CN106599359A - Design method of hollow blade filled by spherical net structure and engine - Google Patents
Design method of hollow blade filled by spherical net structure and engine Download PDFInfo
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- CN106599359A CN106599359A CN201610982067.9A CN201610982067A CN106599359A CN 106599359 A CN106599359 A CN 106599359A CN 201610982067 A CN201610982067 A CN 201610982067A CN 106599359 A CN106599359 A CN 106599359A
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- 238000000034 method Methods 0.000 title claims abstract description 34
- 238000013461 design Methods 0.000 title claims abstract description 25
- 238000004519 manufacturing process Methods 0.000 claims abstract description 24
- 238000004088 simulation Methods 0.000 claims abstract description 24
- 238000004364 calculation method Methods 0.000 claims abstract description 9
- 239000000463 material Substances 0.000 claims description 22
- 238000005516 engineering process Methods 0.000 claims description 15
- 238000005457 optimization Methods 0.000 claims description 9
- 238000000465 moulding Methods 0.000 claims description 7
- 238000010438 heat treatment Methods 0.000 claims description 6
- 238000003754 machining Methods 0.000 claims description 4
- 238000012360 testing method Methods 0.000 claims description 4
- 239000007787 solid Substances 0.000 abstract 2
- 239000000654 additive Substances 0.000 abstract 1
- 230000000996 additive effect Effects 0.000 abstract 1
- 238000012546 transfer Methods 0.000 description 6
- 238000010276 construction Methods 0.000 description 2
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- 239000002184 metal Substances 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
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Abstract
The invention provides a design method of a hollow blade filled by a spherical reticular structure, which comprises the following steps: 1) carrying out pneumatic design on the hollow blade to obtain the blade surface shape of the hollow blade; 2) replacing a solid structure with spherical units with different parameters at different positions in the solid blade model to obtain a spherical reticular hollow blade; 3) establishing a finite element model, and carrying out simulation calculation on the finite element model to obtain a simulation result; 4) optimizing the spherical reticular structure of the spherical reticular hollow blade based on the simulation result of the step 3); 5) repeating the simulation calculation of the step 3) on the optimized spherical reticular hollow blade obtained in the step 4), returning to the step 4) to readjust the spherical reticular structure if the performance requirement is not met, and performing the next step if the performance requirement is met; 6) and manufacturing the optimized spherical reticular hollow blade by an additive manufacturing method. The invention has the advantages of improving various performances of the blade and lightening the mass of the blade.
Description
Technical field
The present invention relates to the method for designing of blade, more particularly to a kind of hollow blade using spherical netted structure filling
Method for designing and engine.
Background technology
Blade in aero-engine includes fan blade, compressor blade, turbo blade etc., and the development of blade is in aviation
Occupy critical role in development of engine, blade is mainly used in fan, compressor, turbine.In recent years, with structure design,
The raising of the correlation techniques such as manufacturing process, the performance of material, world-renowned Aeroengine Design and manufacturing company develop and
Demonstrate various advanced blade technologies, such as hollow blade, composite material blade, some have been applied to active service or are grinding
On aerial engine fan and compressor, and achieve good effect.
Generation and maturation with increases material manufacturing technology, traditional structure design, processing technology are changed.Increase material system
The technology of making is the technology that the method gradually added up using material manufactures entity component, is added relative to traditional material removal-cutting
Work technology, is the manufacture method of a kind of " from bottom to top ".The technology can be realized with high-performance labyrinth compact metal zero
Part it is quick, without mould, near-net-shape, be particularly suited for the overall manufacture of large and complex structure part, the appearance of increasing material manufacturing,
Restriction of the conventional machining process to Machine Design is overturned, this causes mechanical design field that great variety occurs.Using increasing material system
Making technology manufacture aero-engine has many advantages, such as, such as：Can the integrated engine component for manufacturing high complexity；Raising is started
The use temperature of machine parts；It is conveniently adjusted the performance of increasing material manufacturing parts；Functionally gradient material (FGM) etc. can be developed.
How preferably to improve the properties of blade, and mitigate leaf quality, it will design to aero-engine and
Manufacture exerts far reaching influence.
The content of the invention
In order to solve the problems of the prior art, the invention provides a kind of hollow leaf using spherical netted structure filling
The method for designing and engine of piece.
