CN105808838B - A kind of more inner-cavity structure design methods of hollow fan blade - Google Patents
A kind of more inner-cavity structure design methods of hollow fan blade Download PDFInfo
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Abstract
The present invention proposes a kind of more inner-cavity structure design methods of hollow fan blade, and by constructing blade and blade body contour 3D models, region division is carried out to blade, creates cavity entity in corresponding region, last boolean's difference operation obtains final hollow fan blade.The invention has the advantages that complete multi-cavity hollow fan blade construction design method is proposed, and each cavity area provides multiple control points to ensure to realize the setting for seamlessly transitting and not waiting wall thickness.By using the method, wall thickness parameter and location parameter can be only being inputted, obtain more cavity area accurate placements, and automatically generate multi-cavity blade.There is no limit can carry out multi-cavity hollow fan blade design to platform of this method to three-dimensional software with the method on multi software platform.
Description
Technical field
The present invention relates to hollow fan blade design fields, are tied more particularly, to a kind of more inner cavities of hollow fan blade
Structure design method.
Background technology
The fan blade of modern civilian big Bypass Ratio Turbofan Engine mostly uses wide string blade design.With the narrow string with boss
Blade is compared, and wide string blade, which has, to be increased engine stall margin, anti-foreign object damage, improves motor power, reduce the number of blade
The advantages that, it is applied on the engine.But wide string fan blade centrifugal load increases, and is meeting reliability requirement
Meanwhile wheel disc quality is significantly increased, and subtracts matter designing technique if not using, wide string fan blade would become hard to be applied to big bypass ratio hair
Motivation.For this purpose, the aero-engines such as RR, PW company, greatly develops the wide string fan blade design technology of hollow-core construction, successively develops
Honeycomb, band truss core mechanism and coreless structure hollow fan blade, honeycomb because subtract matter effect and bearing capacity by
Limit is replaced by band truss core and coreless structure hollow fan blade.And the design of truss-like hollow fan blade is extremely complex,
Reinforcing rib is in the hollow region of blade, upper end, bottom end, leading edge, trailing edge must and blade combine together, the shape of other parts
Then to change with the shape blade free form surface of bending, cause reinforcing rib truss layout need complicated calculations derive and it is high-leveled and difficult
The modeling of degree.
Also there is researcher to propose the hollow fan blade design method of coreless structure, but these existing sides in the prior art
The emphasis of method be under conditions of intensive analysis, with reference to solid vane design criteria carry out cavity design, for different blades outside
Shape adjusts cavity parameter.The limitation of this method is：Mainly for intensive analysis rather than structural modeling, to novel multi-region
The more cavity structures in domain, since constraint is more, difficulty is big, and by the requirement of free form surface fairing, it is difficult to be realized by geometric parameter
The rapid modeling of cavity.
Invention content
The purpose of the present invention is for the prior art truss-like hollow fan blade design in reinforcing rib truss position and
Shape calculates the problems such as error is larger, calculating is complicated cumbersome, reinforcing rib truss is difficult to seamlessly transit, and proposes a kind of hollow fan leaf
The more inner-cavity structure design methods of piece.By constructing blade and blade body contour 3D models, region division is carried out to blade, in corresponding region
Cavity entity is created, last boolean's difference operation obtains final hollow fan blade.
