阅读说明：本技术 一种风扇叶片及航空发动机 (Fan blade and aeroengine ) 是由 冯锦璋 柴象海 于 2019-10-09 设计创作，主要内容包括：本公开公开了一种风扇叶片,包括：第一面板,设置于迎风面；第二面板,对应于所述第一面板,设置于背风面；多个隔板,间隔地支撑于所述第一面板和所述第二面板之间,能够将所述风扇叶片内部分隔为多个空腔；以及多个填充物,填充于所述空腔的内部,并相对于所述第一面板和所述第二面板的位置固定。基于上述技术方案,本公开能够利用填充物吸收风扇叶片的鸟撞冲击载荷,提升风扇叶片的抗鸟撞性能；并使风扇叶片在等效的强度、刚度和抗鸟撞条件下具有更高的空心率与更轻的重量；还能使风扇叶片的加工制造效率高、质量稳定。(The present disclosure discloses a fan blade, comprising: the first panel is arranged on the windward side; the second panel corresponds to the first panel and is arranged on a leeward surface; a plurality of partitions supported at intervals between the first panel and the second panel and capable of partitioning the interior of the fan blade into a plurality of cavities; and a plurality of fillers filled in the cavity and fixed relative to the first panel and the second panel. Based on the technical scheme, the bird impact load of the fan blades can be absorbed by the filler, and the bird impact resistance of the fan blades is improved; and the fan blade has higher hollow rate and lighter weight under the conditions of equivalent strength, rigidity and bird impact resistance; and the fan blade has high processing and manufacturing efficiency and stable quality.)

1. A fan blade, comprising:

the first panel is arranged on the windward side;

the second panel corresponds to the first panel and is arranged on a leeward surface;

a plurality of partitions supported at intervals between the first panel and the second panel and capable of partitioning the interior of the fan blade into a plurality of cavities; and

and the fillers are filled in the cavity and are fixed relative to the positions of the first panel and the second panel.

2. The fan blade of claim 1, wherein the plurality of fillers comprises a plurality of hollow spheres.

3. The fan blade of claim 2, wherein the spherical shell of the hollow sphere is assembled from a plurality of unit cell structures adjacent to each other, and each unit cell structure comprises at least one aperture.

4. The fan blade of claim 3, wherein the unit cell structure is a hexagonal structure, a hexagonal hole is formed in the center of the hexagonal structure, and each side of the hexagonal hole is parallel to each corresponding side of the hexagonal structure.

5. The fan blade of claim 3, wherein the hollow ball is made by an additive manufacturing technology, the hollow ball comprises a plurality of layers of spherical shells sleeved with each other, and the positions of the spherical shells of the adjacent layers are relatively fixed.

6. The fan blade of claim 2, wherein the inner side of the first panel and/or the second panel is provided with a spherical crown shaped pit, the spherical crown shaped pit and the hollow ball are of equal radius, and the hollow ball can be fixed in position by being partially embedded into the spherical crown shaped pit.

7. The fan blade of claim 6, wherein the spherical cap shaped dimples and the hollow spheres are in an interference fit in an operational state of the fan blade, and wherein the spherical cap shaped dimples and the hollow spheres are in a clearance fit during assembly of the fan blade by heating the first panel and/or the second panel and cooling the hollow spheres.

8. The fan blade of claim 6, wherein, outward in the span direction of the fan blade, the proportion of the hollow ball embedded in the spherical-crown-shaped pit is gradually increased in proportion to the volume of the hollow ball.

9. The fan blade of claim 1, wherein each of the plurality of spacers extends continuously from the blade root to the blade tip of the fan blade, and the plurality of hollow balls located in the same cavity have a set pitch therebetween in the span direction of the fan blade.

10. The fan blade of claim 9, wherein the diameters of the plurality of hollow balls in the same cavity are gradually reduced and the distribution density is gradually increased along the spanwise direction of the fan blade.

11. The fan blade of claim 2, wherein the density of the hollow spheres is greater in a region proximate to the leading and trailing edges of the fan blade than in a region intermediate the fan blade along the chord of the fan blade.

12. The fan blade of claim 1 wherein the first and second panels are made by an additive manufacturing technique, the first and second panels having a non-uniform thickness distribution.

13. The fan blade of claim 12 wherein the first and second panels each have a thickness in a set proportion to the thickness of the fan blade in the thickness direction of the fan blade.

14. The fan blade of claim 1, wherein the plurality of fillers comprise a plurality of hollow hollowed polyhedrons, polygonal pits corresponding to the hollowed polyhedrons are formed in the inner sides of the first panel and/or the second panel, and the hollowed polyhedrons can be fixed in position by partially embedding the polygonal pits.

