CN106623772B - A kind of aero-engine diffuser Integral casting die - Google Patents
A kind of aero-engine diffuser Integral casting die Download PDFInfo
- Publication number
- CN106623772B CN106623772B CN201611170293.3A CN201611170293A CN106623772B CN 106623772 B CN106623772 B CN 106623772B CN 201611170293 A CN201611170293 A CN 201611170293A CN 106623772 B CN106623772 B CN 106623772B
- Authority
- CN
- China
- Prior art keywords
- aero
- annular cavity
- diffuser
- body structure
- casting die
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/02—Lost patterns
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
The invention discloses a kind of aero-engine diffuser Integral casting dies, including pedestal and upper cover plate, the annular cavity body structure of integrally formed diffuser is provided between pedestal and upper cover plate, the center of annular cavity body structure is provided with the core pulling of truncated cone-shaped, and the wax injection nozzle being connected to annular cavity is provided on annular cavity body structure；The bottom of annular cavity body structure is provided with the ejecting structure of ejection forming diffuser.It can make diffuser casting once annular monolithic molding, be bonded without follow-up wax pattern, and the formation that wall thickness aero-engine diffuser was pulled out and ensured to wax pattern can be solved on mold.
Description
Technical field
The invention belongs to aero-engine technology fields, are related to a kind of aero-engine diffuser casting device, especially
A kind of aero-engine diffuser Integral casting die
Background technology
Diffuser is one of aero-engine and gas turbine important composition part, be located at compressor and main chamber it
Between, the kinetic energy of the high-speed air for exporting compressor impeller is changed into pressure energy, and the gas that will then have pressure energy is defeated
Send allows temperature before being heated to turbine to main chamber supercharging, does work to enter exhaust apparatus, and the size of pressure energy exactly weighs
Measure one of the important indicator of engine performance.
The advanced annular diffuser in the world at present, in view of mitigate weight and ensure design of part stability dual reason,
It mostly uses hollow support plate to connect as channel while reducing part wall thickness as far as possible in the case where not influencing intensity, substantially
Degree increases part manufacture difficulty.
A closed channel characteristics, same time delay are formed due to being connected by hollow support plate between diffuser outer edge and inner edge
The different external support plate of hade degree forms the feature of falling draft being difficult to by normal angled depanning, and causes part wall thickness thin, because
This investment casting mould design and manufacture are extremely difficult.Existing casting technique is that entire annular diffuser part is split into intermediate branch
The seperated wax pattern component of plate quantity is independently molded, then seperated wax pattern component is combined integral diffuser by wax pattern technique for sticking
Wax pattern pours into casting, and this casting technique is relatively easy for mold manufacturing.But since wall thickness is thin and bonding operating error
Reason, easily causes part shape and size is undesirable, shift phenomenon easily occurs, and part low qualified is molded simultaneously
Efficiency is low.
And diffuser integral one-step molding, following difficulties are primarily present, there is presently no corresponding mold energy
Enough solve these problems：Ensure that the final size in part channel prevents the problem on deformation in forming process simultaneously；Ensure in part
The shape and final size of ring internal wall features prevent the problem on deformation in forming process simultaneously；Outer shroud support plate is formed with curtain plate
The feature of falling draft is difficult to be molded problem, and since the angle that outer shroud support plate extending direction and curtain plate are formed is less than 90 °, formation is pulled out
Mould phenomenon；Have both the ejection problem of loop configuration and thin-walled characteristic part in a mold, it is necessary to accomplish smoothly to eject wax pattern,
Keep Mould operation smooth without deformation, without damage；The problem of multigroup splicing insert and the big moulding complexity of die bottom plate size, to mold
Processing and fitter assembly have caused great difficulties.
Invention content
The purpose of the present invention is to provide a kind of aero-engine diffuser monoblock cast devices, can make diffuser casting
Primary annular monolithic molding, is bonded, and can solve wax pattern on mold and pull out and ensure wall thickness aviation without follow-up wax pattern
The formation of engine diffuser.