The technical scheme is that：
The more inner-cavity structure design methods of a kind of hollow fan blade, it is characterised in that：Include the following steps：
Step 1：The blade shape three-dimensional modeling data of existing multi-cavity hollow fan blade is read, or hollow according to multi-cavity
Fan blade design parameter establishes blade shape threedimensional model；If blade shape threedimensional model includes the dried layer section along short transverse
Upper thread and mean camber line；Each layer cross section line is made of leaf basin, blade back, leading edge and trailing edge；
Step 2：For each layer cross section line, using shape curve in following steps construction cavity：
Step 2.1：According to the cavity size design requirement of multi-cavity hollow fan blade, corresponding arc length percentage is selected,
It realizes and determines two point u on mean camber line3And u7, point u3Close to leading edge, point u7Close to trailing edge；Cross point u3It is mean camber line normal L1, mistake
Point u7It is mean camber line normal L2；L1Proparea is formed with leading edge, leaf basin, blade back；L2Back zone is formed with trailing edge, leaf basin, blade back；By L1To
Trailing edge direction biases d1, obtain the fronts Zhong Qu boundary line L3, d1For middle proparea wall thickness, L3Point u is met at mean camber line4；By L2Forward edge
Direction biases d2, obtain the back Zhong Qu boundary line L4, d2For middle back zone wall thickness, L4Point u is met at mean camber line6；L3、L4With leaf basin, leaf
Antiform Cheng Zhongqu；
Step 2.2：In mean camber line close to up-front endpoint u1With point u3Between mean camber line on take a point u2, cross point u2It does
Mean camber line normal L5；In mean camber line close to the endpoint u of trailing edge9With point u7Between mean camber line on take a point u8, cross point u8Do middle arc
Collimation method line L7；In point u4With point u6Between mean camber line on take a point u5, cross point u5It is mean camber line normal L6；
Step 2.3：It includes point p to take the wall thickness control point in propareai, i=1,2,3,4,5,6, p1For leaf basin and up-front friendship
Point, p4For blade back and up-front intersection point, p2For leaf basin and L5Intersection point, p5For blade back and L5Intersection point, p3For leaf basin and L1Friendship
Point, p6For blade back and L1Intersection point；The wall thickness control point in the areas Qu Zhong includes point ci, i=1,2,3,4,5,6, c1For leaf basin and L3's
Intersection point, c4For blade back and L3Intersection point, c2For leaf basin and L6Intersection point, c5For blade back and L6Intersection point, c3For leaf basin and L4Friendship
Point, c6For blade back and L4Intersection point；It includes point a to take the wall thickness control point of back zonei, i=1,2,3,4,5,6, a1For leaf basin and trailing edge
Intersection point, a4For the intersection point of blade back and trailing edge, a2For leaf basin and L7Intersection point, a5For blade back and L7Intersection point, a3For leaf basin and L2
Intersection point, a6For blade back and L2Intersection point；
Step 2.4：According to the cavity size design requirement of the layer cross section, the wall thickness control point in proparea, middle area and back zone
Place is biased leaf basin and blade back；According to cavity layout to offset line and L1、L2、L3And L4It is trimmed, obtains cavity
Contour line, wherein proparea cavity are connected smoothly close to up-front profile and border using camber line, and back zone cavity is close to trailing edge
Profile and border is seamed using complete split at meter to trailing edge；
Step 3：According to the cavity contour line of each layer cross section, cavity entity is established；By cavity entity and blade shape entity
Difference operation is sought, multi-cavity hollow fan blade model is obtained.
Further preferred embodiment, a kind of more inner-cavity structure design methods of hollow fan blade, it is characterised in that：Point
u2For mean camber line section u1u3Midpoint；Point u8For mean camber line section u7u9Midpoint；Point u5For mean camber line section u4u6Midpoint.
Further preferred embodiment, a kind of more inner-cavity structure design methods of hollow fan blade, it is characterised in that：Step
In rapid 2.4, proparea cavity is accomplished by the following way close to up-front profile and border：In proparea cavity leaf basin side wheel profile C1fIt leans on
C is at nearly up-front terminal A1fTangent line lA, in proparea cavity blade back side wheel profile C2fC is at up-front terminal B2f's
Tangent line lB, mistake A, B are done and lA、lBThe arc S of inscribeAB, arc SABIt is proparea cavity close to up-front profile and border.
