CN109948187A - Centrifugal compressor wheel disc laryngeal structure optimum design method based on equal-intensity theory - Google Patents
Centrifugal compressor wheel disc laryngeal structure optimum design method based on equal-intensity theory Download PDFInfo
- Publication number
- CN109948187A CN109948187A CN201910121817.7A CN201910121817A CN109948187A CN 109948187 A CN109948187 A CN 109948187A CN 201910121817 A CN201910121817 A CN 201910121817A CN 109948187 A CN109948187 A CN 109948187A
- Authority
- CN
- China
- Prior art keywords
- centrifugal compressor
- wheel disc
- temperature
- wheeling disk
- laryngeal
- 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
Classifications
-
- 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
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The centrifugal compressor wheel disc laryngeal structure optimum design method based on equal-intensity theory that the invention discloses a kind of, its step are as follows: (1) based on the two-dimensional geometry model of centrifugal compressor wheeling disk structure, establishing finite element model；(2) consider that the structure temperature field under most harsh design conditions, centrifugal force and chamber pressure are inputted as load, to the analysis and solution of wheeling disk structure static strength；(3) the maximum radial stress and its corresponding temperature loading for extracting centrifugal compressor wheel disc throat leading edge, being vented at side；(4) wheel disc throat leading edge under relevant temperature, the material yield strength at exhaust side maximum radial stress are obtained；(5) margin of safety for calculating wheel disc throat leading edge, being vented at side maximum radial stress, using equal strength reserve factor as constraint condition, optimization wheel disc throat leading edge, the geometric configuration for being vented side.The present invention is optimized by the equal-intensity theory to centrifugal compressor wheel disc laryngeal structure, improves the structure utilization rate of centrifugal compressor leaf dish.
Description
Technical field
The invention belongs to centrifugal compressor wheel disc design field, it is related to a kind of centrifugal compressor wheel disc laryngeal structure optimization and sets
Meter method, in particular to a kind of centrifugal compressor wheel disc laryngeal structure optimum design method based on equal-intensity theory.
Background technique
Gas-turbine unit is a kind of highly complex and accurate thermal machine, is mainly used for providing for aircraft dynamic
Power.As the heart of aircraft, it is known as " jewel on modern industry imperial crown ", is related to a large amount of front subject and basic subject,
It directly affects the performance, reliability and economy of aircraft, is the important embodiment of a national science and technology, industry and military capability of the country.
Main three big components of gas-turbine unit are compressor, combustion chamber and turbine.The main function of compressor is
It is done work using high-speed rotating blade to air to improve the pressure of air.Compressor has axial-flow type and centrifugal two types,
Centrifugal compressor have it is small in size, single stage supercharging than it is high the features such as, be widely used in the engines such as small-sized turbofan, whirlpool spray, whirlpool axis.
Wheel disc is the main load-bearing part of engine rotor, is equipped with blade in wheel rim, when rotating at high speed, wheel disc is subjected to
The centrifugal load of blade at wheel rim, while also subject to the centrifugal load of wheel disc itself.According to the loaded and stress distribution of wheel disc
Feature, wheel disc disc usually will appear laryngeal structure.
At this stage, when wheel disc laryngeal structure designs, it is believed that throat section is consistent from air inlet side to exhaust side temperature,
I.e. without axial temperature difference, wheel disc laryngeal structure is designed according to the method for iso-stress along axial direction.And in the case of being actually on active service, centrifugation pressure
Mechanism of qi wheel disc is thicker, and blade pressure ratio is high, and throat's inlet and outlet side is caused to form certain axial temperature difference, and air inlet side temperature is low,
Exhaust side temperature is high, and the yield strength of material is often reduced as temperature increases, so designed according to iso-stress, it will necessarily
There are some field strengths deposit is excessive, and some field strengths are laid in lesser situation and are in other words wanted meeting structural strength
It asks down, structural material performance cannot be made full use of according to the design method of iso-stress, there are also very big optimization spaces for structure.
Summary of the invention
For the drawbacks described above and deficiency for overcoming the prior art, the centrifugation pressure based on equal-intensity theory that the present invention provides a kind of
Throat's leading edge maximum stress can be designed larger, throat row by mechanism of qi wheel disc laryngeal structure optimum design method, this method
Maximum stress design in gas side is smaller, and the margin of safety on such throat both sides is suitable, can both make full use of structural material performance,
Wheeling disk structure weight can be effectively reduced again, improve the overall structure performance of centrifugal compressor wheeling disk structure.
