CN105808838A - Multi-inner-cavity structure design method for hollow fan blade - Google Patents
Multi-inner-cavity structure design method for hollow fan blade Download PDFInfo
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Abstract
The invention provides a multi-inner-cavity structure design method for a hollow fan blade. The method comprises the following steps: constructing a blade body contour 3D model; performing region partition on a blade body; building cavity entities in corresponding regions; and lastly, performing subtract of the Boolean operation to obtain a final hollow fan blade. The method has the beneficial effects that a complete multi-cavity hollow fan blade structure design method is provided, and a plurality of control points are provided in each of cavity regions in order to ensure implementation of smooth transition and setting of unequal wall thicknesses. Through use of the method, a multi-cavity region accurate layout can be obtained and a multi-cavity blade can be generated automatically in a way of only inputting wall thickness parameters and position parameters. The method has no limitation on a platform of three-dimensional software, and multi-cavity hollow fan blade design can be performed on a plurality of software platforms through the method.
Description
Technical field
The present invention relates to hollow fan blade design field, especially relate to a kind of hollow fan blade many inner-cavity structures method for designing.
Background technology
The fan blade of modern civilian big Bypass Ratio Turbofan Engine adopts wide string blade design.With compared with the narrow string blade of boss, wide string blade has increase engine stall margin, anti-foreign object damage, improves motor power, reduces the advantages such as the number of blade, is applied on the engine.But, wide string fan blade centrifugal load increases, and while meeting reliability requirement, wheel disc quality is significantly increased, and subtracts matter designing technique if not adopting, and wide string fan blade would become hard to be applied to large-bypass-ratio engine.For this, the aero-engine companies such as RR, PW, greatly develop hollow-core construction width string fan blade design technology, successively develop honeycomb texture, band truss core mechanism and coreless structure hollow fan blade, honeycomb texture is limited with bearing capacity because subtracting matter effect, replaced by band truss core and coreless structure hollow fan blade.And the design of truss-like hollow fan blade is extremely complex, reinforcement is in the hollow region of blade, upper end, bottom, leading edge, trailing edge must and blade combine together, the shape of other parts then to change with the profile blade free form surface of bending, causes that the complicated calculations of the layout needs of reinforcement truss is derived and highly difficult modeling.
Prior art also there is research worker propose the hollow fan blade method for designing of coreless structure, but these are existing methodical it is important that when intensity analysis, carry out cavity design with reference to solid vane design criteria, adjust cavity parameter for different blade profiles.The limitation of this method is: mainly for intensity analysis rather than structural modeling, to the novel many cavity structures of multizone, big owing to retraining many, difficulty, is subject to again the requirement of free form surface fairing, it is difficult to realized the rapid modeling of cavity by geometric parameter.
Summary of the invention
It is an object of the invention to for reinforcement truss position in the truss-like hollow fan blade design of prior art and shape calculating error is relatively big, it is loaded down with trivial details to calculate complexity, reinforcement truss is difficult to problems such as seamlessly transitting, it is proposed to one hollow fan blade many inner-cavity structures method for designing.By constructing blade and blade body contour 3D model, blade being carried out region division, create cavity entity at respective regions, last boolean's difference operation obtains final hollow fan blade.
