CN117272529A - Multi-parameter frequency modulation design method for thin-web spur gear of aero-engine - Google Patents
Multi-parameter frequency modulation design method for thin-web spur gear of aero-engine Download PDFInfo
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- CN117272529A CN117272529A CN202310881777.2A CN202310881777A CN117272529A CN 117272529 A CN117272529 A CN 117272529A CN 202310881777 A CN202310881777 A CN 202310881777A CN 117272529 A CN117272529 A CN 117272529A
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- 238000013461 design Methods 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 22
- 238000004364 calculation method Methods 0.000 claims abstract description 9
- 238000004458 analytical method Methods 0.000 claims abstract description 8
- 230000009191 jumping Effects 0.000 claims description 12
- 238000005452 bending Methods 0.000 claims description 2
- 230000006872 improvement Effects 0.000 abstract description 4
- 230000004584 weight gain Effects 0.000 abstract description 4
- 235000019786 weight gain Nutrition 0.000 abstract description 4
- 230000005540 biological transmission Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 8
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- 230000008859 change Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 2
- 238000012938 design process Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
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- 239000007858 starting material Substances 0.000 description 1
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- 239000013585 weight reducing agent Substances 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
- G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/02—Reliability analysis or reliability optimisation; Failure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The application belongs to an aeroengine, and particularly relates to a multi-parameter frequency modulation design method for a thin radial plate spur gear of the aeroengine, which comprises the steps of confirming a preliminary scheme of a gear shaft and establishing a three-dimensional model of the gear shaft; based on the preliminary scheme, mode trial calculation is carried out, the thickness of the radial plate, the tooth width size and the round angle size are sequentially adjusted until no resonance point exists in all the common working rotating speed ranges, any gear can be free of calculated resonance points in the working rotating speed ranges, the weight gain of the gear is small, structural improvement design can be carried out according to the analysis result in the design stage, the possibility of resonance fatigue damage of the gear in working is reduced, and therefore the working reliability of the thin radial plate straight gear of the aeroengine is improved.
Description
Technical Field
The application belongs to aeroengines, and particularly relates to a multi-parameter frequency modulation design method for a thin radial plate spur gear of an aeroengine.
Background
The gear transmission system is an important component part of an aviation turbofan and turbojet engine mechanical system (comprising a central transmission device, an engine accessory case and an aircraft accessory case), wherein the central transmission device is connected with the engine accessory case through a central transmission rod, and the engine accessory case is connected with the aircraft accessory case through a flexible shaft. When the engine is started, a starter arranged on the aircraft accessory casing transmits output power to the high-voltage rotor of the engine through a gear system, a flexible shaft, a transmission rod and other parts, so that the engine is started; when the engine works normally, accessories arranged on the aircraft accessory case and the engine accessory case extract power from the high-pressure rotor of the engine through a series of gear transmission systems such as the aircraft accessory case, the engine accessory case and the central transmission, so that the normal work is ensured.
The transmission gear is usually designed as a lightweight, thin web gear structure, typically ranging in size from 3mm to 6mm, with the schematic diagram shown in fig. 1, limited by the aero-engine weight index. The natural frequency of the straight gear in the structural form is lower, multiple steps of natural frequencies exist in the working rotating speed range, and the main failure mode is pitch diameter type vibration fatigue failure. In order to avoid vibration fatigue failure of the gear transmission system in operation, the natural frequencies of all steps of the gear shaft are changed by adjusting the dimension parameters of the thickness B (see figure 1) of the radial plate in the design process, and the calculated resonance rotating speed is adjusted to be out of the common working rotating speed range.
The prior art solutions related to the present invention, as described above, have the main drawbacks: considering the purpose of weight reduction, the straight gear web of the aero-engine is usually designed to be lighter and thinner, the overall rigidity is weaker, a plurality of resonance points possibly appear in the working rotation speed range, as shown in fig. 2, in the range from the slow-running rotation speed to the highest rotation speed, three-section-diameter forward traveling waves and four-section-diameter backward traveling waves vibrate, and the four-section-diameter forward traveling wave resonance margin is lower; the prior art method is adopted to change the thickness weight gain of the gear web, the degree of improvement of the natural frequency of each order of the gear after adjustment is equivalent to the change rate of the web thickness (see table 1), and the change condition of the natural frequency of each order of table 1 along with the web thickness
The problem that the high-order vibration mode resonance point is called out of the working rotation speed range, but the natural frequency of the low-order vibration mode is increased so that the resonance point enters the working rotation speed range is solved, all the resonance points cannot be adjusted out of the working rotation speed range, resonance fatigue damage can occur to the gear in working, and therefore the functionality and reliability of the aeroengine are affected.
