CN108763839B - A kind of centrifugal impeller boss crack propagation characteristic simulation part design method - Google Patents
A kind of centrifugal impeller boss crack propagation characteristic simulation part design method Download PDFInfo
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Abstract
The present invention relates to a kind of centrifugal impeller boss crack propagation characteristic simulation part design methods, obtain the geometrical model of centrifugal impeller, measure radius, the boss radical length of boss structure；The working condition and the material property parameter under working condition for obtaining centrifugal impeller；Centrifugal impeller finite element analysis model is established, the stress maximum point for obtaining centrifugal impeller boss position is calculated；Using rectangular plate test specimen as basic configuration, plate two sides symmetric position band boss structure, boss is consistent with the radius of rectangular slab, boss radical length and practical structures, by adjusting piece lengths method, so that simulating piece is closed on lug boss position, draw direction maximum stress occur consistent with practical structures, and proof stress gradient is identical；The stress intensity factor of simulating piece and the relationship of specimen thickness are checked, determines that the thickness of test specimen, gained simulating piece can simulate the stress-strain field of centrifugal impeller boss structure, and can be used for carrying out crack expansion test.
Description
Technical field
The present invention relates to one kind to be directed to aero-engine centrifugal impeller boss crack propagation characteristic simulation part design method, it
It is a kind of it can be considered that centrifugal impeller structure stress concentration, the crack propagation characteristic simulation part design method of stress gradient, belong to
Aerospace technical field of engines.
Background technique
The labyrinth feature of centrifugal impeller often causes stress to concentrate in regional area in aero-engine, causes to split
Line distal end load is in non-uniform Distribution along crack propagation path.Due to the crack expansion test based on standard component, office cannot be embodied
The stress in portion region is concentrated, on each crack propagation increment that load is close generally by the way of discrete crack propagation step-length
Like being uniform load, when crack propagation increment reduces to a certain extent, the crack propagation law being closer to can get.So
And since stress raisers are more obvious (local stress gradients are bigger), the deviation of this approximation method is bigger, therefore, it is necessary to
Design features simulating piece simultaneously carries out crack expansion test, simulates stress raisers in laboratory environments, obtains corresponding
Crack propagation law.
A kind of existing patent CN201710255317.3 " test method of blade construction simulating piece " sets for blade construction
Fatigue life simulating piece is counted, the design principle of simulating piece is mainly the equivalent stress and practical structures phase of multiple dangerous points
Closely, do not consider that the stress distribution of dangerous point adjacent area is equivalent.
" Yang Xingyu, Dong Liwei, Geng Zhonghang wait compressor disk tongue-and-groove low-cycle fatigue simulating piece to design to existing literature
With test [J] aviation power journal, 2008,23 (10): the low circulation that 1829-1834 " is designed according to compressor disc tenon groove structure
Fatigue life test ensure that maximum pull, stress gradient, strain gradient and the practical structures of simulating piece are more consistent, but not
The design and assessment of crack propagation correlation properties are carried out, testpieces can be applied to low cycle fatigue life test, without can be carried out
Fatigue crack propagation test.
Summary of the invention
The technology of the present invention solution: it is special to overcome the deficiencies of the prior art and provide a kind of centrifugal impeller boss crack propagation
Simulating piece design method is levied, can fully reflect stress concentration, the stress gradient of centrifugal impeller boss.
The technology of the present invention solution: a kind of centrifugal impeller boss crack propagation characteristic simulation part design method, in conjunction with from
The static analysis of lobus cardiacus wheel realizes in laboratory conditions as a result, design is able to reflect the crack propagation modeling part of feature structure
Simulate the crack propagation behavior of real structure.Realize that steps are as follows:
The first step obtains the geometrical model of centrifugal impeller, measures radius, the centrifugal impeller of centrifugal impeller boss
Boss radical length.The geometrical model refers to by computer aided design software, completes according to Practical Project Demand Design
Centrifugal impeller 3-D geometric model；The radius refers to half of the knuckle between centrifugal impeller boss and impeller
Diameter；The boss radical length refers to the radical length of centrifugal impeller boss.
