CN216009013U - Fan blade and turbofan engine - Google Patents
Fan blade and turbofan engine Download PDFInfo
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- CN216009013U CN216009013U CN202120293485.3U CN202120293485U CN216009013U CN 216009013 U CN216009013 U CN 216009013U CN 202120293485 U CN202120293485 U CN 202120293485U CN 216009013 U CN216009013 U CN 216009013U
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Abstract
The utility model relates to a fan blade and a turbofan engine, which are used for relieving the problem that the blade is easy to damage due to collision. The fan blade comprises a fan blade body, at least part of the outer surface of the fan blade body is provided with a coating, and the coating is made of an elastic explosion-proof material. The coating made of the elastic explosion-proof material has high strength and flexibility, and the body structure inside the coating is effectively protected when the coating is impacted by bird impact, so that the body of the fan blade is not damaged, the local material is prevented from being damaged and falling off, and the integrity of the blade is kept.
Description
Technical Field
The utility model relates to the field of aerospace equipment, in particular to a fan blade and a turbofan engine.
Background
The large bypass ratio turbofan engine has the characteristics of low oil consumption, large takeoff thrust, low noise, large windward area and the like. Large-size and light-weight fan blades are one of the key technologies of a turbofan engine with a large bypass ratio. Lightweight fan blade types include titanium alloy hollow fan blades and composite-titanium alloy covered fan blades. If the weight reduction effect of the light fan blade is measured by the equivalent hollow rate (the weight reduced by the actual blade/the weight of the solid titanium alloy blade with the same size), the hollow rate of the titanium alloy hollow fan blade can reach 40%, and the equivalent hollow rate of the composite material-titanium alloy edge-covered fan blade can reach more than 60%, so that the weight reduction effect is very considerable.
The bird impact load is a load which must be considered when the fan blade is designed, in order to improve the impact load resistance of the blade and prevent the fan blade from being damaged and falling off when being impacted by a bird body, the composite material blade adopts a titanium alloy edge-covering structure to enhance the impact resistance of the blade, the titanium alloy edge-covering is fixed on the composite material blade body through gluing, the preparation difficulty is high, the cost is high, the mechanical property requirement of a connection interface is high when the metal and the composite material are connected, particularly, the interface is easy to split when the blade is impacted, and the metal and the composite material are separated and fall off.
Disclosure of Invention
Some embodiments of the utility model provide a fan blade and a turbofan engine, which are used for relieving the problem that the blade is easy to damage due to collision.
Some embodiments of the utility model provide a fan blade, which comprises a fan blade body, wherein at least part of the outer surface of the fan blade body is provided with a coating, and the coating is made of an elastic explosion-proof material.
In some embodiments, the elastic blast resistant material comprises a polyurea elastomer.
In some embodiments, the fan blade body is made of a composite or metallic material.
In some embodiments, the fan blade body includes a main body portion and a reinforcement portion, the main body portion is made of a composite material, the reinforcement portion covers an edge of the main body portion, which is vulnerable to impact damage, the reinforcement portion is made of a metal material, and the coating layer is disposed at a connection position of the main body portion and the reinforcement portion.
In some embodiments, the interior of the fan blade body is configured as a hollow structure.
In some embodiments, the interior of the fan blade body is provided with a plurality of baffles that divide the hollow structure into a plurality of cavities.
In some embodiments, the partition plates are arched, and the joint of two adjacent partition plates adopts a fillet transition.
In some embodiments, the cavity is circular, semi-circular, or square in cross-section.
In some embodiments, the coating is provided over the entire outer surface of the fan blade body.
Some embodiments of the present invention provide a turbofan engine comprising the fan blade described above.