The invention provides a kind of method for designing of the hollow blade using spherical netted structure filling, including following step
Suddenly：
1) pneumatic design of hollow blade is carried out, the blade face moulding of hollow blade is obtained；
2) to step 1）The blade face moulding of the hollow blade for obtaining generates entity leaf model, and carries out centrifugal force analogue simulation
Experiment, according to the simulation result of entity leaf model, the spherical list of diverse location different parameters inside entity leaf model
Unit obtains spherical netted hollow blade replacing entity structure；
3) to step 2）The spherical netted hollow blade for obtaining sets up FEM model, carries out simulation calculation to it and is emulated
As a result；
4) based on step 3）Simulation result, optimize the spherical network structure of spherical netted hollow blade；
5) to step 4）Spherical netted hollow blade repeat step 3 after the optimization for obtaining）Simulation calculation, if be unsatisfactory for
Performance requirement, then return to step 4）Spherical network structure is readjusted, if meeting performance requirement, next step is carried out；
6) the spherical netted hollow blade by the method for increasing material manufacturing, after manufacture optimization.
As a further improvement on the present invention, it is further comprising the steps of：
7) according to design requirement, to step 6）Spherical netted hollow blade obtained by increasing material manufacturing carries out heat treatment and surface adds
Work；
8) profit experimentally, test by the spherical netted hollow blade to completing heat treatment and Surface Machining, such as discontented
Foot requirement, returns to step 1）If meeting and requiring, design is completed.
As a further improvement on the present invention, in step 4) in, by the number for increasing or deleting ball shaped unit, adjustment
The parameter of each ball shaped unit, adjusts the contact relation between multiple ball shaped units, so as to optimize spherical network structure.
As a further improvement on the present invention, step 4) in ball shaped unit include ball, spherical shell, containing pertusate ball, contain
Any one in the spherical shell of hole, the topological structure of ball or its any combination.
As a further improvement on the present invention, step 4) in the ball shaped unit parameter include ball shaped unit it is interior
Footpath, external diameter, position coordinates, material, density, spherical shell surface whether hole, the topological structure of spherical shell.
As a further improvement on the present invention, step 4) in the plurality of ball shaped unit between contact relation include phase
Hand over, it is tangent, from if between multiple ball shaped units being overlapping relation, intersecting part is all to delete or all retain
Or part retains.
As a further improvement on the present invention, in step 3) in, to step 2）The spherical netted hollow blade for obtaining is set up
FEM model, intensity, vibration, heat transfer, the calculating of the performance simulation of fatigue life are carried out to it.
As a further improvement on the present invention, step 3) described in the finite element mould for setting up spherical netted hollow blade
Type, including using hyperelement technology ball shaped unit is simplified, and sets up ball shaped unit database, forms the basic hyperelement of standard, is led to
The relation crossed between hyperelement simplifies modeling process, reduces the free degree sum of model, shortens the time required to calculating.
As a further improvement on the present invention, spherical network structure extends to the surface of spherical netted hollow blade, makes ball
The netted hollow blade of shape is separately formed by spherical network structure.
Present invention also offers a kind of engine, including being filled out using the spherical network structure of utilization any one of above-mentioned
The spherical netted hollow blade that the method for designing of the hollow blade for filling is designed.
The invention has the beneficial effects as follows：By such scheme, it is proposed that the spherical reticulated designed for increases material manufacturing technology
Lattice structure, realizes blade of aviation engine from structure design, sets up to model, to simulation analysis, then to the docking of manufacture, ball
Shape unit has simple structure, the characteristics of mechanical performance is excellent, by the parameters for adjusting ball shaped unit, and its arrangement stacking institute
The network structure of formation can be largely increased in the aspect performance such as weight, intensity, vibration characteristics, heat transfer, improve blade
Properties, and mitigate leaf quality.
Description of the drawings
Fig. 1 be a kind of method for designing design of the hollow blade using spherical netted structure filling of the present invention obtain it is spherical
The schematic diagram of netted hollow blade.
Specific embodiment
Below in conjunction with the accompanying drawings the present invention is further described for explanation and specific embodiment.
As shown in figure 1, a kind of method for designing of the hollow blade using spherical netted structure filling, it is set up and is increasing material system
Make technically, by the arrangement of hollow ball shape unit, form three-dimensional hollow network structure replace entity structure or its
His conventional hollow structure, by the parameter such as position, external diameter, internal diameter, material for designing each hollow ball shape unit, and multiple balls
Contact relation between shape unit, so as to realize the optimization of the performance such as the weight of blade, intensity, vibration, heat transfer, pneumatic.The method
The spherical network structure of design can be realized using material manufacturing technology is increased, be remarkably improved Blade Properties, reduces leaf weight.
Under present situation without ready-made proprietary emulation tool, the method can adopt hyperelement technical finesse ball cellular construction, foundation to have
Limit meta-model, significantly shortens the time needed for blade construction design, modeling and simulating, structure optimization.The present invention includes using simultaneously
The blade of the method design, and including the aero-engine and gas turbine of above-mentioned blade.
