CN111723510A - Identification method of dangerous mode of blade - Google Patents
Identification method of dangerous mode of blade Download PDFInfo
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- CN111723510A CN111723510A CN202010595155.XA CN202010595155A CN111723510A CN 111723510 A CN111723510 A CN 111723510A CN 202010595155 A CN202010595155 A CN 202010595155A CN 111723510 A CN111723510 A CN 111723510A
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- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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Abstract
The disclosure relates to a method for identifying a blade danger mode, which comprises the following steps: determining excitation sources of the blades and excitation areas of the excitation sources; when the blade is a rotor blade, determining the maximum vibration data of the blade in the excitation region of all resonance modes excited by each excitation source and the maximum vibration data of the whole blade within the working rotating speed range of the rotor blade; determining the influence coefficients of all the resonance modes excited by each excitation source according to the maximum vibration data of the blade in the excitation region of all the resonance modes excited by each excitation source and the maximum vibration data of the whole blade; determining the resonant rotation speed, the vibration stress distribution and the steady-state stress of the blade; weighting and scoring the influence coefficients according to the resonance rotating speed, the vibration stress distribution and the steady-state stress, and determining the score of the influence coefficients; and judging the dangerous modes of the blades according to the scores.
Description
Technical Field
The disclosure relates to the technical field of impeller machinery, in particular to a method for identifying dangerous modes of blades.
Background
In recent years, as the performance requirements of impeller machinery (such as an aircraft engine) are increased, the thickness of the blade tends to be thinner and thinner, the frequency of the blade is also denser, and faults of the blade caused by high-order vibration occur. The low rigidity of the blade and the coupling of the disk can bring high density of natural frequency, and simultaneously, the number of excitation structures on the upstream and the downstream of the blade is large.
In the prior art, the low-order resonance of the blade is usually required to be avoided, and the high-order mode is rarely involved. The existing design technology does not relate to high-order modes, and hazardous high-order modal resonances cannot be identified in the design stage, so that the hazardous high-order modal resonances cannot be avoided in the design stage.
It is to be noted that the information disclosed in the above background section is only for enhancement of understanding of the background of the present disclosure, and thus may include information that does not constitute prior art known to those of ordinary skill in the art.
Disclosure of Invention
The invention aims to provide a method for identifying dangerous modes of a blade, which can identify dangerous modes in a known excitation range of the blade.
According to an aspect of the present disclosure, there is provided an identification method of a blade risk modality, the identification method including:
determining excitation sources of the blades and excitation areas of the excitation sources;
when the blade is a rotor blade, determining the maximum vibration data of the blade in the excitation region of all resonance modes excited by each excitation source and the maximum vibration data of the whole blade within the working rotating speed range of the rotor blade;
determining the influence coefficients of all the resonance modes excited by each excitation source according to the maximum vibration data of the blade in the excitation region of all the resonance modes excited by each excitation source and the maximum vibration data of the whole blade;
determining the resonant rotation speed, the vibration stress distribution and the steady-state stress of the blade;
weighting and scoring the influence coefficients according to the resonance rotating speed, the vibration stress distribution and the steady-state stress, and determining the score of the influence coefficients;
and judging the dangerous modes of the blades according to the scores.
In an exemplary embodiment of the present disclosure, the identification method further includes:
and when the blade is a stator blade, determining the maximum vibration data of the blade in the excitation area of all resonance modes excited by each excitation source and the maximum vibration data of the whole blade.
In an exemplary embodiment of the present disclosure, discriminating a danger modality of the blade according to the score includes:
presetting a target value;
and when the score is larger than or equal to the target value, judging that the blade is in a dangerous mode.
In an exemplary embodiment of the present disclosure, the method further includes the step of determining a danger mode of the blade according to the score, further including:
and when the score is smaller than the target value, judging that the blade is not in a dangerous mode.
In an exemplary embodiment of the present disclosure, the vibration data is vibration displacement.
In an exemplary embodiment of the present disclosure, the vibration data is a vibration stress.
In an exemplary embodiment of the disclosure, a ratio of maximum vibration data of the blade in the excitation region of all resonance modes excited by each excitation source to maximum vibration data of the entire blade is the influence coefficient.