The present invention is technical solution used by solving its technical problem are as follows:
A kind of centrifugal compressor wheel disc laryngeal structure optimum design method based on equal-intensity theory, which is characterized in that should
Method includes the following steps:
SS1. based on the two-dimensional geometry model of centrifugal compressor wheeling disk structure, centrifugal compressor wheeling disk structure finite element is generated
Model；
SS2. the centrifugal compressor wheeling disk structure finite element model generated based on step SS1 inputs centrifugal compressor wheel disc
The density of structural material, the elasticity modulus varied with temperature and thermal expansion coefficient, with the structure temperature under most harsh design conditions
Field, centrifugal force and chamber pressure are inputted as load, are constrained its axial and circumferential displacement boundary conditions, are completed to centrifugal compressor wheel disc
The analysis and solution of structural static strength；
SS3. the maximum radial stress S of centrifugal compressor wheel disc throat leading edge is extractedX1And its corresponding temperature TSX1, extract
The maximum radial stress S on centrifugal compressor wheel disc throat exhaust sideX2And its corresponding temperature TSX2；
SS4. according to the corresponding relationship of the temperature of centrifugal compressor wheeling disk structure material and yield strength, T is respectively obtainedSX1
And TSX2The yield strength σ of corresponding centrifugal compressor wheeling disk structure material1And σ2；
SS5. the margin of safety coefficient F for calculating separately wheel disc throat leading edge, being vented at side maximum radial stress1、F2,
In, F1=σ1/SX1, F2=σ2/SX2；
SS6. using wheel disc laryngeal structure leading edge, be vented side geometric configuration as optimized variable, with equal strength reserve factor
It is excellent to establish centrifugal compressor wheel disc laryngeal structure to minimize centrifugal compressor wheeling disk structure weight as target for constraint condition
Change designs a model, final to realize the centrifugal compressor wheel disc laryngeal structure optimization design based on equal-intensity theory.
Preferably, in the step SS1, the two-dimensional geometry model based on centrifugal compressor wheeling disk structure is single by definition
Element type, grid division construct centrifugal compressor wheeling disk structure finite element model.
Preferably, in the step SS2, the density of centrifugal compressor wheeling disk structure material, the springform varied with temperature
Amount and thermal expansion coefficient, are obtained by Materials Handbook.
Preferably, in the step SS3, most harsh design conditions, which refer to be centrifuged under the high rotary speed working state of high temperature, calms the anger
The maximum operating condition of machine laryngeal structure axial temperature difference.
Preferably, in the step SS4, the temperature of centrifugal compressor wheeling disk structure material is corresponding with yield strength to be closed
System, is obtained by Materials Handbook.
Preferably, in the step SS6, centrifugal compressor wheel disc laryngeal structure mathematical optimization models are shown below:
Design variable X=(x1,x2)
Optimization aim min f=mass (x1,x2)
Constraint condition F1-F2=0
F1,F1≥Fcriterion
Wherein, x1And x2The geometric configuration curve for respectively representing wheel disc laryngeal structure leading edge, being vented side；Mass indicate from
Heart air compressor structure weight, it is the function about design variable；FcriterionThe margin of safety coefficient mark required for design criteria
Standard is determined according to the design criteria of selection.
The advantages of the present invention over the prior art are that: the centrifugal compressor wheel disc of the invention based on equal-intensity theory
Laryngeal structure optimum design method passes through the margin of safety of constraint wheel disc laryngeal structure leading edge and exhaust side maximum radial stress
Coefficient optimizes wheel disc laryngeal structure configuration, can meet wheeling disk structure intensity service performance on the basis of, effectively mitigate from
Heart compressor disk construction weight is more applicable for wheel disc throat temperature ladder relative to the optimum design method of existing iso-stress
Spend higher temperature loading situation.
Detailed description of the invention
Fig. 1 is that the centrifugal compressor wheel disc laryngeal structure optimum design method of the invention based on equal-intensity theory realizes stream
Cheng Tu；
Fig. 2 is the targeted centrifugal compressor wheeling disk structure two-dimensional finite element model schematic diagram of the present invention；
Fig. 3 is the temperature field cloud atlas of the targeted most harsh design conditions of centrifugal compressor wheeling disk structure of the present invention；
Fig. 4 is that the radial stress before the targeted centrifugal compressor wheel disc laryngeal structure optimization of the present invention is distributed isopleth
Figure；
Fig. 5 is the targeted centrifugal compressor wheel disc laryngeal structure leading edge of the present invention and the optimization front and back comparison of exhaust side
Figure；
Fig. 6 is that the radial stress after the targeted centrifugal compressor wheel disc laryngeal structure optimization of the present invention is distributed isopleth
Figure.
