CN106250575A - A kind of woven composite Turbine Blade Temperature Field field computational methods considering fiber orientation - Google Patents
A kind of woven composite Turbine Blade Temperature Field field computational methods considering fiber orientation Download PDFInfo
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Abstract
The invention discloses a kind of woven composite Turbine Blade Temperature Field field computational methods considering fiber orientation, the heat conductivity of the fibre-woven composite with CMC material as representative presents anisotropy, have three heat conduction principal directions, by this materials application when the turbo blade, owing to blade profile distorts, causing its heat conduction principal direction to there is deflection angle with the coordinates computed system of leaf model, the anisotropic heat conductivity direction of blade diverse location is different.The present invention obtains the deflection angle of material conducts heat principal direction and coordinates computed system according to blade profile and CMC material weaving, and it is calculated the local anisotropy heat conductivity of blade diverse location, it is re-introduced in the finite element program that leaf temperature field calculates, the final woven composite Turbine Blade Temperature Field field obtaining consideration fiber orientation.Compared with the method for directly given overall situation anisotropic thermal coefficient, the present invention more meets the practical structures of braided material turbo blade, and calculated leaf temperature field precision is higher.
Description
Technical field
The invention belongs to Engineering Thermophysics technical field, be specifically related to a kind of woven composite whirlpool considering fiber orientation
Impeller blade Calculation Method of Temperature Field.
Background technology
Along with stepping up of aero-engine performance, particularly thrust-weight ratio, turbine inlet fuel gas temperature is more and more higher.Not
The thrust-weight ratio carrying out the 5th generation opportunity of combat electromotor is up to about 15-20, and turbine inlet temperature will be up to 2200-2300K, and this is the most far away
Exceed the heat-resistant limit of current turbine material.Therefore with ceramic matric composite, (Ceramic Matrix Composite is called for short
CMC material) it is that the high temperature resistant composite of representative has obtained more concern, and progressively march toward engineering operational phase.
CMC material adds fiber etc. in ceramic matrix and strengthens phase so that it is on the basis of resistant to elevated temperatures, intensity also obtains greatly
The features such as big raising, has lightweight simultaneously, life-span length.But for fiber reinforced composites such as CMC, owing to it is internal non-
The architectural feature of homogenizing, and fiber axially heat conductivity with radial direction differs greatly, and then its heat conductivity is shown
Significantly anisotropic character.The heat conductivity of carbon/vinyl ester composites such as Mutnuri experiment test, result shows
Along the Equivalent Thermal Conductivities of machine direction, it it is about 2 times of vertical fibers direction Equivalent Thermal Conductivities.It addition, work as material internal
When the volume fraction of fiber is increased to 70% by 60%, the heat conductivity along machine direction increases to from 1.035W/m K
2.407W/m K, almost adds one times.Tian etc. utilize 3 ω methods experiments to have studied carbon fiber-reinforced resin base composite wood
The Equivalent Thermal Conductivities of material, the Equivalent Thermal Conductivities of result display parallel cut and thickness direction is respectively 6.316W/m*K and
0.611W/m*K, the Equivalent Thermal Conductivities ratio in both direction is 10.3.In Xu and K.Yagi etc. also indicate that composite
Direction and the arrangement mode of portion's fiber all have large effect to the heat conductivity of composite.
The generation of estimating of leaf temperature field will necessarily be affected by the anisotropy of CMC material heat conductivity, and for existing
For aero engine turbine blades, operating temperature exceed safe handling temperature 10 DEG C it is possible to bring blade ablation, more than 50
Material mechanical performance DEG C then may be made to reduce 40-50%, and blade will appear from the serious consequences such as crackle even fracture.Therefore right
Temperature field when CMC turbo blade carries out heat analysis, obtained by application tradition heat analysis method, it will there is bigger error.
This is each to different due to embody due to internal non-homogeneous, the anisotropic property of CMC material and its macro equivalent physical parameter
Property feature, compare conventional metals turbo blade heat analysis, the thermal model of CMC material turbo blade set up need to consider more
Influence factor.The most prominent is exactly introducing and the description method of anisotropic thermal coefficient.Owing to abroad grinding for CMC
Study carefully relatively early, along with the states such as material property gradually steps up and the gradually maturation of preparation technology, American-European have carried out ceramic base again
The simulating examination of condensation material typical parts and simulating piece even through engineering approaches is applied, wherein about CMC at aero engine turbine blades
On applied research, the most also have been built up corresponding Engineering Design method.