The technical scheme is that
Described a kind of hollow fan blade many inner-cavity structures method for designing, it is characterised in that: comprise the following steps:
Step 1: read the blade profile three-dimensional modeling data of existing multi-cavity hollow fan blade, or set up blade profile threedimensional model according to multi-cavity hollow fan blade design parameter；Blade profile threedimensional model includes the some layer cross section lines along short transverse and mean camber line；Each layer cross section line forms by leaf basin, blade back, leading edge and trailing edge；
Step 2: for each layer cross section line, adopts sigmoid curves in following steps structure cavity:
Step 2.1: the cavity size designing requirement according to multi-cavity hollow fan blade, selects corresponding arc length percentage ratio, it is achieved determine 2 u on mean camber line3And u7, put u3Near leading edge, put u7Near trailing edge；Cross some u3It is mean camber line normal L1, cross some 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 L1D is biased to trailing edge direction1, obtain Zhong Qu front boundary line L3, d1For middle proparea wall thickness, L3A u is met at mean camber line4；By L2Forward edge direction biasing d2, obtain boundary line L behind middle district4, d2For middle back zone wall thickness, L4A u is met at mean camber line6；L3、L4Middle district is formed with leaf basin, blade back；
Step 2.2: at the mean camber line end points u near leading edge1With a u3Between mean camber line on take 1 u2, cross some u2It is mean camber line normal L5；At the mean camber line end points u near trailing edge9With a u7Between mean camber line on take 1 u8, cross some u8It is mean camber line normal L7；At a u4With a u6Between mean camber line on take 1 u5, cross some u5It is mean camber line normal L6；
Step 2.3: the wall thickness control point taking proparea includes a pi, i=1,2,3,4,5,6, p1For the intersection point of leaf basin Yu leading edge, p4For the intersection point of blade back Yu leading edge, p2For leaf basin and L5Intersection point, p5For blade back and L5Intersection point, p3For leaf basin and L1Intersection point, p6For blade back and L1Intersection point；The wall thickness control point in Qu Zhong district includes a 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；The wall thickness control point taking back zone includes an ai, i=1,2,3,4,5,6a1For the intersection point of leaf basin Yu trailing edge, a4For the intersection point of blade back Yu trailing edge, a2For leaf basin and L7Intersection point, a5For blade back and L7Intersection point, a3For leaf basin and L2Intersection point, a6For blade back and L2Intersection point；
Step 2.4: the cavity size designing requirement according to this layer cross section, in proparea, leaf basin and blade back be biased by the wall thickness control point place of middle district and back zone；According to cavity layout to offset line and L1、L2、L3And L4Pruning, obtain the contour line of cavity, wherein proparea cavity adopts camber line to be connected smoothly near the profile border of leading edge, and back zone cavity adopts near the profile border of trailing edge entirely to split and seams meter to trailing edge place；
Step 3: the cavity contour line according to each layer cross section, sets up cavity entity；Cavity entity and blade profile entity are sought difference operation, obtains multi-cavity hollow fan blade model.
Further preferred version, described a kind of hollow fan blade many inner-cavity structures method for designing, it is characterised in that: some u2For mean camber line section u1u3Midpoint；Point u8For mean camber line section u7u9Midpoint；Point u5For mean camber line section u4u6Midpoint.
Further preferred version, described a kind of hollow fan blade many inner-cavity structures method for designing, it is characterised in that: in step 2.4, proparea cavity is accomplished by near the profile border of leading edge: at proparea cavity leaf basin side wheel profile C1fIt is C near the terminal A place of leading edge1fTangent line lA, at proparea cavity blade back side wheel profile C2fIt is C near the terminal B place of leading edge2fTangent line lB, cross A, B and do and lA、lBThe arc S of inscribeAB, arc SABFor the proparea cavity profile border near leading edge.
Further preferred version, described a kind of hollow fan blade many inner-cavity structures method for designing, it is characterised in that: in step 2.4, back zone cavity seams meter be accomplished by near entirely splitting of trailing edge profile border:
It is prolongation tangent line l at mean camber line near the end points O place of trailing edge, l is put d/2 to leaf basin lateral deviation and obtains straight line l1, d is for entirely splitting seam width；Junction point O and wall thickness control point a1, with straight line l1Meet at a C；With C point for the center of circle, a1C is that radius draws circle, hands over back zone cavity leaf basin side wheel profile C1bIn E point；Take the midpoint F of a C, some E, be Quadric spline curve S according to some C, E, a FCEEnsure at a C and the G putting E place1Continuously；Obtain the back zone cavity leaf basin side profile border near trailing edge by C1b、SCEAnd l1Composition；
It is prolongation tangent line l at mean camber line near the end points O place of trailing edge, l is put d/2 to blade back lateral deviation and obtains straight line l2；Junction point O and wall thickness control point a4, with straight line l2Meet at a D；With D point for the center of circle, a4D is that radius draws circle, hands over back zone cavity blade back side wheel profile C2bIn G point；Take the midpoint H of a D, some G, be Quadric spline curve S according to some D, G, a HDGEnsure at a D and the G putting G place1Continuously；Obtain the back zone cavity blade back side profile border near trailing edge by C2b、SDGAnd l2Composition.