Based on the technical scheme, the utility model at least has the following beneficial effects:
in some embodiments, the fan blade comprises a fan blade body, at least part of the outer surface of the fan blade body is provided with a coating, and the coating is made of an elastic explosion-proof material; the coating made of the elastic explosion-proof material has high strength and flexibility, and the body structure inside the coating is effectively protected when the coating is impacted by bird impact, so that the body of the fan blade is not damaged, the local material is prevented from being damaged and falling off, and the integrity of the blade is kept.
Drawings
The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the utility model and together with the description serve to explain the utility model without limiting the utility model. In the drawings:
FIG. 1 is a schematic view of a fan blade body provided in accordance with some embodiments of the utility model;
FIG. 2 is a schematic sectional view A-A of FIG. 1;
FIG. 3 is a schematic view of a fan blade body including a main body portion and a stiffener portion provided in accordance with some embodiments of the present invention;
FIG. 4 is a schematic view of a partially coated fan blade body provided in accordance with some embodiments of the utility model;
FIG. 5 is a schematic view of a fan blade body partially coated according to further embodiments of the present invention;
FIG. 6 is a schematic, partially cross-sectional view of a fan blade body provided in accordance with further embodiments of the utility model;
FIG. 7 is an enlarged, fragmentary illustration of a hollow structure of a fan blade body provided in accordance with further embodiments of the present invention.
The reference numbers in the drawings illustrate the following:
1-a fan blade body; 11-a body portion; 12-a reinforcement;
2-coating; 3-a separator; 4-a cavity; 5-leading edge; 6-pressure surface.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments. It is to be understood that the described embodiments are merely a few embodiments of the utility model, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without any inventive step, are within the scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
After the composite material fan blade is impacted, the problem of interface separation between the composite material and the metal reinforcing part is easy to occur, and in addition, the composite material body is easy to crack and even drop; for fan blades made of other lightweight metal/alloy/metal matrix composite materials, because of the limited strength properties of the materials, cracks and even partial structural detachment can occur when the fan blades are impacted by bird strikes.
Based on the problem that the lightweight fan blade is easily cracked and damaged when being impacted by bird strike, even a part of materials fall off, some embodiments of the disclosure provide a fan blade for relieving the problem that the fan blade is easily cracked and damaged when being impacted.
As shown in fig. 1 and 2, in some embodiments, the fan blade comprises a fan blade body 1, at least part of the outer surface of the fan blade body 1 is provided with a coating 2, and the coating 2 is made of an elastic explosion-proof material.
The coating 2 made of the elastic explosion-proof material has ultrahigh strength and flexibility, and under the action of strong explosion shock waves, the fan blade body 1 protected by the coating 2 made of the elastic explosion-proof material can deform but cannot be damaged and separated, so that the integrity of the blade is always kept.
The elastic explosion-proof material is sprayed on the surface of an object, so that the impact wave and fragments of explosives can be effectively resisted, and the bulletproof and impact-proof effects can be enhanced. The elastic explosion-proof material can be sprayed on the surfaces of various objects such as metal, alloy, composite material and the like. Based on the performance characteristics of the elastic explosion-proof material, the coating 2 is formed by spraying the elastic explosion-proof material on the outer surface of the fan blade body, and due to the high toughness of the coating 2, the coating cannot crack when the fan blade is impacted to deform, so that the internal body material of the fan blade can be effectively protected, and the integrity of the blade is kept.
The coating 2 formed by the elastic explosion-proof material is arranged on the outer surface of the fan blade body 1, so that the fan blade can be further designed in a light weight mode, the weight of the fan blade is reduced, and the processing cost of the fan blade is reduced; and the coating 2 formed by the elastic explosion-proof material can also enhance the performances of wear resistance, corrosion resistance and the like of the fan blade.
In some embodiments, the elastic blast resistant material comprises a polyurea elastomer.
In some embodiments, the fan blade body 1 is made of a composite material. Optionally, the composite material comprises a carbon fiber composite material.
In some embodiments, the fan blade body 1 is made of a metallic material.
