CN106874550A - A kind of aeroengine fan blades reproducing method based on increasing material design - Google Patents
A kind of aeroengine fan blades reproducing method based on increasing material design Download PDFInfo
- Publication number
- CN106874550A CN106874550A CN201710018560.3A CN201710018560A CN106874550A CN 106874550 A CN106874550 A CN 106874550A CN 201710018560 A CN201710018560 A CN 201710018560A CN 106874550 A CN106874550 A CN 106874550A
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- China
- Prior art keywords
- fan blades
- increasing material
- aeroengine fan
- aeroengine
- reproducing method
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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
- G06F30/17—Mechanical parametric or variational design
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention provides a kind of based on the aeroengine fan blades reproducing method for increasing material design, on the premise of the aerodynamic configuration and functional characteristic for not changing aeroengine fan blades, designed using sub-surface fine mesh structure, introduce sphere hollow unit, the hollow network structure of dome shape for meeting structural intergrity requirement is internally formed in the aeroengine fan blades by multiple sphere hollow units, finally completes to remanufacture using increases material manufacturing technology.The beneficial effects of the invention are as follows：Aeroengine fan blades weight can effectively be mitigated, aeroengine fan blades blade root problem of stress concentration is solved, change the difficult present situation of conventional diffusion connection weldering manufacture craft complex operations, give full play to and increase the effect that material manufactures and designs in aeroengine fan blades are remanufactured.
Description
Technical field
The present invention relates to aeroengine fan blades, more particularly to a kind of aerial engine fan based on increasing material design
Blade reproducing method.
Background technology
Aeroengine fan blades forming technology under traditional handicraft is complicated, and manufacture is difficult, involves great expense.
The content of the invention
In order to solve the problems of the prior art, the invention provides a kind of based on the aerial engine fan for increasing material design
Blade reproducing method.
The invention provides a kind of based on the aeroengine fan blades reproducing method for increasing material design, do not changing boat
On the premise of the aerodynamic configuration and functional characteristic of empty engine blower blade, designed using sub-surface fine mesh structure, introduce sphere
Hollow unit, is internally formed that to meet structure complete by multiple sphere hollow units in the aeroengine fan blades
The hollow network structure of dome shape of whole property requirement, finally completes to remanufacture using increases material manufacturing technology.
As a further improvement on the present invention, between the adjacent sphere hollow unit in it is intersecting, tangent, in
Any one.
It is including following present invention also offers a kind of based on the aeroengine fan blades reproducing method for increasing material design
Step：
S1, the functional architecture model for setting up existing aeroengine fan blades；
S2, hit, contain according to mitigating weight, reduce stress raisers, effectively adjustment blade fundamental vibration frequency and meet bird
Design requirement, the functional architecture model of aeroengine fan blades is designed using sub-surface fine mesh structure, introduce sphere
Hollow unit, is internally formed that to meet structure complete by multiple sphere hollow units in the aeroengine fan blades
The hollow network structure of dome shape of whole property requirement, forms increasing material and designs a model；
S3, above-mentioned increasing material is designed a model using finite element analysis instrument carry out service check, and service check is not less than setting
Desired value is to enter next step；Previous step is otherwise returned to complete to increase material design again；
S4, the increasing material the checked importing increasing material manufacturing equipment completion increasing material that designs a model will be analyzed remanufacture.
As a further improvement on the present invention, also including step S5, carry out reliability demonstration.
The beneficial effects of the invention are as follows：Aeroengine fan blades weight can effectively be mitigated, aeroplane engine is solved
Machine fan blade blade root problem of stress concentration, changes the difficult present situation of conventional diffusion connection weldering manufacture craft complex operations, fully
Play increasing material and manufacture and design the effect in aeroengine fan blades are remanufactured.
Brief description of the drawings
Fig. 1 is a kind of flow chart based on the aeroengine fan blades reproducing method for increasing material design of the present invention.
Fig. 2 is using a kind of boat based on the aeroengine fan blades reproducing method manufacture for increasing material design of the present invention
The schematic diagram of empty engine blower blade.
Fig. 3 is using a kind of boat based on the aeroengine fan blades reproducing method manufacture for increasing material design of the present invention
The generalized section of empty engine blower blade.
Fig. 4 is using a kind of boat based on the aeroengine fan blades reproducing method manufacture for increasing material design of the present invention
The generalized section of empty engine blower blade.
Specific embodiment
The invention will be further described for explanation and specific embodiment below in conjunction with the accompanying drawings.
