CN108890219A - Three layers of hollow blade structure of one kind and its manufacturing method - Google Patents
Three layers of hollow blade structure of one kind and its manufacturing method Download PDFInfo
- Publication number
- CN108890219A CN108890219A CN201810593281.4A CN201810593281A CN108890219A CN 108890219 A CN108890219 A CN 108890219A CN 201810593281 A CN201810593281 A CN 201810593281A CN 108890219 A CN108890219 A CN 108890219A
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- China
- Prior art keywords
- core plate
- boss
- covering
- layers
- hollow blade
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
Abstract
The present invention relates to a kind of three layers of hollow blade structure and its manufacturing methods.This method includes：By mechanically or chemically processing method, the covering inner surface in two sides processes multiple boss；Position coating diffusion connection interleaving agent other than covering inner surface convex platform；By mechanically or chemically processing method, the core plate of splaying of variable cross-section thickness is processed；In the narrowed thickness end processing gas inlet slot for core plate of splaying；Intermediate core plate is clamped between two side skins of boss, welds edge sealing in three layer stacked structure surroundings of formation；Three layer stacked structures after combination edge sealing are placed in hot isobaric furnace after Vacuum Package and are diffused connection, intermediate core plate and the covering of two sides is realized at boss position and connects；Superplastic forming is carried out to being filled with inert gas inside three layer stacked structures after diffusion connection by the air inlet duct on core plate, is made non-diffusing join domain bulging other than boss position of core plate and covering and is closed with the type face paste of superplastic forming die.
Description
Technical field
The present invention relates to blade of aviation engine manufacturing technology field, more particularly to a kind of three layers of hollow blade structure and
Its manufacturing method.
Background technique
Superplastic forming/diffusion connection（super plastic forming/diffusion bonding, SPF/DB）Skill
Art is called the initiative technology of modern Aviation industry, it materially increases the utilization rate of aeronautical material and improvement
Reliability of structure and maintainability.SPF/DB group technology breaches traditional metal plate forming as a kind of advanced manufacturing technology
Method, not only cost-saved, mitigation weight, but also can realize that Near net shape shapes, it is excellent when manufacturing complex appearance and multilayered structure
Gesture is obvious.
Blade of aviation engine belongs to thin-walled Flexible Deforming Parts, and the manufacturing process of blade profile has directly engine performance
Influence.In the prior art, the three layers of hollow blade structure shaped using SPF/DB group technology, when forming, internal core plate with
It is mutually pulled after plate contact, rib intersection on panel is caused the problem of gauffer recess, i.e. panel " groove " defect easily occur
Problem generallys use thinned core thickness to avoid " groove " defect, when core thickness is much smaller than plate thickness, can drop significantly
The overall performance of the support strength of low core plate, three layers of hollow blade structure will decrease.
Therefore, a kind of three layers of hollow blade structure and its manufacture manufactured using SPF/DB group technology are inventor provided
Method, to solve defect of the existing technology.
Summary of the invention
The embodiment of the invention provides a kind of three layers of hollow blade structure and its manufacturing methods, by covering inner surface office
Portion thickeies and uses the core plate at variable cross-section thickness bottom, when avoiding trench defect, while solving because core plate is thinned, overall performance
The problem of reduction.
In a first aspect, the embodiment of the present invention proposes the manufacturing method of three layers of hollow blade structure, the manufacturing method packet
It includes：
Covering boss is processed, by mechanically or chemically processing method, the covering inner surface in two sides processes multiple boss, described
Boss position with the core plate for being connected；
Interleaving agent is coated, the position coating diffusion connection interleaving agent other than the covering inner surface convex platform；
It processes core plate of splaying and the core plate of splaying of variable cross-section thickness is processed by mechanically or chemically processing method；
Processing gas inlet slot, in the narrowed thickness end processing gas inlet slot of the core plate of splaying；
Edge sealing is combined, intermediate core plate is clamped between two side skins for being machined with boss, in three layer stacked structures four of formation
Week welding edge sealing；
Three layer stacked structures after the combination edge sealing are placed in hot isobaric furnace after Vacuum Package and expand by diffusion connection
Connection is dissipated, the intermediate core plate and the covering of two sides is realized at the boss position and connects；
Superplastic forming, by the air inlet duct on the core plate to diffusion connection after three layer stacked structures inside be filled with indifferent gas
Body is placed in superplastic forming die and carries out superplastic forming, connects the non-diffusing of the core plate and covering other than boss position
It connects region bulging and is closed with the type face paste of superplastic forming die.