A kind of method for designing of the hollow blade using spherical netted structure filling, specifically includes following steps：
1) pneumatic design of hollow blade is carried out, the blade face moulding of hollow blade is obtained, specifically, carrying out fan, gas compressor blade
The pneumatic design of piece or turbo blade, obtains the blade face moulding of blade.Can the less processing technology for considering blade, strong during design
The restriction of the factors such as degree, vibration, heat transfer；
2) to step 1）The blade face moulding of the hollow blade for obtaining generates entity leaf model, and carries out centrifugal force analogue simulation
Experiment, according to the simulation result of entity leaf model, the spherical list of diverse location different parameters inside entity leaf model
Unit obtains spherical netted hollow blade replacing entity structure；
3) to step 2）The spherical netted hollow blade for obtaining sets up FEM model, carries out simulation calculation to it and is emulated
As a result；
4) based on step 3）Simulation result, optimize the spherical network structure of spherical netted hollow blade；
5) to step 4）Spherical netted hollow blade repeat step 3 after the optimization for obtaining）Simulation calculation, if be unsatisfactory for
Performance requirement, then return to step 4）Spherical network structure is readjusted, if meeting performance requirement, next step is carried out, is had
Body is, to step 4）Leaf model repeat step 3 after the optimization for obtaining）Simulation calculation, if being unsatisfactory for performance requirement,
Return to step 4 readjusts spherical cancellated parameter, the requirement until meeting weight, intensity, vibrations, heat transfer；
6) the spherical netted hollow blade by the method for increasing material manufacturing, after manufacture optimization.
It is further comprising the steps of：
7) according to design requirement, to step 6）Spherical netted hollow blade obtained by increasing material manufacturing carries out heat treatment and surface adds
Work；
8) profit experimentally, test by the spherical netted hollow blade to completing heat treatment and Surface Machining, such as discontented
Foot requirement, returns to step 1）If meeting and requiring, design is completed.
In step 4) in, by the number for increasing or deleting ball shaped unit, the parameter of each ball shaped unit is adjusted, adjust
Contact relation between multiple ball shaped units, so as to optimize spherical network structure.
Step 4) in ball shaped unit include ball, spherical shell, containing pertusate ball, the spherical shell containing hole, ball topological structure
In any one or its any combination.
Step 4) in the internal diameter of parameter including ball shaped unit of the ball shaped unit, external diameter, position coordinates, material, close
Degree, spherical shell surface whether hole, the topological structure of spherical shell.
Step 4) in the plurality of ball shaped unit between contact relation include it is intersecting, tangent, from if multiple balls
It is overlapping relation between shape unit, intersecting part either all retains for all deletions or part retains.
In step 3) in, to step 2）The spherical netted hollow blade for obtaining sets up FEM model, it is carried out intensity,
Vibration, heat transfer, the performance simulation of fatigue life are calculated.
Step 3) described in the FEM model for setting up spherical netted hollow blade, including being simplified using hyperelement technology
Ball shaped unit, sets up ball shaped unit database, forms the basic hyperelement of standard, and by the relation between hyperelement modeling is simplified
Process, reduces the free degree sum of model, shortens the time required to calculating.
Spherical network structure extends to the surface of spherical netted hollow blade, makes spherical netted hollow blade by spherical netted
Structure is separately formed.
A kind of engine, including the hollow blade using the spherical netted structure filling of utilization any one of above-mentioned
The spherical netted hollow blade that method for designing is designed, the engine is preferably aero-engine or gas turbine.
Above content is to combine specific preferred embodiment further description made for the present invention, it is impossible to assert
The present invention be embodied as be confined to these explanations.For general technical staff of the technical field of the invention,
On the premise of without departing from present inventive concept, some simple deduction or replace can also be made, should all be considered as belonging to the present invention's
Protection domain.
Claims (10)
1. a kind of method for designing of the hollow blade using spherical netted structure filling, it is characterised in that comprise the following steps：
1) pneumatic design of hollow blade is carried out, the blade face moulding of hollow blade is obtained；
2) to step 1）The blade face moulding of the hollow blade for obtaining generates entity leaf model, and carries out centrifugal force analogue simulation reality
Test, according to the simulation result of entity leaf model, the ball shaped unit of diverse location different parameters inside entity leaf model
To replace entity structure to obtain spherical netted hollow blade；
3) to step 2）The spherical netted hollow blade for obtaining sets up FEM model, simulation calculation is carried out to it and obtains emulation knot
Really；
4) based on step 3）Simulation result, optimize the spherical network structure of spherical netted hollow blade；
5) to step 4）Spherical netted hollow blade repeat step 3 after the optimization for obtaining）Simulation calculation, if being unsatisfactory for property
Can require, then return to step 4）Spherical network structure is readjusted, if meeting performance requirement, next step is carried out；
6) the spherical netted hollow blade by the method for increasing material manufacturing, after manufacture optimization.