Disclosure of Invention
In order to solve the problems, the multi-parameter frequency modulation design method for the thin web spur gear of the aero-engine comprises the following steps:
step 1: confirming a preliminary scheme of a gear shaft, and establishing a three-dimensional model of the gear shaft;
step 2: based on a preliminary scheme, performing modal trial calculation to obtain a radial thickness range of the gear shaft without resonance points in a first preset rotating speed range;
when the web thickness range is a non-empty set, setting a preliminary scheme with the web thickness range as a final scheme, and jumping to the step 5;
when the range is an empty set, selecting a corresponding web thickness value when the resonance point is closest to the edge of the first preset rotating speed range; setting a preliminary scheme with the web thickness value as a first scheme, and jumping to the step 3;
step 3: acquiring a tooth width range of the gear shaft without resonance points in a second preset range rotating speed based on the first scheme;
when the tooth width range is a non-empty set, setting a first scheme with the tooth width range as a final scheme, and jumping to the step 5;
when the range is the empty set, selecting a corresponding tooth width value when the resonance point is close to the edge of the second preset rotating speed range; setting the preliminary scheme with the tooth width value as a second scheme, and jumping to the step 4;
step 4: acquiring a fillet size range of the gear shaft without resonance points in a third preset range of rotating speed based on the second scheme;
when the fillet size range is a non-empty set, setting a first scheme with the fillet size range as a final scheme, and jumping to step 5;
when the size range of the round angle is an empty set, jumping to the step 1;
step 5: taking the values of the radial plate thickness range, the tooth width range or the fillet size range in the final scheme to carry out modal analysis of the final scheme;
step 6: and (5) outputting a final scheme when the modal analysis result meets the preset requirement, and returning to the step (5) when the gear shaft of the final scheme does not meet the preset requirement.
Preferably, the first preset rotating speed range is 80% -95% of the rotating speed;
preferably, the second preset rotating speed range is that the low-order vibration mode resonance rotating speed of the gear shaft is lower than the lower limit of the common working rotating speed, and the adjacent high-order vibration mode resonance rotating speed is in the preset range of the upper limit of the common working rotating speed.
Preferably, the second preset rotating speed range is that the low-order vibration mode resonance rotating speed of the gear shaft in consideration of frequency division and frequency multiplication is within the preset range of the upper limit of the common working rotating speed, and the adjacent high-order vibration mode resonance rotating speed is lower than the lower limit of the common working rotating speed.
Preferably, the gear width size is adjusted by a dichotomy method to obtain the fillet size range of the gear shaft without resonance points in the rotating speed of the third preset range.
Preferably, the web thickness is less than the tooth width at values in the web thickness range.
Preferably, the tooth width is determined to be at a minimum in accordance with the tooth bending fatigue and contact fatigue strength reserves when taking values over the tooth width range
The advantages of the present application include: compared with the original method for modulating frequency by only adjusting the thickness of the web, the multi-parameter frequency modulation design method for the thin web spur gear of the aero-engine breaks through the precise control technology of the natural frequency of each order of the spur gear, defines the application range of each design parameter, provides a multi-parameter frequency modulation design flow, can realize that any gear does not have a calculated resonance point in the working rotating speed range, has less weight gain, can carry out structural improvement design depending on the analysis result in the design stage, reduces the possibility of resonance fatigue damage of the gear in working, and further improves the working reliability of the thin web spur gear of the aero-engine.
Drawings
FIG. 1 is a schematic view of a typical thin web spur gear;
FIG. 2 is a schematic diagram of a typical spur gear calculated resonance point;
FIG. 3 is a flow chart of a multiparameter FM design;
FIG. 4 is a schematic diagram of a tooth width adjustment application;
FIG. 5 is a schematic diagram of a fillet adjustment application;
FIG. 6 is a diagram of a parent candel;
fig. 7 is a diagram of a multi-parameter frequency modulated campbell.