From the point of view of open source information, the most representational is that U.S. NASAGlenn research center is opened in the works at UEET
Exhibition for SiCfThe preparation of the turbo blade simulating piece of/SiC and assessment mode.This center demonstrates three-dimensional not only by test
Five to the SiC of knitting formingf/ SiC turborotor excellent properties in high-temperature fuel gas shock environment, and for this leaf
Sheet establishes the reliability prediction method under actual condition, and develops corresponding software, the research worker of NASA more than
During Calculation of Reliability, the mechanics of materials and the discreteness of thermodynamic property, blade are taken into full account from the angle of probability analysis
The uncertainty of external and internal pressure load, the fluctuation of blade construction parameter, material failure critical load discreteness etc. can to blade
By the impact of property, wherein the discreteness data of material property parameter stem from the physical property measurement result carried out for material, additionally
In blade finite element modeling, about the anisotropy of CMC physical property and bent, by blade profile, the material property main formula that causes
All carefully studied to phenomenons such as Existential Space distributions, found eventually through calculating, for current blade design scheme,
The probability that can not meet design requirement is 1.6%.Fact proved that above research work is SiCfThe commercialization of/SiC turbo blade
Solid foundation has been established in utilization.
Owing to the research of China's ceramic matric composite is started late, currently for the research of CMC also in material level, close
The most less in engineering and the Application Design technique study of CMC turbo blade, mostly focus simply on some specific technological difficulties
Problem.
Sun Jie etc., will based on cooled turbine blade blade profile and consideration method anisotropic to material property in NASA research
Plain weave composite material rigidity performance prediction and turborotor thermosetting coupling analysis combine, by optimization of material and knot
Structure is optimized integration, and from material and two yardsticks of structure, establishes ceramic base woven composite turborotor
Structure and material Integrated optimization design method.Above method is limited to constraints with material stress, blade displacement, with
Vanelets quality is optimization aim, it is thus achieved that good effect of optimization, but the method does not consider composite wood during calculating
The discreteness of material physical parameter, therefore the method wants to realize engineer applied and also needs to improve.
Xu Rui etc., on the basis of unidirectional composite material heat conductivity Research on Calculation, with Mark II turbo blade are
Object, use self-programming finite element and Fluent analogy method, and primary study heat conductivity anisotropy, heat conductivity are random
Property fluctuation to leaf temperature be distributed, particularly leading edge and the impact of trailing edge high-temperature area, it is thus achieved that leaf temperature field is to difference master
The sensitivity of heat conductivity and blade high-temperature area Changing Pattern on direction.Above achievement in research is at CMC turbo blade
Heat considers in analyzing that the discreteness of material property provides the technical scheme referred to, but in literary composition object of study can see as by
The Mark II turbo blade that unidirectional fibre is constituted, this exists with the most commercial three-dimensional slope turbine blade arrangement
Bigger difference.
Sun etc. are with reference to the research method in NASA Glenn research center with Sun Jie, from material and two yardsticks of structure,
Set up a set of for 2.5D CfThe material of/SiC guide vane-structure-integrated optimization and the method for reliability assessment.Author
Initially with monte carlo method to 2.5D CfThe mechanical performance randomness of/SiC ceramic matrix composite material is studied, and research finds
2.5D CfThe macro-mechanical performance of/SiC ceramic matrix composite material is closely related with the randomness of material component and microstructure, then
Establish a 2.5D C considering material property discretenessf/ SiC guide blade structures optimized FEMs model, and carry out
Optimize and calculate, finally by being integrated the distributed model of blade mechanism Performance Calculation result analyzing, demonstrate optimum results
Reliability.In general, above method has had stronger engineering practicability, although its objective is blade construction optimization and
Mechanics property analysis, but still foundation for CMC turbo blade thermal model has good reference.
Its hot physical property of ceramic matric composite especially FRCMC has obvious anisotropy,
After composite is heated, hot-fluid direction of transfer and size are the most relevant with composite locality heat conductivity principal direction and size,
Add the material localized thermal conductivity principal direction that the complex appearance of turbo blade causes to deflect so that blade interior-heat flow point
Cloth is more complicated, and then changes final leaf temperature distribution.Therefore the thermal model at CMC turbo blade sets up process
In, it is necessary to consider the microstructure characteristic of CMC material and the macrostructure of blade.