2. the method for designing of the hollow blade using spherical netted structure filling according to claim 1, it is characterised in that：
It is further comprising the steps of：
7) according to design requirement, to step 6）Spherical netted hollow blade obtained by increasing material manufacturing carries out heat treatment and surface adds
Work；
8) profit experimentally, test by the spherical netted hollow blade to completing heat treatment and Surface Machining, such as discontented
Foot requirement, returns to step 1）If meeting and requiring, design is completed.
3. the method for designing of the hollow blade using spherical netted structure filling according to claim 1, it is characterised in that：
In step 4) in, by the number for increasing or deleting ball shaped unit, the parameter of each ball shaped unit is adjusted, adjust multiple spherical
Contact relation between unit, so as to optimize spherical network structure.
4. the method for designing of the hollow blade using spherical netted structure filling according to claim 3, it is characterised in that：
Step 4) in ball shaped unit include ball, spherical shell, containing pertusate ball, the spherical shell containing hole, the topological structure of ball in it is any
A kind of or its any combination.
5. the method for designing of the hollow blade using spherical netted structure filling according to claim 3, it is characterised in that：
Step 4) in the ball shaped unit parameter including ball shaped unit internal diameter, external diameter, position coordinates, material, density, spherical shell table
Face whether hole, the topological structure of spherical shell.
6. the method for designing of the hollow blade using spherical netted structure filling according to claim 3, it is characterised in that：
Step 4) in the plurality of ball shaped unit between contact relation include it is intersecting, tangent, from, if multiple ball shaped units it
Between be overlapping relation, intersecting part either all retain or part retains all to be deleted.
7. the method for designing of the hollow blade using spherical netted structure filling according to claim 1, it is characterised in that：
In step 3) in, to step 2）The spherical netted hollow blade for obtaining sets up FEM model, intensity, vibration is carried out to it, is passed
Heat, the performance simulation of fatigue life are calculated.
8. the method for designing of the hollow blade using spherical netted structure filling according to claim 1, it is characterised in that：
Step 3) described in the FEM model for setting up spherical netted hollow blade, simplify spherical list including using hyperelement technology
Unit, sets up ball shaped unit database, forms the basic hyperelement of standard, and by the relation between hyperelement modeling process is simplified,
The free degree sum of model is reduced, is shortened the time required to calculating.
9. the method for designing of the hollow blade using spherical netted structure filling according to claim 1, it is characterised in that：
Spherical network structure extends to the surface of spherical netted hollow blade, makes spherical netted hollow blade independent by spherical network structure
Constitute.
10. a kind of engine, it is characterised in that：Including using the spherical netted knot of utilization any one of claim 1 to 9
The spherical netted hollow blade that the method for designing of the hollow blade of structure filling is designed.
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| CN201610982067.9A CN106599359B (en) | 2016-11-08 | 2016-11-08 | Design method of hollow blade filled by spherical net structure and engine |
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| CN201610982067.9A CN106599359B (en) | 2016-11-08 | 2016-11-08 | Design method of hollow blade filled by spherical net structure and engine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112329138A (en) * | 2020-10-29 | 2021-02-05 | 深圳意动航空科技有限公司 | Spherical shell structure generation method and device, storage medium and electronic equipment |
| CN112628195A (en) * | 2019-10-09 | 2021-04-09 | 中国航发商用航空发动机有限责任公司 | Fan blade and aeroengine |
| CN114082988A (en) * | 2021-10-28 | 2022-02-25 | 浙江意动科技股份有限公司 | Method for repairing aero-engine cold and hot end blade |
| CN115688314A (en) * | 2022-11-03 | 2023-02-03 | 北京全四维动力科技有限公司 | Finite element analysis based turbine blade pre-twisting simulation design method and device |
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| CN101078354A (en) * | 2007-06-06 | 2007-11-28 | 北京航空航天大学 | Porous metal vane coupling design method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112628195A (en) * | 2019-10-09 | 2021-04-09 | 中国航发商用航空发动机有限责任公司 | Fan blade and aeroengine |
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| CN114082988A (en) * | 2021-10-28 | 2022-02-25 | 浙江意动科技股份有限公司 | Method for repairing aero-engine cold and hot end blade |
| CN115688314A (en) * | 2022-11-03 | 2023-02-03 | 北京全四维动力科技有限公司 | Finite element analysis based turbine blade pre-twisting simulation design method and device |
| CN115688314B (en) * | 2022-11-03 | 2024-01-23 | 北京全四维动力科技有限公司 | Method and device for pre-twisting simulation design of turbine blade based on finite element analysis |
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