Further, the ratio of the skin thickness and the core thickness is not less than 2.
Further, the method for the processing covering boss includes the machining process using cutting.
Further, using the method for carrying out chemical process in acid solution, i.e., the method for the processing covering boss includes
Covering inner surface other than boss position coats acid solution interleaving agent, then carries out chemistry milling to the covering with acid solution, makes to apply
It is covered with the position other than the boss position of acid solution interleaving agent to be thinned, covering inner surface is made to process multiple boss.
Further, knuckle is processed in the intermediate location of the boss position and the covering inner surface, it is described
Knuckle is not less than the height of the boss, wherein the height of the boss is the covering other than boss position through acid solution chemistry
The thinned thickness of milling.
Further, the section for splaying core plate centre position is the variable cross-section thickness of linear transitions.
Further, after the completion of the superplastic forming step, the intermediate core plate is configured to the hollow knot of W-shaped girder rib lattice
Structure.
Second aspect provides a kind of three layers of hollow blade structure, which includes the intermediate core plate of truss structure
With the skin panel of two sides, the covering inner surface has multiple boss thickened, and the core plate is the core of splaying of variable cross-section thickness
Plate is machined with air inlet duct in the thinning end of the thickness of the core plate, and the thickness of the boss is greater than the thickness of the core plate, institute
It states core plate and is connected with the covering of the two sides at the boss position.
Further, the intermediate location of position containing boss and the covering inner surface is machined with knuckle, the transition
Fillet is not less than the height of the boss.
Further, the intermediate core plate and the covering of two sides are titanium alloy material.
To sum up, three layers of hollow blade structure of one kind of the invention and its manufacturing method, firstly, passing through the inner surface in covering
Connecting portion processes boss, on the one hand, and it avoids groove of the covering under by core plate pulling force effect in forming process and occurs,
On the other hand, in non-diffusing join domain, since skin thickness is not constrained by formability, it can be achieved that being largely thinned, from
And further realize the loss of weight of structure.Secondly, core plate uses variable cross-section thickness design, it may be implemented and covering is in local thickness
Matching, to be conducive to being thinned for covering under the premise of meeting the requirement of formability, further realize the loss of weight of blade construction.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, will make below to required in the embodiment of the present invention
Attached drawing is briefly described, it should be apparent that, drawings described below is only some embodiments of the present invention, for
For those of ordinary skill in the art, without creative efforts, it can also be obtained according to these attached drawings other
Attached drawing.
Fig. 1（a）And Fig. 1（b）Be the prior art hollow blade structure superplastic forming during covering and core plate it is mutual
Active force and groove schematic diagram.
Fig. 2 is three layers of hollow blade structural schematic diagram of one kind of the embodiment of the present invention.
Fig. 3 is the schematic cross-section of the core plate of the embodiment of the present invention.
Fig. 4 is the core thickness direction schematic diagram of Fig. 3.
Fig. 5 is the manufacturing method flow chart of three layers of hollow blade structure of one kind of the embodiment of the present invention.
In figure：
1- covering；2- boss；3- core plate；4- air inlet duct.
Specific embodiment
Embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples.Following embodiment it is detailed
Thin description and attached drawing cannot be used to limit the scope of the invention for illustratively illustrating the principle of the present invention, i.e., of the invention
It is not limited to described embodiment, covers part, component and connection type under the premise of without departing from the spirit of the present invention
Any modification, replacement and improvement.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to accompanying drawings and in conjunction with the embodiments.
Fig. 1（a）And Fig. 1（b）Be the prior art hollow blade structure superplastic forming during covering and core plate it is mutual
Active force and groove schematic diagram.Such as Fig. 1（a）And Fig. 1（b）Shown, three layers of SPF/DB hollow structure are by two sides exterior skin and centre
Layer core plate composition, the stress state and formability of geometrical structure parameter and forming process have direct relation.Main geometry
Parameter such as corrugation angle, covering and core thickness etc. must satisfy certain matching relationship, just be able to achieve the complete forming of structure.It is existing
There is three-decker skin thickness to design in same section for equal thickness, middle layer core plate designs for equal thickness.Skin thickness often subtracts
Small 0.1mm, weight reduces 150g, but being further thinned for skin thickness is limited by formability requirement, and the potentiality of loss of weight have
Limit.Therefore, a kind of new blade construction and its manufacturing method need to be proposed.