The purpose of the present invention is achieved through the following technical solutions：
This aero-engine diffuser Integral casting die, including pedestal and upper cover plate, set between pedestal and upper cover plate
It is equipped with the annular cavity body structure of integrally formed diffuser, the center of annular cavity body structure is provided with the pumping of truncated cone-shaped
Core is provided with the wax injection nozzle being connected to annular cavity on annular cavity body structure；The bottom of annular cavity body structure is provided with
The ejecting structure of ejection forming diffuser.
Further, the features of the present invention also characterized in that：
Wherein annular cavity body structure is made of several capsule components, and capsule components include annular fixed block, inner ring
Shape fixed block bottom is provided with outer shroud fixed block, and the periphery of annular fixed block is provided with loose piece.
Blade movable block group is wherein provided at the top of annular fixed block.
It is wherein set as bottom plate in the middle part of pedestal, annular cavity body structure is provided on bottom plate, annular cavity body structure
Outside is provided with outer round piece.
Wherein outer round piece matches with capsule components, and outer round piece is slidably arranged on pedestal.
Wherein core pulling is limited by small loose piece and is fixed.
Wherein ejecting structure includes the eccentric angled slide block being arranged in pedestal, and liftout plate and top are provided on eccentric angled slide block
Go out block.
Wherein eccentric angled slide block is connect with the handle for being arranged in chassis outer side.
Wherein ventilation device is provided between pedestal and annular cavity.
The beneficial effects of the invention are as follows：Diffuser is divided into ring part and central part by the casting mould, ring body at
The wax injection nozzle being arranged on shape part can make monolithic molding of wax pattern of diffuser, and without casting bonding respectively, effectively
The casting accuracy and production efficiency of part are improved, while the core pulling of truncated cone-shaped is inverted in the center of interior annular housing, solution
It has determined and has arrived draft problem, and diffuser wax pattern can smoothly be ejected, solved after the forming of diffuser wax pattern by ejecting structure
The problems such as deformation that diffuser wax pattern generates in the process in taking-up, damage, core pulling can reinforce anti-deformation effect, avoid
To the deformation of diffuser thin-walled portion during die sinking.
Further, capsule components ring-shaped combination forms annular cavity body structure, keeps a combination thereof more flexible；And inner ring
Ring part is divided into outer shroud, inner ring and main body three parts by shape fixed block, outer shroud fixed block and loose piece, further makes diffusion
The forming of device is more accurate, qualification rate higher.
Further, it is slidably arranged on pedestal for outer round piece, outer round piece of installation and dismounting can be facilitated, and
Outer round piece with blade activity group for fixing and limiting annular cavity portion.
Further, ventilation device ensures the exhaust in diffuser forming process, and the ruler of diffuser has been effectively ensured
Very little precision and production efficiency.
Description of the drawings
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is the sectional view of annular cavity body structure in the present invention；
Fig. 3 is the structural schematic diagram with type movable block in the present invention；
Fig. 4 is the schematic diagram of ejecting structure in the present invention；
Fig. 5 is the schematic diagram of bottom structure in the present invention；
Fig. 6 is the sectional view of bottom structure in the present invention；
Fig. 7 is the schematic diagram of internal structure of the present invention；
Fig. 8 is the schematic diagram that inner cavity shapes loose piece in the present invention；
Fig. 9 is the structural schematic diagram of blade profile loose piece group in the present invention；
Figure 10 is the structural schematic diagram of round piece of present invention China and foreign countries；
Figure 11 is the structural schematic diagram of core pulling in the present invention；
Figure 12 is the connection diagram of round piece of present invention China and foreign countries and bottom plate.
