CN116541970A - Energy method-based compressor blade vibration reduction optimization design evaluation method - Google Patents
Energy method-based compressor blade vibration reduction optimization design evaluation method Download PDFInfo
- Publication number
- CN116541970A CN116541970A CN202310778221.0A CN202310778221A CN116541970A CN 116541970 A CN116541970 A CN 116541970A CN 202310778221 A CN202310778221 A CN 202310778221A CN 116541970 A CN116541970 A CN 116541970A
- Authority
- CN
- China
- Prior art keywords
- blade
- optimized
- energy
- ratio
- vibration
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000005457 optimization Methods 0.000 title claims abstract description 76
- 230000009467 reduction Effects 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 title claims abstract description 35
- 238000013461 design Methods 0.000 title claims abstract description 33
- 238000011156 evaluation Methods 0.000 title claims abstract description 28
- 238000004458 analytical method Methods 0.000 claims abstract description 23
- 230000000694 effects Effects 0.000 claims abstract description 22
- 230000004044 response Effects 0.000 claims abstract description 7
- 238000013016 damping Methods 0.000 claims description 9
- 238000004364 calculation method Methods 0.000 description 7
- 230000008859 change Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- 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
-
- 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
- G06F2119/06—Power analysis or power optimisation
-
- 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
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- General Engineering & Computer Science (AREA)
- Evolutionary Computation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Automation & Control Theory (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides an energy method-based compressor blade vibration reduction optimization design evaluation method, which comprises the following steps: acquiring a dangerous area of the optimized front blade; calculating the total kinetic energy ratio of the total kinetic energy of the optimized front blade to the total kinetic energy of the optimized rear blade; calculating a first strain energy duty ratio of a dangerous area of the optimized front blade and a second strain energy duty ratio of a dangerous area of the optimized rear blade based on modal analysis; calculating the dangerous area strain energy ratio of the blade before optimization and the blade after optimization according to the total kinetic energy ratio, the first strain energy ratio and the second strain energy ratio; based on the dangerous area strain energy ratio, obtaining the vibration stress ratio of the dangerous area of the optimized front blade and the optimized rear blade; and (5) evaluating the vibration reduction optimizing effect of the blade after optimization based on the vibration stress ratio. According to the evaluation method, on the basis of harmonic response analysis, energy distribution is introduced to accurately evaluate the vibration reduction optimizing effect of the blade.
Description
Technical Field
The invention belongs to the field of aero-engines, relates to a vibration reduction optimization design technology of a compressor blade, and particularly relates to an energy method-based vibration reduction optimization design evaluation method of the compressor blade.
Background
Common faults in the development and use processes of the aero-engine comprise cracks and corner falling of the compressor blade, and when the compressor blade falls off the corner, the compressor blade is easy to damage or even break the later stage blade, so that the test run and the use safety of the engine are seriously affected. The main cause of the crack or corner failure of the compressor blade is the high cycle fatigue problem caused by resonance, and the fracture of the blade with the type of failure is often characterized by high cycle fatigue, and the working time of most failure parts is relatively long.
Optimization of blade structure is often required to address high cycle fatigue failure of the blade due to resonance, but optimization of how to evaluate the vibration damping effect of the blade has been a problem in the industry. At present, the traditional analysis method generally adopts a harmonic response analysis method, but because the blade structure is changed after optimization, calculation references are inconsistent, so that calculation results have larger deviation, therefore, the harmonic response analysis method only can provide the blade optimization direction, and the vibration reduction optimization effect of the blade is difficult to embody.
Disclosure of Invention
The invention aims to solve the problems that the comparison standard is inconsistent and the calculation result is larger and the vibration reduction optimization effect of a blade is difficult to evaluate due to the change of the blade structure before and after the optimization of the blade of the air compressor, and provides an energy method-based air compressor blade vibration reduction optimization design evaluation method.
The technical scheme for realizing the aim of the invention is as follows: an energy method-based compressor blade vibration reduction optimization design evaluation method comprises the following steps:
s2, acquiring a dangerous area of the optimized front blade;
s3, calculating the total kinetic energy ratio of the total kinetic energy of the optimized front blade to the total kinetic energy of the optimized rear blade;
s4, calculating a first strain energy duty ratio of a dangerous area of the optimized front blade and a second strain energy duty ratio of a dangerous area of the optimized rear blade based on modal analysis;
s5, calculating the dangerous area strain energy ratio of the blade before optimization and the blade after optimization according to the total kinetic energy ratio, the first strain energy ratio and the second strain energy ratio;
s6, based on the strain energy ratio of the dangerous area, obtaining the vibration stress ratio of the dangerous area of the blade before optimization and the dangerous area of the blade after optimization;
s7, evaluating the vibration reduction optimization effect of the optimized blade based on the vibration stress ratio.