15. An aircraft engine comprising a fan blade according to any one of claims 1 to 14.

Technical Field

The disclosure relates to the field of gas turbines, in particular to a fan blade and an aircraft engine.

Background

Large bypass ratio fan blades are key components of large passenger aircraft engines. The traditional solid fan blade has heavy weight, large centrifugal force and prominent flutter and vibration problems, can not meet the requirements of design and low oil consumption of a large-scale engine, and the superplastic forming/diffusion connection Valon-structured titanium alloy wide-chord hollow fan blade and the carbon fiber composite fan blade are typical structures of the international large-bypass-ratio turbofan engine at present, but are protected by patents of main manufacturers of foreign aeroengines.

While a number of patents have addressed 3D printing techniques associated with aircraft engines, a search of the published patents has revealed that 3D printing techniques have been used extensively in many parts of engines, including vanes, vane shrouds, blisks, combustion chamber walls, nozzles, and the like, and have even expanded to other more extensive structural aspects. Due to the introduction of the additive manufacturing technology, the structure of the aeroengine part does not receive the restriction of the traditional processing technology, the wider design space is provided, and the processing of complex structures such as a hollow ball and the like can be realized.

Chinese patent application CN106599359 discloses a method for designing a hollow blade filled with a spherical mesh structure and an engine, and a 3D printing technology is used to obtain the spherical mesh hollow blade by replacing the solid structure with spherical units at different positions inside a solid blade model, thereby improving various performances of the blade and reducing the blade mass. The invention mentions that the hollow blade is manufactured by using a 3D printing technology to obtain a more complex blade structure, but is difficult to realize in practice because the 3D printing can manufacture a complex three-dimensional structure, but cannot form a suspended structure, that is, a spherical net structure cannot form a whole sphere from a suspended point and then is crosslinked with other spheres, so that although the idea of using the 3D printing in blade manufacturing is provided, the patent is not feasible in principle.

Disclosure of Invention

In view of this, the embodiments of the present disclosure provide a fan blade and an aircraft engine, which can utilize a filler to absorb a bird strike impact load of the fan blade, so as to improve bird strike resistance of the fan blade; and the fan blade has higher hollow rate and lighter weight under the conditions of equivalent strength, rigidity and bird impact resistance; and the fan blade has high processing and manufacturing efficiency and stable quality.

In one aspect of the present disclosure, there is provided a fan blade comprising:

the first panel is arranged on the windward side;

the second panel corresponds to the first panel and is arranged on a leeward surface;

a plurality of partitions supported at intervals between the first panel and the second panel and capable of partitioning the interior of the fan blade into a plurality of cavities; and

and the fillers are filled in the cavity and are fixed relative to the positions of the first panel and the second panel.

In some embodiments, the plurality of fillers comprises a plurality of hollow-out spheres.

In some embodiments, the spherical shell of the hollow sphere is formed by splicing a plurality of unit cell structures in a manner of being adjacent to each other, and each unit cell structure comprises at least one small hole.

In some embodiments, the unit cell structure is a hexagonal structure, a hexagonal small hole is opened at the center of the hexagonal structure, and each side of the hexagonal small hole is parallel to each corresponding side of the hexagonal structure.

In some embodiments, the hollow-out ball is made by additive manufacturing technology, the hollow-out ball comprises a plurality of layers of ball shells sleeved with each other, and the positions of the ball shells of the adjacent layers are relatively fixed.

In some embodiments, the inner side of the first panel and/or the second panel is provided with a spherical crown shaped pit, the spherical crown shaped pit has the same radius with the hollow ball, and the hollow ball can be fixed in position by being partially embedded into the spherical crown shaped pit.

In some embodiments, in the operating state of the fan blade, the spherical cap shaped recess and the hollow ball are in an interference fit, and in the assembling process of the fan blade, the spherical cap shaped recess and the hollow ball are in a clearance fit by heating the first panel and/or the second panel and cooling the hollow ball.

In some embodiments, the volume proportion of the part of the hollow ball embedded into the spherical-crown-shaped pit is gradually increased along the spanwise direction of the fan blade.

In some embodiments, each of the plurality of baffles extends continuously from the blade root to the blade tip of the fan blade, and the plurality of hollow balls located in the same cavity have a set distance therebetween in the spanwise direction of the fan blade.

In some embodiments, along the span direction of the fan blade, the diameters of the plurality of hollow balls in the same cavity are gradually reduced, and the distribution density is gradually increased.

In some embodiments, the distribution density of the hollow spheres in the region near the leading edge and the trailing edge of the fan blade is greater than the distribution density in the region in the middle of the fan blade along the chord direction of the fan blade.