Wherein：1 is pedestal；2 be bottom plate；3 be outer round piece；4 be pumping block；5 be core pulling；6 be diffuser；7 be loose piece；8
For blade loose piece group；9 is with type loose piece groups；10 be inner ring fixed block；11 be outer shroud fixed block；12 be resetting block；13 be bias
Angled slide block；14 be handle；15 be upper cover plate；16 be latch segment；17 be liftout plate；18 be angled slide block；19 be wax injection nozzle；20 be small
Loose piece.
Specific implementation mode
The present invention is described in further detail below in conjunction with the accompanying drawings：
The present invention provides a kind of aero-engine diffuser Integral casting dies, as shown in figures 1 to 6, including pedestal 1, bottom
It is provided with annular cavity body structure between seat 1 and upper cover plate 15, annular cavity body structure is connected to wax injection nozzle 19, and wax injection nozzle 19 is used
Casting is carried out in the annular cavity of inside annular housing inside configuration；Inner ring cavity body structure is made of several capsule components, chamber
Body component includes inner ring fixed block 10, and the bottom of inner ring fixed block 10 is provided with the outer shroud fixed block 11 for fixing its position,
The outside of inner ring fixed block 10 is provided with loose piece 7, and the top of inner ring fixed block 10 is provided with blade loose piece group 8；As shown in figure 3,
Wherein it is additionally provided with type movable block between outer shroud fixed block 11 and inner ring fixed block 10；As shown in Fig. 4,6 and 9, pedestal 1 it is interior
Portion is additionally provided with eccentric angled slide block 13, and eccentric angled slide block 13 is also connect with the handle 14 being arranged on the outside of pedestal 1, and handle 14 controls
The ejection work of eccentric angled slide block 13；Liftout plate 17 is provided on eccentric angled slide block 13, as shown in figure 5, being arranged on liftout plate 17
There are angled slide block 18, the center of liftout plate 17 to be provided with resetting block 12, resetting block 12, inner ring fixed block 10 and outer shroud fixed block
11 molding for carrying out diffuser.
As Figure 7-9, on a base plate 2, outer shroud fixed block 11 is to be arranged in inner ring fixed block to the setting of outer shroud fixed block 11
The fixed structure of outer ring bottom, loose piece 7 surround circular configuration, are arranged in the periphery of core pulling 5, blade activity group 8 is arranged in loose piece 7
Periphery, and loose piece 7 and blade activity group 8 are arranged in the inner ring of annular cavity body structure.
As shown in figure 12, enclosing for annular cavity body structure is additionally provided with several outer round piece 3, outer round piece 3 and bottom plate 2
On sliding rail connection, and outer round piece 3 can slide extraction/installation on a base plate 2, and outer round piece 3 for fixing and limiting
Position annular cavity body structure；As shown in Figure 10, outer round piece 3 of internal structure is matched with the outer ring of annular cavity body structure.
As shown in figure 11, core pulling 5 is truncated cone-shaped structure, and the up big and down small centre bit mounted on annular cavity body structure
It sets, as shown in Fig. 2, being additionally provided with small loose piece 20 in core pulling 5, small loose piece 20 is extracted out for fixed limit core pulling 5, small loose piece 20
Afterwards, you can take out limit core pulling 5.
Several ventholes being connected to angled slide block 18 are wherein additionally provided on inner ring fixed block 10, venthole is arranged for ensureing
Gas is smooth.
The present invention installation anabolic process be：Once mounting bias angled slide block 13, top from bottom to top on horizontal bottom plate 2
Ejecting plate 17, inner ring fixed block 10, outer shroud fixed block 11, with type loose piece group 9, loose piece 7, blade loose piece group 8 and round piece 3 outer；Its
Middle blade loose piece group 8 formed the narrow band of falling draft blade inner cavity, by core pulling 5, loose piece 7, with type loose piece group 9, inner ring fixed block
The 10 two mouthfuls small annular cavities broad in the middle collectively constituted.