Further, in the step S2, the acquiring the dangerous area of the blade to be optimized includes:
s21, acquiring vibration dangerous orders of the blade to be optimized, and strain energy distribution, relative vibration stress distribution, pitch line and frequency under the vibration dangerous orders based on modal analysis;
s22, dividing the blade to be optimized into a plurality of areas according to pitch lines, and acquiring dangerous areas in the plurality of areas under the vibration dangerous orders according to the relative vibration stress distribution, wherein the dangerous areas are corresponding dangerous areas under the vibration dangerous orders.
Further, in the step S22, the step of obtaining the dangerous area from the plurality of areas under the vibration dangerous order according to the relative vibration stress distribution includes:
and acquiring a region corresponding to the maximum relative vibration stress in the relative vibration stress distribution as a dangerous region.
Further, in the step S3, the calculating the total kinetic energy ratio of the total kinetic energy of the optimized front blade to the total kinetic energy of the optimized rear blade includes:
s31, calculating the kinetic energy of each region according to the strain energy distribution, the relative vibration stress distribution and the frequency of the optimized front blade, and summing to obtain the total kinetic energy of the optimized front blade;
calculating the kinetic energy of each region according to the strain energy distribution, the relative vibration stress distribution and the frequency of the optimized blade, and summing to obtain the total kinetic energy of the optimized blade;
s32, calculating the total kinetic energy ratio of the total kinetic energy of the blade before optimization and the total kinetic energy of the blade after optimization.
Still further, in the step S4, the calculating, based on the modal analysis, a first strain energy ratio of the dangerous area of the optimized front blade and a second strain energy ratio of the dangerous area of the optimized rear blade includes:
s41, acquiring total strain energy of the blade based on strain energy distribution in modal analysis;
s42, selecting strain energy in a set range in a dangerous area of the blade, and calculating the ratio of the strain energy to the total strain energy as a strain energy duty ratio, wherein the strain energy duty ratio comprises a first strain energy duty ratio and a second strain energy duty ratio.
Further, in the step S7, the evaluating the vibration damping optimization effect of the optimized blade based on the vibration stress ratio includes:
when the vibration stress ratio is more than 1, the vibration reduction effect of the optimized rear blade is smaller than that of the optimized front blade;
when the vibration stress ratio is smaller than 1, the vibration reduction effect of the optimized rear blade is larger than that of the optimized front blade.
In an improved embodiment, the energy method-based method for evaluating the vibration reduction optimization design of the compressor blade further comprises the following steps:
s8, optimizing the blade after optimization again according to the vibration reduction optimizing effect evaluation result until the vibration stress ratio is smaller than 1.
Further, in the above step, the vibration reduction optimizing blade is obtained after iterative optimization according to the harmonic response analysis result.
In another improved embodiment, the energy method-based compressor blade vibration damping optimization design evaluation method further comprises:
s1, acquiring the mode shapes of the optimized front blade and the optimized rear blade based on mode analysis before vibration reduction optimization design evaluation, and performing vibration reduction optimization design evaluation when the mode shapes of the optimized front blade and the optimized rear blade are the same.
Compared with the prior art, the invention has the beneficial effects that: the evaluation method provided by the invention is suitable for structural optimization design of the blade at each stage of the air compressor, and the vibration reduction optimization effect of the optimized blade can be accurately evaluated through parameters such as the kinetic energy duty ratio, the strain energy ratio and the vibration stress ratio.
Drawings
In order to more clearly illustrate the technical solution of the embodiments of the present invention, the drawings that are needed in the description of the embodiments will be briefly described.
FIG. 1 is a flow chart of an energy method based method for evaluating an optimized design for vibration damping of a compressor blade in an embodiment;
fig. 2 is a schematic view of the positions of 4 pitch lines of a certain type of compressor blade in an embodiment.
