CN116306112A - Multi-dimensional damage-resistant prediction method and device for thrust bearing of aero-engine - Google Patents
Multi-dimensional damage-resistant prediction method and device for thrust bearing of aero-engine Download PDFInfo
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Abstract
The application relates to a multi-dimensional damage-resistant prediction method and device for a thrust bearing of an aeroengine, wherein the method comprises the following steps: determining structural design information of a thrust bearing of the aero-engine; constructing a thrust bearing three-dimensional digital prototype with geometrical feature, wherein the thrust bearing three-dimensional digital prototype comprises an inner ring piece, a rotary rolling body and a retainer; based on a three-dimensional digital prototype of the thrust bearing, the thrust bearing of the aero-engine is predicted for damage resistance according to structural design information. The design scheme of the bearing is evaluated by adopting multiple dimensions, the engineering design application is oriented, and the built simulation environment is based on bearing special software and business software, so that cross-specialized integration can be realized.
Description
Technical Field
The application relates to the technical field of aeroengine damage prediction, in particular to a multi-dimensional damage-resistant prediction method and device for a thrust bearing of an aeroengine.
Background
Different from the simulation of traditional mechanical parts, the thrust bearing of the aeroengine is used for a main shaft supporting position, has the characteristics of high temperature, high speed, complex load and the like, relates to a high-speed rotating body with multiple physical phenomena such as dynamics, fluid, heat and the like, and needs to consider envelope load spectral lines of the aeroengine in the process of adapting to flight. The multi-dimensional damage-resistant prediction method has the core aim of predicting whether the designed thrust bearing of the aeroengine has damage or not in a typical service envelope spectrum environment.
Along with the design requirement of the aero-engine on the high reliability of the bearing, the simulation analysis means is required to be combined with the engineering design application, and the possible damage of the bearing is effectively predicted while the optimization is carried out in the full design flow.
Disclosure of Invention
In order to overcome at least one defect in the prior art, the embodiment of the application provides a multi-dimensional damage-resistant prediction method and device for a thrust bearing of an aeroengine.
In a first aspect, a method for predicting multi-dimensional damage resistance of an aero-engine thrust bearing is provided, comprising:
determining structural design information of a thrust bearing of the aero-engine;
constructing a thrust bearing three-dimensional digital prototype with geometrical feature, wherein the thrust bearing three-dimensional digital prototype comprises an inner ring piece, a rotary rolling body and a retainer;
based on a three-dimensional digital prototype of the thrust bearing, the thrust bearing of the aero-engine is predicted for damage resistance according to structural design information.
In one embodiment, based on a three-dimensional digital prototype of the thrust bearing, the method for predicting damage resistance of the thrust bearing of the aeroengine according to structural design information comprises:
based on a thrust bearing three-dimensional digital prototype, a finite element model of the retainer is established according to structural design information, and a mode analysis method is adopted to predict the resonance characteristic rule of the retainer in the high-speed operation process;
judging whether the rotation speed corresponding to the resonance intersection point of the retainer coincides with the rotation speed of the working load spectrum according to the resonance characteristic rule, if so, the retainer meets the design requirement, otherwise, the structural design of the retainer is adjusted.
In one embodiment, based on a three-dimensional digital prototype of the thrust bearing, the method for predicting damage resistance of the thrust bearing of the aeroengine according to structural design information comprises:
based on a thrust bearing three-dimensional digital prototype, an inner ring member finite element model is established according to structural design information, and a fluid domain of a lubrication part under the ring is extracted according to the inner ring member finite element model;
and (3) carrying out oil passing capacity analysis by adopting fluid analysis software aiming at the fluid field of the lubricating part under the ring, wherein if the oil passing quantity of the oil hole of the inner ring is larger than the oil supply quantity of the thrust bearing, the inner ring meets the design requirement, otherwise, the structural design of the inner ring is adjusted.