Second step, the working condition and the material property parameter under working condition for obtaining centrifugal impeller.The operating condition item
Part includes the working speed of the operating temperature field of centrifugal impeller, centrifugal impeller；The material property parameter includes centrifugal impeller material
The density of material；Elasticity modulus, Poisson's ratio, Plastic Constitutive parameter and the coefficient of expansion at the working temperature, fracture toughness value.Centrifugation
The operating temperature field of impeller is obtained by analysis of Heat Transfer or actual measurement；The working speed of centrifugal impeller passes through outfield engine work
Make data statistics acquisition；Material property parameter is obtained by material property testing or material data handbook.For varying with temperature
Material property parameter, the corresponding parametric values under whole hundred degrees Celsius are obtained, such as the relevant parameter at 100 DEG C, 200 DEG C, 300 DEG C
Maxima and minima in centrifugal impeller operating temperature field need to be included by value, taken temperature range.
Third step, according to the geometrical model of the first step and the working condition of second step and the material property under working condition
Parameter establishes centrifugal impeller finite element analysis model, calculates the ess-strain number for obtaining centrifugal impeller boss under working condition
According to；It is described
Stress data includes the radial stress value and radial stress ladder of the draw direction stress maximum point of centrifugal impeller boss
Degree.
4th step, ess-strain number of the centrifugal impeller boss obtained based on third step static analysis under working condition
According to, using rectangular plate test specimen as basic configuration, to be loaded as loading along being uniaxially stretched for simulating piece length direction, design from
Lobus cardiacus wheel boss crack propagation characteristic simulation part, definition simulating piece Tensile direction are length direction, and boss radial direction is width
Spend direction.The three times of the distance of the circumferential stress distribution obtained first using in third step are as simulating piece original width, with width
Half as original depth, the length of simulating piece can freely give according to testing machine impulse stroke, clamping end design conditions, build
The finite element analysis model of vertical centrifugal impeller boss simulating piece.By adjusting the radius of simulating piece, width, boss
Radical length changes the big submethod of tensile load, carries out finite element to the Finite Element Static Analysis model of the simulating piece repeatedly
Static analysis makes the simulating piece boss be equal to the maximum obtained in third step along the maximum stress value in tensile loads direction
Radial stress value；Meanwhile make on simulating piece stretch loading direction maximum stress value and third step obtain relative error ±
Within 5%；Further, further, make the diameter obtained along the stress distribution situation and third step of the simulating piece width
It is consistent to stress distribution.After meeting above-mentioned requirements, the dimensional parameters of centre bore simulating piece can be primarily determined, and uniaxial
The magnitude of load of stretching.
5th step determines the thickness of simulating piece by the stress intensity factor of calculating simulation part.The stress intensity factor
For describe Cracked structure crack tip stress field power parameter, numerical values recited be plus load, crack length and
The function of geometrical shapes.The numerical value of stress intensity factor can be calculated by finite element numerical or stress intensity factor experience is public
Formula acquires.When stress intensity factor value is more than or equal to the fracture toughness value of material, it is believed that Cracked structure is by unstable fracture.Base
What is determined in the 4th step centrifugal impeller boss simulating piece size and the magnitude of load that is uniaxially stretched, acquires stress intensity factor
Reach corresponding critical crack length when fracture toughness value；The principle for determining thickness is that simulating piece thickness need to be in critical crack length
More than half, sufficiently to cover crackle in the stabilization expansion process of thickness direction；After determining thickness simultaneously, needed for simulating piece
External applied load will be within the load capability of testing machine used.So far, centrifugal impeller centre bore crack propagation characteristic simulation is completed
The design work of part.Institute
Design simulation part can simulate the stress field of centrifugal impeller center hole structure, and can be used for carrying out crack propagation examination
It tests.
In 4th step, because the size of simulating piece does not determine that area of section changes with design process finally, so into
When row finite element analysis, recommend to set load boundary condition in the form of stress.After the size of simulating piece determines completely, then root
According to examination area of section, loading force needed for conversing test.For example, the outer load stress that is uniaxially stretched determined in the 4th step is
σ, units MPa；Finally determining examination section area of section is A, unit mm2, then testing machine is applied to the load on simulating piece
Power F can calculate as follows:
F=σ A
Wherein the unit of F is N.