Summary of the invention
Goal of the invention: in order to overcome the deficiencies in the prior art, the present invention provides a kind of volume considering fiber orientation
Woven composite Turbine Blade Temperature Field field computational methods, improve the thermoanalytical precision of woven composite turbo blade such as CMC.
Technical scheme: for achieving the above object, the technical solution used in the present invention is:
A kind of woven composite Turbine Blade Temperature Field field computational methods considering fiber orientation, comprise the steps:
Step one: set up the computation model only comprising blade solid domain, and it is carried out stress and strain model；
Step 2: carry out region division according to blade construction feature, is divided into front edge area, ribs region, blade region,
Obtain trizonal outline matched curve respectively；
Step 3: respectively to trizonal outline curve derivation, the tangential direction of blade outer contour can be obtained,
According to the architectural feature of CMC material braiding blade, this tangential direction is i.e. considered as local heat conductivity principal direction；
Step 4: be outer contour node to the grid node that outer contour is closest, this grid node with described outside
The heat conductivity principal direction of contour line node is identical；
Step 5: after the heat conductivity principal direction obtaining all grid nodes of blade, according to anisotropic thermal coefficient
Matrix conversion method is calculated the anisotropic thermal coefficient of each grid node；
Step 6: calculated anisotropic thermal coefficient is assigned to the grid node of correspondence, completes braided fiber whirlpool
The setting of heat conductivity in the analysis of impeller blade heat；
Step 7: to the Transfer Boundary Condition in fixed blade inside and outside wall face, carry out the FEM calculation of blade solid domain model,
And then obtain the woven composite Turbine Blade Temperature Field field considering fiber orientation.
Further, in step 3, described blade inlet edge region outer contour is class arc-shaped, uses circular fitting side
Method, radial direction is wall normal direction, and the localized thermal conductivity principal direction of all grid nodes being in same radius is identical,
It is vertical described radius direction.
Further, in step 3, the heat conductivity principal direction of the grid node in described ribs region is consistent, is it
Width.Because width can be considered straight line, the therefore heat conductivity principal direction one of all grid nodes in ribs region
Cause.
Further, in step 4, described blade region includes pressure face, suction surface, by blade outline curve discrete
Cheng Dian；Be respectively directed to pressure face and suction surface matching contour curve function, described contour curve function derivation can be obtained pressure face,
The deflection angle between localized thermal conductivity principal direction coordinate system and coordinates computed system at suction surface outline, is heat conduction system
Number principal direction.
Further, in described step 4, for each grid node of blade interior, find therewith at outer contour
Closest grid node, when outer contour grid node is abundant, inner mesh node and corresponding contour line node it
Between line i.e. can be considered the vertical line of outer contour, then the heat conduction of this inner mesh node and corresponding outer contour grid node
Coefficient principal direction is identical.The heat conductivity principal direction of grid node i.e. its deflection angle with coordinates computed system.
Material thermal conductivity main formula at the matching contour curve function stand of pressure face and suction surface blade outline
Moving towards to space, therefore the drift angle of outline position easily obtains, and difficult point is blade interior location localized thermal conductivity main formula
To calculating, the heat conductivity principal direction understanding blade wall thickness direction material according to previous analysis keeps one with local wall normal direction
Cause.According to this characteristic, the present invention uses " nearest outline node substitution method " to calculate the heat conductivity of blade grid node
Principal direction, is specially and makees vertical line from a certain inner mesh node to outer contour, and this vertical line will exist one with described outer contour
Individual intersection point, then on this vertical line, all internal nodes all have identical heat conductivity principal direction with this intersection point.Due to point to line it
Between vertical line segment distance the shortest, therefore in the case of number of grid is the closeest, the heat conductivity master of the grid node of blade interior
Director space drift angle is consistent with the drift angle, heat conductivity principal direction space of the grid node at the blade outline at closest place.