In one embodiment, based on a three-dimensional digital prototype of the thrust bearing, the method for predicting damage resistance of the thrust bearing of the aeroengine according to structural design information comprises:
based on a three-dimensional digital prototype of the thrust bearing, determining the impact force of a rotating rolling body of the thrust bearing on a retainer based on explicit dynamic analysis or rigid-flexible coupling dynamic analysis method according to structural design information;
the impact force of the rotating rolling body based on the thrust bearing to the retainer is determined by adopting a finite element analysis method, and the impact resistance of the retainer is predicted.
In one embodiment, the method further comprises:
determining a working condition load spectrum of an aeroengine thrust bearing;
determining installation matching conditions, material attribute information and attribute parameters of lubricating oil of an aeroengine thrust bearing;
based on a three-dimensional digital prototype of the thrust bearing, a complete dynamics analysis method is adopted to predict the centroid movement track of the retainer according to structural design information, working condition load spectrum, installation coordination conditions, material attribute information and attribute parameters of lubricating oil of the thrust bearing of the aeroengine.
In one embodiment, the method further comprises:
determining the installation matching conditions of the thrust bearing of the aero-engine;
and predicting the installation adaptability of the thrust bearing according to the installation matching conditions, wherein the installation adaptability of the thrust bearing comprises the actual interference magnitude and the hoop tensile stress of the thrust bearing in the working state.
In one embodiment, the method further comprises:
when the actual interference is larger than zero and the circumferential tensile stress does not exceed the limit value of the ferrule material, the design requirement is met.
In one embodiment, the method further comprises:
determining a working condition load spectrum of an aeroengine thrust bearing;
according to the working condition load spectrum, predicting four evaluation indexes of working play, contact stress, oil film lubrication parameters and service life of the thrust bearing under the enveloping working condition by adopting a quasi-statics analysis method or a quasi-dynamics analysis method; judging whether the four evaluation indexes meet the design requirements of the thrust bearing application environment.
In one embodiment, the thrust bearing application environment design requirements include:
the radial working play of the thrust bearing is larger than zero; bearing contact stress under enveloping steady-state working condition is not more than 2500MPa; the oil film lubrication parameter is more than 1; the comprehensive cycle life of the bearing is not less than the required development life of the engine; in the working state, the gap between the bearing non-bearing half-ring and the rotary rolling body is not smaller than zero, and the bearing is prevented from three-point contact, namely the thrust bearing non-bearing half-ring does not bear load; in the working state, the rotary rolling bodies cannot climb out of the edges of the roller path.
In one embodiment, the method further comprises:
calculating the power loss of the thrust bearing under different working condition load spectrums; transmitting the power loss to a thrust bearing host machine for bearing cavity thermal field analysis, and predicting the internal and external temperatures of the thrust bearing; when the internal and external temperatures of the thrust bearing do not exceed the allowable temperature of the bearing material, the design requirement is met.
In a second aspect, there is provided an aero-engine thrust bearing multi-dimensional damage-resistant prediction apparatus, comprising:
the structural design information determining module is used for determining structural design information of the thrust bearing of the aero-engine;
the three-dimensional digital prototype construction module is used for constructing a thrust bearing three-dimensional digital prototype with geometrical feature, and the thrust bearing three-dimensional digital prototype comprises a bearing outer ring piece, an inner ring piece, a rotary rolling body and a retainer;
and the damage resistance prediction module is used for predicting damage resistance of the thrust bearing of the aeroengine based on the three-dimensional digital prototype of the thrust bearing according to structural design information.
Compared with the prior art, the application has the following beneficial effects: according to the multi-dimensional damage-resistant prediction method and device for the thrust bearing of the aeroengine, the design scheme of the bearing is evaluated by adopting multiple dimensions, the method and device are oriented to engineering design application, and the constructed simulation environment is based on special bearing software and business software, so that cross-specialized integration can be realized.
Drawings
The present application may be better understood by reference to the following description taken in conjunction with the accompanying drawings, which are incorporated in and form a part of this specification, together with the following detailed description. In the drawings:
FIG. 1 shows a schematic diagram of a multi-dimensional damage-resistant prediction of an aero-engine thrust bearing;
FIG. 2 shows a flow diagram of an aircraft engine thrust bearing multi-dimensional damage-tolerant prediction method according to an embodiment of the present application;
fig. 3 shows a block diagram of a multi-dimensional damage-resistant prediction device for an aero-engine thrust bearing according to an embodiment of the present application.