Beneficial effect
The invention has the beneficial effects as follows, it is proposed that complete multi-cavity hollow fan blade construction design method, and each cavity area provides multiple control point to ensure to realize seamlessly transitting and the setting of the wall thickness such as not.By using the method, it is possible to only input wall thickness parameter and location parameter, obtaining many cavity area accurate placement, and automatically generate multi-cavity blade.The platform of three-dimensional software is not limited by this method, it is possible to use the method to carry out multi-cavity hollow fan blade design on multi software platform.
The additional aspect of the present invention and advantage will part provide in the following description, and part will become apparent from the description below, or is recognized by the practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or the additional aspect of the present invention and advantage are from conjunction with will be apparent from easy to understand the accompanying drawings below description to embodiment, wherein:
Fig. 1 is certain model fan blade model.
Fig. 2 is profile blade sectional view.
In figure, SQY-leading edge；SYB-blade back；SYP-Ye basin；SWY-trailing edge.
Fig. 3 creates blade mean camber line.
In figure, T1-leaf basin is scanned the pipeline of gained；T2-blade back is scanned the pipeline of gained；S1、S2-pipeline T1、T2Intersection；S-blade mean camber line.
Fig. 4 is that in blade, shape cavity area divides.
In figure, Dformer-proparea cavity area；Dmid-middle district cavity area；Dback-back zone cavity area；L1Boundary line ,-proparea；L2Boundary line ,-back zone；L3Boundary line ,-Zhong Qu front；L4Boundary line behind-middle district；d1-middle proparea wall thickness, i.e. boundary line, proparea L1Offset or dish；d2-middle back zone wall thickness, i.e. boundary line, back zone L2Offset or dish.
Fig. 5 is each cavity area wall thickness control point.
In figure, ui(i=1,2 ..., 9) arc length percentage points on-mean camber line；L5Cavity area midpoint ,-proparea, i.e. mean camber line u2The normal at place；L6Cavity area midpoint ,-middle district, i.e. mean camber line u5The normal at place；L7Cavity area midpoint ,-back zone, i.e. mean camber 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 district cavity area wall thickness control point；ai(i=1,2,3,4,5,6)-back zone cavity area wall thickness control point.
Fig. 6 does not prune interior shape contour line.
In figure, C1、C3、C5-Ye basin offset line；C2、C4、C6-blade back offset line；.
Fig. 7 is shape in the cavity after pruning.
In figure, C1f、C1m、C1b-Ye basin offset line C1Each cavity area contour line of gained after pruning；C2f、C2m、C2b-blade back offset line C2Each cavity area of gained after pruning；L31、L32、L33-middle district cavity area front boundary line L3The boundary line, each cavity region front, middle district of gained after pruning；L41、L42、L43Boundary line L after-middle district cavity area4Boundary line after each cavity region in middle district of gained after pruning.
Fig. 8 is proparea cavity area enlarged drawing.
In figure, C1f、C2fShape contour line in the proparea cavity of gained after the pruning of-Ye basin blade back offset line；A, B-contour line C1f、C2fThe terminal of nearly edge；lA-cross A dot profile line C1fTangent line；lB-cross B dot profile line C2fTangent line；SAB-and straight line lA、lBIt is inscribed within the circular arc of A, B.
Fig. 9 creates the nearly trailing edge place of cavity, back zone entirely to split seam.