In 5th step, crackle form on centre bore simulating piece need to reference to centre bore position on centrifugal impeller it is practical go out
Existing crackle form.The crackle form of usual pore structure is corner crack at hole.Referring in stress intensity factor handbook, infinity is cut
Arc chord angle cracks in face, stress intensity factor calculation formula are as follows:
M={ 1.13-0.09 (a/c) }
+{-0.54+0.89·[0.2+(a/c)]-1}(a/B)2
+{0.5-[0.65+(a/c)]-1
+14(1-a/c)24}(a/B)4
Φ2=1+1.464 (a/c)1.65
Wherein a is crack depth, and c is crack length, and B is specimen thickness, and σ t is tensile load, and π is pi, and K is to answer
Power intensity factor, the value of dimensionless factor M is related with position of the point on crack front is calculated, by inquiry stress intensity because
Sub- handbook chart determines；
The present invention is with prior art beneficial effect: a kind of existing patent CN201710255317.3 " blade construction mould
Intend the test method of part " fatigue life simulating piece is devised for blade construction, the design principle of simulating piece is predominantly multiple
The equivalent stress of dangerous point is close with practical structures, and does not consider that the stress distribution of dangerous point adjacent area is equivalent.Existing literature
" Yang Xingyu, Dong Liwei, Geng Zhonghang wait the design of compressor disk tongue-and-groove low-cycle fatigue simulating piece and test [J] aviation dynamic
Mechanics report, 2008,23 (10): 1829-1834 " is tested according to the low cycle fatigue life that compressor disc tenon groove structure designs, and is protected
Maximum pull, stress gradient and the practical structures for having demonstrate,proved simulating piece are more consistent, but do not carry out setting for crack propagation correlation properties
Meter and assessment, testpieces can be applied to low cycle fatigue life test, without can be carried out fatigue crack propagation test.
And the present invention is devised according to the stress distribution of centrifugal impeller boss using rectangular plate simulating piece as fundamental form
The crack propagation characteristic simulation part of shape, simulates the maximum stress and stress distribution of practical boss structure.By adjusting
Geometric dimension and simulating piece external applied load complete the determination of simulating piece geometric dimension.By the stress intensity factor of calculating simulation part,
Critical crack length has been determined, simulating piece is made to can be used for the experiment of low-cycle fatigue crack propagation.
Detailed description of the invention
Fig. 1 is centrifugal impeller boss crack propagation characteristic simulation part design method flow chart of the invention；
Fig. 2 is simulating piece geometric shape drawing, (a) top view；(b) main view；(c) left view；L is simulating piece length；W
For simulating piece width；B is the thickness of simulating piece；B1 is boss radical length；R is radius；W1 is projection width；
Fig. 3 is simulating piece example finite Element Stress cloud atlas；
Fig. 4 is simulating piece example stress distribution and structure stress distribution comparison diagram.
Specific embodiment
With reference to the accompanying drawing, to a kind of technology of centrifugal impeller boss crack propagation characteristic simulation part design method of the present invention
Scheme is described further.
As shown in Figure 1, realizing step the present invention relates to a kind of centrifugal impeller boss crack propagation characteristic simulation part design method
It is rapid as follows: (1) to obtain the geometrical model of centrifugal impeller, measure radius, the boss radical length of boss；(2) it obtains
The working condition and the material property parameter under working condition of centrifugal impeller, including load, temperature, elasticity modulus, surrender are by force
Degree etc.；(3) centrifugal impeller finite element analysis model is established, the stress maximum point for obtaining centrifugal impeller boss is calculated, obtains the point
Radial stress value and radial stress gradient；(4) using rectangular plate test specimen as basic configuration, boss simulating piece is designed, makes to simulate
Part closes on lug boss position, and draw direction maximum stress occur consistent with practical structures, and proof stress gradient, equivalent strain are identical；
(5) stress intensity factor of simulating piece and the relationship of specimen thickness are checked, determines that the thickness of test specimen, gained simulating piece can simulate
The stress of centrifugal impeller center hole structure, and can be used for carrying out crack expansion test.
Consider centrifugal impeller structure stress concentration, the crack propagation characteristic simulation part design method of stress gradient, the present invention
The kind centrifugal impeller boss crack propagation characteristic simulation part design method mentioned, process are shown in Fig. 1.
The technology of the present invention solution: a kind of centrifugal impeller centre bore crack propagation characteristic simulation part design method, in conjunction with
Centrifugal impeller static analysis is as a result, design is able to reflect the crack propagation characteristic simulation part of feature structure.