Fig. 2 is three layers of hollow blade structural schematic diagram of one kind of example in real time of the invention.Fig. 3 and Fig. 4 is the embodiment of the present invention
Core plate schematic cross-section.In conjunction with shown in Fig. 2, Fig. 3 and Fig. 4, which includes the intermediate core plate 3 of truss structure
With 1 panel of covering of two sides, 1 inner surface of covering has multiple boss 2 thickened, and core plate 3 is the core plate of splaying of variable cross-section thickness,
The thinning end of the thickness of core plate 3 is machined with air inlet duct 4, and the thickness of boss 2 is greater than the thickness of core plate 1, the illiteracy of core plate 3 and two sides
Skin 1 is connected at the position of boss 2.
In the present embodiment, the covering 1 of intermediate core plate 3 and two sides is titanium alloy material, table in 2 position of boss and covering 1
The intermediate location in face is machined with knuckle, which is not less than the height of boss 2.
The present invention also provides a kind of manufacturing methods of above-mentioned three layers of hollow blade structure.Fig. 5 is the embodiment of the present invention
A kind of manufacturing method flow chart of three layers of hollow blade structure.In conjunction with Fig. 2, Fig. 3, Fig. 4 and Fig. 5, which includes following
Step S110 ~ step S170：
S110 is that processing covering boss step is processed by mechanically or chemically processing method in the inner surface of the covering 1 of two sides
Multiple boss 2,2 position of boss with core plate 3 for being connected.Wherein, the thickness of the thickness of covering 1 and core plate 3 is in the two
The ratio for being connected with each other position is not less than 2.
In this step, process covering inner surface convex platform 2 method can using cutting machining process or
Using the method for carrying out chemical process in acid solution, wherein the method that use removal material in acid solution processes boss is specific
For：For covering inner surface coating acid solution protective film other than 2 position of boss as acid solution interleaving agent, it is former that other positions retain metal
Beginning surface, then chemistry milling is carried out to the covering with acid solution, subtract the position other than 2 position of boss coated with acid solution protective film
It is thin, so that covering inner surface is processed multiple boss 2.
And knuckle is processed in the intermediate location of 2 position of boss and covering inner surface, which is not less than
The height of boss 2, wherein the height of boss 2 is the thickness that the skin thickness other than 2 position of boss is thinned through acid solution chemistry milling.
S120 is coating interleaving agent step, the position coating diffusion connection isolation other than 1 inner surface convex platform 2 of covering
Agent.In this step, using the only solder flux of the prior art as diffusion connection interleaving agent, as long as can prevent at coating position
Diffusion connection.
S130 is to process core plate step of splaying to process splaying for variable cross-section thickness by mechanically or chemically processing method
Core plate 3.Splay the intermediate position of core plate 3 section be linear transitions variable cross-section thickness, can be real using the method for mechanical grinding
Existing linear transitions.The variable cross-section thickness at its both ends can be linear transitions, be also possible to non-linear transition, can be under thicker
1/3 region brush protective glue of portion, other positions retain metal initial surface, realize 1/3 region of top by chemical processes
Thickness is thinned.
S140 is processing gas inlet slot step, in the narrowed thickness end processing gas inlet slot 4 for core plate 3 of splaying.It is general to use machinery
Cutting mode processes notch as air inlet duct 4, for being passed through argon gas class indifferent gas by the air inlet duct 4 in superplastic forming
Body.
S150 is combination edge sealing step, and intermediate core plate 3 is clamped between two side skins 1 for being machined with boss 2, is being formed
Three layer stacked structure surroundings weld edge sealing.
S160 is diffusion Connection Step, and three layer stacked structures after combination edge sealing are placed in hot equipressure after Vacuum Package
It is diffused connection in furnace, realizes intermediate core plate 3 and the covering 1 of two sides at 2 position of boss and connects.
S170 be superplastic forming step, by the air inlet duct 4 on core plate 3 to diffusion connection after three layer stacked structures inside
It is filled with inert gas, is placed in superplastic forming die and carries out superplastic forming, makes core plate 3 and covering 1 other than 2 position of boss
Non-diffusing join domain bulging is simultaneously closed with the type face paste of superplastic forming die.After the completion of superplastic forming step, intermediate core plate 3 shapes
For the hollow structure of W-shaped girder rib lattice.
Three layers of hollow blade structure of one kind of the invention and its manufacturing method, firstly, passing through the inner surface connection in covering
Position processes boss, on the one hand, and it avoids groove of the covering under by core plate pulling force effect in forming process and occurs, it is another
Aspect, in non-diffusing join domain, since skin thickness is not constrained by formability, it can be achieved that being largely thinned, thus into
The loss of weight of one step realization structure.Secondly, core plate uses variable cross-section thickness design, it may be implemented and covering is in local thickness
Match, to be conducive to being thinned for covering under the premise of meeting the requirement of formability, further realize the loss of weight of structure.
It should be clear that all the embodiments in this specification are described in a progressive manner, each embodiment it
Between the same or similar part may refer to each other, the highlights of each of the examples are it is different from other embodiments it
Place.The invention is not limited to particular step described above and shown in figure and structures.Also, for brevity,
Here the detailed description to known method technology is omitted.
The above description is only an example of the present application, is not restricted to the application.The scope of the present invention is not being departed from
In the case where to those skilled in the art, various changes and changes are possible in this application.It is all in spirit herein and
Any modification, equivalent replacement, improvement and so within principle, should be included within the scope of claims hereof.
Claims (10)
1. a kind of manufacturing method of three layers of hollow blade structure, the hollow blade structure include truss structure intermediate core plate with
The skin panel of two sides, which is characterized in that the manufacturing method includes：
Covering boss is processed, by mechanically or chemically processing method, the covering inner surface in two sides processes multiple boss, described
Boss position with the core plate for being connected；
Interleaving agent is coated, the position coating diffusion connection interleaving agent other than the covering inner surface convex platform；
It processes core plate of splaying and the core plate of splaying of variable cross-section thickness is processed by mechanically or chemically processing method；
Processing gas inlet slot, in the narrowed thickness end processing gas inlet slot of the core plate of splaying；
Edge sealing is combined, intermediate core plate is clamped between two side skins for being machined with boss, in three layer stacked structures four of formation
Week welding edge sealing；
Three layer stacked structures after the combination edge sealing are placed in hot isobaric furnace after Vacuum Package and expand by diffusion connection
Connection is dissipated, the intermediate core plate and the covering of two sides is realized at the boss position and connects；
Superplastic forming, by the air inlet duct on the core plate to diffusion connection after three layer stacked structures inside be filled with indifferent gas
Body is placed in superplastic forming die and carries out superplastic forming, connects the non-diffusing of the core plate and covering other than boss position
It connects region bulging and is closed with the type face paste of superplastic forming die.
2. the manufacturing method of three layers of hollow blade structure according to claim 1, which is characterized in that the skin thickness with
The core thickness is not less than in the ratio that the two is connected with each other position.
3. the manufacturing method of three layers of hollow blade structure according to claim 1, which is characterized in that the processing covering is convex
The method of platform includes the machining process using cutting.
4. the manufacturing method of three layers of hollow blade structure according to claim 1, which is characterized in that the processing covering is convex
The method of platform includes the covering inner surface coated acid that is, other than boss position using the method for carrying out chemical process in acid solution
Liquid protective film, then chemistry milling is carried out to the covering with acid solution, make the portion other than the boss position coated with acid solution protective film
Position is thinned, and covering inner surface is made to process multiple boss.
5. the manufacturing method of three layers of hollow blade structure according to claim 4, which is characterized in that at the boss position
Knuckle is processed with the intermediate location of the covering inner surface, the knuckle is not less than the height of the boss,
Described in boss height be boss position other than covering through acid solution chemistry milling be thinned thickness.
6. the manufacturing method of three layers of hollow blade structure according to claim 1, which is characterized in that in the core plate of splaying
Between position section be linear transitions variable cross-section thickness.
7. the manufacturing method of three layers of hollow blade structure according to claim 1, which is characterized in that the superplastic forming step
After the completion of rapid, the intermediate core plate is configured to the hollow structure of W-shaped girder rib lattice.