Detailed Description
Exemplary embodiments of the present application will be described hereinafter with reference to the accompanying drawings. In the interest of clarity and conciseness, not all features of an actual embodiment are described in the specification. It will of course be appreciated that in the development of any such actual embodiment, numerous implementation-specific decisions may be made to achieve the developers' specific goals, and that these decisions may vary from one implementation to another.
It should be noted that, in order to avoid obscuring the present application with unnecessary details, only the device structures closely related to the solution according to the present application are shown in the drawings, and other details not greatly related to the present application are omitted.
It is to be understood that the present application is not limited to the described embodiments due to the following description with reference to the drawings. In this context, embodiments may be combined with each other, features replaced or borrowed between different embodiments, one or more features omitted in one embodiment, where possible.
The embodiment of the application provides a multi-dimensional damage-resistant prediction method for a thrust bearing of an aeroengine, which specifically predicts damage resistance of the thrust bearing from three dimensions, and fig. 1 shows a schematic diagram of the multi-dimensional damage-resistant prediction of the thrust bearing, wherein the schematic diagram comprises an installation and use evaluation dimension, a quasi-statics/quasi-dynamics dimension, dynamics and a fluid dimension. The design scheme of the bearing is evaluated by adopting multiple dimensions, the engineering design application is oriented, and the built simulation environment is based on bearing special software and business software, so that cross-specialized integration can be realized.
Fig. 2 shows a flow diagram of an aero-engine thrust bearing multi-dimensional damage-tolerant prediction method according to an embodiment of the present application, see fig. 2, the method comprising:
step S1, structural design information of a thrust bearing of the aero-engine is determined;
in this step, structural design information is determined according to the detailed design scheme of the thrust bearing of the aeroengine, where the structural design information may include an inner diameter, an outer diameter, a pitch diameter, an inner groove bottom diameter, an outer groove bottom diameter, a rolling body diameter, a number of rolling bodies, an inner flange diameter, an outer flange diameter, a guiding manner, a cage outer diameter, a cage inner diameter, a pocket size, and the like.
S2, constructing a thrust bearing three-dimensional digital prototype with geometrical feature, wherein the thrust bearing three-dimensional digital prototype comprises an inner ring piece, a rotary rolling body and a retainer;
in the step, a three-dimensional digital model machine of the bearing with geometrical feature is built according to a design scheme by designing a collaborative management system and combining parameterization means, and the three-dimensional digital model machine comprises an inner ring piece, a rotary rolling body, a retainer and a bearing outer ring piece.
And S3, based on the three-dimensional digital prototype of the thrust bearing, performing damage-resistant prediction on the thrust bearing of the aero-engine according to structural design information.
In this embodiment, the damage-resistant prediction of the aero-engine thrust bearing from the dynamic, fluid dimensions may include damage-resistant prediction of the inner ring, the rotating rolling elements, and the cage.
In one embodiment, based on the three-dimensional digital prototype of the thrust bearing, the method for predicting damage resistance of the thrust bearing of the aeroengine according to structural design information can comprise:
based on a thrust bearing three-dimensional digital prototype, a finite element model of the retainer is established according to structural design information, and a mode analysis method is adopted to predict the resonance characteristic rule of the retainer in the high-speed operation process;
judging whether the rotation speed corresponding to the resonance intersection point of the retainer coincides with the rotation speed of the working load spectrum according to the resonance characteristic rule, if so, the retainer meets the design requirement, otherwise, the structural design of the retainer is adjusted.
In one embodiment, based on the three-dimensional digital prototype of the thrust bearing, the method for predicting damage resistance of the thrust bearing of the aeroengine according to structural design information can further comprise:
based on a thrust bearing three-dimensional digital prototype, an inner ring member finite element model is established according to structural design information, and a fluid domain of a lubrication part under the ring is extracted according to the inner ring member finite element model;
and (3) carrying out oil passing capacity analysis by adopting fluid analysis software aiming at the fluid field of the lubricating part under the ring, wherein if the oil passing quantity of the oil hole of the inner ring is larger than the oil supply quantity of the thrust bearing, the inner ring meets the design requirement, otherwise, the structural design of the inner ring is adjusted.
