CN105562613B - A kind of one-time formed method of aero-engine porous plate diverging cooling turbo blade ceramic core - Google Patents
A kind of one-time formed method of aero-engine porous plate diverging cooling turbo blade ceramic core Download PDFInfo
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- CN105562613B CN105562613B CN201410530280.7A CN201410530280A CN105562613B CN 105562613 B CN105562613 B CN 105562613B CN 201410530280 A CN201410530280 A CN 201410530280A CN 105562613 B CN105562613 B CN 105562613B
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Abstract
The invention discloses a kind of one-time formed method of aero-engine porous plate diverging cooling turbo blade ceramic core, the principle of soluble material is utilized, there is provided a kind of one-time formed method of turbo blade ceramic core, substantially increase the qualification rate of product.
Description
Technical field
The present invention relates to a kind of manufacture craft of aero engine turbine blades, ceramic core especially in manufacture craft
One-step moulding method.
Background technology
Aero engine turbine blades with the type of cooling using are compared, much more each one layer of cooling chamber of leaf basin, blade back.
Using an aero engine turbine blades typically only inner chamber for the general type of cooling.And aero-engine porous plate dissipates
Cooling turbine bucket also has one or more layers chamber in addition to having inner chamber, in leaf basin, blade back, by impact gas between inner chamber and outer layer chamber
Hole UNICOM.
Blade of aviation engine inner chamber is extremely complex, and the method that can not be machined into obtains.At present, aero-engine leaf
Piece is all to obtain casting using the method for hot investment casting.Then by being machined to casting, final satisfaction assembling is obtained
With the part of requirement.
The foundry industry of the blank of blade of aviation engine is extremely complex.First have to first produce the pottery for meeting interior chamber size
Porcelain core, ceramic core is then put into casting die compacting wax-pattern apperance, then combined wax-pattern apperance, applies shell, be calcined, pour
Note etc. process obtains the metal casting for including ceramic core, then will obtain casting after the ceramic core dissolving in metal casting.
So ceramic core is very important for production blade of aviation engine casting.
For aero-engine porous plate diverging cooling turbo blade due to there is two layers of the chamber in inner chamber and outer layer chamber, ceramic core is different
It is often complicated.In order to obtain chamber size in accurate, it is desirable to which the size of ceramic core in itself is very accurate.
At present, the manufacture of domestic air mail engine porous plate diverging cooling turbo blade ceramic core uses two kinds substantially
Method：One kind is that ceramic core is divided into several parts to manufacture respectively, then by being manually bonded to obtain bulk ceramics type
Core；Another kind is that casting is divided into several parts to manufacture respectively, and then welding assembly obtains overall casting.
Manufactured respectively by the way that ceramic core is divided into several parts, then by being manually bonded to obtain bulk ceramics type
The method of core has the following disadvantages：
A, ceramic core is divided into several parts to manufacture respectively, parts-moulding can be caused difficult.In general, aviation is sent out
Motivation porous plate diverging cooling turbo blade ceramic core outer layer chamber thickness only has 0.7mm or so, and length has 50-120
Long, after split, when suppressing hygrometric state outer layer chamber part, the deformation brought during depanning can not solve, and ceramic core exists
Deformation in roasting and strengthening process can be very huge.Once there is substantial amounts of deformation, the size of ceramic core can not just ensure,
The outer wall wall thickness of aero-engine porous plate diverging cooling turbo blade also only has 0.7mm or so, once ceramic core
Deflection exceedes certain numerical value, and after just causing cast, casting the phenomenon of leakage core occurs and causes casting to scrap；
B, artificial bonded ceramics core parts, can cause the loss of significance of ceramic core to be further exacerbated by, and one manually glues
The relative position relation of each part can not be ensured by connecing, and two are manually bonded no uniformity, data analysis band that can to the later stage
Carry out problem, manufactured respectively using ceramic core is divided into several parts, then by being manually bonded to obtain bulk ceramics type
The method of core manufactures aero-engine porous plate diverging cooling turbo blade ceramic core, can cause the structure of ceramic core
Differed greatly with size and theoretical values, and no rule can be followed, it will have a strong impact on the quality of casting, casting can be caused qualified
Rate is low, efficiency is low, and substantial amounts of production capacity is occupied, can also draw high the manufacturing cost of casting.