In figure, S-mean camber line；O-mean camber line S nearly trailing edge place end points；L-mean camber line S is at the tangent line of O point；D-splits seam width entirely；l1、l2-tangent line l biases the straight line of d/2 gained to both sides；a1、a4-back zone wall thickness control point；C-straight line Oa1With biasing straight line l1Intersection point；D-straight line Oa4With biasing straight line l2Intersection point；C1b、C2b-back zone cavity contour line；E-circle C and back zone cavity contour line C1bIntersection point；The midpoint of F-point C and some E；G-circle D and back zone cavity contour line C2bIntersection point；The midpoint of H-point D and some G；SCE-by the Quadric spline curve of some C, F, E generation；SDG-by the Quadric spline curve of some D, G, H generation.
Shape cavity in the complete blade of Figure 10.
The each cross section of Figure 11 blade profile.
In figure, 1-blade profile basal cross section；N-blade profile basal cross section；I-blade profile i-th cross section.
Figure 12 is shape cavity in each cross section of blade.
Figure 13 is each cavity entity.
In figure, BF-proparea cavity entity；BM-middle district cavity entity；BB-back zone cavity entity.
Figure 14 is multi-cavity hollow fan blade entity.
Detailed description of the invention
Being described below in detail embodiments of the invention, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has the element of same or like function from start to finish.The embodiment described below with reference to accompanying drawing is illustrative of, it is intended to is used for explaining the present invention, and is not considered as limiting the invention.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ", " thickness ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", " outward ", " clockwise ", orientation or the position relationship of the instruction such as " counterclockwise " are based on orientation shown in the drawings or position relationship, it is for only for ease of the description present invention and simplifies description, rather than the device of instruction or hint indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not considered as limiting the invention.
Certain the model leaf model adopted in the present embodiment is certain model fan blade model as shown in Figure 1, under UGNX software environment, by constructing fan blade 3D model, cavity area is divided according to blade profile mean camber line, then creating each cavity inner mold entity, last boolean's difference operation obtains final hollow fan blade.Concrete enforcement step is as follows:
Step 1: set up blade profile threedimensional model according to multi-cavity hollow fan blade design parameter；As it is shown in figure 1, construct cross section SPL according to aerodynamic data, by UGNX software construction blade profile threedimensional model.It is of course also possible to directly read existing blade profile threedimensional model.
For ensureing blade smooth-shaped fairing, blade exterior cross-section curve is the curve of the complete Guan Bi created according to aerodynamic data point, and the establishment of mean camber line and blade cavity inner mold is with leaf basin, blade back, leading edge, trailing edge for benchmark.Therefore 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 it is shown on figure 3, the leaf basin blade back after dividing is used the method for scanning respectively, generate T with the ultimate range of leaf basin blade back for radius1、T2Two pipelines.Try to achieve the crossing SPL S of pipeline1、S2, and it is projected into blade trim line place plane, obtain blade mean camber line S.
Step 2: for each layer cross section line, adopts sigmoid curves in following steps structure cavity:
With mean camber line for benchmark, according to the arc length percentage ratio of mean camber line as dividing location parameter, create the boundary line of each interior shape cavity, shape in blade is divided into three cavity area, as shown in Figure 4: proparea cavity area Dformer, middle district cavity area DmidWith back zone cavity area Dback。
Step 2.1: the cavity size designing requirement according to the present embodiment multi-cavity hollow fan blade, with mean camber line near leading edge end points for starting point, determine 2 u at mean camber line 20% and 60% place respectively3And u7, put u3Near leading edge, put u7Near trailing edge.Cross some u3It is mean camber line normal L1As proparea boundary straight line, cross some u7It is mean camber line normal L2As back zone boundary straight line；L1Proparea is formed with leading edge, leaf basin, blade back；L2Back zone is formed with trailing edge, leaf basin, blade back.By L1D is biased to trailing edge direction1, obtain Zhong Qu front boundary line L3, d1For middle proparea wall thickness, L3A u is met at mean camber line4；By L2Forward edge direction biasing d2, obtain boundary line L behind middle district4, d2For middle back zone wall thickness, L4A u is met at mean camber line6；L3、L4Middle district is formed with leaf basin, blade back.