Further preferred embodiment, a kind of more inner-cavity structure design methods of hollow fan blade, it is characterised in that：Step
In rapid 2.4, back zone cavity seams meter and is accomplished by the following way close to complete split of trailing edge profile and border：
It is done at endpoint O of the mean camber line close to trailing edge and extends tangent line l, l is obtained into straight line l to leaf basin side biasing d/21, d is
Split slit width degree entirely；Tie point O and wall thickness control point a1, with straight line l1Meet at point C；Using C points as the center of circle, a1C is that radius draws circle, is handed over
Back zone cavity leaf basin side wheel profile C1bIn E points；The midpoint F for taking point C, point E is Quadric spline curve S according to point C, E, FCEEnsure
G at point C and point E1Continuously；Back zone cavity is obtained close to the leaf basin side profile boundary of trailing edge by C1b、SCEAnd l1Composition；
It is done at endpoint O of the mean camber line close to trailing edge and extends tangent line l, l is obtained into straight line l to blade back side biasing d/22；Even
Contact O and wall thickness control point a4, with straight line l2Meet at point D；Using D points as the center of circle, a4D is that radius draws circle, hands over back zone cavity blade back side
Contour line C2bIn G points；The midpoint H for taking point D, point G is Quadric spline curve S according to point D, G, HDGEnsure at point D and point G
G1Continuously；Back zone cavity is obtained close to the blade back side profile boundary of trailing edge by C2b、SDGAnd l2Composition.
Advantageous effect
The invention has the advantages that complete multi-cavity hollow fan blade construction design method is proposed, and it is each
Cavity area provides multiple control points to ensure to realize the setting for seamlessly transitting and not waiting wall thickness.It, can be with by using the method
Wall thickness parameter and location parameter are only being inputted, is obtaining more cavity area accurate placements, and automatically generate multi-cavity blade.This method
To the platform of three-dimensional software, there is no limit can carry out multi-cavity hollow fan blade on multi software platform with the method and set
Meter.
The additional aspect and advantage of the present invention will be set forth in part in the description, and will partly become from the following description
Obviously, or practice through the invention is recognized.
Description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become in the description from combination following accompanying drawings to embodiment
Obviously and it is readily appreciated that, wherein：
Fig. 1 is certain model fan blade model.
Fig. 2 is shape blade sectional view.
In figure, SQYLeading edge；SYBBlade back；SYPLeaf basin；SWYTrailing edge.
Fig. 3 is to create blade mean camber line.
In figure, T1The pipeline of gained is scanned to leaf basin；T2The pipeline of gained is scanned to blade back；S1、S2Pipeline T1、T2's
Intersection；S- blade mean camber lines.
Fig. 4 is that shape cavity area divides in blade.
In figure, DformerProparea cavity area；DmidMiddle area's cavity area；DbackBack zone cavity area；L1Proparea boundary
Line；L2Back zone boundary line；L3The fronts-Zhong Qu boundary line；L4The back-Zhong Qu boundary line；d1Middle proparea wall thickness, i.e. proparea boundary line L1Partially
Set distance；d2Middle back zone wall thickness, i.e. back zone boundary line L2Offset or dish.
Fig. 5 is each cavity area wall thickness control point.
In figure, uiArc length percentage points on (i=1,2 ..., 9)-mean camber line；L5Proparea cavity area midpoint, i.e., middle arc
Line u2The normal at place；L6Middle area's cavity area midpoint, i.e. mean camber line u5The normal at place；L7Back zone cavity area midpoint, i.e., middle arc
Line u8The normal at place；pi(i=1,2,3,4,5,6)-proparea cavity area wall thickness control point；ci(i=1,2,3,4,5,6)-middle area
Cavity area wall thickness control point；ai(i=1,2,3,4,5,6)-back zone cavity area wall thickness control point.
Fig. 6 is not trim interior shape contour line.
In figure, C1、C3、C5Leaf basin offset line；C2、C4、C6Blade back offset line；.
Fig. 7 be trimming after cavity in shape.