The fan blades mentioned in the present embodiment include composite fan blades, hybrid fan blades composed of composite and metal/alloy, or metal/alloy fan blades, and the like. For the composite material fan blade, the light metal/alloy fan blade and other fan blades, the coating 2 is arranged on the outer surface of the fan blade body 1, and the coating 2 can effectively protect the body structure inside the fan blade body when being impacted by bird impact, so that the fan blade body 1 is not damaged, the damage and the falling of local materials are avoided, and the integrity of the fan blade is kept.
In some embodiments, as shown in fig. 3, the fan blade body 1 includes a main body portion 11 and a reinforcing portion 12, the main body portion 11 is made of a composite material, the reinforcing portion 12 covers a portion of the main body portion 11 that is vulnerable to impact, the reinforcing portion 12 is made of a metal material, and the coating layer 2 is disposed at a connection portion of the main body portion 11 and the reinforcing portion 12.
For the fan blade made of composite materials and metal, the coating layer 2 is arranged at the joint of the main body part 11 and the reinforcing part 12, so that the separation of the material connection interface is effectively prevented when the fan blade is impacted by a bird body, the composite materials are damaged and fall off, and the integrity of the fan blade is maintained.
Of course, the coating 2 may be provided separately in other regions of the fan blade body 1.
For example: as shown in fig. 4, the coating layer 2 covers the reinforcing portion 12 therein, and covers the entire circumferential surface of the main body portion 11 where the reinforcing portion 12 is located.
For example: as shown in fig. 5, the coating layer 2 covers most of the reinforcing part 12 between the top and bottom parts, and covers the entire circumferential surface of the main body part 11 corresponding to the position where most of the reinforcing part 12 is located.
In some embodiments, as shown in fig. 2, the coating 2 is provided over the entire outer surface of the fan blade body 1.
Aiming at the problem that the material of the fan blade is easy to break and fall after the bird body is impacted, the coating 2 formed by the elastic explosion-proof material is arranged on the outer surface of the whole fan blade body 1, and the explosion-proof coating has low density and considerable toughness, so that the structure of the fan blade body 1 can be protected under the action of impact force, even if the fan blade body deforms, the fan blade cannot be damaged or cannot fall off due to local material damage, the structural integrity of the fan blade is ensured, meanwhile, the fan blade also absorbs part of impact energy due to deformation, and the impact force borne by the fan blade body is dispersed.
As shown in fig. 4 and 5, for the composite material fan blade with the metal reinforcing sheet, because the strength at the connecting interface of the two materials is insufficient, the reinforcing sheet is easy to fall off during bird collision, so the coating 2 made of the elastic explosion-proof material can be separately arranged at the connecting area of the interface; or selectively spraying the explosion-proof material coating 2 on the areas of the fan blades which are easily damaged by the impact of the bird body.
In some embodiments, the interior of the fan blade body 1 is configured as a hollow structure, which can reduce the weight of the fan blade, and the bond coating 2 can reduce the stress concentration area, avoiding material damage caused by stress concentration.
The coating 2 formed by the elastic explosion-proof material can protect the fan blade from being damaged by impact load, and the abrasion resistance and the corrosion resistance of the blade are enhanced; and because of the protection of the coating 2 formed by the elastic explosion-proof material, the fan blade can further reduce the material consumption, or adopt other lighter metal/composite materials, improve the hollow rate of the fan blade.
In some embodiments, as shown in fig. 6 and 7, the fan blade body 1 is provided with a plurality of baffles 3 inside, the plurality of baffles 3 dividing the hollow structure into a plurality of cavities 4.
In some embodiments, as shown in fig. 7, the partition plates 3 are arched, and the connection between two adjacent partition plates 3 adopts a rounded transition.