In one embodiment, based on the three-dimensional digital prototype of the thrust bearing, the method for predicting damage resistance of the thrust bearing of the aeroengine according to structural design information can further comprise:
based on a three-dimensional digital prototype of the thrust bearing, determining the impact force of a rotating rolling body of the thrust bearing on a retainer based on explicit dynamic analysis or rigid-flexible coupling dynamic analysis method according to structural design information;
the impact force of the rotating rolling body based on the thrust bearing to the retainer is determined by adopting a finite element analysis method, and the impact resistance of the retainer is predicted.
In one embodiment, the method for predicting multi-dimensional damage resistance of the thrust bearing of the aeroengine further comprises:
firstly, determining a working condition load spectrum of a thrust bearing of an aeroengine; here, according to different working conditions of the thrust bearing, working condition load spectrums are defined, including the requirements of environment temperature, radial load, axial load and rotating speed in various states of cruising, slow driving, climbing, landing and the like.
Then, determining installation matching conditions, material attribute information and attribute parameters of lubricating oil of the thrust bearing of the aeroengine; here, the mounting matching conditions include mounting matching relation of the shaft and the bearing, mounting matching relation of the seat and the bearing, material attribute information at least includes elastic modulus, poisson's ratio, thermal expansion coefficient and density, and attribute parameters of the lubricating oil at least include lubricating oil density, kinematic viscosity and heat conductivity coefficient.
And finally, based on a three-dimensional digital prototype of the thrust bearing, predicting the centroid movement track of the retainer by adopting a complete dynamics analysis method according to structural design information, working condition load spectrum, installation matching conditions, material attribute information and attribute parameters of lubricating oil of the thrust bearing of the aeroengine, and judging the risk of deflection of the bearing retainer and the guide ring.
In other embodiments, the method of the present application further performs damage-resistant prediction from the installation usage assessment dimension, the method further comprising:
determining the installation matching conditions of the thrust bearing of the aero-engine; here, the mounting mating condition includes a mounting mating relationship of the shaft and the bearing, the seat and the bearing,
and predicting the installation adaptability of the thrust bearing according to the installation matching conditions, wherein the installation adaptability of the thrust bearing comprises the actual interference magnitude and the hoop tensile stress of the thrust bearing in the working state.
Specifically, in this embodiment, the design requirement is met when the actual interference is greater than zero and the hoop tensile stress does not exceed the defined value of the ferrule material.
In further embodiments, the methods of the present application further provide for damage-resistant prediction from a quasi-static/quasi-dynamic dimension, the method further comprising:
determining a working condition load spectrum of an aeroengine thrust bearing; here, according to different working conditions of the thrust bearing, working condition load spectrums are defined, including the requirements of environment temperature, radial load, axial load and rotating speed in various states of cruising, slow driving, climbing, landing and the like.
According to the working condition load spectrum, predicting four evaluation indexes of working play, contact stress, oil film lubrication parameters and service life of the thrust bearing under the enveloping working condition by adopting a quasi-statics analysis method or a quasi-dynamics analysis method; judging whether the four evaluation indexes meet the design requirements of the thrust bearing application environment.
Specifically, in the above-described embodiment, the thrust bearing application environment design requirements include:
the radial working play of the thrust bearing is larger than zero; bearing contact stress under enveloping steady-state working condition is not more than 2500MPa; the oil film lubrication parameter is more than 1; the comprehensive cycle life of the bearing is not less than the required development life of the engine; in the working state, the gap between the bearing non-bearing half-ring and the rotary rolling body is not smaller than zero, and the bearing is prevented from three-point contact, namely the thrust bearing non-bearing half-ring does not bear load; in the working state, the rotary rolling bodies cannot climb out of the edges of the roller path.