In figure, C1f、C1m、C1bLeaf basin offset line C1Each cavity area contour line of gained after trimming；C2f、C2m、C2bLeaf
Carry on the back offset line C2Each cavity area of gained after trimming；L31、L32、L33Middle area's cavity area front boundary line L3Gained after trimming
The middle each cavity region front in area boundary line；L41、L42、L43Middle area's cavity area back boundary line L4Each inner cavity in middle area of gained after trimming
Region back boundary line.
Fig. 8 is proparea cavity area enlarged drawing.
In figure, C1f、C2fShape contour line in the proparea cavity of gained after the trimming of leaf basin blade back offset line；A, B- contour lines
C1f、C2fThe terminal of nearly edge；lACross A dot profile lines C1fTangent line；lBCross B dot profile lines C2fTangent line；SABWith straight line
lA、lBIt is inscribed within the circular arc of A, B.
Fig. 9 is to create to split seam entirely at the nearly trailing edge of back zone cavity.
In figure, S- mean camber lines；Endpoint at the nearly trailing edges of O- mean camber lines S；Tangent lines of the l- mean camber lines S in O points；D- splits slit width entirely
Degree；l1、l2Tangent line l biases the straight line obtained by d/2 to both sides；a1、a4Back zone wall thickness control point；C- straight lines Oa1With biasing straight line
l1Intersection point；D- straight lines Oa4With biasing straight line l2Intersection point；C1b、C2bBack zone cavity contour line；E- justifies C and back zone cavity profile
Line C1bIntersection point；The midpoint of F- point C and point E；G- justifies D and back zone cavity contour line C2bIntersection point；The midpoint of H- point D and point G；
SCEThe Quadric spline curve generated by point C, F, E；SDGThe Quadric spline curve generated by point D, G, H.
Shape cavity in the complete blades of Figure 10.
Each section of Figure 11 blade shapes.
In figure, 1- blade shape basal cross sections；N- blade shape basal cross sections；I-th of section of i- blades shape.
Figure 12 is shape cavity in each section of blade.
Figure 13 is each cavity entity.
In figure, BFProparea cavity entity；BMMiddle area's cavity entity；BBBack zone cavity entity.
Figure 14 is multi-cavity hollow fan blade entity.
Specific implementation mode
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning to end
Same or similar label indicates same or similar element or element with the same or similar functions.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to for explaining the present invention, and is not considered as limiting the invention.
In the description of the present invention, it is to be understood that, term "center", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside", " up time
The orientation or positional relationship of the instructions such as needle ", " counterclockwise " is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of
The description present invention and simplified description, do not indicate or imply the indicated device or element must have a particular orientation, with spy
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
Certain the model leaf model used in the present embodiment is certain model fan blade model as shown in Figure 1, in UG NX
Under software environment, by constructing fan blade 3D models, cavity area is divided according to blade shape mean camber line, then creates each sky
Intracavitary type entity, last boolean's difference operation obtain final hollow fan blade.Specific implementation steps are as follows：
Step 1：Blade shape threedimensional model is established according to multi-cavity hollow fan blade design parameter；As shown in Figure 1, according to
Aerodynamic data constructs section spline curve, and blade shape threedimensional model is constructed by UG NX softwares.It is of course also possible to directly read
Take existing blade shape threedimensional model.
To ensure blade smooth-shaped fairing, blade exterior cross-section curve is according to aerodynamic data point and create one is complete
The curve of whole closure, and the establishment of mean camber line and blade cavity inner mold is on the basis of leaf basin, blade back, leading edge, trailing edge.Therefore according to
According to blade profile cross section curve curvature variation, blade appearance curve is divided into leading edge S as shown in Figure 2QY, blade back line SYB, leaf
Basin line SYP, trailing edge line SWY。
As shown in figure 3, to the leaf basin blade back after division respectively with method is scanned, using the maximum distance of leaf basin blade back as radius
Generate T1、T2Two pipelines.Acquire the intersection spline curve S of pipeline1、S2, and it is projected into plane where blade trim line,
Obtain blade mean camber line S.