Detailed Description
The invention will be further described with reference to specific embodiments, and advantages and features of the invention will become apparent from the description. These examples are merely exemplary and do not limit the scope of the invention in any way. It will be understood by those skilled in the art that various changes and substitutions of details and forms of the technical solution of the present invention may be made without departing from the spirit and scope of the present invention, but these changes and substitutions fall within the scope of the present invention.
The specific embodiment discloses an energy method-based method for evaluating vibration reduction optimization design of a compressor blade, which is shown in fig. 1 and comprises the following steps:
s2, acquiring a dangerous area of the optimized front blade.
S3, calculating the total kinetic energy ratio of the total kinetic energy of the blade before optimization and the total kinetic energy of the blade after optimization.
S4, calculating a first strain energy duty ratio of the dangerous area of the optimized front blade and a second strain energy duty ratio of the dangerous area of the optimized rear blade based on modal analysis.
S5, calculating the dangerous area strain energy ratio of the blade before optimization and the blade after optimization according to the total kinetic energy ratio, the first strain energy ratio and the second strain energy ratio.
S6, based on the dangerous area strain energy ratio, obtaining the vibration stress ratio of the dangerous area of the blade before optimization and the dangerous area of the blade after optimization.
S7, evaluating the vibration reduction optimization effect of the optimized blade based on the vibration stress ratio.
Further, in the step S2, the acquiring the dangerous area of the blade to be optimized includes:
s21, acquiring vibration dangerous orders of the blade to be optimized, and strain energy distribution, relative vibration stress distribution, pitch line and frequency under the vibration dangerous orders based on modal analysis;
s22, dividing the blade to be optimized into a plurality of areas according to pitch lines, and acquiring dangerous areas in the plurality of areas under the vibration dangerous orders according to the relative vibration stress distribution, wherein the dangerous areas are corresponding dangerous areas under the vibration dangerous orders.
The method for analyzing the modal is an effective means in the method for analyzing the vibration characteristics, a response prediction model of the blade under the known excitation condition is established by analyzing the dynamic characteristics of the blade, the dynamic characteristics of the blade under the actual working state are predicted, and then the modal array shape of the blade is obtained.
For example: referring to fig. 2, a schematic view of positions of 4 pitch lines of a certain type of compressor blade is shown, the blade is of a typical blade tip high-order chord bending vibration type, the blade tip is in M-shaped vibration, the vibration type is divided into four pitch lines, the four pitch lines divide the blade into 4 areas, wherein the distance between the pitch line and the mass center of each area is the following mass center radiusAnd->。
Further, in the step S22, the step of obtaining the dangerous area from the plurality of areas under the vibration dangerous order according to the relative vibration stress distribution includes:
and acquiring a region corresponding to the maximum relative vibration stress in the relative vibration stress distribution as a dangerous region.
Further, in the step S3, the calculating the total kinetic energy ratio of the total kinetic energy of the optimized front blade to the total kinetic energy of the optimized rear blade includes:
s31, calculating the kinetic energy of each region according to the strain energy distribution, the relative vibration stress distribution and the frequency of the optimized front blade, and summing to obtain the total kinetic energy of the optimized front blade;
calculating the kinetic energy of each region according to the strain energy distribution, the relative vibration stress distribution and the frequency of the optimized blade, and summing to obtain the total kinetic energy of the optimized blade;
s32, calculating the total kinetic energy ratio of the total kinetic energy of the blade before optimization and the total kinetic energy of the blade after optimization.
What should be stated here is: in general, the total energy of blade body is formed from strain energy and kinetic energy when blade is vibrated, and the calculation formula of total energyThe method comprises the following steps:wherein->Is the elastic modulus; />Is strain; m is the mass of the blade; />Is frequency; r is the barycenter radius of the blade; v is the blade volume.
And the kinetic energy of the blade in the ideal state in the vibration processAnd strain energy->Continuously interconverting, wherein when the strain energy is maximum, the kinetic energy is 0; similarly, when the kinetic energy is maximum, the strain energy is 0. In the specific embodiment, a kinetic energy calculation formula is selected to optimize the total energy before and after +.>Scaling to the same reference. Defining the state 1 before blade optimization and the state 2 after blade optimization, and then the total energy ratio of the two states is as follows:
wherein (1)>And->Total energy of the optimized front blade and the optimized rear blade respectively; />And->The kinetic energy of the optimized front blade and the optimized rear blade respectively; />And->The mass of the optimized front blade and the mass of the optimized rear blade are respectively; />And->The frequencies of the optimized front blade and the optimized rear blade are respectively; />And->The blade centroid radius of the optimized front blade and the optimized rear blade respectively; />And->The radius of the centroid 1 of the optimized front blade hazard zone and the centroid 2 of the optimized rear blade hazard zone are respectively.