Beneficial effect: the woven composite Turbine Blade Temperature Field field calculating side of the consideration fiber orientation that the present invention provides
Method, it is possible to obtain the inclined of material thermal conductivity principal direction and coordinates computed system according to the profile of blade and CMC material weaving
Gyration, and then the local anisotropy heat conductivity of blade diverse location it is calculated according to these deflection angles, will local
Anisotropic thermal coefficient is incorporated in the finite element program that leaf temperature field calculates, the final braiding obtaining consideration fiber orientation
Composite turbine leaf temperature field.Compared with the method for directly given overall situation anisotropic thermal coefficient, the present invention provides
Method more meets the practical structures of braided material turbo blade, and calculated leaf temperature field precision is higher.
Accompanying drawing explanation
Fig. 1 is CMC braided material turbo blade photo and microstructure schematic diagram；
Fig. 2 is fibre-woven composite turbo blade hot analysis process figure；
Fig. 3 is blade computation model and grid；
Fig. 4 is that leaf area divides schematic diagram；
Fig. 5 is that blade inlet edge region anisotropic thermal coefficient arranges schematic diagram；
Fig. 6 is that blade ribs region anisotropic thermal coefficient arranges schematic diagram；
Fig. 7 is blade region and internal node anisotropic thermal coefficient arranges schematic diagram；
Fig. 8 is not consider fiber orientation and consider the blade heat conductivity method to set up contrast schematic diagram of fiber orientation；
Fig. 9 is not consider fiber orientation and consider the composite turbine leaf temperature field cloud atlas contrast of fiber orientation.
Detailed description of the invention
Below in conjunction with the accompanying drawings the present invention is further described.
The present invention is directed to Ceramic Matrix Composite (CMC) material fibrage composite wood as representative
Material, it is considered to the heat conductivity anisotropy that the feature of its internal structure causes, and when being applied to turbo blade, due to blade
Profile distortion, cause the heat conduction principal direction of CMC material and the coordinates computed system of leaf model to there is deflection angle so that blade is not
The anisotropic heat conductivity direction of co-located is different, and the present invention can obtain material according to the profile of blade and CMC material weaving
Material heat conduction principal direction and the deflection angle of coordinates computed system, and then it is calculated blade diverse location according to these deflection angles
Local anisotropy heat conductivity, is incorporated into the finite element program that leaf temperature field calculates by local anisotropy heat conductivity
In, the final woven composite Turbine Blade Temperature Field field obtaining consideration fiber orientation.
Fig. 1 gives form of presentation be three-dimensional five to the photo and three of CMC material turbine nozzle vane prefabricated component
By CMC material micromodel, dimension five micromodels to braided material, can be seen that its braiding structure exists principal direction ζ,
And other both directions η and ν, the result of study in document the heat conductivity understanding ζ direction is relatively big, for heat conduction principal direction,
And the heat conductivity approximation in η and ν direction.The heat conduction principal direction coordinate system of definition braided material is (ζ, η, ν), and global calculation is sat
Mark system is (X, Y, Z), as shown in fig. 1.Simultaneously by Fig. 1 it can be seen that blade prefabricated component weaves principal direction ζ and blade type
Face keeping parallelism, i.e. braiding principal direction tangentially reach unanimity, therefore in the position that blade is different, due to it with local blade profile
The change of profile, also there is drift angle by difference and with coordinates computed system in the heat conductivity principal direction of material.Additionally, due to the present invention
Object of study is prismatic blade, at leaf height direction fiber weave structure in periodicity, and therefore heat conduction principal direction and coordinates computed system
Drift angle does not changes on blade height direction, i.e. ν direction is the most parallel with Z-direction.
The present invention uses Finite Element Method to calculate the CMC material Turbine Blade Temperature Field field of anisotropic heat conductivity.Calculating process
In important be a little that the heat how the anisotropic thermal coefficient of CMC material turbo blade is incorporated into turbo blade is divided
In analysis.Fig. 2 gives CMC material turbo blade is carried out thermoanalytical flow chart.Initially set up and comprise main fuel gas fluid territory
Three dimendional blade model, by FEM calculation based on fluent, obtain the Transfer Boundary Condition of blade outside wall surface；Then build
The vertical computation model only comprising blade solid domain, calculates anisotropic thermal coefficient according to the geometric properties of blade and is assigned to correspondence
Calculating node；Finally give three dimendional blade solid domain computation model by outer for the blade obtained in first step Transfer Boundary Condition,
Carry out FEM calculation and obtain the CMC material Turbine Blade Temperature Field field distribution of anisotropic heat conductivity.