Step 2：For each layer cross section line, using shape curve in following steps construction cavity：
On the basis of mean camber line, according to the arc length percentage of mean camber line as location parameter is divided, each interior shape cavity is created
Boundary line, shape in blade is divided into three cavity areas, as shown in Figure 4：Proparea cavity area Dformer, middle area's cavity zone
Domain DmidWith back zone cavity area Dback。
Step 2.1：According to the cavity size design requirement of the present embodiment multi-cavity hollow fan blade, with mean camber line by nearby
Acies point is starting point, determines two point u at mean camber line 20% and 60% respectively3And u7, point u3Close to leading edge, point u7Close to trailing edge.
Cross point u3It is mean camber line normal L1As proparea boundary straight line, point u is crossed7It is mean camber line normal L2As back zone boundary straight line；L1With
Leading edge, leaf basin, blade back form proparea；L2Back zone is formed with trailing edge, leaf basin, blade back.By L1D is biased to trailing edge direction1, in obtaining
Area front boundary line L3, d1For middle proparea wall thickness, L3Point u is met at mean camber line4；By L2Forward edge direction biases d2, after obtaining middle area
Boundary line L4, d2For middle back zone wall thickness, L4Point u is met at mean camber line6；L3、L4Middle area is formed with leaf basin, blade back.
Step 2.2：In mean camber line close to up-front endpoint u1With point u3Between mean camber line on take a point u2, preferred point u2
For mean camber line section u1u3Midpoint, cross point u2It is mean camber line normal L5；In mean camber line close to the endpoint u of trailing edge9With point u7Between
A point u is taken on mean camber line8, preferred point u8For mean camber line section u7u9Midpoint, cross point u8It is mean camber line normal L7；In point u4With point u6
Between mean camber line on take a point u5, preferred point u5For mean camber line section u4u6Midpoint, cross point u5It is mean camber line normal L6。
Step 2.3：The interior shape of cavity is by its structure of the wall thickness state modulator of change wall thickness control point, to realize sky
The not uniform thickness of cavity region wall thickness simultaneously ensures that shape transition is smooth in cavity, three cavity areas for before, during and after, be respectively created as
Six wall thickness controls point shown in fig. 5：
The wall thickness control point in proparea includes point pi, i=1,2,3,4,5,6, p1For leaf basin and up-front intersection point, p4For blade back
With up-front intersection point, p2For leaf basin and L5Intersection point, p5For blade back and L5Intersection point, p3For leaf basin and L1Intersection point, p6For blade back
With L1Intersection point；
The wall thickness control point in middle area includes point ci, i=1,2,3,4,5,6, c1For leaf basin and L3Intersection point, c4For blade back and L3
Intersection point, c2For leaf basin and L6Intersection point, c5For blade back and L6Intersection point, c3For leaf basin and L4Intersection point, c6For blade back and L4Friendship
Point；
The wall thickness control point of back zone includes point ai, i=1,2,3,4,5,6, a1For the intersection point of leaf basin and trailing edge, a4For blade back
With the intersection point of trailing edge, a2For leaf basin and L7Intersection point, a5For blade back and L7Intersection point, a3For leaf basin and L2Intersection point, a6For blade back
With L2Intersection point；
Step 2.4：According to the cavity size design requirement of the layer cross section, the wall thickness control point in proparea, middle area and back zone
Place is biased leaf basin and blade back；According to cavity layout to offset line and L1、L2、L3And L4It is trimmed, obtains cavity
Contour line, wherein proparea cavity are connected smoothly close to up-front profile and border using camber line, and back zone cavity is close to trailing edge
Profile and border is seamed using complete split at meter to trailing edge.