Further, the method further comprises:
calculating the power loss of the thrust bearing under different working condition load spectrums; transmitting the power loss to a thrust bearing host machine for bearing cavity thermal field analysis, and predicting the internal and external temperatures of the thrust bearing; when the internal and external temperatures of the thrust bearing do not exceed the allowable temperature of the bearing material, the design requirement is met.
Based on the same inventive concept as the method for predicting the multi-dimensional damage resistance of the thrust bearing of the aero-engine provided by the embodiment of the present application, the embodiment of the present application further provides a device for predicting the multi-dimensional damage resistance of the thrust bearing of the aero-engine, and fig. 3 shows a block diagram of a structure of the device for predicting the multi-dimensional damage resistance of the thrust bearing of the aero-engine according to the embodiment of the present application, where the device includes:
a structural design information determination module 31 for determining structural design information of the thrust bearing of the aircraft engine;
here, structural design information is determined according to the detailed design scheme of the thrust bearing of the aeroengine, where the structural design information may include an inner diameter, an outer diameter, a pitch diameter, an inner groove bottom diameter, an outer groove bottom diameter, a rolling body diameter, a number of rolling bodies, an inner flange diameter, an outer flange diameter, a guide manner, a cage outer diameter, a cage inner diameter, a pocket size, and the like.
The three-dimensional digital prototype construction module 32 is used for constructing a thrust bearing three-dimensional digital prototype with geometrical feature, and the thrust bearing three-dimensional digital prototype comprises a bearing outer ring piece, an inner ring piece, a rotary rolling body and a retainer;
here, through designing collaborative management system, combining parameterization means, according to the design scheme, build the three-dimensional digital prototype of bearing that has geometrical feature appearance, it contains inner ring spare, rotatory rolling element, holder, can also include the outer ring spare of bearing.
And the damage-resistant prediction module 33 is used for predicting damage resistance of the thrust bearing of the aero-engine based on the three-dimensional digital prototype of the thrust bearing according to structural design information.
In this embodiment, the damage-resistant prediction of the aero-engine thrust bearing from the dynamic, fluid dimensions may include damage-resistant prediction of the inner ring, the rotating rolling elements, and the cage.
In summary, the method and the device for predicting the multi-dimensional damage resistance of the thrust bearing of the aeroengine adopt a design scheme of evaluating the bearing in multiple dimensions, are oriented to engineering design application, and the constructed simulation environment is based on bearing special software and commercial software, so that cross-specialized integration can be realized.
The foregoing is merely various embodiments of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art can easily think about changes or substitutions within the technical scope of the present application, and the changes and substitutions are intended to be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (11)
1. The multi-dimensional damage-resistant prediction method for the thrust bearing of the aeroengine is characterized by comprising the following steps of:
determining structural design information of a thrust bearing of the aero-engine;
constructing a thrust bearing three-dimensional digital prototype with geometrical feature, wherein the thrust bearing three-dimensional digital prototype comprises an inner ring piece, a rotary rolling body and a retainer;
and based on the three-dimensional digital prototype of the thrust bearing, performing damage-resistant prediction on the thrust bearing of the aeroengine according to the structural design information.
2. The method of claim 1, wherein predicting damage resistance of the thrust bearing of the aircraft engine based on the structural design information based on the three-dimensional digital prototype of the thrust bearing comprises:
based on the thrust bearing three-dimensional digital prototype, establishing a finite element model of the retainer according to the structural design information, and predicting the resonance characteristic rule of the retainer in the high-speed operation process by adopting a modal analysis method;
judging whether the rotation speed corresponding to the resonance intersection point of the retainer coincides with the rotation speed of the working load spectrum according to the resonance characteristic rule, if so, the retainer meets the design requirement, otherwise, the structural design of the retainer is adjusted.
3. The method of claim 1, wherein predicting damage resistance of the thrust bearing of the aircraft engine based on the structural design information based on the three-dimensional digital prototype of the thrust bearing comprises:
based on the thrust bearing three-dimensional digital prototype, establishing the inner ring finite element model according to the structural design information, and extracting a fluid domain of a lubricating part under the ring according to the inner ring finite element model;
and carrying out oil passing capability analysis on the fluid domain of the lubricating part under the ring by adopting fluid analysis software, if the oil passing amount of the oil hole of the inner ring is larger than the oil supply amount of the thrust bearing, the inner ring meets the design requirement, otherwise, the structural design of the inner ring is adjusted.