Specifically, as shown in figure 4, establish the placement position of diffuser 6 in a mold, pulled out according to inner cavity " up-small and down-big "
It puts in mould direction；In order to avoid the limitation of channel connection support plate and channel deformation is prevented, channel characteristics needs are set before whole depanning
It is calculated as activity block group and is taken out molding in advance, the state of " up-small and down-big " is that the fractionation design of activity block group causes very at this time
Big difficulty；Channel characteristics are divided into 6 association cavitys by connecting support plate, " the small chamber of mouth must be fully considered in design process
Greatly " and support plate enclosure space is molded difficult point, therefore the molding type block in each cavity is split as 6 pieces of activity block groups, every piece
Individual activity block must have certain pattern draft, at the same channel support plate molding activity block must can in the channel between
It is moved in parallel in the space that activity block is formed after extracting, molding is avoided interference with by first translating the movement locus extracted afterwards with this
Channel support plate, so support plate molding activity block must be simulated with the pattern draft of both direction eventually by three-dimensional software
And split, channel forming type block is split as channel support plate molding activity block by specific cutting cutter track and channel intermediary form is lived
Ejector half block two major classes amount to 36 pieces of activity blocks, ensure that closed channel normally goes out type with this.Pass through system in assembling process simultaneously
Make multiple auxiliary positioning straight pins identical with listrium wall thickness and is supported on channel forming activity block group and outer rim forming blocks and interior
Edge is molded between loose piece group, in this, as the assembly auxiliary base for ensureing listrium wall thickness, is ensured final wax pattern wall thickness, is innovated in this way
Design and assembly method solve the problems, such as closed channel molding and wall thickness ensure, further ensure the Forming Quality of mold.
As shown in figure 5, by interior ring forming type block be split as Tao Xin positioning inner ring molding activity block and without Tao Xin inner ring at
Type activity block two major classes amount to 12 pieces of activity blocks, by first taking out no Tao Xin inner ring one by one by centripetal and upward 45 ° of directions
It is molded activity block, operation sky is provided for the translation of Tao Xin positioning sliding blocks and the taking-up of Tao Xin positioning inner ring molding activity blocks
Between, then by first sliding Tao Xin positioning sliding blocks make Tao Xin be detached from again one by one take out Tao Xin positioning inner ring be molded activity block method at
Type ring closure cavity.Inner ring is molded activity block by making step positioning annular holder during fitter assembly simultaneously
Group is associated together with outer rim forming blocks as auxiliary positioning reference for assembling, ensures the concentric of inner ring cavity and entirety outer rim with this
It is required that.The design and assembly method innovated in this way solve the problems, such as inner ring mold cavity forming and ensuring coaxiality.
As shown in fig. 6, annulus forming blocks trisection is split, three molding type blocks of formation are used as to be ejected with wax pattern
Mechanism ejection with type activity block group, three activity blocks are taken out one by one again after wax pattern taking-up, draft is molded down with this
Feature.The realization difficult point of this design method, which is activity block group, to be processed with light material, otherwise can be incited somebody to action due to own wt
Wax pattern is damaged or deformation, but light material processing type is poor, not wear-resisting, while having during casting and being shifted by wax liquor impact activity
Risk；By by magnet insert be uniformly bumped into three light materials in type activity block, utilize magnet and steel outer shroud
The suction of locating piece is effectively avoided impacts the phenomenon that shifting with type activity block by wax liquor.
As shown in fig. 7, since diffuser 6 has both loop configuration and thin-walled feature, due to power during manual operation taking-up
The not easy to control reason of degree and direction, easily causes deformation and damage of the wax pattern during taking-up, ultimately cause part it is overproof and
It scraps.Ejecting structure is uniformly mounted on the wax pattern top on liftout plate 17 using the rotation top pressure liftout plate 17 of eccentric angled slide block 13
Go out block while diffuser wax pattern is smoothly ejected into depanning, manual operation removal process is avoided with this, improves wax pattern quality.