In an exemplary embodiment of the present disclosure, excitation sources of a blade and an excitation region of each of the excitation sources are determined through a flow field test or a steady flow field analysis.
In an exemplary embodiment of the present disclosure, the steady state stress is determined according to finite element analysis.
In an exemplary embodiment of the present disclosure, the resonant rotational speed and the vibratory stress distribution are determined from a vibration analysis.
According to the method for identifying the dangerous modes of the blade, when the blade is a rotor blade, the influence coefficients of all the resonance modes excited by each excitation source can be determined according to the maximum vibration data of the blade in the excitation region of all the resonance modes excited by each excitation source and the maximum vibration data of the whole blade, then the influence coefficients are weighted and graded according to the resonance rotating speed, the vibration stress distribution and the steady-state stress, the values of the influence coefficients are determined, and therefore the dangerous modes of the blade are judged according to the values; the method has the advantages that hazardous high-order modal resonances can be identified in the design stage and avoided in the design stage, so that the hazardous high-order modal resonances can be avoided being discovered only in the test or use stage, the design is prevented from being repeated, and huge time, labor and material resource costs are avoided.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.
FIG. 1 is a prior art Campbell diagram of a leaf;
FIG. 2 is a flow chart of a method for identifying a blade risk mode according to an embodiment of the present disclosure;
FIG. 3 is a graph of excitation load spectra of a leading edge of a blade provided in accordance with an embodiment of the present disclosure;
FIG. 4 is a graph of excitation load spectra of a trailing edge of a blade provided in accordance with an embodiment of the present disclosure;
FIG. 5 is a graph illustrating variation of excitation loads along a chord length of an excitation source upstream of a blade according to an embodiment of the present disclosure;
FIG. 6 is a graph illustrating variation of excitation loads along a chord length of an excitation source downstream of a blade according to an embodiment of the present disclosure;
FIG. 7 is a graph illustrating a centrifugal impeller blade vibration displacement according to an embodiment of the present disclosure;
fig. 8 is a vibration displacement distribution diagram of a certain excitation influence area of a centrifugal impeller blade according to an embodiment of the present disclosure.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided to give a thorough understanding of embodiments of the disclosure. One skilled in the relevant art will recognize, however, that the subject matter of the present disclosure can be practiced without one or more of the specific details, or with other methods, steps, etc. In other instances, well-known technical solutions have not been shown or described in detail to avoid obscuring aspects of the present disclosure.
The terms "a," "an," "the," and "" the "are used to indicate the presence of one or more elements/components/etc.; the terms "comprising" and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. other than the listed elements/components/etc.
Applicants have found that in the design of the blade vibrations, resonances are usually avoided by means of a Campbell diagram (as shown in fig. 1). However, due to the low rigidity of the blade and the high density of the natural frequency brought by the coupling of the disks, and the large number of excitation structures on the upstream and downstream of the blade, it is impossible to avoid all resonances (especially high orders) by using a Campbell diagram (Campbell diagram) method.
In the present exemplary embodiment, a method for identifying a blade risk mode is provided, as shown in fig. 2, the method includes:
s100, determining excitation sources of the blades and excitation areas of the excitation sources;
s200, when the blade is a rotor blade, determining the maximum vibration data of the blade in the excitation region of all resonance modes excited by each excitation source and the maximum vibration data of the whole blade in the working rotating speed range of the rotor blade;
step S300, determining influence coefficients of all resonance modes excited by each excitation source according to maximum vibration data of blades in an excitation area of all resonance modes excited by each excitation source and maximum vibration data of the whole blade;
s400, determining the resonant rotation speed, the vibration stress distribution and the steady-state stress of the blade;
s500, weighting and grading the influence coefficients according to the resonance rotating speed, the vibration stress distribution and the steady-state stress, and determining the score of the influence coefficients;
and S600, judging the danger modes of the blades according to the scores.