Detailed Description
For the purposes, technical solutions and advantages of the present application, the following describes the technical solutions in the embodiments of the present application in more detail with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, based on the embodiments herein, which would be apparent to one of ordinary skill in the art without undue burden are within the scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The aim of the invention is to achieve that all calculated resonance points of the gear are outside the usual working speed range. Through a great deal of researches, the natural frequency of the thin web spur gear of the aero-engine is different along with the change rules of the thickness, the tooth width and the round angle size of the web,
after the tooth width is widened, the first-order natural frequency of the spur gear is reduced, the second-order natural frequency is basically unchanged, and the third-order natural frequency is slightly increased (see table 2); after the transfer circular angle between the web and the shaft becomes larger, the first-order and second-order natural frequencies slightly rise, and the third-order natural frequency is basically unchanged. According to the characteristic of the change of the natural frequency of the gear, the multi-parameter frequency modulation design method of the thin radial straight gear of the aeroengine is provided, on the basis of the original gear frequency modulation design parameter B, the tooth width A and the round angle R (see figure 1) are simultaneously used as optimization parameters, the application range of each design parameter is defined, a multi-parameter frequency modulation design flow is provided, the natural frequency of each order of the gear is precisely controlled by repeatedly adjusting the sizes of the tooth width A, the radial B and the round angle R, and all calculated resonance points of the gear are out of the common working rotation speed range.
TABLE 2 variation of natural frequency with tooth width A for each order
TABLE 3 variation of natural frequencies of various orders with fillet R
The design flow is as follows:
the multi-parameter frequency modulation design flow of the thin web spur gear of the aero-engine provided by the invention is shown in fig. 4, and is described in detail as follows:
1) Step 1, confirming information such as a gear shaft structure, working temperature, material properties and the like;
2) Step 2, developing three-dimensional model simplification, and removing small detail features such as rounding, chamfering, grooves and the like in order to improve the calculation efficiency;
3) Step 3, adjusting the size of the radial plate, performing mode trial calculation, and if the calculated resonance point is within the range of 80% -95% of the rotating speed, readjusting the size of the radial plate until no resonance point is within the range of 80% -95% of the rotating speed (refer to fig. 5 and 6);
4) Step 4, adjusting the tooth width size, wherein the method is suitable for the situation that the resonance rotating speed of the low-order vibration mode is lower than the lower limit of the common working rotating speed, but the margin is smaller, and the resonance rotating speed of the adjacent high-order vibration mode is near the upper limit of the common working rotating speed (see fig. 5), adjusting the tooth width size by adopting a dichotomy, and performing modal trial calculation until no resonance point exists in the whole common working rotating speed range;
5) Step 5, adjusting the size of the fillet, which is suitable for the situation that the resonance rotating speed of the low-order vibration mode is near the upper limit of the common working rotating speed when frequency division and frequency multiplication are considered, and the resonance rotating speed of the adjacent high-order vibration mode is lower than the lower limit of the common working rotating speed but the margin is smaller (see fig. 6), adjusting the size of the tooth width by adopting a dichotomy, and performing modal trial calculation until no resonance point exists in all the common working rotating speed ranges;
6) Step 6, carrying out modal analysis of a final scheme to obtain natural frequencies of all orders;
7) Step 7, carrying out resonance rotating speed calculation of a final scheme to ensure that no resonance point exists in a common working rotating speed range;
8) And step 8, outputting a final design scheme and a calculation result.
Illustrating:
the dynamic measurement of a thin-spoke plate straight gear shaft of an aero-engine finds that the two-pitch diameter, the three-pitch diameter and the four-pitch diameter resonance excited by the excitation factors of 33E, 33E/2 and 2 x 33E exist, the vibration stress of each vibration mode is not low, the figure of the campbell diagram is shown in figure 7, and all resonance points cannot be adjusted out of the common working rotating speed range only by changing the thickness of the spoke plate of the gear shaft. Therefore, the multi-parameter frequency modulation design method for the thin web spur gear of the aeroengine is provided, meanwhile, the thickness, the tooth width and the round angle of the web are adjusted, the final structural scheme is determined through repeated adjustment, the parameters of the web B are adjusted from 7mm to 8.5mm, the parameters of the tooth width A are adjusted from 13.1mm to 13.5mm, the parameters of the round angle R are adjusted from 3mm to 10mm, a multi-parameter frequency modulation candel diagram is shown in fig. 7, the vibration exciting factors of the gear 33E/2 have no intersection point in the working rotating speed range, the resonance points of the vibration exciting factors of the gear 33E and the vibration exciting factors of the gear 33E are below the slow-running rotating speed (the stay time is short), and the gear shaft can be ensured to have no vibration fatigue risk after the frequency modulation method is adopted, and the gear shaft can work safely and reliably.