Embodiment 1, the present invention realize that steps are as follows:
The first step obtains the geometrical model of centrifugal impeller, and radius, the boss for measuring centrifugal impeller boss are radial
Length.The geometrical model refers to the centrifugal impeller by computer aided design software, completed according to Practical Project Demand Design
3-D geometric model；The radius refers to the radius of the knuckle between boss and impeller；The boss is radially long
Degree refers to the radical length of centrifugal impeller boss.Such as the radius of certain centrifugal impeller boss is 20mm, radical length is
4mm。
Second step, the working condition and the material property parameter under working condition for obtaining centrifugal impeller.The operating condition item
Part includes the working speed of the operating temperature field of centrifugal impeller, centrifugal impeller；The material property parameter includes centrifugal impeller material
The density of material；Elasticity modulus, Poisson's ratio, Plastic Constitutive parameter and the coefficient of expansion at the working temperature, fracture toughness value.Centrifugation
The operating temperature field of impeller is obtained by analysis of Heat Transfer or actual measurement；The working speed of centrifugal impeller passes through outfield engine work
Make data statistics acquisition；Material property parameter is obtained by material property testing or material data handbook.For varying with temperature
Material property parameter, the corresponding parametric values under whole hundred degrees Celsius are obtained, such as the relevant parameter at 100 DEG C, 200 DEG C, 300 DEG C
Maxima and minima in centrifugal impeller operating temperature field need to be included by value, taken temperature range.
Third step, according to the geometrical model of the first step and the working condition of second step and the material property under working condition
Parameter establishes centrifugal impeller finite element analysis model, calculates the ess-strain number for obtaining centrifugal impeller boss under working condition
According to；The stress data includes the radial stress value and radial stress ladder of the draw direction stress maximum point of centrifugal impeller boss
Degree.In this embodiment, on the boss structure radial stress maximum point that static analysis calculates is radially 459MPa to stress value, along diameter
To radial stress distribution situation it is as follows: at 0.8mm, stress value 409MPa；At 1.8mm, at stress value 359MPa, 4mm, answer
Force value is 334MPa.
4th step, stress data of the centrifugal impeller boss obtained based on third step static analysis under working condition,
Using rectangular plate test specimen as basic configuration, to be loaded as loading along being uniaxially stretched for simulating piece length direction, design centrifugation
Impeller boss crack propagation characteristic simulation part, as shown in Figure 2.Definition simulating piece Tensile direction is length direction, and L is simulating piece
Length；Boss radial direction is width direction, and W is simulating piece width；B is the thickness of simulating piece；B1 is boss radical length；R
For radius；W1 is projection width.Obtained first using in third step circumferential stress distribution distance three times as
Simulating piece original width, using the half of width as original depth, the length of simulating piece can be according to testing machine impulse stroke, clamping
End design conditions freely give, and establish the finite element analysis model of centrifugal impeller boss simulating piece.By adjusting the mistake of simulating piece
Radius of corner, width, the radical length of boss, the change big submethod of tensile load are crossed, repeatedly to the finite element of the simulating piece
Static analysis model carries out Finite Element Static Analysis, is equal to the simulating piece boss along the maximum stress value in tensile loads direction
The maximum radial stress value obtained in third step；Meanwhile making the maximum stress value and that loading direction is stretched on simulating piece
The relative error that three steps obtain is within ± 5%；Further, further, make the stress distribution along the simulating piece width
The radial stress distribution obtained in situation and third step is consistent.After meeting above-mentioned requirements, center casement can be primarily determined
The dimensional parameters of quasi- part, and the magnitude of load being uniaxially stretched.The simulating piece dimensional parameters determined in the embodiment of the present invention are as follows: L
=100mm, W=20mm, B=8mm, B1=7.3mm, R=4mm, W1=6mm.Simulating piece example finite Element Stress cloud atlas such as Fig. 3
Shown, on the direction cloud atlas instruction simulation part x stress value, the unit of stress on figure is Pa, and maximum stress value appears in simulating piece
It examines at section, stress value 459MPa, it is consistent with the structure maximum stress value that static analysis calculates；Simulating piece example stress distribution
Chart is compared with structure stress distribution, as shown in figure 4, distance of the abscissa representative away from stress maximum point in chart, unit mm,
Ordinate represents stress value, unit MPa, and soft dot data are the actual stress value of wheel disc boss structure, and cross data are
Stress value on simulating piece, it is seen that designed simulating piece stress distribution and center hole structure stress distribution is more coincide.It generates
It is 346.8MPa that tensile stress is carried outside simulating piece required for the stress and stress distribution.