If cavity size design requirement gives the wall thickness parameter of each wall thickness control point of every layer cross section, directly use pair
The wall thickness parameter in section is answered to be biased leaf basin blade back, if cavity size design requirement simply shows blade top section and bottom
The wall thickness control point wall thickness parameter in section obtains centre then according to the long-pending folded axle height value in intermediate each section using interpolation method
The wall thickness control point wall thickness parameter in each section.For a certain wall thickness control point, interpolation formula is：
Wherein, D1、DnFor the wall thickness parameter value of top section and basal cross section；z1、znFor the height value of top section and basal cross section；zi
For the height value in intermediate i-th of section；DiFor the wall thickness parameter value in intermediate i-th of section.
In the present embodiment, as shown in fig. 6, at each cavity area wall thickness control point, by wall thickness parameter value respectively to leaf
Basin blade back, which is biased, tentatively obtains the contour line C of shape in blade1、C2.Simultaneously as area's cavity area width is larger in blade,
Subtract matter rate to improve it, therefore a plurality of cavities are created in middle region, leaf basin blade back is carried out at middle area's wall thickness control point again
Biasing, obtains the interior shape contour line C of middle region3、C4And C5、C6。
Cut operation is carried out to each interior shape cavity area again.It is specific as shown in Figure 7：
Delete each cavity mean camber line midpoint normal L5、L6、L7；
With boundary line L before and after middle area3、L4For boundary, by mean camber line offset line C3、C4、C5、C6It deletes part other than middle area's cavity
It removes, obtains shape contour line in each cavity in middle area；
Delete each cavity area boundary line L1、L2、L3、L4Positioned at leaf basin offset line C1With leaf basin line SYPBetween part；It deletes
Each cavity area boundary line L1、L2、L3、L4Positioned at blade back offset line C2With blade back line SYBBetween part；
Delete mean camber line offset line C1、C2Part between each cavity area boundary line obtains the interior shape contour line in each region
C1f、C1m、C1bAnd C2f、C2m、C2b；
Boundary line L before and after area in deletion3、L4It is located at leaf basin offset line C3、C5Between part and be located at blade back offset line
C4、C6Between part, obtain each luminal border line L in middle area31、L32、L33And L41、L42、L43。
Proparea cavity is accomplished by the following way close to up-front profile and border：As shown in figure 8, in proparea cavity leaf basin side
Contour line C1fC is at up-front terminal A1fTangent line lA, in proparea cavity blade back side wheel profile C2fClose to up-front endpoint
C is at B2fTangent line lB, mistake A, B are done and lA、lBThe arc S of inscribeAB, arc SABIt is proparea cavity close to up-front profile and border.
Back zone cavity seams meter and is accomplished by the following way close to complete split of trailing edge profile and border：
It is done at endpoint O of the mean camber line close to trailing edge and extends tangent line l, l is obtained into straight line l to leaf basin side biasing d/21, d is
Split slit width degree entirely；Tie point O and wall thickness control point a1, with straight line l1Meet at point C；Using C points as the center of circle, a1C is that radius draws circle, is handed over
Back zone cavity leaf basin side wheel profile C1bIn E points；The midpoint F for taking point C, point E is Quadric spline curve S according to point C, E, FCEEnsure
G at point C and point E1Continuously；Back zone cavity is obtained close to the leaf basin side profile boundary of trailing edge by C1b、SCEAnd l1Composition；
It is done at endpoint O of the mean camber line close to trailing edge and extends tangent line l, l is obtained into straight line l to blade back side biasing d/22；Even
Contact O and wall thickness control point a4, with straight line l2Meet at point D；Using D points as the center of circle, a4D is that radius draws circle, hands over back zone cavity blade back side
Contour line C2bIn G points；The midpoint H for taking point D, point G is Quadric spline curve S according to point D, G, HDGEnsure at point D and point G
G1Continuously；Back zone cavity is obtained close to the blade back side profile boundary of trailing edge by C2b、SDGAnd l2Composition.