In some embodiments, the first and second panels are made by additive manufacturing techniques, the first and second panels having a non-uniform thickness distribution.

In some embodiments, the first and second panels each have a thickness in a set proportion to the thickness of the fan blade in the thickness direction of the fan blade.

In some embodiments, the plurality of fillers include a plurality of hollow hollowed-out polyhedrons, the inner side of the first panel and/or the second panel is provided with polygonal pits corresponding to the hollowed-out polyhedrons, and the hollowed-out polyhedrons can be fixed in position by partially embedding the polygonal pits.

In another aspect of the present disclosure, there is provided an aircraft engine comprising a fan blade as described in any of the previous embodiments.

Based on the technical scheme, the embodiment of the disclosure can at least produce one of the following technical effects:

through the good deformation energy absorption effect of the hollow balls, the bird impact load capacity of the fan blades is absorbed, the bird impact resistance of the fan blades is improved, and through the reasonable arrangement of the hollow balls in the cavities, the bird impact resistance is further improved;

the fan blades have higher hollow rate and lighter weight under the conditions of equivalent strength, rigidity and bird impact resistance by the hollow ball filling mode;

the blade panel and the hollow ball are respectively molded by adopting an additive manufacturing technology, and then the blade panel and the hollow ball are assembled, so that the fan blade is high in processing efficiency and good in quality stability.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the disclosure and together with the description serve to explain the disclosure and not to limit the disclosure. In the drawings:

FIG. 1 is a schematic structural view of a fan blade provided in an embodiment of the present disclosure;

FIG. 2 is a structural schematic view of a chord-wise cross-sectional angle of a fan blade provided by an embodiment of the present disclosure;

fig. 3 is a schematic view of a hollow-out ball structure of a fan blade according to an embodiment of the disclosure.

Reference numerals: 1. the device comprises a first panel, a second panel, a first partition board, a second partition board, a hollow ball, a first partition board, a second partition board, a hollow ball, a first unit cell structure and a second unit cell structure, wherein the first panel 2 is a first panel, the second panel 3;

a. a blade root, a blade tip, a leading edge c and a trailing edge d.

Detailed Description

The contents of the present disclosure and the points of distinction between the present disclosure and the prior art can be understood with reference to the drawings and the text below. The technical solutions (including the preferred technical solutions) of the present disclosure are further described in detail by the figures and by way of enumerating some alternative embodiments of the present disclosure.

It should be noted that: any technical features and any technical solutions in the present embodiment are one or more of various optional technical features or optional technical solutions, all the alternative technical features and alternative technical solutions of the present disclosure cannot be exhaustively listed in this document for the sake of brevity of description, and it is not convenient for each embodiment of the technical features to emphasize that it is one of various optional embodiments, so those skilled in the art should know that: any one of the technical means provided by the present disclosure may be replaced or any two or more of the technical means or technical features provided by the present disclosure may be combined with each other to obtain a new technical solution.

Any technical features and any technical solutions in the present embodiment do not limit the scope of the present disclosure, and the scope of the present disclosure should include any alternative technical solutions that can be conceived by those skilled in the art without inventive efforts and new technical solutions that can be obtained by those skilled in the art by combining any two or more technical means or technical features provided by the present disclosure with each other.

The technical scheme provided by the disclosure is explained in more detail with reference to the accompanying drawings 1-3.

In one aspect of the present disclosure, there is provided a fan blade comprising:

the first panel 1 is arranged on the windward side;

the second panel 2 corresponds to the first panel 1 and is arranged on the leeward side;

a plurality of partitions 3 supported at intervals between the first panel 1 and the second panel 2, and capable of partitioning the inside of the fan blade into a plurality of cavities; and

and a plurality of fillers filled in the cavity and fixed relative to the first panel 1 and the second panel 2.

Based on the first panel 1 and the second panel 2, a hollow fan blade can be enclosed, and the fan blade has a blade-shaped structure similar to a traditional fan blade, so that the fan of the aircraft engine can do work on the air inlet of the fan to accelerate the air inlet and change the airflow direction.

The plurality of baffles 3 are supported at intervals between the first panel 1 and the second panel 2 for dividing the inner space of the fan blade into a plurality of cavities for accommodating the plurality of fillers; furthermore, the spacer 3 may be disposed relatively perpendicularly between the first panel 1 and the second panel 2 to transmit compressive and tensile stresses between the first panel 1 and the second panel 2 and to reinforce the bending and torsional strength of the fan blade.