Specific embodiments of the present invention and operation principle are：The setting-up eccentricity angled slide block 13 first on pedestal 1, then will top
Ejecting plate 17 and angled slide block 18 and resetting block 12 and inner ring fixed block 10, outer shroud fixed block 11 are molded, at this time angled slide block 18
End will be concordant with 10 upper surface of inner ring fixed block and the lower surface of outer shroud fixed block respectively, then with bottom plate 2 mold, so
Outer round piece 3 is in turn mounted to type activity group 9 by the guide groove on bottom plate 2 by assembly on outer shroud fixed block 11 afterwards
Position will be taken out block 4 and is assembled on outer round piece 3, installs blade loose piece group 8 and loose piece 7 successively during this period, will using handle 14
Part loose piece 7 is installed in place, finally by core pulling 5 be put into mold center, after locking upper cover plate 15 inject wax carry out diffuser 6 at
Type after molding, goes lower core pulling 5 successively, and part loose piece 7 is then detached 6 surface of diffuser by handle 14 again, is then taken successively
Lower loose piece 7 and blade activity group 8, outer round piece 3 guide groove along bottom plate 2 is detached, using the effect of eccentric angled slide block 13,
Diffuser 6 is ejected by liftout plate 17 and angled slide block, removes integrated diffuser wax pattern, completes one-pass molding.
In the walls of formation such as round outside piece 3 of diffuser part and loose piece 7 can one-pass molding, this mold provides energy
Enough make the one-pass molding of diffuser wax pattern, without the precision casting mold of follow-up technique for sticking, and wax pattern can be solved on mold and gone out
Deformation problem after mould manufactures essence for aero-engine and the precision casting mould of gas turbine diffuser to diffuser casting
Degree plays key effect.
The precision casting mold that this mold is developed aiming at aero-engine and gas turbine diffuser, using vertical
The molding mode of mold is changed to integral one-step molding by formula mould structure by original fractionation bonding forming, is played in this way
It avoids the thick big feature wax pattern in the part of diffuser 6 from shrinking the whole wax pattern of image and size, in turn simplifies mould design and manufacture and wax pattern
Profiling operation difficulty, in turn avoiding 6 main part of diffuser needs the later stage to be bonded secondary operation error, and production effect is greatly improved
Rate.The innovation of this mold uses channel loose piece group fractionation technology, 5 position of reasonable layout mould core pulling, eccentric rotary ejection side
Case and magnet insert are applied to represent the highest level of industry investment casting mould design with the implementation of type loose piece method.In mould
That is innovated in the processing of tool completes 36 pieces of channel using numerical control lathe, five-shaft high-speed machining center and precision WEDM machine combination technology
The grasp of the overall processing of 12 pieces of activity block groups of activity block group and inner ring, this technology greatly improves ring-shaped combination class precision
The processing quality of part, effectively increases the production efficiency and qualification rate of diffuser castings production, and overcomes a series of problems.
Certain machine diffuser part is divided into main body, outer shroud, inner ring and four part of ceramic core and carries out wax pattern molding by the present invention,
Later stage bonding casting.So that closed venturi is formed hatch frame with this, then so that wax pattern is gone out type by the design scheme of venturi type block；
It plays in this way and avoids the thick big feature wax pattern effect of contraction entirety wax pattern shape of parts locally and size, in turn simplify mold and set
Meter manufacture and wax pattern profiling operation difficulty, and reduce the process that part main part needs later stage bonding combination, significantly carry
High production efficiency.Solid foundation has been established for new machine scientific research from now on, has made the middle-size and small-size annular precise in aero-engine
The manufacturing technology of mo(u)lded piece has been improved, be China's new generation aero-engine in terms of the design and manufacture of precision casting mould
Abundant experience is had accumulated, technical basis is provided to the manufacture of later loop-like shape one-piece parts investment casting mould design.