8. a kind of three layers of hollow blade structure, using the system of the described in any item three layers of hollow blade structures of such as claim 1-7
Make method, which is characterized in that the hollow blade structure includes the intermediate core plate of truss structure and the skin panel of two sides, described
Covering inner surface has multiple boss thickened, and the core plate is the core plate of splaying of variable cross-section thickness, becomes in the thickness of the core plate
Thin end is machined with air inlet duct, and the thickness of the boss is greater than the thickness of the core plate, the illiteracy of the core plate and the two sides
Skin is connected at the boss position.
9. three layers of hollow blade structure according to claim 8, which is characterized in that in the boss position and the covering
The intermediate location on surface is machined with knuckle, and the knuckle is not less than the height of the boss.
10. three layers of hollow blade structure according to claim 8, which is characterized in that the illiteracy of the intermediate core plate and two sides
Skin is titanium alloy material.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810593281.4A CN108890219B (en) | 2018-06-11 | 2018-06-11 | Three layers of hollow blade structure of one kind and its manufacturing method |
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| CN201810593281.4A CN108890219B (en) | 2018-06-11 | 2018-06-11 | Three layers of hollow blade structure of one kind and its manufacturing method |
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| CN108890219A true CN108890219A (en) | 2018-11-27 |
| CN108890219B CN108890219B (en) | 2019-09-20 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109396676A (en) * | 2018-12-12 | 2019-03-01 | 中国航空制造技术研究院 | The method for controlling three layers of hollow interlayer body structure surface trench defect |
| CN111156196A (en) * | 2020-01-10 | 2020-05-15 | 中国航空制造技术研究院 | Rotor blade structure of fan/compressor of aircraft engine and design method thereof |
| CN111531335A (en) * | 2020-05-23 | 2020-08-14 | 北京普惠三航科技有限公司 | Multilayer structure and processing method thereof |
| CN112372130A (en) * | 2020-11-02 | 2021-02-19 | 中国航空制造技术研究院 | Preparation method of titanium alloy hollow structure |
| CN114211204A (en) * | 2021-12-21 | 2022-03-22 | 北京星航机电装备有限公司 | Gamma-shaped half-section end ring and superplastic forming method thereof |
| CN114310165A (en) * | 2021-12-21 | 2022-04-12 | 北京星航机电装备有限公司 | Inner support of cabin body, forming method of inner support and semi-closed cabin body |
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| CN202719358U (en) * | 2012-08-16 | 2013-02-06 | 中航商用航空发动机有限责任公司 | Core board and vane and hollow fan used in aero-engine |
| CN107283118A (en) * | 2017-04-28 | 2017-10-24 | 常州天泰航材科技有限公司 | A kind of TC4 titanium alloys truss structure engine blade preparation method |
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| CN202719358U (en) * | 2012-08-16 | 2013-02-06 | 中航商用航空发动机有限责任公司 | Core board and vane and hollow fan used in aero-engine |
| CN107283118A (en) * | 2017-04-28 | 2017-10-24 | 常州天泰航材科技有限公司 | A kind of TC4 titanium alloys truss structure engine blade preparation method |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109396676A (en) * | 2018-12-12 | 2019-03-01 | 中国航空制造技术研究院 | The method for controlling three layers of hollow interlayer body structure surface trench defect |
| CN111156196A (en) * | 2020-01-10 | 2020-05-15 | 中国航空制造技术研究院 | Rotor blade structure of fan/compressor of aircraft engine and design method thereof |
| CN111156196B (en) * | 2020-01-10 | 2021-10-29 | 中国航空制造技术研究院 | Rotor blade structure of fan/compressor of aircraft engine and design method thereof |
| CN111531335A (en) * | 2020-05-23 | 2020-08-14 | 北京普惠三航科技有限公司 | Multilayer structure and processing method thereof |
| CN112372130A (en) * | 2020-11-02 | 2021-02-19 | 中国航空制造技术研究院 | Preparation method of titanium alloy hollow structure |
| CN114211204A (en) * | 2021-12-21 | 2022-03-22 | 北京星航机电装备有限公司 | Gamma-shaped half-section end ring and superplastic forming method thereof |
| CN114310165A (en) * | 2021-12-21 | 2022-04-12 | 北京星航机电装备有限公司 | Inner support of cabin body, forming method of inner support and semi-closed cabin body |
| CN114211204B (en) * | 2021-12-21 | 2023-02-03 | 北京星航机电装备有限公司 | Gamma-shaped half-section end ring and superplastic forming method thereof |
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