In this embodiment, when the total kinetic energy of the optimized front blade and the total kinetic energy of the optimized rear blade are calculated, the total kinetic energy is selected to be the maximum value, that is, the default strain energy is 0, and the total energy is the total kinetic energy, and the total energy before and after the optimization is converted to the same comparison standard through the formula.
Still further, in the step S4, the calculating, based on the modal analysis, a first strain energy ratio of the dangerous area of the optimized front blade and a second strain energy ratio of the dangerous area of the optimized rear blade includes:
s41, acquiring total strain energy of the blade based on strain energy distribution in modal analysis;
s42, selecting strain energy in a set range in a dangerous area of the blade, and calculating the ratio of the strain energy to the total strain energy as a strain energy duty ratio, wherein the strain energy duty ratio comprises a first strain energy duty ratio and a second strain energy duty ratio.
When the dangerous area of the blade before optimization is optimized, the proportion of the strain energy at the position to the strain energy of the whole blade body changes with the optimization, in the step, the proportion of the strain energy of the area to the total strain energy of the blade body can be calculated by taking the strain value in the set range of the dangerous area, such as selecting 1cm x 1cm area, and the proportion of the strain energy of the area to the total strain energy of the blade body is used as the strain energy proportion of the dangerous area before and after the blade optimization, including the first strain energy proportionAnd a second strain energy ratio->。
From the results of the above steps S3 and S4, the dangerous area strain energy ratio of the optimized front blade to the optimized rear blade in step S5 can be obtainedThe calculation formula of (2) is as follows: />
Since strain energy is proportional to the square of strain, i.e., strain energy is proportional to the square of stress, the formula can beCalculating a vibration stress ratio of a dangerous area of the optimized front and rear blades, wherein +.>And->Vibration stresses in the danger zone of the optimized front blade and the optimized rear blade, respectively.
Further, in the step S7, the evaluating the vibration damping optimization effect of the optimized blade based on the vibration stress ratio includes:
when the vibration stress ratio is more than 1, the vibration reduction effect of the optimized rear blade is smaller than that of the optimized front blade;
when the vibration stress ratio is smaller than 1, the vibration reduction effect of the optimized rear blade is larger than that of the optimized front blade.
In a modified embodiment of this specific embodiment, referring to fig. 1, the method for evaluating the vibration reduction optimization design of a compressor blade based on the energy method further includes:
s8, optimizing the blade after optimization again according to the vibration reduction optimizing effect evaluation result until the vibration stress ratio is smaller than 1.
Preferably, in the above step, the vibration reduction optimizing blade is obtained after iterative optimization according to the harmonic response analysis result.
In another modified embodiment of this specific embodiment, referring to fig. 1, the energy method-based method for evaluating the vibration damping optimization design of a compressor blade further includes:
s1, acquiring the mode shapes of the optimized front blade and the optimized rear blade based on mode analysis before vibration reduction optimization design evaluation, and performing vibration reduction optimization design evaluation when the mode shapes of the optimized front blade and the optimized rear blade are the same.
What needs to be specifically stated is: if the mode shapes before and after the optimization change, the method for evaluating the vibration reduction optimization design of the compressor blade disclosed by the embodiment is not applicable any more and needs to be re-evaluated in other modes.
The above evaluation method has the following advantages: the method is suitable for structural optimization design of the blades at each stage of the air compressor, the vibration reduction optimization effect of the optimized blades can be accurately evaluated through parameters such as kinetic energy duty ratio, strain energy ratio and vibration stress ratio, the complicated finite element design iteration in the existing evaluation method is reduced, and more accurate calculation results can be used for reducing test cost and shortening the blade design period.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (9)
1. The energy method-based compressor blade vibration reduction optimization design evaluation method is characterized by comprising the following steps of:
acquiring a dangerous area of the optimized front blade;
calculating the total kinetic energy ratio of the total kinetic energy of the optimized front blade to the total kinetic energy of the optimized rear blade;
calculating a first strain energy duty ratio of a dangerous area of the optimized front blade and a second strain energy duty ratio of a dangerous area of the optimized rear blade based on modal analysis;
calculating the dangerous area strain energy ratio of the blade before optimization and the blade after optimization according to the total kinetic energy ratio, the first strain energy ratio and the second strain energy ratio;
based on the dangerous area strain energy ratio, obtaining the vibration stress ratio of the dangerous area of the optimized front blade and the optimized rear blade;
and (5) evaluating the vibration reduction optimizing effect of the blade after optimization based on the vibration stress ratio.