Claims (9)
1. a kind of aero-engine diffuser Integral casting die, which is characterized in that including pedestal (1) and upper cover plate (15), bottom
The annular cavity body structure of integrally formed diffuser is provided between seat (1) and upper cover plate (15), in annular cavity body structure
Heart position is provided with the core pulling (5) of truncated cone-shaped, and the wax injection nozzle being connected to annular cavity is provided on annular cavity body structure
(19)；The bottom of annular cavity body structure is provided with the ejecting structure of ejection forming diffuser.
2. aero-engine diffuser Integral casting die according to claim 1, which is characterized in that the annular chamber
Body structure is made of several capsule components, and capsule components include annular fixed block (10), annular fixed block (10) bottom
It is provided with outer shroud fixed block (11), the periphery of annular fixed block (10) is provided with loose piece (7).
3. aero-engine diffuser Integral casting die according to claim 2, which is characterized in that the annular is solid
Determine to be provided with blade movable block group (8) at the top of block (10).
4. aero-engine diffuser Integral casting die according to claim 2, which is characterized in that the pedestal (1)
Middle part be set as bottom plate (2), annular cavity body structure is provided on bottom plate (2), is provided on the outside of annular cavity body structure
Outer round piece (3).
5. aero-engine diffuser Integral casting die according to claim 4, which is characterized in that described outer round piece
(3) it is matched with capsule components, and outer round piece (3) are slidably arranged on pedestal (1).
6. aero-engine diffuser Integral casting die according to claim 1, which is characterized in that the core pulling (5)
It is limited and is fixed by small loose piece (20).
7. aero-engine diffuser Integral casting die according to claim 1, which is characterized in that the ejecting structure
Including the eccentric angled slide block (13) being arranged in pedestal (1), liftout plate (17) and angled slide block are provided on eccentric angled slide block (13)
(18)。
8. aero-engine diffuser Integral casting die according to claim 7, which is characterized in that the eccentric ejection
Block (13) is connect with the handle (14) being arranged on the outside of pedestal (1).
9. aero-engine diffuser Integral casting die according to claim 1, which is characterized in that the pedestal (1)
It is provided with ventilation device between annular cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611170293.3A CN106623772B (en) | 2016-12-16 | 2016-12-16 | A kind of aero-engine diffuser Integral casting die |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611170293.3A CN106623772B (en) | 2016-12-16 | 2016-12-16 | A kind of aero-engine diffuser Integral casting die |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106623772A CN106623772A (en) | 2017-05-10 |
| CN106623772B true CN106623772B (en) | 2018-11-02 |
Family
ID=58823237
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611170293.3A Active CN106623772B (en) | 2016-12-16 | 2016-12-16 | A kind of aero-engine diffuser Integral casting die |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106623772B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107570662B (en) * | 2017-09-20 | 2020-02-21 | 北京星航机电装备有限公司 | Wax pressing die with interlayer cavity in middle |
| CN108312395B (en) * | 2018-03-22 | 2020-04-07 | 中国航发南方工业有限公司 | Wax mould and wax mould stripping method |
| CN108607953B (en) * | 2018-07-04 | 2024-01-30 | 纽威工业材料（大丰）有限公司 | Valve gap wax matrix integral forming die |
| CN112177688A (en) * | 2020-09-28 | 2021-01-05 | 宁国市华成金研科技有限公司 | Engine precision casting guider and machining method thereof |
| CN112620579B (en) * | 2020-12-17 | 2021-09-14 | 成都成发泰达航空科技有限公司 | Die assembling tool for single-blade wax die of turbine guider |
| CN112945509B (en) * | 2021-04-22 | 2022-04-15 | 中国空气动力研究与发展中心超高速空气动力研究所 | Opening plugging device for contraction section of hypersonic speed wind tunnel diffuser |