The fillers are filled in the cavity, so that the load of the fan blade under bird impact can be absorbed through the self deformation energy absorption characteristic, and the bird impact resistance of the fan blade is improved. Furthermore, considering that the fan blade rotates very fast in the operating condition, the position of the plurality of fillers with respect to the first and second panels 1, 2 is fixed, preventing the plurality of fillers from shaking inside the cavity and damaging the internal structure of the fan blade.

Further, in some embodiments, the plurality of fillers comprises a plurality of hollow balls 4. The hollow ball 4 has a good deformation energy absorption effect, and the hollow ball 4 can be filled in a mode that the fan blade has a higher hollow rate under the conditions of equivalent strength, rigidity and bird impact resistance, so that the weight of the fan blade is reduced to a certain extent.

Further, in some embodiments, the spherical shell of the hollow sphere 4 is formed by combining a plurality of unit cell structures 41 adjacent to each other, and each unit cell structure 41 includes at least one small hole.

The unit cell structures 41 are assembled closely adjacent to each other to form the spherical shell of the hollow ball 4, and the unit cell structures 41 include pentagonal structures, hexagonal structures or other possible polygonal structures or irregular-shaped structures with certain spatial radians based on the requirement of three-dimensional close-fitting (for example, a plurality of pieces of leather are assembled to form a soccer ball). Of course, the plurality of unit cells 41 may have the same size and structure or different sizes and structures according to the type of the unit cells 41, so as to adapt to the manufacturing technology of the hollow ball 4, such as welding, bonding, thermoplastic molding, additive manufacturing or integral molding.

For example, in some embodiments, the unit cell structure 41 is a hexagonal structure, a hexagonal hole is opened at the center of the hexagonal structure, and each side of the hexagonal hole is parallel to each corresponding side of the hexagonal structure.

When the unit cell structures 41 are hexagonal structures, the plurality of unit cell structures 41 can be densely paved into spherical shells of the hollow spheres 4 with the same size; and because the hexagonal structure is close to the circular, the atress of its each limit is comparatively even, consequently can make fretwork ball 4 possesses the characteristic of better energy absorption deformation.

And the hexagonal small hole is formed in the center of the hexagonal structure, and the energy absorption deformation effect of the hollow ball 4 can be further enhanced because each side is parallel to each side of the hexagonal structure, and the weight of the fan blade is further reduced.

Further, in order to increase the energy absorption effect after the impact, in some embodiments, the hollow-out ball 4 is manufactured by an additive manufacturing technology, the hollow-out ball 4 includes a plurality of ball shells sleeved with each other, and the positions of the ball shells of the adjacent layers are relatively fixed.

Because the multi-layer sleeved spherical shell structure is difficult to obtain by the traditional processing method, the hollow ball 4 adopts the additive manufacturing process, the advantage of the additive manufacturing technology that parts with any complex shapes can be quickly and precisely manufactured can be fully utilized, and the processing efficiency of the hollow ball 4 is greatly improved.

Further, in order to achieve the fixation of the hollow ball 4 with respect to the first panel 1 and/or the second panel 2, in some embodiments, the inner side of the first panel 1 and/or the second panel 2 is provided with a spherical cap shaped pit, the spherical cap shaped pit has a same radius with the hollow ball 4, and the hollow ball 4 can be fixed in position by partially embedding the spherical cap shaped pit.

Further, in order to prevent the hollow ball 4 from jumping relative to the fan blade during operation, in some embodiments, in an operating state of the fan blade, the spherical crown shaped concave pit and the hollow ball 4 are in an interference fit; in the assembling process of the fan blade, in order to assemble the spherical crown type concave pits and the hollow balls 4 with the sizes in interference fit with each other, the first panel 1 and/or the second panel 2 can be heated, and the hollow balls 4 are cooled, so that the spherical crown type concave pits and the hollow balls 4 are in clearance fit in the assembling link. And after the hollow ball 4 is arranged from the bottom of the tenon of the fan blade and is embedded into the spherical crown type concave pit, restoring the temperature to the room temperature, and enabling the hollow ball 4 to be relatively fixed after being expanded.

Further, considering the influence of the large centrifugal force of the fan blades, in some embodiments, the volume proportion of the hollow ball 4 embedded into the spherical-crown-shaped pit is gradually increased along the outward direction of the fan blades. At this time, the larger the embedded portion, the tighter the fitting of the hollow ball 4 and the spherical crown type concave pit to each other, and the larger the centrifugal force that can be borne. Therefore, the closer to the blade tip b, the larger the proportion of the volume of the part of the hollow ball 4 is embedded.