2. The energy method-based assessment method for optimizing vibration damping design of a compressor blade according to claim 1, wherein the acquiring the dangerous area of the blade to be optimized comprises:
based on modal analysis, obtaining the vibration dangerous orders of the blade to be optimized, and strain energy distribution, relative vibration stress distribution, pitch line and frequency under the vibration dangerous orders;
dividing the blade to be optimized into a plurality of areas according to pitch lines, and acquiring dangerous areas in the plurality of areas under the vibration dangerous orders according to the relative vibration stress distribution, wherein the dangerous areas are corresponding dangerous areas under the vibration dangerous orders.
3. The energy method-based method for evaluating an optimal design of vibration damping of a compressor blade according to claim 2, wherein the acquiring dangerous areas of the plurality of areas under the vibration dangerous order according to the relative vibration stress distribution comprises:
and acquiring a region corresponding to the maximum relative vibration stress in the relative vibration stress distribution as a dangerous region.
4. The energy method-based compressor blade vibration reduction optimization design evaluation method according to claim 2, wherein the calculating the total kinetic energy ratio of the total kinetic energy of the optimized front blade to the total kinetic energy of the optimized rear blade comprises:
calculating the kinetic energy of each region according to the strain energy distribution, the relative vibration stress distribution and the frequency of the optimized front blade, and obtaining the total kinetic energy of the optimized front blade after summing;
calculating the kinetic energy of each region according to the strain energy distribution, the relative vibration stress distribution and the frequency of the optimized blade, and summing to obtain the total kinetic energy of the optimized blade;
and calculating the total kinetic energy ratio of the total kinetic energy of the optimized front blade to the total kinetic energy of the optimized rear blade.
5. The energy method-based compressor blade vibration reduction optimization design evaluation method according to claim 2, wherein the calculating a first strain energy ratio of a dangerous area of an optimized front blade and a second strain energy ratio of a dangerous area of an optimized rear blade based on modal analysis includes:
based on strain energy distribution in modal analysis, obtaining total strain energy of the blade;
and selecting strain energy in a set range in a dangerous area of the blade, and calculating the ratio of the strain energy to the total strain energy as a strain energy duty ratio, wherein the strain energy duty ratio comprises a first strain energy duty ratio and a second strain energy duty ratio.
6. The energy method-based compressor blade vibration reduction optimization design evaluation method according to claim 1, wherein the vibration reduction optimization effect evaluation of the optimized blade based on the vibration stress ratio comprises the following steps:
when the vibration stress ratio is more than 1, the vibration reduction effect of the optimized rear blade is smaller than that of the optimized front blade;
when the vibration stress ratio is smaller than 1, the vibration reduction effect of the optimized rear blade is larger than that of the optimized front blade.
7. The energy method-based compressor blade vibration damping optimization design evaluation method according to claim 1, further comprising:
and (3) optimizing the blade after optimization again according to the vibration reduction optimizing effect evaluation result until the vibration stress ratio is less than 1.
8. The energy method-based compressor blade vibration reduction optimization design evaluation method according to claim 1, wherein the vibration reduction optimization blade is obtained after iterative optimization according to a harmonic response analysis result.
