CN108090292A - A kind of width string fan blade two dimensional finite element modeling method - Google Patents
A kind of width string fan blade two dimensional finite element modeling method Download PDFInfo
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Abstract
The invention belongs to aero-engine fields, and in particular to a kind of wide string fan blade two dimensional finite element modeling method.A kind of two dimensional finite element modeling method for being suitable for wide string fan blade, includes the following steps：1 two dimensional finite element mesh generation, the extraction of 2 three dimendional blade thickness informations, the mapping of 3 two dimensional finite element web thickness, 4 blade centrifugal force compensation amendments.The three dimensional mass and Stiffness Distribution of the energy wide string fan blade of real simulation, make the fan wheel disc stress that two-dimensional finite element model is calculated tally with the actual situation；Its technical principle is clear, and operating method is simple and easy to do, is suitable for engineer application；The two-dimensional finite Meta Model of rest blade class formation is also extrapolated to, improves the Strength Simulation precision of engine part.
Description
Technical field
The invention belongs to aero-engine fields, and in particular to a kind of wide string fan blade two-dimensional finite Meta Model side
Method.
Background technology
In the design process of aero-engine, pass through frequently with two dimensional model during rotor assembly finite element stress analysis, and
The two-dimensional finite element model of blade is typically the plane stress element using tape thickness, and entire blade two dimensional model has same
Thickness is to simulate its quality centrifugal force.This rotor blade two dimensional model is primarily upon overall centrifugal force load, does not consider true
The quality and Stiffness Distribution of fertile leaf piece, thus in rotor two dimensional model finite element stress analysis, the load of blade transmission may be caused
Lotus is distributed and real structure generates difference or even the stress of wheel disc is calculated for two-dimensional finite element model and true three-dimension structure goes out
Existing difference, especially for the wide string fan Blisk of more disc, this species diversity is more obvious so that two dimensional finite element mould
The stress distribution of each disc is calculated in type and real structure is not inconsistent.
The content of the invention
The present invention be directed to two-dimensional finite element model is used to analyze wide string fan propeller stress point in Aeroengine Design
During analysis, the quality and Stiffness Distribution of non-accurate simulation real blade, so that the wheel disk stress that two-dimensional finite element model is calculated
The problem of not being inconsistent with real structure provides a kind of two dimensional finite element modeling method for being suitable for wide string fan blade.
Technical scheme
A kind of two dimensional finite element modeling method for being suitable for wide string fan blade, includes the following steps：
Step 1: two dimensional finite element mesh generation
Wide string fan propeller structure such as Fig. 1 is made of wide string fan blade (1) and wheel disc (2).By wide string fan propeller
Two-dimensional structure is separated along wheel rim runner (3), wherein four angle points of wide string fan blade (1) meridian projected outline are from blade root leading edge
(4) it is respectively blade root leading edge (4), blade tip leading edge (5), blade tip trailing edge (6), blade root trailing edge (7) by arranged clockwise, such as Fig. 2, with
Blade root leading edge (4) establishes rectangular coordinate system for origin, and vertically, Y-axis is in the horizontal direction for X-axis.With wide string fan blade (1)
Meridian projected outline establishes meridional plane, and setup unit length is discrete for quadrangle list by wide string fan blade (1) meridional plane
Member, wherein element length according to the demand of simulation precision set, cell type be tape thickness plane stress element, each list
Member has unique number and location information.Each unit in wide string fan blade (1) meridian plane two dimensional finite element grid can be obtained
EiBarycenter I, center-of-mass coordinate be (xi,yi), the thickness h of unitiFor value to be set.
Step 2: three dimendional blade thickness information is extracted
The three-dimensional structure of wide string fan propeller along wheel rim runner (3) is separated, is equally established with blade root leading edge (4) for origin
Rectangular coordinate system, vertically, Y-axis is in the horizontal direction for X-axis；The blade profile section of wide string fan blade (1) three-dimensional structure of extraction
(8) data, the coordinate of any point J is (X on blade profile section (8)i, Yi, Zi), such as Fig. 3.Any blade profile section (8) is in YZ planes
Projection such as Fig. 4, obtain length Hs of any point J along Z-direction in the range of blade profile sectioni=Zi1-Zi2, and set along Y direction
Step-length extracts blade profile section thickness.
