeting the actual requirements is obtained, and consistency of impression analysis and actual measurement impression analysis is improved.

Inventors

WANG WENJUAN
QIAN LULU
GAO JIAN

Assignees

中国航发商用航空发动机有限责任公司

Dates

Publication Date: 20260508
Application Date: 20241106

Claims (9)

1. The aviation spiral bevel gear dynamic impression analysis method is characterized by comprising the following steps of: based on gear design parameters of the spiral bevel gear, establishing a spiral bevel gear system analysis model containing accurate tooth surfaces; Applying load, adjusting tooth surface design parameters, and adopting a spiral bevel gear system analysis model to respectively perform machining state impression LTCA analysis and assembly state impression LTCA analysis until the impression requirement is met; and (3) applying a load, adjusting EPG parameters, and adopting a spiral bevel gear system analysis model to perform dynamic imprint LTCA analysis until the imprint requirement is met.
2. The method for analyzing dynamic seal marks of aviation spiral bevel gears according to claim 1, wherein the step of establishing a spiral bevel gear system analysis model containing accurate tooth surfaces based on gear design parameters of the spiral bevel gears comprises: Performing tooth surface initial design based on gear design parameters of the spiral bevel gear, and establishing a gear simulation model through MASTA software; The gear shaft and the casing full finite element model which are exported through Workbench software are imported into MASTA software for joint simulation; Carrying out bearing simulation modeling in MASTA software according to actual bearing parameters; and inputting tooth surface design parameters of the spiral bevel gear in MASTA software, and establishing a spiral bevel gear system analysis model containing accurate tooth surfaces.
3. The method of dynamic seal impression analysis of an aviation spiral bevel gear according to claim 2, wherein after the step of introducing a full finite element model of a gear shaft and a casing derived by a Workbench software into MASTA software for joint simulation and before the step of bearing modeling by MASTA software according to actual bearing parameters, further comprising: And replacing the gear shaft with a shaft model established by MASTA software, and then connecting the full-finite element shaft with the casing for polycondensation.
4. A method of dynamic seal impression analysis for an aviation spiral bevel gear according to any one of claims 1 to 3, wherein the step of applying a load to adjust tooth surface design parameters, and performing machine state seal impression LTCA analysis and assembly state seal impression LTCA analysis using spiral bevel gear system analysis models, respectively, until seal impression requirements are met comprises: Performing machining state impression LTCA analysis, if the static impression requirement is met, performing assembly state impression LTCA analysis, if the static impression requirement is not met, adjusting an applied load or tooth surface design parameters, and performing machining state impression LTCA analysis again until the static impression requirement is met; And carrying out assembly state impression LTCA analysis, carrying out dynamic impression LTCA analysis if the static impression requirement is met, adjusting the applied load or the tooth surface design parameters if the static impression requirement is not met, and carrying out assembly state impression LTCA analysis again until the static impression requirement is met.
5. The method of dynamic seal impression analysis for an aviation spiral bevel gear according to claim 4, wherein said machining state seal impression LTCA analysis comprises: The EPG parameter is set to 0 and LTCA analysis is performed.
6. The method of dynamic seal impression analysis for an aviation spiral bevel gear according to claim 4, wherein said assembly state seal impression LTCA analysis comprises: setting loading conditions as preset loads, wherein the range of the preset loads is 20-30N m, and EPG parameters are set to 0, and carrying out LTCA analysis.
7. The method for dynamic seal impression analysis of an aviation spiral bevel gear according to any one of claims 1 to 6, wherein the step of applying a load, adjusting EPG parameters, and performing dynamic seal impression LTCA analysis using a spiral bevel gear system analysis model until seal impression requirements are satisfied comprises: For the working surface, the EPG parameter is set to zero for dynamic imprint LTCA analysis, and for the starting surface, the EPG parameter is set according to the actual assembly and working conditions for dynamic imprint LTCA analysis.
8. The method of claim 7, wherein the step of performing the dynamic footprint LTCA analysis for the starting surface, in which the EPG parameters are set according to the actual assembly and the working conditions, further comprises: and (3) applying a load, setting the EPG parameters from half play to full play according to actual parameters of the bearing, and respectively performing dynamic imprint LTCA analysis until the imprint condition is met.
9. The method for dynamic footprint analysis of an aviation spiral bevel gear according to claim 8, wherein the step of applying a load, setting a half-play to full-play range of EPG parameters according to actual parameters of a bearing, and respectively performing dynamic footprint LTCA analysis until footprint conditions are satisfied comprises: if the EPG parameters are in the half-play and full-play ranges, the dynamic impression analysis does not meet the requirements, and the tooth surface parameters are reversely adjusted; If the EPG parameter is in the half-play range, the dynamic imprint analysis meets the requirement, and if the EPG parameter is in the full-play range, the dynamic imprint analysis does not meet the requirement, the EPG parameter, the applied load and the tooth surface design parameter are adjusted; if the EPG parameter is in the half-play range and the full-play range, the dynamic impression analysis meets the requirements, and the impression is optimized by adjusting the tooth surface design parameter or the loading load, so that the optimal impression parameter is obtained.

Description

Aviation spiral bevel gear dynamic impression analysis method Technical Field The invention relates to the field of aviation spiral bevel gear footprint analysis, in particular to an aviation spiral bevel gear dynamic footprint analysis method. Background The spiral bevel gear has the advantages of large overlap ratio, stable transmission, strong bearing capacity and the like, and is applied to a central transmission gear box (IGB) and a transfer Transmission Gear Box (TGB) of a transmission system in the field of aeroengines. The meshing quality of the spiral bevel gear directly affects the load carrying capacity and vibration performance of the system. In engineering, the aviation spiral bevel gear bears larger working load and thermal expansion in the working process, a certain clearance is needed to exist in the bearing to ensure that clamping stagnation does not occur, the axial clearance of the aviation bearing is about 300-600 mu m, and the large clearance greatly affects the contact area position of the gear pair. In addition, for bevel gears with two meshing surfaces, in engineering, in order to ensure that the working surface (the surface which runs for a long time) is not influenced by axial play, the conical points of the bevel gears are overlapped when the bevel gears are assembled, the single side of the bearing has no axial play, and when the starting surface (the other group of meshing surfaces of the gear pair and the working surface) runs, the bearing play needs to be eaten first and then is deformed under loading, so that the bearing play can change according to different working conditions. In this case, the tooth surface impression analysis needs to correctly consider the influence of the bearing play, otherwise, the contact area obtained by simulation and the actual contact area have great errors. The influence of bearing clearance (the bearing clearance is 0) is not considered in the traditional spiral bevel gear impression simulation analysis, or the bearing clearance is directly introduced into a bearing model (the bearing is positioned at a theoretical position, and the clearance at two sides is half of the bearing clearance) for modeling. For an aviation bevel gear system containing a large-clearance bearing, the consistency of dynamic contact marks and actual measurement marks obtained by the two models is poor. Disclosure of Invention The following presents a simplified summary of one or more aspects in order to provide a basic understanding of such aspects. This summary is not an extensive overview of all contemplated aspects, and is intended to neither identify key or critical elements of all aspects nor delineate the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that is presented later. The invention aims to provide an aviation spiral bevel gear dynamic seal impression analysis method, which can solve the problem that the dynamic contact seal impression obtained by aviation bevel gear seal impression simulation analysis of a large-clearance bearing has poor consistency with an actual measurement seal impression. Embodiments of the invention may be implemented as follows: the embodiment of the invention provides an aviation spiral bevel gear dynamic impression analysis method, which comprises the following steps of: based on gear design parameters of the spiral bevel gear, establishing a spiral bevel gear system analysis model containing accurate tooth surfaces; Applying load, adjusting tooth surface design parameters, and adopting a spiral bevel gear system analysis model to respectively perform machining state impression LTCA analysis and assembly state impression LTCA analysis until the impression requirement is met; and (3) applying a load, adjusting EPG parameters, and adopting a spiral bevel gear system analysis model to perform dynamic imprint LTCA analysis until the imprint requirement is met. In addition, the aviation spiral bevel gear dynamic impression analysis method provided by the embodiment of the invention can also have the following additional technical characteristics: Optionally, the step of establishing the spiral bevel gear system analysis model including the accurate tooth surface based on the gear design parameters of the spiral bevel gear comprises the following steps: Performing tooth surface initial design based on gear design parameters of the spiral bevel gear, and establishing a gear simulation model through MASTA software; The gear shaft and the casing full finite element model which are exported through Workbench software are imported into MASTA software for joint simulation; Carrying out bearing simulation modeling in MASTA software according to actual bearing parameters; and inputting tooth surface design parameters of the spiral bevel gear in MASTA software, and establishing a spiral bevel gear system analysis model containing