Manufactured respectively by the way that casting is divided into several parts, the method that then welding obtains overall casting is present so
The shortcomings that：If porous plate diverging cooling turbo blade obtains casting using welding procedure, it can have a strong impact on that porous plate is sent out
Dissipate cooling turbine bucket life-span, using porous plate diverging cooling technology aero-engine at work, turbine portion
Blade needs to bear 1900 DEG C -2150 DEG C of temperature, and needs to rotate at a high speed when engine works, can produce it is huge from
Mental and physical efforts, weld seam can not bear so high temperature, and huge centrifugal force also easily causes porous plate diverging cooling turbine leaf
Piece produces fatigue fracture from commissure, and these are all huge hidden danger.
The content of the invention
The characteristics of present invention utilizes soluble material, disclose aero-engine porous plate diverging cooling turbo blade pottery
The one-time formed method of porcelain core.
To achieve these goals, the technical proposal of the invention is realized in this way：A kind of aero-engine of the present invention is more
The one-time formed method of aperture layer plate diverging cooling turbo blade ceramic core, comprises the following steps：
A, it is special according to the inner chamber of aero-engine porous plate diverging cooling turbo blade ceramic core and outer layer cavity configuration
Point, design some soluble process components；
B, it is each soluble process components are compressing with single mould；
C, all soluble parts are placed into bulk ceramics core mold by mutual location structure suppress it is whole
The ceramic core of body；
D, after the completion of suppressing, soluble process components is dissolved with special solution, finally give overall aero-engine
Porous plate diverging cooling turbo blade ceramic core.
Further, the material of described soluble part is wax.
The present invention is come disposal molding aero-engine porous plate diverging cooling turbine using soluble process components
The method of blade ceramic core.Compared with above-mentioned other method, the qualification rate of casting can obtain big lifting first, disposably
The relative position relation and dimensional accuracy of each structure of ceramic core of shaping can be guaranteed；Secondly the production efficiency of casting will
Big lifting can be obtained, the lifting of qualification rate can be obviously improved production efficiency, and the lifting of production efficiency can will be original occupied
Production capacity is preferably utilized, and creates bigger economic results in society；Again, due to ceramic core be it is one-time formed,
So the problem of welding is not present in casting, the life-span of casting in itself will be guaranteed, reduces the accident rate of aero-engine, also drops
The advantages of low aero-engine maintenance and repair cost.
Embodiment
Technical scheme seat involved in the present invention is further illustrated with reference to embodiments.
Embodiment
The manufacturing process flow of the ceramic core of blade is substantially：The ceramic core of hygrometric state is first suppressed with mould, is then roasted
The ceramic core for burning hygrometric state is allowed to fully be dehydrated, then the ceramic core after roasting is strengthened.Ceramic core is set finally can
Metal is due to contraction and to pottery when bearing during casting pouring metal liquid to enormous impact force caused by ceramic core and cooling
The enclasping force that porcelain core applies.
The present invention uses soluble process components disposal molding aero-engine porous plate diverging cooling turbo blade
Ceramic core, that is to say, that in the inner chamber of aero-engine porous plate diverging cooling turbo blade ceramic core and outer layer chamber
Between design several such process components, the process components by soluble material it is waxed into.Each soluble process components
It is all compressing with single mould, all soluble parts are then placed into bulk ceramics by mutual location structure
Overall ceramic core is suppressed in core mold, after the completion of compacting, waxed process components is dissolved with special solution, finally given
Overall aero-engine porous plate diverging cooling turbo blade ceramic core.Pass through the complete aero-engine porous layer
Plate diverging cooling turbo blade ceramic core casting of metals obtains corresponding turbo blade.
The general principle and principal character of the present invention has been described in detail in above example.The technical staff of the industry should
Solution, the present invention is not limited to the above embodiments, merely illustrating the principles of the invention described in above-described embodiment and specification,
On the premise of the spirit and scope of the utility model is not departed from, various changes and modifications of the present invention are possible, and these change and changed
Enter all fall within the protetion scope of the claimed invention.The claimed scope of the invention is by appended claims and its equivalent
Define.