It is object of study that the present invention chooses certain type gas-turbine blade, and Fig. 3 gives the computation model of blade, the tool of model
As shown in FIG., a height of 80mm of leaf, a length of 42.68mm of shaft orientation string, circumference chord length is 56.21mm to body physical dimension, and this blade is cold
But structure specifically includes: three cold air cavity, suction surface 2 aerofluxus fenestra, pressure face 3 aerofluxus fenestras, leading edge 3 aerofluxus fenestra.
In stress and strain model, vane end faces uses triangle unstrctured grid, and blade uses the prism generated from end face stretching
Structured grid, blade construction transitional region grid is automatically encrypted, and final number of meshes is 57842, adjacent cells size
The maximum rate of growth is 1.964, average rate of increase 1.088, and final blade grid is as shown in Figure 3.
Show that by the braiding structure of CMC vane in Fig. 1 the principal direction of blade heat conductivity coefficient is cut with local blade profile
To reaching unanimity.Owing to blade profile molded line is complicated, first the present invention carries out subregion according to the construction features of blade, then for
Zones of different construction features is respectively adopted distinct methods and carries out the calculating of drift angle, heat conduction principal direction space.Wherein Labelling Regions such as Fig. 4
Shown in, it is respectively as follows: 1.. leading edge；2.. ribs (forward and backward ribs)；3.. blade (pressure face, suction surface, trailing edge).
Definition braided material ζ direction heat conductivity is k11, η and ν direction heat conductivity is k22.Owing to blade is prismatic blade,
CMC braided material heat conduction principal direction only deflects at X/Y plane, and therefore the heat conductivity in the i.e. leaf height direction of blade Z-direction keeps
Do not become k22, and the heat conductivity of X and Y-direction will change at blade diverse location.Due to braiding principal direction ζ and local leaf
Sheet profile tangentially reaches unanimity, therefore the derivation of region each to blade outline matched curve, i.e. available local heat conduction main formula
To the tangent value of deflection angle between coordinate system and coordinates computed system, it is stipulated that deflection angle is negative value clockwise, and tangent value can table
Reach for:
Tan φ=-f'(x) (1)
F'(x in formula) represent the corresponding matched curve in each region function derivative, φ represents that blade local heat conduction principal direction is sat
Mark system and the coordinates computed system angle along Z axis deflection angle.Next with Fig. 4 Leaf as object, convolution (1), show leaf
The each region of sheet, heat conduction principal direction asks for process and the calculating of anisotropic thermal coefficient relative to coordinates computed system deflection angle
Method.
Owing to blade inlet edge region outer contour approximates circular arc, therefore circular fitting is used for blade inlet edge region, as
Shown in Fig. 5, arc angle span is-80 ° to 80 °, and it is (2.46,5.32) that matching obtains center coordinate of arc, radius side
To being wall normal direction, all node localized thermal conductivity directions being thus in same radius are identical, are vertical being somebody's turn to do
Radius direction.According to central angle and relation the most remaining between cutting angle, can obtain all nodes in this radius (x, y)
Heat conduction principal direction coordinate system deflection angle is:
φ1=pi/2-arctan ((y-5.32)/(x-2.46)) (2)
For ribs region, its heat conduction principal direction is its width, can be considered straight line, therefore ribs region institute
The heat conductivity direction having node is consistent, as shown in Figure 6.Obtain directly along its edge contour matching respectively for front and back's ribs
Line:
f1(x)=2.1165x-26.011
f2(x)=0.9462x-26.059 (3)
The slope of these two straight lines is the deflection relative to coordinates computed system of before and after's ribs heat conduction principal direction coordinate system
Angle is:
φ2=-arctan (f1' (x))=-2.1165
φ3=-arctan (f2' (x))=-0.9462 (4)
For blade region, blade outline curve discrete is become a little, be respectively directed to pressure face and suction surface matched curve
Function, the contour curve function derivation obtaining above matching can obtain local heat conduction principal direction at pressure face, suction surface outline
Deflection angle between coordinate system and coordinates computed system.Above iunction for curve represents the material conducts heat at blade outline
Principal direction space is moved towards, and therefore the φ of outline position easily obtains, and difficult point is blade interior location local heat conduction principal direction
Calculating, the heat conduction principal direction understanding blade wall thickness direction material according to previous analysis is consistent with local wall normal direction holding.Depend on
According to this characteristic, the present invention Finite Element Method in leaf temperature field uses " nearest outline node substitution method " to count in calculating
Calculating blade internal node φ value, it may be assumed that after using finite element grid by blade discrete region, blade interior zone is i.e. available internal
Node represents.Making vertical line from a certain internal node to outer contour, will there is an intersection point with outer contour in this vertical line, then this hangs down
On line, all nodes all have identical heat conduction principal direction with this intersection point.Owing between point to line, vertical line segment distance is the shortest, therefore
Number of grid do the closeest in the case of, the blade outline at drift angle, blade interior point heat conduction principal direction space and closest place
Drift angle, heat conduction principal direction space, place is consistent.Fig. 7 gives for a certain internal node, and in profile node, traversal finds distance outside
The nearest node i.e. schematic diagram of round dot, i.e. " nearest outline node substitution method ", it can be seen that red node joint internal with blade
The line of point is basically perpendicular to outer contour, meets local, blade region heat conduction principal direction characteristic distributions.