Step 3: two dimensional finite element web thickness maps
The center-of-mass coordinate array of all blade units in two dimensional finite element grid is set as [x, y], corresponding thickness information
Array is h.The coordinate array that three-dimensional blade profile section (8) projects on X/Y plane is [X, Y], and corresponding thickness information array is
NH, wherein N are fan rotor blade number.It is mapped by location-based matrix by the thickness information of threedimensional model [X, Y] position
Array NH is mapped to the thickness information array h at two dimensional model [x, y], in this approach by the quality and Stiffness Distribution of three-dimensional blade profile
It is mapped on two dimensional finite element grid.
Step 4: blade centrifugal force compensation amendment
For the blade centrifugal force error generated in the above process, need to compensate and correct.If wide string fan blade (1)
Density of material is ρ1, the volume of three dimendional blade is V1, barycenter radius is R1；Unit E in two-dimensional finite element modeliBarycenter radius
For xi, thickness has been obtained as h by mappingi, cellar area is measurable and is set to Ai, the grid sum of two-dimensional finite element model
For n；By blade centrifugal force equivalence principle, the equivalent density for obtaining two-dimensional finite element model should be
Complete the two-dimensional finite Meta Model of wide string fan blade (1).
Element length scope is 0.1mm~1mm in the step 1.
Three dimendional blade thickness extraction step-length is 0.05mm~0.1mm in the step 2.
Beneficial effects of the present invention
A kind of two dimensional finite element modeling method of wide string fan blade provided by the invention, can the wide string fan leaf of real simulation
The three dimensional mass and Stiffness Distribution of piece make the fan wheel disc stress that two-dimensional finite element model is calculated tally with the actual situation；Its
Technical principle is clear, and operating method is simple and easy to do, is suitable for engineer application；The two dimension for being also extrapolated to rest blade class formation has
Meta Model is limited, improves the Strength Simulation precision of engine part.
Description of the drawings
Fig. 1 is wide string fan propeller figure
Fig. 2 is wide string fan blade two-dimensional structure figure
Fig. 3 is wide string fan blade three-dimensional blade profile sectional view
Fig. 4 is three-dimensional blade profile cross section projection
Fig. 5 is the flow chart of the present invention
Specific embodiment
A kind of two dimensional finite element modeling method for being suitable for wide string fan blade, includes the following steps：
Step 1: two dimensional finite element mesh generation
Wide string fan propeller structure such as Fig. 1 is made of wide string fan blade (1) and wheel disc (2).By wide string fan propeller
Two-dimensional structure is separated along wheel rim runner (3), wherein four angle points of wide string fan blade (1) meridian projected outline are from blade root leading edge
(4) it is respectively blade root leading edge (4), blade tip leading edge (5), blade tip trailing edge (6), blade root trailing edge (7) by arranged clockwise, such as Fig. 2, with
Blade root leading edge (4) establishes rectangular coordinate system for origin, and vertically, Y-axis is in the horizontal direction for X-axis.With wide string fan blade (1)
Meridian projected outline establishes meridional plane, and setup unit length is discrete for quadrangle list by wide string fan blade (1) meridional plane
Member, wherein element length according to the demand of simulation precision set, cell type be tape thickness plane stress element, each list
Member has unique number and location information.Each unit in wide string fan blade (1) meridian plane two dimensional finite element grid can be obtained
EiBarycenter I, center-of-mass coordinate be (xi,yi), the thickness h of unitiFor value to be set.
Step 2: three dimendional blade thickness information is extracted
The three-dimensional structure of wide string fan propeller along wheel rim runner (3) is separated, right angle is established for origin with blade root leading edge (4)
Coordinate system, vertically, Y-axis is in the horizontal direction, consistent with the coordinate definition of two dimensional finite element grid, convenient for blade two for X-axis
It ties up in finite element grid thickness mapping process and is corresponded into row position；The blade profile section of wide string fan blade (1) three-dimensional structure of extraction
(8) parameter, the coordinate of any point J is (X on blade profile section (8)i, Yi, Zi) such as Fig. 3.Any blade profile section (8) is in YZ planes
Projection such as Fig. 4, obtain length Hs of any point J along Z-direction in the range of blade profile sectioni=Zi1-Zi2, HiAs coordinate (Xi,
Yi, Zi) the corresponding vane thickness in position.Since the blade root leading edge of blade profile section (8), step-length is set to extract along Y direction
The vane thickness of position is needed, this step-length should be less than the element length of two dimensional finite element grid in step 1, obtain in this approach every
A blade profile section thickness information completes the thickness information extraction of three dimendional blade.