Claims (1)
1. a kind of one-time formed method of aero-engine porous plate diverging cooling turbo blade ceramic core, it is characterized in that,
Comprise the following steps：
A, according to the inner chamber of aero-engine porous plate diverging cooling turbo blade ceramic core and outer layer cavity configuration feature, if
Count some soluble process components；
B, it is each soluble process components are compressing with single mould；
C, all soluble parts are placed into bulk ceramics core mold by mutual location structure and suppress entirety
Ceramic core；
D, after the completion of suppressing, the solution that use can dissolve soluble process components dissolves soluble process components, finally gives
Overall aero-engine porous plate diverging cooling turbo blade ceramic core；
Aero-engine porous plate diverging cooling turbo blade ceramic core one-step moulding method also includes：First suppressed with mould
The ceramic core of hygrometric state, the ceramic core for being then calcined hygrometric state are allowed to fully be dehydrated, then the ceramic core after roasting are carried out strong
Change；Ceramic core is set finally to bear during casting pouring metal liquid to enormous impact force caused by ceramic core and cooling
When metal due to contraction and to ceramic core apply enclasping force；
Using soluble process components disposal molding aero-engine porous plate diverging cooling turbo blade ceramic core,
Designed between the inner chamber of aero-engine porous plate diverging cooling turbo blade ceramic core and outer layer chamber as several
Process components, the process components by soluble material it is waxed into；Each soluble process components are pressed into single mould
Type, then all soluble parts are placed into bulk ceramics core mold by mutual location structure and suppress entirety
Ceramic core, after the completion of compacting, the solution that use can dissolve soluble process components dissolves waxed process components, finally gives
Overall aero-engine porous plate diverging cooling turbo blade ceramic core；Pass through complete aero-engine porous plate
Diverging cooling turbo blade ceramic core casting of metals obtains corresponding turbo blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410530280.7A CN105562613B (en) | 2014-10-10 | 2014-10-10 | A kind of one-time formed method of aero-engine porous plate diverging cooling turbo blade ceramic core |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410530280.7A CN105562613B (en) | 2014-10-10 | 2014-10-10 | A kind of one-time formed method of aero-engine porous plate diverging cooling turbo blade ceramic core |
Publications (2)
| Publication Number | Publication Date |
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| CN105562613A CN105562613A (en) | 2016-05-11 |
| CN105562613B true CN105562613B (en) | 2018-02-13 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107116183B (en) * | 2017-05-10 | 2019-12-24 | 钢铁研究总院 | Method for preparing complex hollow cavity casting by matching ceramic core and soluble core |
| CN107983913B (en) * | 2017-11-22 | 2019-05-24 | 扬州峰明光电新材料有限公司 | The precision pouring technique of U-shaped magnesium alloy member |
| CN115106482A (en) * | 2022-07-28 | 2022-09-27 | 中国科学院金属研究所 | Inner cavity forming and wall thickness size control process method for large-size hollow guide blade |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US5820774A (en) * | 1996-10-28 | 1998-10-13 | United Technologies Corporation | Ceramic core for casting a turbine blade |
| CN1538887A (en) * | 2001-08-10 | 2004-10-20 | ��ķ�չ���ʦ����˾ | Method and device for production of molds or cores for foundry purposes |
| CN100560248C (en) * | 2007-06-19 | 2009-11-18 | 西安交通大学 | A kind of core and shell integrated ceramic casting mold manufacture method |
| CN101559472B (en) * | 2008-04-18 | 2011-02-16 | 沈阳工业大学 | Soluble mold core and preparation method thereof |
| US8899303B2 (en) * | 2011-05-10 | 2014-12-02 | Howmet Corporation | Ceramic core with composite insert for casting airfoils |
| CN104014737B (en) * | 2014-05-19 | 2016-11-02 | 沈阳工业大学 | A kind of preparation technology of complexity embedded cavity structure ceramic core |
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