According to the method for identifying the dangerous modes of the blade, when the blade is a rotor blade, the influence coefficients of all the resonance modes excited by each excitation source can be determined according to the maximum vibration data of the blade in the excitation region of all the resonance modes excited by each excitation source and the maximum vibration data of the whole blade, then the influence coefficients are weighted and graded according to the resonance rotating speed, the vibration stress distribution and the steady-state stress, the values of the influence coefficients are determined, and therefore the dangerous modes of the blade are judged according to the values; the method has the advantages that hazardous high-order modal resonances can be identified in the design stage and avoided in the design stage, so that the hazardous high-order modal resonances can be avoided being discovered only in the test or use stage, the design is prevented from being repeated, and huge time, labor and material resource costs are avoided.
Next, the steps of the blade risk mode identification method in the present exemplary embodiment will be further described.
In step S100, the excitation sources of the blades and the excitation regions of the respective excitation sources are determined.
Specifically, as shown in fig. 3-6; the main excitation sources borne by the blade and the influence areas thereof, namely the excitation areas of all the excitation sources, can be determined through unsteady flow field analysis or flow field test. Wherein, the abscissa of fig. 3 and 4 is Amplitude (Frequency) and the ordinate is Frequency (Amplitude); the abscissa of fig. 5 and 6 is the chord length (chord) of the blade, and the ordinate is the frequency (Amplitude), where span is the chord length.
In step S200, when the blade is a rotor blade, the maximum vibration data of the blade and the maximum vibration data of the entire blade in the excitation region of all the resonance modes excited by each excitation source are determined within the operating rotational speed range of the rotor blade.
Specifically, according to the main excitation sources and the influence areas thereof determined by the steps, when the blade is a rotor blade, in the working rotating speed range of the rotor blade, the maximum vibration data of the blade in the excitation areas of all resonance modes excited by the excitation sources and the maximum vibration data of the whole blade are calculated; when the blade is a stator blade and the blade has no working rotating speed range, the maximum vibration data of the blade in the excitation region of all resonance modes excited by each excitation source and the maximum vibration data of the whole blade are directly calculated.
Wherein the vibration data may be vibration displacement or vibration stress. The vibration displacement or vibration stress used for calculating the influence coefficient can be obtained by vibration analysis or vibration test, and the vibration displacement or the displacement stress can be a total amount or a component in a certain direction.
In step S300, the influence coefficients of all the resonance modes excited by each excitation source are determined based on the maximum vibration data of the blade in the excitation region of all the resonance modes excited by each excitation source and the maximum vibration data of the entire blade.
Specifically, according to the maximum vibration data of the blade in the excitation region of all the resonance modes excited by each excitation source and the maximum vibration data of the whole blade obtained in the above steps, the influence coefficients of all the resonance modes excited by each excitation source are respectively calculated. The ratio of the maximum vibration data of the blade in the excitation region of all resonance modes excited by the excitation source to the maximum vibration data of the whole blade is an influence coefficient.
The influence coefficient calculation formula is as follows:
wherein:
Anithe maximum vibration displacement or the maximum stress of the ith excitation source in a main influence area of the blade in the nth-order mode;
Anmaximum vibrational displacement or vibrational stress in the nth order mode of the blade.
For example, fig. 7 and 8 show the distribution of the vibration displacement of the centrifugal impeller blade and the distribution of the vibration displacement of the centrifugal impeller blade in a certain excitation influence area, and the influence coefficient of a certain centrifugal impeller blade under 17-fold frequency excitation is shown in table 1:
table 1:
in step S400, the resonant rotational speed, vibratory stress distribution, and steady state stress of the blade are determined.
Specifically, the steady state stress may be determined according to finite element analysis; and determining the resonance rotating speed and the vibration stress distribution according to vibration analysis.
In step S500, the influence coefficients are weighted and scored according to the resonance rotation speed, the vibration stress distribution, and the steady-state stress, and the score of the influence coefficients is determined.
Specifically, the influence coefficients are weighted and scored according to the resonance rotating speed, the vibration stress distribution and the steady-state stress, and the score of the influence coefficients is determined.
In step S600, the danger mode of the blade is judged according to the score.