Further, in order to adapt the partition boards 3 to the condition that the fan blade is subjected to a large centrifugal force, in some embodiments, each partition board 3 in the plurality of partition boards 3 extends continuously from the blade root a to the blade tip b of the fan blade, and the plurality of hollow balls 4 in the same cavity have a set distance therebetween along the span direction of the fan blade.

Further, in order to enhance the bird strike resisting effect of the fan blade, in some embodiments, the diameters of the plurality of hollow balls 4 in the same cavity are gradually reduced and the distribution density is gradually increased along the spanwise direction of the fan blade.

Further, in order to enhance the bird strike resisting effect of the leading edge c and the trailing edge d of the fan blade, in some embodiments, along the chord direction of the fan blade, the distribution density of the hollow balls 4 in the area close to the leading edge c and the trailing edge d of the fan blade is greater than that in the area located in the middle of the fan blade.

Further, in some embodiments, the first panel 1 and the second panel 2 are made by additive manufacturing techniques, the thickness of the first panel 1 and the second panel 2 being non-uniformly distributed. At the moment, the aerodynamic shape of the outer surface of the fan blade can be kept unchanged, and the upper panel and the lower panel form a cavity, so that the thicknesses of the first panel 1 and the second panel 2 can be adjusted in equal proportion, and the local thicknesses of the upper panel and the lower panel of the fan blade can be reduced.

Further, in some embodiments, the thickness of the first panel 1 and the second panel 2 is in a set proportion to the thickness of the fan blade along the thickness direction of the fan blade, so that the strength of the first panel 1 and the second panel 2 is similar to or consistent with that of the original fan blade.

Further, the fillers are not limited to the hollow-out ball 4, that is, in some embodiments, the fillers include hollow-out polyhedrons, polygonal recesses corresponding to the hollow-out polyhedrons are disposed on the inner sides of the first panel 1 and/or the second panel 2, and the hollow-out polyhedrons can be fixed in position by partially embedding the polygonal recesses.

In another aspect of the present disclosure, there is provided an aircraft engine comprising a fan blade as described in any of the previous embodiments.

Based on the technical scheme, the embodiment of the disclosure can at least produce one of the following technical effects:

through the good deformation energy absorption effect of the hollow balls, the bird impact load capacity of the fan blades is absorbed, the bird impact resistance of the fan blades is improved, and through the reasonable arrangement of the hollow balls in the cavities, the bird impact resistance is further improved;

the fan blades have higher hollow rate and lighter weight under the conditions of equivalent strength, rigidity and bird impact resistance by the hollow ball filling mode;

the blade panel and the hollow ball are respectively molded by adopting an additive manufacturing technology, and then the blade panel and the hollow ball are assembled, so that the fan blade is high in processing efficiency and good in quality stability.

Any embodiment disclosed in the foregoing disclosure, unless otherwise indicated, discloses numerical ranges that are preferred ranges, as those skilled in the art will appreciate: the preferred ranges are merely those values which are obvious or representative of the technical effect which can be achieved. Since the numerical values are too large to be exhaustive, some of the numerical values disclosed in this disclosure are provided to exemplify the technical solutions of the present disclosure, and the enumerated numerical values should not be construed as limiting the scope of the present disclosure.

If the terms "first," "second," etc. are used herein to define parts, those skilled in the art will recognize that: the terms "first" and "second" are used merely to distinguish one element from another in a descriptive sense and are not intended to have a special meaning unless otherwise stated.

Also, if the disclosure above discloses or refers to parts or structures fixedly connected to each other, the fixedly connected may be understood as: a detachable fixed connection (for example using bolts or screws) is also understood as: non-detachable fixed connections (e.g. riveting, welding), but of course, fixed connections to each other may also be replaced by one-piece structures (e.g. manufactured integrally using a casting process) (unless it is obviously impossible to use an integral forming process).

In addition, terms used in any technical aspects of the present disclosure to represent positional relationships or shapes include, unless otherwise stated, states or shapes that are similar, analogous or approximate thereto. Any of the components provided by the present disclosure may be either assembled from separate components or manufactured as a single component by an integral molding process.

If the terms "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the description of the present disclosure, the above-described terms are intended to be based on the orientations and positional relationships shown in the drawings, and are used only for convenience in describing and simplifying the disclosure, and do not indicate or imply that the referenced device, mechanism, component, or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be taken as limiting the scope of the present disclosure.

Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present disclosure and not for limiting the same; although the present disclosure has been described in detail with reference to preferred embodiments, those of ordinary skill in the art will understand that: modifications to the specific embodiments of the disclosure or equivalent substitutions for parts of the technical features may still be made; all such modifications are intended to be included within the scope of the claims of this disclosure without departing from the spirit thereof.