5th step determines the thickness of simulating piece by the stress intensity factor of calculating simulation part.The stress intensity factor
For describe Cracked structure crack tip stress field power parameter, numerical values recited be plus load, crack length and
The function of geometrical shapes.The numerical value of stress intensity factor can be calculated by finite element numerical or stress intensity factor experience is public
Formula acquires.When stress intensity factor value is more than or equal to the fracture toughness value of material, it is believed that Cracked structure is by unstable fracture.Base
What is determined in the 4th step centrifugal impeller boss simulating piece size and the magnitude of load that is uniaxially stretched, acquires stress intensity factor
Reach corresponding critical crack length when fracture toughness value；The principle for determining thickness is that simulating piece thickness need to be in critical crack length
More than half, sufficiently to cover crackle in the stabilization expansion process of thickness direction；After determining thickness simultaneously, needed for simulating piece
External applied load will be within the load capability of testing machine used.So far, centrifugal impeller centre bore crack propagation characteristic simulation is completed
The design work of part.Designed simulating piece can simulate the stress field of centrifugal impeller center hole structure, and can be used for carrying out crackle
Expanding test.
In 4th step, because the size of simulating piece does not determine that area of section changes with design process finally, so into
When row finite element analysis, recommend to set load boundary condition in the form of stress.After the size of simulating piece determines completely, then root
According to examination area of section, loading force needed for conversing test.For example, the outer load stress that is uniaxially stretched determined in the 4th step is
σ, units MPa；Finally determining examination section area of section is A, unit mm2, then testing machine is applied to the load on simulating piece
Power F can calculate as follows:
F=σ A
Wherein the unit of F is N.
In 5th step, crackle form on centre bore simulating piece need to reference to centre bore position on centrifugal impeller it is practical go out
Existing crackle form.The crackle form of usual pore structure is corner crack at hole.Referring in stress intensity factor handbook, infinity is cut
Arc chord angle cracks in face, stress intensity factor calculation formula are as follows:
M={ 1.13-0.09 (a/c) }
+{-0.54+0.89·[0.2+(a/c)]-1}(a/B)2
+{0.5-[0.65+(a/c)]-1
+14(1-a/c)24}(a/B)4
Φ2=1+1.464 (a/c)1.65
Wherein a is crack depth, and c is crack length, and B is specimen thickness, and σ t is tensile load, and π is pi, and K is to answer
Power intensity factor, the value of dimensionless factor M is related with position of the point on crack front is calculated, by inquiry stress intensity because
Sub- handbook chart determines.
The critical crack length for acquiring real case simulation part is 3mm.The principle for determining thickness is that simulating piece thickness need to be critical
More than half of crack length, sufficiently to cover crackle in the stabilization expansion process of thickness direction；After determining thickness simultaneously, mould
External applied load needed for quasi- part within the load capability of testing machine used, will determine the thickness B=6mm of simulating piece；Required is outer
Load is 54.4kN.
Above embodiments are provided just for the sake of the description purpose of the present invention, and are not intended to limit the scope of the invention.This
The range of invention is defined by the following claims.It does not depart from spirit and principles of the present invention and the various equivalent replacements made and repairs
Change, should all cover within the scope of the present invention.
Claims (5)
1. a kind of centrifugal impeller boss crack propagation characteristic simulation part design method, which comprises the following steps:
(1) geometrical model for obtaining centrifugal impeller measures the radius of centrifugal impeller boss structure, boss to length；
(2) working condition and the material property parameter under working condition for obtaining centrifugal impeller；The working condition include from
The operating temperature field of lobus cardiacus wheel, centrifugal impeller working speed；The material property parameter includes the density of centrifugal impeller material；
Elasticity modulus, Poisson's ratio, Plastic Constitutive parameter and the coefficient of expansion at the working temperature, fracture toughness value；
(3) the material property ginseng according to the geometrical model of step (1) and the working condition of step (2) and under working condition
Number establishes centrifugal impeller finite element analysis model, calculates the ess-strain number for obtaining centrifugal impeller boss under working condition
According to；The stress-strain data includes centrifugal impeller lug boss position draw direction maximum stress point i.e. maximum radial stress value, and
Using centrifugal impeller lug boss position draw direction maximum stress point as starting point, the radial direction along centrifugal impeller boss radius augment direction is answered
Power distribution；
(4) stress-strain data under the centrifugal impeller boss working condition obtained based on step (3) analysis, with rectangular plate