Specific embodiment
The centrifugal compressor wheel disc laryngeal structure optimum design method based on equal-intensity theory that the invention proposes a kind of is
The characteristics of more fully understanding the invention and its actual applicability of engineering realized according to implementing procedure as shown in Figure 1
To the optimization design of certain centrifugal compressor wheel disc laryngeal structure, comprising the following steps:
SS1. based on the two-dimensional geometry model of centrifugal compressor wheeling disk structure, definition unit type, grid division, generate from
Heart compressor disk structural finite element model, as shown in Figure 2；
SS2. the material according to selected by centrifugal compressor wheel disc consults Materials Handbook, obtains density, varies with temperature
The material parameters such as elasticity modulus and thermal expansion coefficient, input the structure temperature field under most harsh design conditions as shown in Figure 3, from
Mental and physical efforts and chamber pressure；Its axial and circumferential displacement boundary conditions is constrained, the analysis to centrifugal compressor wheeling disk structure static strength is completed
It solves, the radial stress distribution for obtaining centrifugal compressor laryngeal structure before optimizing is as shown in Figure 4.Most harsh design conditions refer to
The maximum operating condition of centrifugal compressor laryngeal structure axial temperature difference under the high rotary speed working state of high temperature.
SS3. the maximum radial stress and its corresponding temperature for extracting centrifugal compressor wheel disc throat leading edge, are denoted as S respectivelyX1
And TSX1, the maximum radial stress and its corresponding temperature on centrifugal compressor wheel disc throat exhaust side are extracted, is denoted as S respectivelyX2And TSX2；
SS4. according to Materials Handbook, T is obtainedSX1And TSX2The surrender of the corresponding centrifugal compressor wheeling disk structure material of temperature is strong
Degree, is denoted as σ respectively1And σ2；
SS5. the margin of safety coefficient for calculating wheel disc throat leading edge, being vented at side maximum radial stress, is denoted as F respectively1
And F2, wherein F1=σ1/SX1, F2=σ2/SX2；
SS6. using wheel disc laryngeal structure leading edge, be vented side geometric configuration as optimized variable, with equal strength reserve factor
It establishes the centrifugation being shown below to minimize centrifugal compressor wheeling disk structure weight as objective function for constraint condition and calms the anger
Wheel disk laryngeal structure mathematical optimization models:
Design variable X=(x1,x2)
Optimization aim min f=mass (x1,x2)
Constraint condition F1-F2=0
F1,F1≥Fcriterion
Wherein, x1And x2The geometric configuration curve for respectively representing wheel disc laryngeal structure leading edge, being vented side；Mass indicate from
Heart air compressor structure weight, it is the function about design variable；FcriterionThe margin of safety coefficient mark required for design criteria
Standard, here Fcriterion=1.25.Finally, the centrifugal compressor wheel disc laryngeal structure optimization design based on equal-intensity theory is realized,
Laryngeal structure geometric configuration is with the comparison before optimization as shown in figure 5, structural weight reduction 200g, the structure after optimization are radially answered after optimization
Power distribution is as shown in fig. 6, be increased to 528MPa by 407MPa compared to throat's leading edge radial stress before optimizing, stress improves
30%.Throat is vented side radial stress and is increased to 390MPa by 372MPa, and stress improves 5%.Throat's inlet and outlet become after optimization
Radial stress surrender reserve factor is equal, is 1.54, meets F1=F2>=1.25 criterion calls.Leading edge is radial before optimizing
Yield stress reserve factor is 2.0, and exhaust side radial stress surrender reserve factor is 1.6, inlet and outlet side radial stress before optimizing
Deposit difference is larger.