Specifically, the method for distinguishing the danger modes of the blades according to the scores comprises the following steps: presetting a target value; when the score is larger than or equal to the target value, judging that the blade is in a dangerous mode; and when the score is smaller than the target value, judging that the blade is not in the dangerous mode. The preset value can be obtained according to specific experience, for example, the preset value can be a value related to an influence coefficient, and when the preset value is greater than or equal to 20%, it is determined that the blade is in a dangerous mode. Of course, when the influence coefficient is greater than or equal to 10% or 30%, it may be determined that the blade is in the dangerous mode, and a person skilled in the art may take values according to specific situations, which is not limited by the present disclosure.
The weighted score of the influence coefficient is used as a standard for judging the danger mode and the danger degree thereof, and can also be used as an index for evaluating the improved design effect. For example, when the influence coefficient is greater than 60%, the degree of danger of the blade may be considered to be large. Of course, when the influence coefficient is greater than 50% or 70%, the risk degree of the blade is considered to be greater, and a person skilled in the art can take values according to specific situations, which is not limited by the disclosure.
The method can identify the dangerous mode and the dangerous degree of the blade in the working rotating speed range of the blade, can improve the dangerous mode in the design stage and evaluate the improved design effect in all modes in the known excitation frequency range without avoiding resonance. The method can be applied to troubleshooting and improved design of the blades of the centrifugal impeller of the aircraft engine, and the centrifugal impeller which is identified according to the method and correspondingly improved works safely and reliably.
Moreover, although the steps of the methods of the present disclosure are depicted in the drawings in a particular order, this does not require or imply that the steps must be performed in this particular order, or that all of the depicted steps must be performed, to achieve desirable results. Additionally or alternatively, certain steps may be omitted, multiple steps combined into one step execution, and/or one step broken down into multiple step executions, etc.
Through the above description of the embodiments, those skilled in the art will readily understand that the exemplary embodiments described herein may be implemented by software, or by software in combination with necessary hardware. Therefore, the technical solution according to the embodiments of the present disclosure may be embodied in the form of a software product, which may be stored in a non-volatile storage medium (which may be a CD-ROM, a usb disk, a removable hard disk, etc.) or on a network, and includes several instructions to enable a computing device (which may be a personal computer, a server, a mobile terminal, or a network device, etc.) to execute the method according to the embodiments of the present disclosure.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
Claims (10)
1. A method for identifying a blade risk mode, comprising:
determining excitation sources of the blades and excitation areas of the excitation sources;
when the blade is a rotor blade, determining the maximum vibration data of the blade in the excitation region of all resonance modes excited by each excitation source and the maximum vibration data of the whole blade within the working rotating speed range of the rotor blade;
determining the influence coefficients of all the resonance modes excited by each excitation source according to the maximum vibration data of the blade in the excitation region of all the resonance modes excited by each excitation source and the maximum vibration data of the whole blade;
determining the resonant rotation speed, the vibration stress distribution and the steady-state stress of the blade;
weighting and scoring the influence coefficients according to the resonance rotating speed, the vibration stress distribution and the steady-state stress, and determining the score of the influence coefficients;
and judging the dangerous modes of the blades according to the scores.
2. The identification method according to claim 1, characterized in that the identification method further comprises:
and when the blade is a stator blade, determining the maximum vibration data of the blade in the excitation area of all resonance modes excited by each excitation source and the maximum vibration data of the whole blade.
3. The method according to claim 1, wherein distinguishing the danger modality of the blade according to the score comprises:
presetting a target value;
and when the score is larger than or equal to the target value, judging that the blade is in a dangerous mode.
4. The method of identifying according to claim 3, wherein discriminating a dangerous modality of the blade based on the score further comprises:
and when the score is smaller than the target value, judging that the blade is not in a dangerous mode.
5. The identification method of claim 1, wherein the vibration data is vibration displacement.
6. The identification method of claim 1, wherein the vibration data is vibration stress.
7. The method according to claim 5 or 6, wherein the ratio of the maximum vibration data of the blade in the excitation region of all the resonance modes excited by each excitation source to the maximum vibration data of the entire blade is the influence coefficient.
8. The identification method according to claim 1, wherein the excitation sources of the blade and the excitation regions of each of the excitation sources are determined by a flow field test or a steady flow field analysis.