Test specimen is that basic configuration is convenient for crackle observation, to be loaded as loading along being uniaxially stretched for simulating piece length direction, if
Centrifugal impeller boss crack propagation characteristic simulation part is counted, the Finite Element Static Analysis model of the simulating piece is established, makes simulating piece
Centrifugal impeller boss along tensile loads direction stress value be equal to step (3) in obtain maximum radial stress value；Further
, it is consistent the stress distribution situation along the simulating piece width with the radial stress distribution obtained in step (3)；To
The determination for the magnitude of load that the dimensional parameters and simulating piece for completing the simulating piece are uniaxially stretched；
(5) thickness for determining the simulating piece, size based on the simulating piece determined in step (4) and is uniaxially stretched
Magnitude of load is acquired when the stress intensity factor of the simulating piece reaches fracture toughness value pair by stress intensity factor formula
The critical crack length answered is that it is convex to complete the centrifugal impeller according to the thickness for determining simulating piece with the critical crack length
The design work of platform crack propagation characteristic simulation part；
In the step (4), the Finite Element Static Analysis model of the simulating piece is established are as follows: be based on the simulating piece Tensile side
To for length direction, the radial direction of the centrifugal impeller boss of simulating piece is width direction, with the diameter of the centrifugal impeller boss of simulating piece
It is initial radial length to length, with the radius of practical structures for initial radius of corner, at least to be obtained in step (3)
The three times of the distance of the radial stress distribution taken are as simulating piece original width, using the half of simulating piece original width as initially
Thickness establishes the finite element analysis model of centrifugal impeller boss crack propagation characteristic simulation part, by adjusting the transition of simulating piece
Radius of corner, width, the radical length of boss, the change big submethod of uniaxial tensile load, repeatedly to the limited of the simulating piece
First static analysis model carries out Finite Element Static Analysis, makes the simulating piece boss along the maximum stress value etc. in tensile loads direction
The maximum radial stress value obtained in step (3).
2. a kind of centrifugal impeller boss crack propagation characteristic simulation part design method according to claim 1, feature exist
In: in the step (4), the error range of the radial stress distribution is within ± 5%.
3. a kind of centrifugal impeller boss crack propagation characteristic simulation part design method according to claim 1, feature exist
In: in the step (3), if radial stress distribution is obtained by measuring the radial direction done in radial line to stress value.
4. a kind of centrifugal impeller boss crack propagation characteristic simulation part design method according to claim 1, feature exist
In: in the step (5), stress intensity factor calculation formula is as follows:
M={ 1.13-0.09 (a/c) }+{ -0.54+0.89 [0.2+ (a/c)]-1}(a/B)2+{0.5-[0.65+(a/c)]-1+
14(1-a/c)24}(a/B)4
Φ2=1+1.464 (a/c)1.65
Wherein a is crack depth, and c is crack length, and B is specimen thickness, and σ t is tensile load, and π is pi, and K is that stress is strong
The factor is spent, the value of dimensionless factor M is related with position of the point on crack front is calculated, by inquiring stress intensity factor hand
Volume chart determines.
5. a kind of centrifugal impeller boss crack propagation characteristic simulation part design method according to claim 1, feature exist
In: in the step (5), determine that the thickness principle of simulating piece is: simulating piece thickness need in more than half of critical crack length,
Sufficiently to cover crackle in the stabilization expansion process of simulating piece thickness direction.
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| CN112197922B (en) * | 2020-08-25 | 2022-03-25 | 中国航发湖南动力机械研究所 | Turbine blade vibration fatigue simulation piece and design method thereof |
| CN113283022B (en) * | 2021-04-25 | 2024-06-18 | 北京航空工程技术研究中心 | Design method of low-cycle fatigue simulation part of aero-engine structure |
| CN113505506B (en) * | 2021-06-29 | 2024-03-29 | 南京航空航天大学 | Design method of crack propagation simulation piece at dangerous part of wheel disc |
| CN113792398B (en) * | 2021-09-08 | 2022-11-22 | 中国航发北京航空材料研究院 | Design method of combustion chamber casing hole structure characteristic simulation test piece |
| CN114840943B (en) * | 2022-05-16 | 2022-11-25 | 北京航空航天大学 | Fatigue crack propagation simulation piece design method based on consistency of crack propagation path and stress intensity factor |
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| 发动机轮盘模拟技术理论与方法;由美雁等;《机械设计》;20070228;第24卷(第2期);第62-64页 * |
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Inventor after: Hu Dianyin Inventor after: Guo Xiaojun Inventor after: Liu Zonghui Inventor after: Cui Jinduo Inventor after: Zhao Miaodong Inventor after: Mao Jianxing Inventor before: Hu Dianyin Inventor before: Guo Xiaojun Inventor before: Liu Zongye Inventor before: Cui Jinduo Inventor before: Zhao Miaodong Inventor before: Mao Jianxing |