In conclusion the centrifugal compressor wheel disc laryngeal structure optimization design side proposed by the present invention based on equal-intensity theory
Method, this method is using centrifugal compressor wheel disc throat leading edge, exhaust side geometric configuration as optimization design variable, with equal strength deposit
Coefficient is constraint condition, to minimize centrifugal compressor wheeling disk structure weight as optimization object function, realizes and is meeting intensity
Effective loss of weight of centrifugal compressor wheeling disk structure on the basis of it is required that.This method and other methods have compatibility, and physical significance is bright
It is really, subsequent that based on the institute to mention the optimum results that method obtains more efficient.
The above is only presently preferred embodiments of the present invention, are not limited in any way to protection scope of the present invention；It can
Expanded application in similar structures similar to the optimization design field of the wheel disc class intensity of Temperature Distribution, it is all using equivalents or to wait
The technical solution of effect replacement and formation, all falls within rights protection scope of the present invention.
Part of that present invention that are not described in detail belong to the well-known technology of those skilled in the art.
Claims (6)
1. a kind of centrifugal compressor wheel disc laryngeal structure optimum design method based on equal-intensity theory, which is characterized in that the party
Method realizes that steps are as follows:
SS1. based on the two-dimensional geometry model of centrifugal compressor wheeling disk structure, centrifugal compressor wheeling disk structure finite element mould is generated
Type；
SS2. the centrifugal compressor wheeling disk structure finite element model generated based on step SS1 inputs centrifugal compressor wheeling disk structure
The density of material, the elasticity modulus varied with temperature and thermal expansion coefficient, under most harsh design conditions structure temperature field, from
Mental and physical efforts and chamber pressure are inputted as load, are constrained its axial and circumferential displacement boundary conditions, are completed to centrifugal compressor wheeling disk structure
The analysis and solution of static strength；
SS3. the maximum radial stress S of centrifugal compressor wheel disc throat leading edge is extractedX1And its corresponding temperatureExtract centrifugation
The maximum radial stress S on compressor disk throat exhaust sideX2And its corresponding temperature
SS4. it according to the corresponding relationship of the temperature of centrifugal compressor wheeling disk structure material and yield strength, respectively obtainsWithThe yield strength σ of the corresponding centrifugal compressor wheeling disk structure material of temperature1And σ2；
SS5. the margin of safety coefficient F for calculating separately wheel disc throat leading edge, being vented at side maximum radial stress1、F2, wherein F1
=σ1/SX1, F2=σ2/SX2；
SS6. using wheel disc laryngeal structure leading edge, be vented side geometric configuration as optimized variable, be about with equal strength reserve factor
Beam condition is established the optimization of centrifugal compressor wheel disc laryngeal structure and is set to minimize centrifugal compressor wheeling disk structure weight as target
Model is counted, it is final to realize the centrifugal compressor wheel disc laryngeal structure optimization design based on equal-intensity theory.
2. the method according to the claims, which is characterized in that in the step SS1, be based on centrifugal compressor wheel disc
The two-dimensional geometry model of structure constructs centrifugal compressor wheeling disk structure finite element mould by definition unit type, grid division
Type.
3. the method according to the claims, which is characterized in that in the step SS2, centrifugal compressor wheeling disk structure
The density of material, the elasticity modulus varied with temperature and thermal expansion coefficient, are obtained by Materials Handbook.
4. the method according to the claims, which is characterized in that in the step SS3, most harsh design conditions refer to
The maximum operating condition of centrifugal compressor laryngeal structure axial temperature difference under the high rotary speed working state of high temperature.
5. the method according to the claims, which is characterized in that in the step SS4, centrifugal compressor wheeling disk structure
The temperature of material and the corresponding relationship of yield strength, are obtained by Materials Handbook.