Compared with the original method for modulating frequency by only adjusting the thickness of the web, the multi-parameter frequency modulation design method for the thin web spur gear of the aero-engine breaks through the precise control technology of the natural frequency of each order of the spur gear, defines the application range of each design parameter, provides a multi-parameter frequency modulation design flow, can realize that any gear does not have a calculated resonance point in the working rotating speed range, has less weight gain, can carry out structural improvement design depending on the analysis result in the design stage, reduces the possibility of resonance fatigue damage of the gear in working, and further improves the working reliability of the thin web spur gear of the aero-engine.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should 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 (7)
1. The multi-parameter frequency modulation design method for the thin web spur gear of the aeroengine is characterized by comprising the following steps of:
step 1: confirming a preliminary scheme of a gear shaft, and establishing a three-dimensional model of the gear shaft;
step 2: based on a preliminary scheme, performing modal trial calculation to obtain a radial thickness range of the gear shaft without resonance points in a first preset rotating speed range;
when the web thickness range is a non-empty set, setting a preliminary scheme with the web thickness range as a final scheme, and jumping to the step 5;
when the range is an empty set, selecting a corresponding web thickness value when the resonance point is closest to the edge of the first preset rotating speed range; setting a preliminary scheme with the web thickness value as a first scheme, and jumping to the step 3;
step 3: acquiring a tooth width range of the gear shaft without resonance points in a second preset range rotating speed based on the first scheme;
when the tooth width range is a non-empty set, setting a first scheme with the tooth width range as a final scheme, and jumping to the step 5;
when the range is the empty set, selecting a corresponding tooth width value when the resonance point is close to the edge of the second preset rotating speed range; setting the preliminary scheme with the tooth width value as a second scheme, and jumping to the step 4;
step 4: acquiring a fillet size range of the gear shaft without resonance points in a third preset range of rotating speed based on the second scheme;
when the fillet size range is a non-empty set, setting a first scheme with the fillet size range as a final scheme, and jumping to step 5;
when the size range of the round angle is an empty set, jumping to the step 1;
step 5: taking the values of the radial plate thickness range, the tooth width range or the fillet size range in the final scheme to carry out modal analysis of the final scheme;
step 6: and (5) outputting a final scheme when the modal analysis result meets the preset requirement, and returning to the step (5) when the gear shaft of the final scheme does not meet the preset requirement.
2. The aircraft engine thin web spur gear multiparameter tuning design method of claim 1, wherein the first preset rotational speed range is 80% -95% rotational speed.
3. The method for designing the multi-parameter frequency modulation of the thin-web spur gear of the aeroengine according to claim 1, wherein the second preset rotating speed range is that the low-order vibration mode resonance rotating speed of the gear shaft is lower than the lower limit of the common working rotating speed, and the adjacent high-order vibration mode resonance rotating speed is within the preset range of the upper limit of the common working rotating speed.
4. The method for designing the multi-parameter frequency modulation of the thin web spur gear of the aeroengine according to claim 1, wherein the second preset rotating speed range is that the low-order vibration mode resonance rotating speed of the gear shaft is in a preset range of the upper limit of the common working rotating speed when frequency division and frequency multiplication are considered, and the adjacent high-order vibration mode resonance rotating speed is lower than the lower limit of the common working rotating speed.
5. The aircraft engine thin web spur gear multiparameter frequency modulation design method of claim 1, wherein the fillet size range of the gear shaft without resonance points in the third preset range of rotational speed is obtained by adjusting the tooth width size by a dichotomy.
6. The aircraft engine thin web spur gear multiparameter tuning design method of claim 1, wherein the web thickness is less than the tooth width when taking values in the web thickness range.
7. The aircraft engine thin web spur gear multiparameter fm design method of claim 1, wherein the tooth width is determined to be a minimum based on the tooth bending fatigue and contact fatigue strength reserves at values in the tooth width range.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310881777.2A CN117272529A (en) | 2023-07-18 | 2023-07-18 | Multi-parameter frequency modulation design method for thin-web spur gear of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310881777.2A CN117272529A (en) | 2023-07-18 | 2023-07-18 | Multi-parameter frequency modulation design method for thin-web spur gear of aero-engine |
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| CN117272529A true CN117272529A (en) | 2023-12-22 |
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| CN202310881777.2A Pending CN117272529A (en) | 2023-07-18 | 2023-07-18 | Multi-parameter frequency modulation design method for thin-web spur gear of aero-engine |
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| CN (1) | CN117272529A (en) |
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- 2023-07-18 CN CN202310881777.2A patent/CN117272529A/en active Pending
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