A kind of aeroengine fan blades reproducing method based on increasing material design, is not changing aerial engine fan
On the premise of the aerodynamic configuration and functional characteristic of blade 1, designed using sub-surface fine mesh structure, introduce sphere hollow unit 2, led to
Cross multiple sphere hollow units 2 and meet structural intergrity requirement in being internally formed for the aeroengine fan blades 1
Dome shape hollow network structure, finally complete to remanufacture using increases material manufacturing technology, mitigate aeroengine fan blades 1
Own wt, solves the problems, such as that the Root Stress of aeroengine fan blades 1 is concentrated, while effectively shortening the manufacturing cycle, reduces
Cost.
Increases material manufacturing technology is the technology that a kind of method that use material gradually adds up manufactures part, different from traditional material
Material removal subtracts material process technology.Increases material manufacturing technology achieves quickly development over nearly 20 years.This technology does not need traditional
Cutter and multi-step process, can quickly and critically produce the zero of arbitrary complicated shape in same equipment
Part, is effectively shortened the process-cycle of part, reduces the technology difficulty of part processing, improves the processing essence of part processing
Degree.
Sub-surface fine mesh structure designing technique is a kind of new structure design model, can effectively mitigate the weight of part
Amount and solve the problem of stress concentration of part, while the functional character of design of part will not be changed, strengthen part stability and
Life-span.
The radius of the sphere hollow unit 2, thickness are unfettered, can arbitrarily be matched somebody with somebody according to the requirement of original structure functional characteristic
Put.
In intersecting, tangent, any one between the adjacent sphere hollow unit 2, can be according to original knot
Structure characteristic requirements arbitrary disposition.
As shown in Figures 1 to 4, it is a kind of based on the aeroengine fan blades reproducing method for increasing material design, specific bag
Include following steps：
S1, the functional architecture model for setting up existing aeroengine fan blades 1；
S2, hit, contain according to mitigating weight, reduce stress raisers, effectively adjustment blade fundamental vibration frequency and meet bird
Design requirement, the functional architecture model of aeroengine fan blades 1 is designed using sub-surface fine mesh structure, introduce sphere
Hollow unit 2, satisfaction knot is internally formed by multiple sphere hollow units 2 in the aeroengine fan blades 1
The hollow network structure of dome shape of structure integrity demands, forms increasing material and designs a model；
S3, above-mentioned increasing material is designed a model using finite element analysis instrument carry out service check, and service check is not less than setting
Desired value is to enter next step, and service check is not less than the desired value of setting including the various performances such as intensity, rigidity（Biography is not weaker than
The component of system technique manufacture）；Otherwise return to previous step to complete to increase material design again, then carry out finite element analysis, until point
Analysis result reaches the requirement of setting；
S4, the increasing material the checked importing increasing material manufacturing equipment completion increasing material that designs a model will be analyzed remanufacture；
S5, if necessary, carries out reliability demonstration.
It is a kind of based on the aeroengine fan blades reproducing method for increasing material design that the present invention is provided, using advanced
Increase material design re-manufacturing technology, be different from the hollow knot of traditional hollow fan blade manufacture craft and traditional fan blade
Structure, can effectively mitigate the own wt of fan blade, solve the problem of stress concentration of fan blade root；Can also effectively adjust
Blade fundamental vibration frequency and meet bird and the design requirement such as hit, contain.Meanwhile, compared to diffusion connection weldering, the present invention is in shaping work
The increasing material manufacturing technological process used in skill is simple, and the manufacturing cycle is shorter, and cost is lower.
It is a kind of based on the aeroengine fan blades reproducing method for increasing material design that the present invention is provided, using sub-surface
Fine mesh structure is designed, and introduces sphere hollow unit, is internally formed in fan blade spherical hollow, is entered using finite element analysis instrument
Row analysis is checked, and optimizes dimensions and the arrangement of hollow ball, reaches design requirement.
It is a kind of based on the aeroengine fan blades reproducing method for increasing material design that the present invention is provided, using advanced
Increase material design re-manufacturing technology, it is no longer necessary to traditional complicated moulding process, directly by setting up accurate threedimensional model, quickly
Required blade construction is produced, can effectively shorten the production cycle of part, reduce the forming technology difficulty of part, improved
The forming accuracy of part.
Above content is to combine specific preferred embodiment further description made for the present invention, it is impossible to assert
Specific implementation of the invention is confined to these explanations.For general technical staff of the technical field of the invention,
On the premise of not departing from present inventive concept, some simple deduction or replace can also be made, should be all considered as belonging to of the invention
Protection domain.