| CN113547070B (en) * | 2021-07-22 | 2022-12-13 | 株洲凯丰实业股份有限公司 | Inner ring core profiling mold of exhaust rectifier |
| CN117324545A (en) * | 2023-10-11 | 2024-01-02 | 中国航发沈阳黎明航空发动机有限责任公司 | Multi-cavity complex casting wax piece forming die and forming method thereof |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6305458B1 (en) * | 1999-03-17 | 2001-10-23 | Baker Hughes Incorporated | Lost foam and sand cores stage manufacturing technology |
| FR2820149B1 (en) * | 2001-01-31 | 2004-05-07 | Ct Technique Des Ind Fonderie | PROCESS FOR THE PROCESSING AND CASTING OF OXIDIZABLE ALLOYS |
| CN201752755U (en) * | 2010-04-09 | 2011-03-02 | 泉州腾达精铸有限公司 | Mold for manufacturing wax patterns |
| CN102101155A (en) * | 2010-11-18 | 2011-06-22 | 大同北方天力增压技术有限公司 | Method for manufacturing gypsum silicon rubber precision cast turbocharger diffuser |
| CN102363199B (en) * | 2011-11-04 | 2013-06-26 | 西安航空动力股份有限公司 | Manufacturing method and fixture of integral bladed-disk wax mold |
| CN203235913U (en) * | 2013-04-24 | 2013-10-16 | 东营嘉扬精密金属有限公司 | Impeller mould fetching and positioning block |
| CN204182860U (en) * | 2014-11-12 | 2015-03-04 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of wax-pattern integrally forming mould |
| CN104923729B (en) * | 2015-06-24 | 2017-01-25 | 西安航空动力股份有限公司 | Manufacturing method of composite shell of large diffuser precision casting |
| CN104999034B (en) * | 2015-07-16 | 2017-04-19 | 西安航空动力股份有限公司 | Casting method of large allowance-free pressure expander precise casting piece |
-
2016
- 2016-12-16 CN CN201611170293.3A patent/CN106623772B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106623772A (en) | 2017-05-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106623772B (en) | A kind of aero-engine diffuser Integral casting die | |
| CN110899616B (en) | Forming mold for wax mold of power turbine casing | |
| CN108057865B (en) | casting device and casting method thereof | |
| CN108723296B (en) | A kind of manufacturing method in Powered Propulsion middle section peculiar to vessel | |
| CN102794402B (en) | Profiling die of single crystal blade spiral crystal selector | |
| CN112296254B (en) | Power turbine impeller wax mold integral demolding mold and wax mold manufacturing method | |
| CN114589290B (en) | A method for forming the inner cavity of a high-temperature alloy hollow guide vane | |
| CN109465403B (en) | Casting process of low-flow casting of submersible pump | |
| CN112935228A (en) | Aviation blade wax matrix mould mold opening device | |
| CN108941466A (en) | The casting technique of V-structure ship cylinder body | |
| CN108057864B (en) | casting device and casting method thereof | |
| CN110328359A (en) | Narrow interval, distortion, multiple-blade dense distribution leaf grating class part manufacturing process | |
| CN109047721A (en) | A kind of automobile-used cabinet low pressure casting die | |
| KR20160094637A (en) | Boss portions sink marks generated prevention device in an injection mold | |
| CN108312395A (en) | Wax mold and wax-pattern molding method | |
| CN214726070U (en) | Injection mold for machining turbofan | |
| CN215791417U (en) | Non-contact large plastic garbage can putting mold for community | |
| CN112846095B (en) | Casting mold for improving casting yield and machining method thereof | |
| CN209811170U (en) | Metal mold gravity casting mould | |
| CN210523727U (en) | Mould and frock are used in molding of closed impeller sodium silicate sand system core | |
| CN207668436U (en) | A kind of swinging double-station wax injector | |
| CN208787495U (en) | A kind of reduction active and inactive mold parting line dislocation mold | |
| CN113547071B (en) | Integral wax mould pressing type mould of exhaust rectifier | |
| CN222740263U (en) | New forms of energy lawn mower chain saw motor end cover forming die | |
| CN203830690U (en) | A die-casting mold for an integral locking multi-slider impeller |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO., LTD. Address before: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE CORPORATION PLC |