9. The identification method of claim 1, wherein the steady state stress is determined according to finite element analysis.
10. The identification method according to claim 1, wherein the resonant rotation speed and the vibratory stress distribution are determined from a vibration analysis.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112487548A (en) * | 2020-11-03 | 2021-03-12 | 中国直升机设计研究所 | Helicopter rotor moving part optimization method based on proofing fatigue load |
| CN113654701A (en) * | 2021-08-24 | 2021-11-16 | 中国航发湖南动力机械研究所 | Dynamic stress measuring device for rotor blade of aircraft engine and application of dynamic stress measuring device |
| CN113984317A (en) * | 2021-10-26 | 2022-01-28 | 中国航发沈阳发动机研究所 | Bidirectional rotating blade disc excitation test device and system |
| CN114151146A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Method for acquiring parameters of airflow excitation force of multi-connected shrouded turbine rotor blade |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104053905A (en) * | 2011-12-20 | 2014-09-17 | 维斯塔斯风力系统集团公司 | Method of controlling wind turbine, and wind turbine |
| KR101480662B1 (en) * | 2014-01-08 | 2015-01-12 | 두산중공업 주식회사 | Wind power generator having blade with anemommter, method for measuring wind velocity, method for controlling operating mode and method for dangerous operating mode warning |
| CN109522592A (en) * | 2018-10-10 | 2019-03-26 | 南京航空航天大学 | A kind of blade of aviation engine FOD, which permits, to be repaired the limit and determines method |
| CN110134990A (en) * | 2019-04-03 | 2019-08-16 | 南京航空航天大学 | The detection method of blade of aviation engine leading edge dangerous position |
-
2020
- 2020-06-28 CN CN202010595155.XA patent/CN111723510B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104053905A (en) * | 2011-12-20 | 2014-09-17 | 维斯塔斯风力系统集团公司 | Method of controlling wind turbine, and wind turbine |
| KR101480662B1 (en) * | 2014-01-08 | 2015-01-12 | 두산중공업 주식회사 | Wind power generator having blade with anemommter, method for measuring wind velocity, method for controlling operating mode and method for dangerous operating mode warning |
| CN109522592A (en) * | 2018-10-10 | 2019-03-26 | 南京航空航天大学 | A kind of blade of aviation engine FOD, which permits, to be repaired the limit and determines method |
| CN110134990A (en) * | 2019-04-03 | 2019-08-16 | 南京航空航天大学 | The detection method of blade of aviation engine leading edge dangerous position |
Non-Patent Citations (1)
| Title |
|---|
| 张俊红等: "流固耦合下轴流压气机叶片振动特性数值研究", 《振动.测试与诊断》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112487548A (en) * | 2020-11-03 | 2021-03-12 | 中国直升机设计研究所 | Helicopter rotor moving part optimization method based on proofing fatigue load |
| CN112487548B (en) * | 2020-11-03 | 2022-05-20 | 中国直升机设计研究所 | Helicopter rotor moving part optimization method based on proofing fatigue load |
| CN113654701A (en) * | 2021-08-24 | 2021-11-16 | 中国航发湖南动力机械研究所 | Dynamic stress measuring device for rotor blade of aircraft engine and application of dynamic stress measuring device |
| CN113654701B (en) * | 2021-08-24 | 2023-07-25 | 中国航发湖南动力机械研究所 | Dynamic stress measuring device for aero-engine rotor blade and application thereof |
| CN114151146A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Method for acquiring parameters of airflow excitation force of multi-connected shrouded turbine rotor blade |
| CN114151146B (en) * | 2021-10-20 | 2023-05-05 | 中国航发四川燃气涡轮研究院 | Method for acquiring airflow exciting force parameters of multi-connection shrouded turbine rotor blade |
| CN113984317A (en) * | 2021-10-26 | 2022-01-28 | 中国航发沈阳发动机研究所 | Bidirectional rotating blade disc excitation test device and system |
| CN113984317B (en) * | 2021-10-26 | 2023-12-15 | 中国航发沈阳发动机研究所 | Bidirectional rotating blade disc excitation test device and system |
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