6. the method according to the claims, which is characterized in that in the step SS6, centrifugal compressor wheel disc throat
Optimal Structure Designing model is shown below:
Design variable X=(x1,x2)
Optimization aim min f=mass (x1,x2)
Constraint condition F1-F2=0
F1,F1≥Fcriterion
Wherein, x1And x2The geometric configuration curve for respectively representing wheel disc laryngeal structure leading edge, being vented side；Mass indicates centrifugation pressure
Mechanism of qi construction weight, it is the function about design variable；FcriterionFor design criteria require margin of safety factor standard,
It is determined according to the design criteria of selection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910121817.7A CN109948187B (en) | 2019-02-17 | 2019-02-17 | Centrifugal compressor wheel disc throat structure optimization design method based on equal strength theory |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910121817.7A CN109948187B (en) | 2019-02-17 | 2019-02-17 | Centrifugal compressor wheel disc throat structure optimization design method based on equal strength theory |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109948187A true CN109948187A (en) | 2019-06-28 |
| CN109948187B CN109948187B (en) | 2023-04-07 |
Family
ID=67006783
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910121817.7A Active CN109948187B (en) | 2019-02-17 | 2019-02-17 | Centrifugal compressor wheel disc throat structure optimization design method based on equal strength theory |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109948187B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103953579A (en) * | 2014-04-24 | 2014-07-30 | 中国科学院工程热物理研究所 | Gas compressor rotor blade with top slit and design method |
| RU2600213C1 (en) * | 2015-05-07 | 2016-10-20 | Владимир Александрович Грибановский | Centrifugal compressor impeller from composite material and method of making thereof |
| CN107679270A (en) * | 2017-08-28 | 2018-02-09 | 西北工业大学 | Centrifugal compressor Optimization Design and system |
-
2019
- 2019-02-17 CN CN201910121817.7A patent/CN109948187B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103953579A (en) * | 2014-04-24 | 2014-07-30 | 中国科学院工程热物理研究所 | Gas compressor rotor blade with top slit and design method |
| RU2600213C1 (en) * | 2015-05-07 | 2016-10-20 | Владимир Александрович Грибановский | Centrifugal compressor impeller from composite material and method of making thereof |
| CN107679270A (en) * | 2017-08-28 | 2018-02-09 | 西北工业大学 | Centrifugal compressor Optimization Design and system |
Non-Patent Citations (5)
| Title |
|---|
| JIAQI LI: "Nonlinear Analysis of Rod Fastened Rotor under Nonuniform Contact Stiffness", 《SHOCK AND VIBRATION》 * |
| 冯引利: "考虑表面加工状态的粉末盘低循环疲劳寿命分析", 《航空动力学报》 * |
| 张坤等: "基于UG、Workbench平台航空发动机多盘转子结构自动优化方法", 《航空动力学报》 * |
| 章胜等: "基于等强度理论的轮盘优化设计方法研究", 《机械科学与技术》 * |
| 雷先华等: "整体压气机转子结构优化设计", 《航空动力学报》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109948187B (en) | 2023-04-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8684684B2 (en) | Turbine assembly with end-wall-contoured airfoils and preferenttial clocking | |
| US8727716B2 (en) | Turbine nozzle with contoured band | |
| US8439643B2 (en) | Biformal platform turbine blade | |
| US8647067B2 (en) | Banked platform turbine blade | |
| EP1712738B1 (en) | Low solidity turbofan | |
| Halila et al. | Energy efficient engine high pressure turbine test hardware detailed design report | |
| CN108229015B (en) | Variable working condition matching design method for high-altitude two-stage turbocharger | |
| US20120244005A1 (en) | High camber compressor rotor blade | |
| US8870525B2 (en) | Bucket assembly for turbine system | |
| US20120192421A1 (en) | Gas turbine engine airfoil | |
| Bunker | Cooling design analysis | |
| JP2012052526A (en) | Shrouded turbine blade with contoured platform and axial dovetail | |
| JP2001132696A (en) | Stationary blade having narrow waist part | |
| CN101078354B (en) | Porous metal vane coupling design method | |
| Harvey et al. | Some effects of non-axisymmetric end wall profiling on axial flow compressor aerodynamics: Part II—Multi-stage HPC CFD study | |
| Wellborn et al. | Redesign of a 12-stage axial-flow compressor using multistage CFD | |
| Vanti et al. | Aeroelastic optimization of an industrial compressor rotor blade geometry | |
| Yang et al. | Hydraulic components’ matching optimization design and entropy production analysis in a large vertical centrifugal pump | |
| CN110043484A (en) | Twin-stage high-loaded fan design method based on circumferential direction vorticity through-flow design | |
| CN109948187A (en) | Centrifugal compressor wheel disc laryngeal structure optimum design method based on equal-intensity theory | |
| Ke et al. | Highly loaded aerodynamic design and three dimensional performance enhancement of a HTGR helium compressor | |
| Belousov et al. | Methodology of modernizing the serial converted gas turbine unit | |
| Ke et al. | Design and aerodynamic analysis of a highly loaded helium compressor | |
| RU2632350C2 (en) | Rectifier of gas-turbine engine with vanes of improved profile | |
| Köller et al. | Development of advanced compressor airfoils for heavy-duty gas turbines: part I—design and optimization |
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 |