Blade heat conductivity arranges localized thermal conductivity deflection angle calculating section in program and is just based on above method volume
Write.In Fig. 2, anisotropic thermal figure setting module is this subprogram flow chart, illustrates to flow chart summary and leads
The setting up procedure of drift angle, hot principal direction space.According to the method, blade pressure surface, the matching respectively of suction surface profile are obtained function
Formula:
f4(x)=4 × 10-5x4-0.0037x3+0.0877x2-1.4474x+3.1255
f5(x)=-2 × 10-6x4-0.0008x3-0.0079x2+0.5461x+3.9076 (5)
The contour curve function derivation obtaining above matching can obtain the local heat conduction principal direction of pressure face and suction surface and sit
Between mark system and coordinates computed system, deflection angle φ expression formula is respectively as follows:
φ4=-arctan (f3' (x))=-arctan (0.00016x3-0.0111x2+0.1754x-1.4474)
φ5=-arctan (f4' (x))=-arctan (-8 × 10-6x3-0.0024x2-0.0158x+0.5461) (6)
After deflection angle φ obtained between blade zones of different heat conductivity principal direction coordinate system and coordinates computed system, can
To start to calculate the anisotropic thermal coefficient of correspondence position, according to the result of study in document, sit in heat conductivity principal direction
In mark system, anisotropic thermal coefficient can be expressed as:
And heat conductivity matrix should be in coordinates computed system:
When there is deflection angle between heat conduction principal direction coordinate system and coordinates computed system, transformational relation therebetween
For:
In formula
In formula, α, β and γ are rotating around X, Y and the deflection angle of Z axis between heat conduction principal direction coordinate system and coordinates computed system
Degree, due in the present invention, heat conduction principal direction coordinate system and coordinates computed system only exist deflection angle φ about the z axis, therefore exist
In calculating, α=β=0 °, γ=φ.
To the Convection Heat Transfer Boundary Conditions in fixed blade inside and outside wall face, carry out the FEM calculation of blade solid domain model, enter
And obtain the woven composite Turbine Blade Temperature Field field considering fiber orientation.
The three-dimensional five chosen in the present invention is 4.10W/m K to braided CMC material at the heat conductivity k11 of principal direction ζ,
The heat conductivity k22 of other both directions η and ν is 1.21W/m K.In order to characterize the anisotropic degree of heat conductivity, fixed
Thermal conductivity ratio r between justice ζ direction and η, ν direction is:
For the apparent advantage providing the blade anisotropic thermal coefficient method to set up that the present invention is shown, this
Bright also calculating does not considers blade profile and the distribution of anisotropic thermal Coefficient Space, directly sets overall situation anisotropic thermal system
The result of calculation of number, and with according to the calculated Comparative result of the inventive method, two kinds of heat conductivity methods to set up are as in Fig. 8
Shown in, respectively by two kinds of method named Case A and Case B.