Step 3: two dimensional finite element web thickness maps
The center-of-mass coordinate array of all units in blade two dimensional finite element grid is obtained as [x, y] by step 1, it is corresponding
Thickness information array be h.The coordinate that the point of thickness information is projected in X/Y plane is extracted in step 2 on three-dimensional blade profile section (8)
Array is [X, Y], and corresponding thickness information array is NH, and wherein N is fan rotor blade number.It is reflected by location-based matrix
It penetrates and the thickness information array NH of threedimensional model [X, Y] position is mapped to thickness information array h at two dimensional model [x, y], lead to
This step operation is crossed the thickness distribution of three-dimensional blade profile has been mapped on two dimensional finite element grid.
Step 4: blade centrifugal force compensation amendment
For the blade centrifugal force error generated in the above process, need to compensate and correct.If wide string fan blade (1)
Density of material is ρ1, the volume of three dimendional blade is V1, barycenter radius is R1；Unit E in two-dimensional finite element modeliBarycenter radius
For xi, thickness has been obtained as h by mappingi, cellar area is measurable and is set to Ai, the grid sum of two-dimensional finite element model
For n；By blade centrifugal force equivalence principle, the equivalent density for obtaining two-dimensional finite element model should beComplete the two-dimensional finite Meta Model of wide string fan blade (1).
Element length scope is 0.1mm~1mm in the step 1.
Three dimendional blade thickness extraction step-length is 0.05mm~0.1mm in the step 2.
Claims (3)
1. a kind of two dimensional finite element modeling method for being suitable for wide string fan blade, it is characterised in that；Include the following steps：
Step 1: two dimensional finite element mesh generation
Wide string fan propeller is made of wide string fan blade (1) and wheel disc (2)；By the two-dimensional structure of wide string fan propeller along wheel rim
Runner (3) separates, wherein four angle points of wide string fan blade (1) meridian projected outline are arranged from blade root leading edge (4) as clockwise
Row are respectively blade root leading edge (4), blade tip leading edge (5), blade tip trailing edge (6), blade root trailing edge (7), are built with blade root leading edge (4) for origin
Vertical rectangular coordinate system, vertically, Y-axis is in the horizontal direction for X-axis；Son is established with wide string fan blade (1) meridian projected outline
Noon plane, setup unit length is discrete for quadrilateral units by wide string fan blade (1) meridional plane, wherein element length according to
The demand of simulation precision is set, and cell type is the plane stress element of tape thickness, each unit have unique number and
Location information；Each unit E in wide string fan blade (1) meridian plane two dimensional finite element grid can be obtainediBarycenter I, barycenter sit
It is designated as (xi,yi), the thickness h of unitiFor value to be set；
Step 2: three dimendional blade thickness information is extracted
The three-dimensional structure of wide string fan propeller along wheel rim runner (3) is separated, right angle is equally established for origin with blade root leading edge (4)
Coordinate system, vertically, Y-axis is in the horizontal direction for X-axis；Blade profile section (8) number of wide string fan blade (1) three-dimensional structure of extraction
According to the coordinate of any point J is (X on blade profile section (8)i, Yi, Zi), projection of any blade profile section (8) in YZ planes is as schemed
4, obtain length Hs of any point J along Z-direction in the range of blade profile sectioni=Zi1-Zi2, and extract leaf along Y direction setting step-length
Type section thickness；
Step 3: two dimensional finite element web thickness maps
The center-of-mass coordinate array of all blade units in two dimensional finite element grid is set as [x, y], corresponding thickness information array
For h；The coordinate array that three-dimensional blade profile section (8) projects on X/Y plane is [X, Y], and corresponding thickness information array is NH,
Middle N is fan rotor blade number；It is mapped by location-based matrix by the thickness information array NH of threedimensional model [X, Y] position
The quality of three-dimensional blade profile and Stiffness Distribution, are mapped to by the thickness information array h being mapped at two dimensional model [x, y] in this approach
On two dimensional finite element grid；
Step 4: blade centrifugal force compensation amendment
For the blade centrifugal force error generated in the above process, need to compensate and correct；If the material of wide string fan blade (1)
Density is ρ1, the volume of three dimendional blade is V1, barycenter radius is R1；Unit E in two-dimensional finite element modeliBarycenter radius be xi,
Thickness has been obtained as h by mappingi, cellar area is measurable and is set to Ai, the grid sum of two-dimensional finite element model is n；It is logical
Blade centrifugal force equivalence principle is crossed, the equivalent density for obtaining two-dimensional finite element model should beComplete
The two-dimensional finite Meta Model of wide string fan blade (1).