Step 2.2: at the mean camber line end points u near leading edge1With a u3Between mean camber line on take 1 u2, it is preferable that some u2For mean camber line section u1u3Midpoint, cross some a u2It is mean camber line normal L5；At the mean camber line end points u near trailing edge9With a u7Between mean camber line on take 1 u8, it is preferable that some u8For mean camber line section u7u9Midpoint, cross some a u8It is mean camber line normal L7；At a u4With a u6Between mean camber line on take 1 u5, it is preferable that some u5For mean camber line section u4u6Midpoint, cross some a u5It is mean camber line normal L6。
Step 2.3: the interior shape of cavity is wall thickness its structure of state modulator by changing wall thickness control point, for realizing the not uniform thickness of cavity area wall thickness and ensureing that in cavity, shape transition is smooth, for before, during and after three cavity area, be respectively created six wall thickness control points as shown in Figure 5:
The wall thickness control point in proparea includes a pi, i=1,2,3,4,5,6, p1For the intersection point of leaf basin Yu leading edge, p4For the intersection point of blade back Yu leading edge, p2For leaf basin and L5Intersection point, p5For blade back and L5Intersection point, p3For leaf basin and L1Intersection point, p6For blade back and L1Intersection point；
The wall thickness control point in middle district includes a 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；
The wall thickness control point of back zone includes an ai, i=1,2,3,4,5,6, a1For the intersection point of leaf basin Yu trailing edge, a4For the intersection point of blade back Yu trailing edge, a2For leaf basin and L7Intersection point, a5For blade back and L7Intersection point, a3For leaf basin and L2Intersection point, a6For blade back and L2Intersection point；
Step 2.4: the cavity size designing requirement according to this layer cross section, in proparea, leaf basin and blade back be biased by the wall thickness control point place of middle district and back zone；According to cavity layout to offset line and L1、L2、L3And L4Pruning, obtain the contour line of cavity, wherein proparea cavity adopts camber line to be connected smoothly near the profile border of leading edge, and back zone cavity adopts near the profile border of trailing edge entirely to split and seams meter to trailing edge place.
If cavity size designing requirement gives the wall thickness parameter of each wall thickness control point of every layer cross section, then directly adopt the wall thickness parameter in corresponding cross section that leaf basin blade back is biased, if cavity size designing requirement simply show the wall thickness control point wall thickness parameter of blade top section and basal cross section, the then long-pending folded axle height value according to each cross section middle, adopts interpolation method to obtain the wall thickness control point wall thickness parameter in each cross section middle.For a certain wall thickness control point, formula for interpolation is:
Wherein, D1、DnWall thickness parameter value for top section and basal cross section；z1、znHeight value for top section and basal cross section；ziHeight value for middle i-th cross section；DiWall thickness parameter value for middle i-th cross section.
In the present embodiment, as shown in Figure 6, at each cavity area wall thickness control point place, respectively leaf basin blade back is biased tentatively obtaining the contour line C of shape in blade by wall thickness parameter value1、C2.Simultaneously as cavity area width in district's is relatively big in blade, subtracts matter rate for improving it, therefore create multiple cavitys in middle region, again at wall thickness control point place of middle district, leaf basin blade back is biased, obtains the interior shape contour line C of middle region3、C4And C5、C6。
Again each interior shape cavity area is carried out cut operation.Specifically as shown in Figure 7:
Delete each cavity mean camber line midpoint normal L5、L6、L7；
With middle district front and rear side boundary line L3、L4For boundary, by mean camber line offset line C3、C4、C5、C6Part beyond middle district cavity is deleted, and obtains shape contour line in each cavity in middle district；
Delete each cavity area boundary line L1、L2、L3、L4It is positioned at leaf basin offset line C1With leaf basin line SYPBetween part；Delete each cavity area boundary line L1、L2、L3、L4It is positioned 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 C in each region1f、C1m、C1bAnd C2f、C2m、C2b；
Front and rear side boundary line L in district's in deletion3、L4Lay respectively at leaf basin offset line C3、C5Between part and be positioned at blade back offset line C4、C6Between part, obtain each luminal border line L in middle district31、L32、L33And L41、L42、L43。
Proparea cavity is accomplished by near the profile border of leading edge: as shown in Figure 8, at proparea cavity leaf basin side wheel profile C1fIt is C near the terminal A place of leading edge1fTangent line lA, at proparea cavity blade back side wheel profile C2fIt is C near the terminal B place of leading edge2fTangent line lB, cross A, B and do and lA、lBThe arc S of inscribeAB, arc SABFor the proparea cavity profile border near leading edge.