4. The method of claim 1, wherein predicting damage resistance of the thrust bearing of the aircraft engine based on the structural design information based on the three-dimensional digital prototype of the thrust bearing comprises:
based on the three-dimensional digital prototype of the thrust bearing, determining the impact force of the rotating rolling body of the thrust bearing on the retainer based on an explicit dynamic analysis or a rigid-flexible coupling dynamic analysis method according to the structural design information;
based on the impact force of the rotating rolling bodies of the thrust bearing on the retainer, determining the strength of the retainer by adopting a finite element analysis method, and predicting the impact resistance of the retainer.
5. The method of claim 1, wherein the method further comprises:
determining a working condition load spectrum of an aeroengine thrust bearing;
determining installation matching conditions, material attribute information and attribute parameters of lubricating oil of an aeroengine thrust bearing;
based on the three-dimensional digital prototype of the thrust bearing, the mass center movement track of the retainer is predicted by adopting a complete dynamics analysis method according to structural design information, working condition load spectrum, installation matching conditions, material attribute information and attribute parameters of lubricating oil of the thrust bearing of the aeroengine.
6. The method of claim 1, wherein the method further comprises:
determining the installation matching conditions of the thrust bearing of the aero-engine;
and predicting the installation adaptability of the thrust bearing according to the installation matching conditions, wherein the installation adaptability of the thrust bearing comprises the actual interference magnitude and the circumferential tensile stress of the thrust bearing in the working state.
7. The method of claim 6, wherein the method further comprises:
when the actual interference is larger than zero and the circumferential tensile stress does not exceed the limit value of the ferrule material, the design requirement is met.
8. The method of claim 1, wherein the method further comprises:
determining a working condition load spectrum of an aeroengine thrust bearing;
according to the working condition load spectrum, predicting four evaluation indexes of working play, contact stress, oil film lubrication parameters and service life of the thrust bearing under the enveloping working condition by adopting a quasi-statics analysis method or a quasi-dynamics analysis method; and judging whether the four evaluation indexes meet the design requirements of the thrust bearing application environment.
9. The method of claim 8, wherein the thrust bearing application environment design requirements include:
the radial working play of the thrust bearing is larger than zero; bearing contact stress under enveloping steady-state working condition is not more than 2500MPa; the oil film lubrication parameter is more than 1; the comprehensive cycle life of the bearing is not less than the required development life of the engine; in the working state, the gap between the bearing non-bearing half-ring and the rotary rolling body is not smaller than zero, and the bearing is prevented from three-point contact, namely the thrust bearing non-bearing half-ring does not bear load; in the working state, the rotary rolling bodies cannot climb out of the edges of the roller path.
10. The method of claim 8, wherein the method further comprises:
calculating the power loss of the thrust bearing under different working condition load spectrums; transmitting the power loss to a thrust bearing host machine for bearing cavity thermal field analysis, and predicting the internal and external temperatures of the thrust bearing; when the internal and external temperatures of the thrust bearing do not exceed the allowable temperature of the bearing material, the design requirement is met.
11. An aeroengine thrust bearing multi-dimensional damage-resistant prediction device, comprising:
the structural design information determining module is used for determining structural design information of the thrust bearing of the aero-engine;
the thrust bearing three-dimensional digital prototype comprises a bearing outer ring piece, an inner ring piece, a rotary rolling body and a retainer;
and the damage resistance prediction module is used for predicting damage resistance of the thrust bearing of the aeroengine based on the three-dimensional digital prototype of the thrust bearing according to the structural design information.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310133730.8A CN116306112A (en) | 2023-02-17 | 2023-02-17 | Multi-dimensional damage-resistant prediction method and device for thrust bearing of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310133730.8A CN116306112A (en) | 2023-02-17 | 2023-02-17 | Multi-dimensional damage-resistant prediction method and device for thrust bearing of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116306112A true CN116306112A (en) | 2023-06-23 |
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