9. The energy method-based compressor blade vibration reduction optimization design evaluation method according to any one of claims 1 to 8, further comprising:
before vibration reduction optimization design evaluation, the mode shapes of the front blade and the rear blade are obtained based on mode analysis, and when the mode shapes of the front blade and the rear blade are the same, vibration reduction optimization design evaluation is performed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310778221.0A CN116541970B (en) | 2023-06-29 | 2023-06-29 | Energy method-based compressor blade vibration reduction optimization design evaluation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310778221.0A CN116541970B (en) | 2023-06-29 | 2023-06-29 | Energy method-based compressor blade vibration reduction optimization design evaluation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116541970A true CN116541970A (en) | 2023-08-04 |
| CN116541970B CN116541970B (en) | 2023-10-03 |
Family
ID=87449079
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310778221.0A Active CN116541970B (en) | 2023-06-29 | 2023-06-29 | Energy method-based compressor blade vibration reduction optimization design evaluation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116541970B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116842876A (en) * | 2023-09-01 | 2023-10-03 | 中国航发四川燃气涡轮研究院 | Vibration stress back-pushing method for guide vane of air compressor |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101158990A (en) * | 2007-11-29 | 2008-04-09 | 北京航空航天大学 | Big and small blade integral leaf disc structural integrity fluid-solid coupling integrated design method |
| US20080124480A1 (en) * | 2004-09-03 | 2008-05-29 | Mo-How Herman Shen | Free layer blade damper by magneto-mechanical materials |
| CN103308289A (en) * | 2013-05-03 | 2013-09-18 | 北京航空航天大学 | Damping characteristic experiment device for saw-toothed triple-mounted shrouded blade |
| US20150086366A1 (en) * | 2013-09-24 | 2015-03-26 | Robert Jeffrey Barnes | Wind turbine blade and blade hub |
| CN104573199A (en) * | 2014-12-19 | 2015-04-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Topological optimization method for constraining and damping blades of aeroengine |
| CN106096098A (en) * | 2016-06-02 | 2016-11-09 | 南京航空航天大学 | A kind of turbo blade Vibration Damping Analysis optimization method |
| CN109858135A (en) * | 2019-01-25 | 2019-06-07 | 西安热工研究院有限公司 | A kind of calculation method that the through-flow head of district's blade safety of steam turbine low-pressure is checked |
| CN111950169A (en) * | 2019-05-14 | 2020-11-17 | 中国航发商用航空发动机有限责任公司 | Method and device for determining vibration limit of blade tip of rotor blade of aircraft engine |
| CN113605993A (en) * | 2021-07-26 | 2021-11-05 | 中国船舶重工集团公司第七0三研究所 | High-pressure turbine moving blade set with damping vibration attenuation blocks |
| CN114117849A (en) * | 2021-11-09 | 2022-03-01 | 北京航空航天大学 | Blade shroud damping vibration attenuation analysis method of low-pressure turbine blade/disk rotor |
| CN114154363A (en) * | 2021-11-09 | 2022-03-08 | 北京航空航天大学 | Method for analyzing vibration attenuation characteristics of high-pressure turbine blade edge plate damper |
| CN114354112A (en) * | 2022-03-18 | 2022-04-15 | 中国航发四川燃气涡轮研究院 | Blade multi-order coupling vibration fatigue analysis method |
| CN114441122A (en) * | 2020-11-06 | 2022-05-06 | 中国航发商用航空发动机有限责任公司 | Vibration fatigue test device and method for composite material fan blade |
| CN114840944A (en) * | 2022-05-16 | 2022-08-02 | 北京航空航天大学 | Crack initiation simulation piece design method based on damage control parameter consistency |
-
2023
- 2023-06-29 CN CN202310778221.0A patent/CN116541970B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080124480A1 (en) * | 2004-09-03 | 2008-05-29 | Mo-How Herman Shen | Free layer blade damper by magneto-mechanical materials |
| CN101158990A (en) * | 2007-11-29 | 2008-04-09 | 北京航空航天大学 | Big and small blade integral leaf disc structural integrity fluid-solid coupling integrated design method |
| CN103308289A (en) * | 2013-05-03 | 2013-09-18 | 北京航空航天大学 | Damping characteristic experiment device for saw-toothed triple-mounted shrouded blade |
| US20150086366A1 (en) * | 2013-09-24 | 2015-03-26 | Robert Jeffrey Barnes | Wind turbine blade and blade hub |
| CN104573199A (en) * | 2014-12-19 | 2015-04-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Topological optimization method for constraining and damping blades of aeroengine |
| CN106096098A (en) * | 2016-06-02 | 2016-11-09 | 南京航空航天大学 | A kind of turbo blade Vibration Damping Analysis optimization method |