Giving k11 in Fig. 9 is 4.10W/m K, when k22 is 1.21W/m K, and Case A and the blade pressure of Case B
Face, suction surface cloud atlas.As can be seen from Figure, being either Case A or Case is B, the temperature of blade inlet edge part is the most relatively
Height, blade trailing edge and film overcast regional temperature are relatively low.For Case A, maximum temperature is positioned at the pressure face district near leading edge
Territory, reaches 1845.7K；And for Case B, maximum temperature is positioned near leading edge stationary point, reach 1824.9K.Contrast finds,
The maximum temperature numerical value of Case B decreases 20.8K relative to Case A, and the area of high-temperature area reduces the most relatively simultaneously, relative to
Case A, Case B high-temperature area is concentrated mainly near leading edge stationary point, and the temperature of leading edge both sides decreases.Analyze reason,
This is that trailing edge temperature is relatively low owing to blade inlet edge temperature is higher, and blade solid interior heat is transmitted to trailing edge by leading edge.By Fig. 9
In it can be seen that in Case A, owing to not considering that anisotropic thermal Coefficient Space is distributed, the principal direction that heat conductivity is bigger
ζ is parallel to the X-axis of coordinates computed system all the time, and in Case B, ζ direction is tied all the time and is parallel to blade outer contour tangent line side
To.Therefore, relatively strong along the capacity of heat transmission that blade wall is tangential in Case B, the heat of leading edge high-temperature area is easier to be delivered to tail
Edge low-temperature region.
This shows and do not consider fiber orientation and consider that the leaf temperature field that fiber orientation calculating simulation obtains has
Bigger difference, and consider that the method for fiber orientation more meets the actual microstructure of material, therefore the present invention can improve CMC
Deng the thermoanalytical precision of woven composite turbo blade.
The above is only the preferred embodiment of the present invention, it should be pointed out that: for the ordinary skill people of the art
For Yuan, under the premise without departing from the principles of the invention, it is also possible to make some improvements and modifications, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (5)
1. the woven composite Turbine Blade Temperature Field field computational methods considering fiber orientation, it is characterised in that: include as
Lower step:
Step one: set up the computation model only comprising blade solid domain, and it is carried out stress and strain model；
Step 2: carry out region division according to blade construction feature, is divided into front edge area, ribs region, blade region, respectively
Obtain trizonal outline matched curve；
Step 3: respectively to trizonal outline curve derivation, the tangential direction of blade outer contour can be obtained, according to
The architectural feature of CMC material braiding blade, this tangential direction is i.e. considered as local heat conductivity principal direction；
Step 4: be outer contour node to the grid node that outer contour is closest, this grid node and described outline
The heat conductivity principal direction of line node is identical；
Step 5: after the heat conductivity principal direction obtaining all grid nodes of blade, according to anisotropic thermal coefficient matrix
Conversion method is calculated the anisotropic thermal coefficient of each grid node；
Step 6: calculated anisotropic thermal coefficient is assigned to the grid node of correspondence, completes braided fiber turbine leaf
The setting of heat conductivity in the analysis of sheet heat；
Step 7: to the Transfer Boundary Condition in fixed blade inside and outside wall face, carries out the FEM calculation of blade solid domain model, and then
Obtain the woven composite Turbine Blade Temperature Field field considering fiber orientation.
The woven composite Turbine Blade Temperature Field field computational methods of consideration fiber orientation the most according to claim 1, its
Being characterised by: in step 3, described blade inlet edge region outer contour is class arc-shaped, uses circular fitting method, radius side
To for wall normal direction, the localized thermal conductivity principal direction of all grid nodes being in same radius is identical, is vertical
Described radius direction.
The woven composite Turbine Blade Temperature Field field computational methods of consideration fiber orientation the most according to claim 1, its
Being characterised by: in step 3, the heat conductivity principal direction of the grid node in described ribs region is consistent, is its width side
To.
The woven composite Turbine Blade Temperature Field field computational methods of consideration fiber orientation the most according to claim 1, its
Being characterised by: in step 4, described blade region includes pressure face, suction surface, is become a little by blade outline curve discrete；Respectively
For pressure face and suction surface matching contour curve function, described contour curve function derivation can be obtained outside pressure face, suction surface
The deflection angle between localized thermal conductivity principal direction coordinate system and coordinates computed system at profile, is heat conductivity main formula
To.
The woven composite Turbine Blade Temperature Field field computational methods of consideration fiber orientation the most according to claim 1, its
It is characterised by: in described step 4, for each grid node of blade interior, finds closest at outer contour
Grid node, when outer contour grid node is abundant, between inner mesh node with corresponding contour line grid node
Line i.e. can be considered the vertical line of outer contour, then the heat conductivity of this inner mesh node and corresponding outer contour grid node
Principal direction is identical.
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