Step 3：According to the cavity contour line of each layer cross section, cavity entity as shown in fig. 13 that is established；By cavity entity with
Blade shape entity seeks difference operation, obtains multi-cavity hollow fan blade model as shown in figure 14.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art are not departing from the principle of the present invention and objective
In the case of can make changes, modifications, alterations, and variations to the above described embodiments within the scope of the invention.
Claims (4)
1. a kind of more inner-cavity structure design methods of hollow fan blade, it is characterised in that：Include the following steps：
Step 1：The blade shape three-dimensional modeling data of existing multi-cavity hollow fan blade is read, or according to multi-cavity hollow fan
Blade design parameter establishes blade shape threedimensional model；Blade shape threedimensional model includes several layer cross section lines along short transverse
And mean camber line；Each layer cross section line is made of leaf basin, blade back, leading edge and trailing edge；
Step 2：For each layer cross section line, using shape curve in following steps construction cavity：
Step 2.1：According to the cavity size design requirement of multi-cavity hollow fan blade, corresponding arc length percentage is selected, is realized
Two point u are determined on mean camber line3And u7, point u3Close to leading edge, point u7Close to trailing edge；Cross point u3It is mean camber line normal L1, cross point u7
It is mean camber line normal L2；L1Proparea is formed with leading edge, leaf basin, blade back；L2Back zone is formed with trailing edge, leaf basin, blade back；By L1To tail
Edge direction biases d1, obtain the fronts Zhong Qu boundary line L3, d1For middle proparea wall thickness, L3Point u is met at mean camber line4；By L2Forward edge side
To biasing d2, obtain the back Zhong Qu boundary line L4, d2For middle back zone wall thickness, L4Point u is met at mean camber line6；L3、L4With leaf basin, blade back
Area in formation；
Step 2.2：In mean camber line close to up-front endpoint u1With point u3Between mean camber line on take a point u2, cross point u2Do mean camber line
Normal L5；In mean camber line close to the endpoint u of trailing edge9With point u7Between mean camber line on take a point u8, cross point u8Do mean camber line normal
L7；In point u4With point u6Between mean camber line on take a point u5, cross point u5It is mean camber line normal L6；
Step 2.3：It includes point p to take the wall thickness control point in propareai, i=1,2,3,4,5,6, p1For leaf basin and up-front intersection point, p4
For blade back and up-front intersection point, p2For leaf basin and L5Intersection point, p5For blade back and L5Intersection point, p3For leaf basin and L1Intersection point, p6
For blade back and L1Intersection point；The wall thickness control point in the areas Qu Zhong includes point ci, i=1,2,3,4,5,6, c1For leaf basin and L3Intersection point,
c4For blade back and L3Intersection point, c2For leaf basin and L6Intersection point, c5For blade back and L6Intersection point, c3For leaf basin and L4Intersection point, c6For
Blade back and L4Intersection point；It includes point a to take the wall thickness control point of back zonei, i=1,2,3,4,5,6, a1For the intersection point of leaf basin and trailing edge,
a4For the intersection point of blade back and trailing edge, a2For leaf basin and L7Intersection point, a5For blade back and L7Intersection point, a3For leaf basin and L2Intersection point, a6
For blade back and L2Intersection point；
Step 2.4：According to the cavity size design requirement of the layer cross section, at the wall thickness control point in proparea, middle area and back zone pair
Leaf basin and blade back are biased；According to cavity layout to offset line and L1、L2、L3And L4It is trimmed, obtains the profile of cavity
Line, wherein proparea cavity are connected smoothly close to up-front profile and border using camber line, profile of the back zone cavity close to trailing edge
Boundary is seamed using complete split at meter to trailing edge；
Step 3：According to the cavity contour line of each layer cross section, cavity entity is established；Cavity entity and blade shape entity are asked
Difference operation obtains multi-cavity hollow fan blade model.