2. a kind of two dimensional finite element modeling method for being suitable for wide string fan blade according to claim 1, feature exist
In；Element length scope is 0.1mm~1mm in the step 1.
3. a kind of two dimensional finite element modeling method for being suitable for wide string fan blade according to claim 1, feature exist
In；Three dimendional blade thickness extraction step-length is 0.05mm~0.1mm in the step 2.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109101772A (en) * | 2018-09-29 | 2018-12-28 | 中国民航大学 | Aerial engine fan unbalance dynamic model rotor equivalent-designing method |
| CN109556765A (en) * | 2018-12-10 | 2019-04-02 | 中国航发四川燃气涡轮研究院 | A kind of blade non-contacting vibration strain measurements conversion method |
| CN112966398A (en) * | 2021-04-13 | 2021-06-15 | 宁波大学 | Voronoi porous gradient structure generation method based on stress distribution |
| CN114526164A (en) * | 2022-04-24 | 2022-05-24 | 中国航发四川燃气涡轮研究院 | Transition state performance modeling method suitable for double-working-mode core machine |
| CN115081280A (en) * | 2022-06-17 | 2022-09-20 | 北京航空航天大学 | Automatic establishing method of finite element model of H-shaped rib hollow fan blade |
| CN116306180A (en) * | 2023-05-22 | 2023-06-23 | 陕西空天信息技术有限公司 | Impeller auxiliary analysis method, device, equipment, medium and product |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105260563A (en) * | 2015-11-03 | 2016-01-20 | 复旦大学 | Finite element prestressed mode analysis method for three-dimensional entity blade and two-dimensional axisymmetric wheel disc variable-dimensionality model of impeller structure |
| CN106484993A (en) * | 2016-10-08 | 2017-03-08 | 中国航空动力机械研究所 | Integral wheel Cyclic Symmetry automatic Mesh Generation Method |
| CN106709179A (en) * | 2016-12-21 | 2017-05-24 | 中国燃气涡轮研究院 | Blade aerodynamic distribution data processing method suitable for finite element free mesh |
-
2017
- 2017-12-26 CN CN201711427365.2A patent/CN108090292B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105260563A (en) * | 2015-11-03 | 2016-01-20 | 复旦大学 | Finite element prestressed mode analysis method for three-dimensional entity blade and two-dimensional axisymmetric wheel disc variable-dimensionality model of impeller structure |
| CN106484993A (en) * | 2016-10-08 | 2017-03-08 | 中国航空动力机械研究所 | Integral wheel Cyclic Symmetry automatic Mesh Generation Method |
| CN106709179A (en) * | 2016-12-21 | 2017-05-24 | 中国燃气涡轮研究院 | Blade aerodynamic distribution data processing method suitable for finite element free mesh |
Non-Patent Citations (3)
| Title |
|---|
| CHUNJIAN WANG 等: "Forced in-plane vibration of a thick ring on a unilateral elastic foundation", 《JOURNALOFSOUNDANDVIBRATION》 * |
| 刘力群: "涡轮增压器压气机叶轮的逆向工程及有限元分析", 《万方数据库》 * |
| 张乘齐 等: "低惯量涡轮转子结构设计与优化", 《燃气涡轮试验与研究》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109101772A (en) * | 2018-09-29 | 2018-12-28 | 中国民航大学 | Aerial engine fan unbalance dynamic model rotor equivalent-designing method |
| CN109101772B (en) * | 2018-09-29 | 2023-01-17 | 中国民航大学 | Equivalent design method for dynamic unbalance simulation rotor of fan of aircraft engine |
| CN109556765A (en) * | 2018-12-10 | 2019-04-02 | 中国航发四川燃气涡轮研究院 | A kind of blade non-contacting vibration strain measurements conversion method |
| CN112966398A (en) * | 2021-04-13 | 2021-06-15 | 宁波大学 | Voronoi porous gradient structure generation method based on stress distribution |
| CN114526164A (en) * | 2022-04-24 | 2022-05-24 | 中国航发四川燃气涡轮研究院 | Transition state performance modeling method suitable for double-working-mode core machine |
| CN115081280A (en) * | 2022-06-17 | 2022-09-20 | 北京航空航天大学 | Automatic establishing method of finite element model of H-shaped rib hollow fan blade |
| CN116306180A (en) * | 2023-05-22 | 2023-06-23 | 陕西空天信息技术有限公司 | Impeller auxiliary analysis method, device, equipment, medium and product |
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