Because the domes have considerable stability, can be downwards outwards dispersion load when receiving pressure, the strength that can bear is bigger, consequently, baffle 3 in the hollow structure is the arch, especially at the leading edge 5 and the pressure face 6 (as shown in fig. 6) of the fan blade that directly bears the impact of the bird body, a plurality of domes of rational distribution for bear the impact effect, and because of the dome characteristic compare other have edges and corners or truss/member form single cell structure, stress concentration district is few when the atress, the atress is regional little promptly, be difficult to produce sharp-pointed piece when destroying.
For example: as shown in FIG. 6, a plurality of hollow cavities 4 separated by hollow structures are arranged at the front edges 5 of the fan blades and the pressure surfaces 6 of the fan blades through a plurality of partition plates 3, so that weak stress areas are reduced, and sharp fragments are prevented from being generated when the fan blades are damaged by impact.
As shown in fig. 7, the partition plates 3 are arched, and the joints of two adjacent partition plates 3 are in fillet transition, so that the connecting area between the partition plate structures is increased, the sharp corner area is reduced, and material damage caused by stress concentration is avoided.
In some embodiments, the cross-section of the cavity 4 is circular, semi-circular or square.
The machining process of the fan blade includes, but is not limited to, selective laser melting, extrusion molding, casting, machining and the like.
The hollow scheme and the elastic explosion-proof coating scheme of the fan blade can be used for the fan blade, and can also be used for structures such as a supercharging-stage rotor blade of an aeroengine, an intermediate casing support plate, an OGV (OUTLET GUIDE VANE) and the like, so that foreign matters are prevented from entering the engine to cause impact damage to related parts of the engine, and the weight of the engine is reduced.
Some embodiments provide a turbofan engine comprising the fan blade described above.
Based on the embodiments of the utility model described above, the technical features of one of the embodiments can be advantageously combined with one or more other embodiments without explicit negatives.
In the description of the present invention, it should be understood that the terms "first", "second", "third", etc. are used to define the components, and are used only for the convenience of distinguishing the components, and if not otherwise stated, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present invention.
Finally, it should be noted that the above examples are only used to illustrate the technical solutions of the present invention and not to limit the same; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the utility model or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the utility model as defined by the appended claims.
Claims (8)
1. A fan blade is characterized by comprising a fan blade body (1), wherein at least part of the outer surface of the fan blade body (1) is provided with a coating (2), and the coating (2) is made of an elastic explosion-proof material;
the fan blade body (1) comprises a main body part (11) and a reinforcing part (12), wherein the main body part (11) is made of a composite material, the reinforcing part (12) covers the edge, prone to impact damage, of the main body part (11), the reinforcing part (12) is made of a metal material, and the coating (2) is arranged at the connecting position of the main body part (11) and the reinforcing part (12).
2. A fan blade as claimed in claim 1, characterized in that the fan blade body (1) is made of a composite material or a metallic material.
3. A fan blade as claimed in claim 1, characterized in that the interior of the fan blade body (1) is configured as a hollow structure.
4. A fan blade according to claim 3, characterized in that the fan blade body (1) is provided with a plurality of partitions (3) inside, which partitions (3) divide the hollow structure into a plurality of cavities (4).
5. A fan blade according to claim 4, characterized in that the baffles (3) are arched, and the junction between two adjacent baffles (3) is rounded.
6. A fan blade as claimed in claim 4, characterized in that the cross-section of the cavity (4) is circular, semicircular or square.
7. A fan blade according to claim 1, characterized in that the coating (2) is provided on the entire outer surface of the fan blade body (1).
8. A turbofan engine comprising a fan blade according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120293485.3U CN216009013U (en) | 2021-02-02 | 2021-02-02 | Fan blade and turbofan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120293485.3U CN216009013U (en) | 2021-02-02 | 2021-02-02 | Fan blade and turbofan engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216009013U true CN216009013U (en) | 2022-03-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120293485.3U Active CN216009013U (en) | 2021-02-02 | 2021-02-02 | Fan blade and turbofan engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216009013U (en) |
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2021
- 2021-02-02 CN CN202120293485.3U patent/CN216009013U/en active Active
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