2. the more inner-cavity structure design methods of a kind of hollow fan blade according to claim 1, it is characterised in that：Point u2For in
Arc segment u1u3Midpoint；Point u8For mean camber line section u7u9Midpoint；Point u5For mean camber line section u4u6Midpoint.
3. the more inner-cavity structure design methods of a kind of hollow fan blade according to claim 1, it is characterised in that：Step 2.4
In, proparea cavity is accomplished by the following way close to up-front profile and border：In proparea cavity leaf basin side wheel profile C1fBy nearby
C is at the terminal A of edge1fTangent line lA, in proparea cavity blade back side wheel profile C2fC is at up-front terminal B2fTangent line
lB, mistake A, B are done and lA、lBThe arc S of inscribeAB, arc SABIt is proparea cavity close to up-front profile and border.
4. the more inner-cavity structure design methods of a kind of hollow fan blade according to claim 1, it is characterised in that：Step 2.4
In, back zone cavity seams meter and is accomplished by the following way close to complete split of trailing edge profile and border：
It is done at endpoint O of the mean camber line close to trailing edge and extends tangent line l, l is obtained into straight line l to leaf basin side biasing d/21, d is to split entirely
Slit width degree；Tie point O and wall thickness control point a1, with straight line l1Meet at point C；Using C points as the center of circle, a1C is that radius draws circle, hands over back zone
Cavity leaf basin side wheel profile C1bIn E points；The midpoint F for taking point C, point E is Quadric spline curve S according to point C, E, FCEEnsure in point
G at C and point E1Continuously；Back zone cavity is obtained close to the leaf basin side profile boundary of trailing edge by C1b、SCEAnd l1Composition；
It is done at endpoint O of the mean camber line close to trailing edge and extends tangent line l, l is obtained into straight line l to blade back side biasing d/22；Tie point O
With wall thickness control point a4, with straight line l2Meet at point D；Using D points as the center of circle, a4D is that radius draws circle, hands over back zone cavity blade back side profile
Line C2bIn G points；The midpoint H for taking point D, point G is Quadric spline curve S according to point D, G, HDGEnsure the G at point D and point G1Even
It is continuous；Back zone cavity is obtained close to the blade back side profile boundary of trailing edge by C2b、SDGAnd l2Composition.
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| CN106599359B (en) * | 2016-11-08 | 2020-01-21 | 南方科技大学 | Design method of hollow blade filled by spherical net structure and engine |
| CN108090275B (en) * | 2017-12-14 | 2021-12-28 | 中国航发沈阳发动机研究所 | Turbine air cooling blade configuration method facing parametric model |
| CN108549773B (en) * | 2018-04-16 | 2022-11-01 | 西北工业大学 | Grid parameterization method and turbine blade multidisciplinary reliability design optimization method based on grid parameterization method |
| CN109214047B (en) * | 2018-07-26 | 2022-12-20 | 中国航发沈阳发动机研究所 | Hollow stator blade modeling method based on UG |
| CN109063352B (en) * | 2018-08-10 | 2023-01-06 | 上海汽轮机厂有限公司 | Method for improving surface smoothness of turbine blade profile |
| CN109622992B (en) * | 2018-11-17 | 2020-08-04 | 宁夏共享精密加工有限公司 | Method for machining deep groove of revolving body |
| CN109409020B (en) * | 2018-12-16 | 2023-04-18 | 中国航发沈阳发动机研究所 | Modeling method of hollow fan blade |
| CN112214849B (en) * | 2020-09-29 | 2022-12-27 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of H-shaped rib hollow fan blade |
| CN113374534B (en) * | 2021-06-09 | 2022-08-30 | 中国航发湖南动力机械研究所 | Turbine blade trailing edge split seam modeling method |
| CN113642130B (en) * | 2021-08-25 | 2024-04-02 | 中国航发湖南动力机械研究所 | Blade cavity design method, machine-readable storage medium and data processing device |
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