Claims (4)
1. a kind of based on the aeroengine fan blades reproducing method for increasing material design, it is characterised in that：Do not changing aviation
On the premise of the aerodynamic configuration and functional characteristic of engine blower blade, designed using sub-surface fine mesh structure, be introduced into sphere
Dummy cell, structural integrity is met by multiple sphere hollow units in being internally formed for the aeroengine fan blades
Property require the hollow network structure of dome shape, finally using increases material manufacturing technology complete remanufacture.
2. according to claim 1 based on the aeroengine fan blades reproducing method for increasing material design, its feature exists
In：In intersecting, tangent, any one between the adjacent sphere hollow unit.
3. it is a kind of based on the aeroengine fan blades reproducing method for increasing material design, it is characterised in that to comprise the following steps：
S1, the functional architecture model for setting up existing aeroengine fan blades；
S2, hit, contain according to mitigating weight, reduce stress raisers, effectively adjustment blade fundamental vibration frequency and meet bird
Design requirement, the functional architecture model of aeroengine fan blades is designed using sub-surface fine mesh structure, introduce sphere
Hollow unit, is internally formed that to meet structure complete by multiple sphere hollow units in the aeroengine fan blades
The hollow network structure of dome shape of whole property requirement, forms increasing material and designs a model；
S3, above-mentioned increasing material is designed a model using finite element analysis instrument carry out service check, and service check is not less than setting
Desired value is to enter next step；Previous step is otherwise returned to complete to increase material design again；
S4, the increasing material the checked importing increasing material manufacturing equipment completion increasing material that designs a model will be analyzed remanufacture.
4. according to claim 3 based on the aeroengine fan blades reproducing method for increasing material design, its feature exists
In：Also include step S5, carry out reliability demonstration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710018560.3A CN106874550A (en) | 2017-01-11 | 2017-01-11 | A kind of aeroengine fan blades reproducing method based on increasing material design |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710018560.3A CN106874550A (en) | 2017-01-11 | 2017-01-11 | A kind of aeroengine fan blades reproducing method based on increasing material design |
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| Publication Number | Publication Date |
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| CN106874550A true CN106874550A (en) | 2017-06-20 |
Family
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| CN201710018560.3A Pending CN106874550A (en) | 2017-01-11 | 2017-01-11 | A kind of aeroengine fan blades reproducing method based on increasing material design |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108228977A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司上海航空测控技术研究所 | A kind of helicopter vibration feature translation method based on flight status parameter |
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| CN101649844A (en) * | 2009-09-09 | 2010-02-17 | 北京戴诺新思动力技术有限公司 | Fan blade based on hollow metal/composite material structure |
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| CN204357771U (en) * | 2014-12-15 | 2015-05-27 | 中航商用航空发动机有限责任公司 | A kind of metal stiffened edge, fan blade and turbogenerator |
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2017
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Patent Citations (7)
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| CN101649844A (en) * | 2009-09-09 | 2010-02-17 | 北京戴诺新思动力技术有限公司 | Fan blade based on hollow metal/composite material structure |
| CN106232270A (en) * | 2014-04-18 | 2016-12-14 | 西门子能源有限公司 | Hypotaxis part is directly formed on turbo blade by increasing material manufacture method and there is to increase at Qi Bishang the turbo blade of the vibroshock that material mode manufactures |
| CN204239323U (en) * | 2014-11-20 | 2015-04-01 | 中航商用航空发动机有限责任公司 | Turbogenerator fan blade |
| CN105604978A (en) * | 2014-11-21 | 2016-05-25 | 中航商用航空发动机有限责任公司 | Shock-resistant enhanced turbine engine fan blade |
| CN105736462A (en) * | 2014-12-12 | 2016-07-06 | 中航商用航空发动机有限责任公司 | Hollow blade and aircraft engine |
| CN204357771U (en) * | 2014-12-15 | 2015-05-27 | 中航商用航空发动机有限责任公司 | A kind of metal stiffened edge, fan blade and turbogenerator |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108228977A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司上海航空测控技术研究所 | A kind of helicopter vibration feature translation method based on flight status parameter |
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| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20201016 Address after: 518000 303, room 5, Huiyuan, 1088, Xue Yuan Avenue, Taoyuan street, Nanshan District, Shenzhen, Guangdong. Applicant after: SHENZHEN YIDONG AVIATION TECHNOLOGY Co.,Ltd. Address before: Nanshan District Xili school in Shenzhen City, Guangdong province 518000 Road No. 1088 Applicant before: SOUTH University OF SCIENCE AND TECHNOLOGY OF CHINA |
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170620 |