| CN109858135A (en) * | 2019-01-25 | 2019-06-07 | 西安热工研究院有限公司 | A kind of calculation method that the through-flow head of district's blade safety of steam turbine low-pressure is checked |
| CN111950169A (en) * | 2019-05-14 | 2020-11-17 | 中国航发商用航空发动机有限责任公司 | Method and device for determining vibration limit of blade tip of rotor blade of aircraft engine |
| CN114441122A (en) * | 2020-11-06 | 2022-05-06 | 中国航发商用航空发动机有限责任公司 | Vibration fatigue test device and method for composite material fan blade |
| CN113605993A (en) * | 2021-07-26 | 2021-11-05 | 中国船舶重工集团公司第七0三研究所 | High-pressure turbine moving blade set with damping vibration attenuation blocks |
| CN114117849A (en) * | 2021-11-09 | 2022-03-01 | 北京航空航天大学 | Blade shroud damping vibration attenuation analysis method of low-pressure turbine blade/disk rotor |
| CN114154363A (en) * | 2021-11-09 | 2022-03-08 | 北京航空航天大学 | Method for analyzing vibration attenuation characteristics of high-pressure turbine blade edge plate damper |
| CN114354112A (en) * | 2022-03-18 | 2022-04-15 | 中国航发四川燃气涡轮研究院 | Blade multi-order coupling vibration fatigue analysis method |
| CN114840944A (en) * | 2022-05-16 | 2022-08-02 | 北京航空航天大学 | Crack initiation simulation piece design method based on damage control parameter consistency |
Non-Patent Citations (2)
| Title |
|---|
| 徐嘉勋: "汽轮机叶片设计问题及其事故调查分析 第二章 设计中的材料准则", 《汽轮机技术》, no. 1, pages 19 - 33 * |
| 董妍: "航空发动机风扇叶片振动应力分析", 《中国新技术新产品》, no. 11, pages 27 - 28 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116842876A (en) * | 2023-09-01 | 2023-10-03 | 中国航发四川燃气涡轮研究院 | Vibration stress back-pushing method for guide vane of air compressor |
| CN116842876B (en) * | 2023-09-01 | 2024-01-09 | 中国航发四川燃气涡轮研究院 | Vibration stress back-pushing method for guide vane of air compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116541970B (en) | 2023-10-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN116541970B (en) | Energy method-based compressor blade vibration reduction optimization design evaluation method | |
| CN107038311B (en) | Wind turbine blade resonance type fatigue test load configuration method | |
| CN110765569A (en) | Multi-objective optimization method for vibration reduction of air conditioner pipeline structure, computer readable storage medium and terminal | |
| CN112084583B (en) | Rotor blade life prediction method and system based on digital twin | |
| Witek et al. | Fatigue analysis of compressor blade with simulated foreign object damage | |
| CN106777783B (en) | Method for predicting blade cracks of aircraft engine | |
| CN111881564B (en) | Method for predicting amplitude-variable fatigue life of mechanical structure | |
| CN111563340A (en) | Rotor blade dynamic stress reconstruction method and system | |
| CN112906281A (en) | Turbine disc crack propagation reliability analysis method based on quasi-Monte Carlo sampling | |
| Clark et al. | Using CFD to reduce resonant stresses on a single-stage, high-pressure turbine blade | |
| CN116305542A (en) | Engine blade multi-order dynamic stress measurement design method based on strain gauge | |
| CN114117849A (en) | Blade shroud damping vibration attenuation analysis method of low-pressure turbine blade/disk rotor | |
| US9835034B2 (en) | Method for detuning a rotor-blade cascade | |
| CN114528743B (en) | Method for calculating dynamic stress monitoring limit value of rotor blade in wide rotating speed range | |
| CN109992906B (en) | Micro-abrasion calculation method for heat transfer tube of steam generator under pump-induced pulsating pressure | |
| CN109344522B (en) | Method and system for calculating grinding quantity of stationary blade of axial flow compressor | |
| CN115204013A (en) | Method for predicting service life of material in multi-axis stress state | |
| CN116050202A (en) | Chaboche blade fatigue life prediction model and method suitable for various average stress performances | |
| CN115758603A (en) | Method for predicting multi-working-condition creep/stress rupture life of turbine blade of aircraft engine | |
| CN115563722A (en) | Analysis method for forced response of blisk | |
| CN114186449B (en) | She Panshan section rigidity evaluation method based on beam bending theory | |
| JP2019515178A (en) | Method for contouring blades of an axial flow turbomachine | |
| CN110489887A (en) | Modeling method that a kind of turbine blade based on CFD is through-flow | |
| Fedorov et al. | Reliable FE modeling of chord-wise blade modes in compressor design process | |
| CN104991990A (en) | Key structure optimum design method for bar cutter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |