CN204164033U - Hollow fan blade for aircraft engine - Google Patents
Hollow fan blade for aircraft engine Download PDFInfo
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- CN204164033U CN204164033U CN201420490696.6U CN201420490696U CN204164033U CN 204164033 U CN204164033 U CN 204164033U CN 201420490696 U CN201420490696 U CN 201420490696U CN 204164033 U CN204164033 U CN 204164033U
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Abstract
The purpose of this utility model is to provide a kind of hollow fan blade for aircraft engine, and it can well in crashworthiness and lightweight requirements.For realizing the hollow fan blade for aircraft engine of described object, comprise the framing system in cavity that blade shell and blade shell surround, be characterized in, this blade is one-body molded by selective laser melting equipment, and described framing system is the combination of Wahlen structure and I-groove beam.
Description
Technical field
The utility model relates to hollow fan blade for aircraft engine.
Background technique
Hollow fan blade, as one of the critical component of commercial aviation motor, significantly reduces the weight of aeroengine, meets the requirement of commercial aviation motor of new generation " low noise, low stain, low cost ", improve market engine competitive ability.
A kind of titanium alloy hollow fan blade, it comprises the framing system in cavity that blade shell and blade shell surround, its construction process is: first on middle central layer, stop solder flux with certain figure spraying, then central layer and two-layer panel one are reinstated argon arc welding and weld edge sealing and leave suction port; The laminate welded is put into the mould identical with blade profile, and puts into together in the press with heating system, be heated to SPF/DB (superplastic formation/diffusion connects) temperature; First in die cavity, be blown into certain argon gas, then insulation makes three layers of titanium intralamellar part subscribe positions to carry out diffusion with periphery and be connected; The argon gas being blown into certain pressure after having connected again in threepayer carries out SPF, and two-layer panel carries out stretching and torsional deformation under SPF shape body, and simultaneously, central layer extends and is out of shape formation truss structure; Sheet material cools with stove after pasting contour forming completely, takes out part and carries out surperficial milling; Last digital control processing goes out blade root and blade profile edge.The framing system of this blade is Wahlen shape (zigzag).
Another kind of titanium alloy hollow fan blade, it comprises the framing system in cavity that blade shell and blade shell surround, its construction process is: blade stock is titanium alloy, be milled into ribbing by machining but there is no two of core semi-symmetric flat blades, diffusion connecting process is then first adopted to connect, flat for two halves blade is put into mould face-to-face, send in vacuum furnace and apply High Temperature High Pressure, obtain the flawless blade blank of diffusion welding uniform quality, then apply SPF Technology blade is shaped.Its operation is that the flat leaf base connected is put into the mould identical with blade net shape, be heated to superplastic forming state, now because the effect blade of gravity pastes mould (this process can make the bending of blade and twist reach 90% of required value) substantially, and then be blown into argon gas to blade interior, the super characteristic of moulding of material is utilized to make blade paste mould completely, be shaped the blade blank of required aerodynamic configuration, and last digital control processing goes out blade root and blade profile.The framing system of this blade is I-shaped grooved.
Patent documentation CN101649844A also discloses a kind of fan blade, and framing system is wherein one or more spatial structure be combined to form in diamond structure, tetrahedral unit framework, hexahedral element structure or cellular structure etc.
Present inventor finds in practice, and the balance of structure in crashworthiness and lightweight of which kind of blade all needs to be improved.
Model utility content
The purpose of this utility model is to provide a kind of hollow fan blade for aircraft engine, and it can well in crashworthiness and lightweight requirements.
For realizing the hollow fan blade for aircraft engine of described object, comprise the framing system in cavity that blade shell and blade shell surround, be characterized in, this blade is one-body molded by selective laser melting equipment, and described framing system is the combination of Wahlen structure and I-groove beam.
Described hollow fan blade for aircraft engine, its further feature is, described blade comprises the top plenum being positioned at vane tip and the bottom pore being positioned at blade bottom that are communicated with described cavity.
Described hollow fan blade for aircraft engine, its further feature is also provided with tangential air drain between described top plenum and described cavity.
Described hollow fan blade for aircraft engine, its further feature is also provided with tangential air drain between described bottom pore and described cavity.
Described hollow fan blade for aircraft engine, its further feature is, described top plenum and described bottom pore are by sealing.
Described hollow fan blade for aircraft engine, its further feature is, described blade is titanium alloy hollow fan blade.
Hollow blade in the past only uses simple " Wahlen " structure, or only uses " I-shaped grooved " structure.But no matter being that structure, the while that its main purpose being the weight in order to alleviate blade, ensureing the integral rigidity of blade, thus improve or ensure that the anti-bird of blade hits impact capacity.But its simple internal cavity structures causes blade hollow rate to improve, thus the weight of blade is caused to alleviate further.In practice according to inventor of the present utility model, due to Wahlen structure and I-shaped trench structure are organically merged, both the rigidity that make use of " Wahlen " structure is strong, shock resistance General is good, make use of again " I-shaped grooved " feature that structure hollow rate is high, under guarantee blade integral rigid strip, guarantee that blade bird is hit impact property and meets the demands, the hollow rate (can more than 40% be reached) that blade was higher in the past can be obtained simultaneously, have effectively achieved the loss of weight of blade.
Accompanying drawing explanation
The above and other feature of the present utility model, character and advantage become more obvious by passing through below in conjunction with the description of drawings and Examples, wherein:
Fig. 1 is the plan view of hollow fan blade for aircraft engine in an embodiment of the present utility model.
Fig. 2 is the sectional drawing along A-A line in Fig. 1.
Fig. 3 is the plan view of the blade in Fig. 1 before non-polishing.
Fig. 4 is the plan view of Fig. 3 Leaf.
Fig. 5 is the worm's eye view of Fig. 3 Leaf.
Embodiment
Below in conjunction with specific embodiments and the drawings, the utility model is described in further detail; set forth more details in the following description so that fully understand the utility model; but the utility model obviously can be implemented with multiple this alternate manner described that is different from; those skilled in the art when doing similar popularization, deduction without prejudice to when the utility model intension according to practical situations, therefore can should not limit protection domain of the present utility model with the content of this specific embodiment.
It should be noted that accompanying drawing all only exemplarily, it is not draw according to the condition of equal proportion, and should not be construed as limiting in this, as to the protection domain of the utility model actual requirement.
As depicted in figs. 1 and 2, fan blade 1 has the framing system in cavity 100 that blade shell 10 and blade shell 10 surround, and framing system is the combination of Wahlen structure 11 and I-groove beam 12.Wahlen structure 11 is the multiple Z-shaped structures of continuous print, the beam of I-groove beam 12 to be cross sections be I shape.The surface of blade shell 10 forms the aerodynamic force surface of blade, produces axially or gas flow direction that is radial or other directions according to design.The top 1B of blade shell 10 is the end of blade, and bottom 1A is the cardinal extremity of blade, for installing blade 1.
The combination of Wahlen structure 11 and I-groove beam 12 except as shown in Figure 2 occupy except half cavity 100 separately, can also be other combinations, the size of this combination and blade has relation, if medium-sized blade, can adopt the portfolio ratio shown in Fig. 2, if large-scale blade, Wahlen structure 11 takes up space will more than I-groove beam 12, if small-sized blade, Wahlen structure 11 can be less than I-groove beam 12.This combination is also relevant with the crashproof position of blade, for specific crashproof position, namely requires the position that crashworthiness is higher, and Wahlen structure 11 will more than I-groove beam 12 with regard to taking up space.
Blade structure shown in Fig. 1 with Fig. 2 is also relevant with its moulding process.Blade 1 is one-body molded by selective laser melting (Select Laser Melting, SLM) equipment.Selective laser melting equipment can be commercial equipment, and its structure has not just been spoken more again, and its common execution technique is as follows:
1) based on threedimensional model, design laser fast shaping auxiliary hole;
2) part utilizing laser fast shaping technique to realize band surplus increases material manufacture;
3) abrasive Flow is utilized to realize removal or the polishing of inside parts;
4) Conventional machining methods is utilized to realize the machining of part outer surface.
Correspondingly, the blade structure for previous embodiment utilizes 3D CASE(Computer Aided Software Engineering) etc. to carry out slicing treatment along leaf height direction to metal stiffened edge model, and thickness is 10 microns ~ 500 microns, carries out sliding-model control to model; Then, arranging laser fast shaping speed, is 5 ms/min ~ 200 ms/min, laser head power 100W ~ 10000W; Secondly powdered metal powder is positioned in laser fast shaping equipment; Then, closing device door, and with vacuum pump, equipment active chamber is become vacuum, and pass into shielding gas, as argon gas.Finally, run laser fast shaping equipment and start " printing " metal stiffened edge until terminate.