Back zone cavity seams meter be accomplished by near entirely splitting of trailing edge profile border:
It is prolongation tangent line l at mean camber line near the end points O place of trailing edge, l is put d/2 to leaf basin lateral deviation and obtains straight line l1, d is for entirely splitting seam width；Junction point O and wall thickness control point a1, with straight line l1Meet at a C；With C point for the center of circle, a1C is that radius draws circle, hands over back zone cavity leaf basin side wheel profile C1bIn E point；Take the midpoint F of a C, some E, be Quadric spline curve S according to some C, E, a FCEEnsure at a C and the G putting E place1Continuously；Obtain the back zone cavity leaf basin side profile border near trailing edge by C1b、SCEAnd l1Composition；
It is prolongation tangent line l at mean camber line near the end points O place of trailing edge, l is put d/2 to blade back lateral deviation and obtains straight line l2；Junction point O and wall thickness control point a4, with straight line l2Meet at a D；With D point for the center of circle, a4D is that radius draws circle, hands over back zone cavity blade back side wheel profile C2bIn G point；Take the midpoint H of a D, some G, be Quadric spline curve S according to some D, G, a HDGEnsure at a D and the G putting G place1Continuously；Obtain the back zone cavity blade back side profile border near trailing edge by C2b、SDGAnd l2Composition.
Step 3: the cavity contour line according to each layer cross section, sets up cavity entity as shown in fig. 13 that；Cavity entity and blade profile entity are sought difference operation, obtains multi-cavity hollow fan blade model as shown in figure 14.
Although above it has been shown and described that embodiments of the invention, it is understandable that, above-described embodiment is illustrative of, being not considered as limiting the invention, above-described embodiment can be changed when without departing from principles of the invention and objective, revises, replace and modification by those of ordinary skill in the art within the scope of the invention.
Claims (4)
1. hollow fan blade many inner-cavity structures method for designing, it is characterised in that: comprise the following steps:
Step 1: read the blade profile three-dimensional modeling data of existing multi-cavity hollow fan blade, or set up blade profile threedimensional model according to multi-cavity hollow fan blade design parameter；Blade profile threedimensional model includes the some layer cross section lines along short transverse and mean camber line；Each layer cross section line forms by leaf basin, blade back, leading edge and trailing edge；
Step 2: for each layer cross section line, adopts sigmoid curves in following steps structure cavity:
Step 2.1: the cavity size designing requirement according to multi-cavity hollow fan blade, selects corresponding arc length percentage ratio, it is achieved determine 2 u on mean camber line3And u7, put u3Near leading edge, put u7Near trailing edge；Cross some u3It is mean camber line normal L1, cross some 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 L1D is biased to trailing edge direction1, obtain Zhong Qu front boundary line L3, d1For middle proparea wall thickness, L3A u is met at mean camber line4；By L2Forward edge direction biasing d2, obtain boundary line L behind middle district4, d2For middle back zone wall thickness, L4A u is met at mean camber line6；L3、L4Middle district is formed with leaf basin, blade back；
Step 2.2: at the mean camber line end points u near leading edge1With a u3Between mean camber line on take 1 u2, cross some u2It is mean camber line normal L5；At the mean camber line end points u near trailing edge9With a u7Between mean camber line on take 1 u8, cross some u8It is mean camber line normal L7；At a u4With a u6Between mean camber line on take 1 u5, cross some u5It is mean camber line normal L6；
Step 2.3: the wall thickness control point taking proparea includes a pi, i=1,2,3,4,5,6, p1For the intersection point of leaf basin Yu leading edge, p4For the intersection point of blade back Yu leading edge, p2For leaf basin and L5Intersection point, p5For blade back and L5Intersection point, p3For leaf basin and L1Intersection point, p6For blade back and L1Intersection point；The wall thickness control point in Qu Zhong district includes a 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；The wall thickness control point taking back zone includes an ai, i=1,2,3,4,5, a1For the intersection point of leaf basin Yu trailing edge, a4For the intersection point of blade back Yu trailing edge, a2For leaf basin and L7Intersection point, a5For blade back and L7Intersection point, a3For leaf basin and L2Intersection point, a6For blade back and L2Intersection point；
Step 2.4: the cavity size designing requirement according to this layer cross section, in proparea, leaf basin and blade back be biased by the wall thickness control point place of middle district and back zone；According to cavity layout to offset line and L1、L2、L3And L4Pruning, obtain the contour line of cavity, wherein proparea cavity adopts camber line to be connected smoothly near the profile border of leading edge, and back zone cavity adopts near the profile border of trailing edge entirely to split and seams meter to trailing edge place；
Step 3: the cavity contour line according to each layer cross section, sets up cavity entity；Cavity entity and blade profile entity are sought difference operation, obtains multi-cavity hollow fan blade model.
2. a kind of hollow fan blade many inner-cavity structures method for designing according to claim 1, it is characterised in that: some u2For mean camber line section u1u3Midpoint；Point u8For mean camber line section u7u9Midpoint；Point u5For mean camber line section u4u6Midpoint.
3. a kind of hollow fan blade many inner-cavity structures method for designing according to claim 1, it is characterised in that: in step 2.4, proparea cavity is accomplished by near the profile border of leading edge: at proparea cavity leaf basin side wheel profile C1fIt is C near the terminal A place of leading edge1fTangent line lA, at proparea cavity blade back side wheel profile C2fIt is C near the terminal B place of leading edge2fTangent line lB, cross A, B and do and lA、lBThe arc S of inscribeAB, arc SABFor the proparea cavity profile border near leading edge.
4. a kind of hollow fan blade many inner-cavity structures method for designing according to claim 1, it is characterised in that: in step 2.4, back zone cavity seams meter be accomplished by near entirely splitting of trailing edge profile border:
It is prolongation tangent line l at mean camber line near the end points O place of trailing edge, l is put d/2 to leaf basin lateral deviation and obtains straight line l1, d is for entirely splitting seam width；Junction point O and wall thickness control point a1, with straight line l1Meet at a C；With C point for the center of circle, a1C is that radius draws circle, hands over back zone cavity leaf basin side wheel profile C1bIn E point；Take the midpoint F of a C, some E, be Quadric spline curve S according to some C, E, a FCEEnsure at a C and the G putting E place1Continuously；Obtain the back zone cavity leaf basin side profile border near trailing edge by C1b、SCEAnd l1Composition；
It is prolongation tangent line l at mean camber line near the end points O place of trailing edge, l is put d/2 to blade back lateral deviation and obtains straight line l2；Junction point O and wall thickness control point a4, with straight line l2Meet at a D；With D point for the center of circle, a4D is that radius draws circle, hands over back zone cavity blade back side wheel profile C2bIn G point；Take the midpoint H of a D, some G, be Quadric spline curve S according to some D, G, a HDGEnsure at a D and the G putting G place1Continuously；Obtain the back zone cavity blade back side profile border near trailing edge by C2b、SDGAnd l2Composition.
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