For the ease of the process of interior surface, as shown in Figures 3 to 5, fan 1 comprises top plenum 21, tangential air drain 22, bottom pore 23.Tangential air drain 22 according to the complexity of later stage clear powder, can carry out selectivity design, also can arrange tangential air drain between bottom pore 23 and central cavity 100.After blade is one-body molded by selective laser melting, " open type " passage utilizing top plenum 21, tangential air drain 22, central cavity 100, bottom pore 23 to be formed carries out powder process clearly, then utilizes abrasive Flow to go material or polishing treatment to hollow blade 1 inner chamber wall.Abrasive particle enters internal cavities from top plenum, discharges (direction can be put upside down) from bottom pore.After the surface treatment to each pore sealing of hole, argon arc welding is namely utilized to seal top plenum, bottom pore.Numerical control machine tool is finally utilized to process hollow fan blade outer surface.
The fan blade 1 of previous embodiment is owing to being by the integral manufacture of selective laser melting technique, therefore, it is possible to obtain the combination of Wahlen structure and trough girder structure, Wahlen structure provides more strong crashworthiness, and trough girder structure provides higher hollow rate, according to crashproof requirement and the leaf blade size at blade position, Wahlen structure and trough girder structure can arbitrarily combine, the interior surface of fan blade 1 is owing to being shaping in advance by selective laser melting technique, again by glossing process, very high roughness requirements can be met, this can improve crashworthiness further.
Although the utility model with preferred embodiment openly as above, it is not that any those skilled in the art, not departing from spirit and scope of the present utility model, can make possible variation and amendment for limiting the utility model.Therefore, every content not departing from technical solutions of the utility model, any amendment done above embodiment according to technical spirit of the present utility model, equivalent variations and modification, all fall within protection domain that the utility model claim defines.
Claims (6)
1. a hollow fan blade for aircraft engine, comprise the framing system in cavity that blade shell and blade shell surround, it is characterized in that, this blade is one-body molded by selective laser melting equipment, and described framing system is the combination of Wahlen structure and I-groove beam.
2. hollow fan blade for aircraft engine as claimed in claim 1, is characterized in that, described blade comprises the top plenum being positioned at vane tip and the bottom pore being positioned at blade bottom that are communicated with described cavity.
3. hollow fan blade for aircraft engine as claimed in claim 2, is characterized in that, be also provided with tangential air drain between described top plenum and described cavity.
4. hollow fan blade for aircraft engine as claimed in claim 2, is characterized in that, be also provided with tangential air drain between described bottom pore and described cavity.
5. hollow fan blade for aircraft engine as claimed in claim 2, it is characterized in that, described top plenum and described bottom pore are by sealing.
6. hollow fan blade for aircraft engine as claimed in claim 1, it is characterized in that, described blade is titanium alloy hollow fan blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420490696.6U CN204164033U (en) | 2014-08-28 | 2014-08-28 | Hollow fan blade for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420490696.6U CN204164033U (en) | 2014-08-28 | 2014-08-28 | Hollow fan blade for aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN204164033U true CN204164033U (en) | 2015-02-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420490696.6U Active CN204164033U (en) | 2014-08-28 | 2014-08-28 | Hollow fan blade for aircraft engine |
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| CN (1) | CN204164033U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105671367A (en) * | 2016-04-22 | 2016-06-15 | 温州市兴宇箱包五金有限公司 | Titanium alloy trunk and production process thereof |
| CN108443178A (en) * | 2018-03-13 | 2018-08-24 | 吴江市大印墨风力发电机制造有限公司 | A kind of fan |
| CN112628195A (en) * | 2019-10-09 | 2021-04-09 | 中国航发商用航空发动机有限责任公司 | Fan blade and aeroengine |
| WO2022077934A1 (en) * | 2020-10-12 | 2022-04-21 | 浙江铭振电子股份有限公司 | Impeller |
-
2014
- 2014-08-28 CN CN201420490696.6U patent/CN204164033U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105671367A (en) * | 2016-04-22 | 2016-06-15 | 温州市兴宇箱包五金有限公司 | Titanium alloy trunk and production process thereof |
| CN108443178A (en) * | 2018-03-13 | 2018-08-24 | 吴江市大印墨风力发电机制造有限公司 | A kind of fan |
| CN112628195A (en) * | 2019-10-09 | 2021-04-09 | 中国航发商用航空发动机有限责任公司 | Fan blade and aeroengine |
| CN112628195B (en) * | 2019-10-09 | 2023-04-25 | 中国航发商用航空发动机有限责任公司 | Fan blade and aeroengine |
| WO2022077934A1 (en) * | 2020-10-12 | 2022-04-21 | 浙江铭振电子股份有限公司 | Impeller |
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| C14 | Grant of patent or utility model | ||
| 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: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |