CN215949936U

CN215949936U - Blade

Info

Publication number: CN215949936U
Application number: CN202121268706.8U
Authority: CN
Inventors: 王少辉; 石英; 刘传欣; 倪晓琴; 曹源; 史同承
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-06-07
Filing date: 2021-06-07
Publication date: 2022-03-04
Anticipated expiration: 2031-06-07

Abstract

The utility model provides a blade, which comprises a composite material body and a first metal body which are connected along the chord direction, wherein the first metal body constructs a front edge part of the blade, and the front edge part comprises a blade front edge, a partial pressure surface and a partial suction surface; the composite material body constructs a tail edge part of the blade, the tail edge part comprises a tail edge of the blade, the pressure surface of the rest part and the suction surface of the rest part, and one end of the first metal body close to the composite material body is inserted into the composite material body; the blade further comprises a second metal body, the second metal body is embedded in the composite material body, and the second metal body and the first metal body are arranged at intervals. According to the utility model, the second metal body arranged at a distance from the first metal body is embedded in the composite material body, so that the rigidity and the shock resistance of the composite material body can be increased, the integral rigidity and the shock resistance of the blade are improved, and the design requirement of the blade on bird impact resistance is met.

Description

Blade

Technical Field

The present invention relates to a blade.

Background

At present, the large-bypass-ratio turbofan engine has the characteristics of low oil consumption, large takeoff thrust, low noise, large windward area and the like, so that the large-bypass-ratio turbofan engine is widely used by civil transport planes. Large-size and light-weight fan blades have been one of the key technologies of turbofan engines with large bypass ratios.

The composite material has the characteristics of small density, high strength and the like, the light metal represented by titanium alloy also has the characteristic of high specific strength, and the composite material and the titanium alloy are combined together to form the fan blade, so that the fan blade has the characteristics of good weight reduction effect and high strength, and can meet the requirement of bird impact resistance. The lightweight fan blade becomes the mainstream proposal for developing the lightweight fan blade with large bypass ratio by each large engine company.

Currently, lightweight fan blades include both composite material fan blades and hybrid construction fan blades.

The composite material fan blade mainly adopts a titanium alloy coated composite material form to form the blade, so that the formed composite material fan blade can meet the requirements of strength and bird impact performance, and has the advantage of small weight of the whole blade. At present, the metal wrapping of the composite material fan blade is limited by the traditional processing technology, only a few suppliers have the capability of processing the metal reinforcing edge internationally, and the technical threshold and the manufacturing cost of the composite material-titanium alloy wrapping fan blade are always high.

Hybrid construction fan blades have similar advantages to composite fan blades, with the entire fan blade being of low weight. The composite core plate has the capability of resisting bird impact, meanwhile, the processing technology of the metal core plate (generally titanium alloy) in the mixed structure is simpler, the 3D printing technology can also be adopted, and the metal core plate can have larger design space.

Specifically, the fan blade with the mixed structure is composed of a composite material (generally a carbon fiber composite material) and a metal (generally a titanium alloy), an arrow-shaped metal core plate is inserted into the composite material, the arrow part of the metal core plate serves as the front edge of the blade, the rigidity is high, the strength is high, the blade is used for resisting bird impact, and the metal core plate and the composite material are connected together by gluing or sewing the part of the metal core plate inserted into the composite material to form the whole fan blade. The metal core plate inserted into the composite material may extend to the middle of the chord direction of the blade or to the trailing edge of the blade. If the titanium core extends to the trailing edge of the blade, the titanium-metal-titanium mixed alloy in the whole blade occupies a larger volume ratio of the whole fan blade, and the whole mass of the fan blade is increased. If the core extends to a position in the middle of the chord direction, the tail edge of the blade is weak in rigidity, and the blade deforms too much under the impact load of bird strike, so that the tail edge can crack or break.

SUMMERY OF THE UTILITY MODEL

The utility model aims to overcome the defects that the tail edge of the blade in the prior art is weak in rigidity and excessively deforms under the impact load of bird strike, so that the tail edge is cracked or damaged, and provides the blade.

The utility model solves the technical problems through the following technical scheme:

the utility model provides a blade, which is characterized by comprising a composite material body and a first metal body which are connected in the chord direction, wherein the first metal body forms a front edge part of the blade, and the front edge part comprises a blade front edge, a partial pressure surface and a partial suction surface; the composite material body constructs a tail edge part of the blade, the tail edge part comprises a tail edge of the blade, the pressure surface of the rest part and the suction surface of the rest part, and one end of the first metal body close to the composite material body is inserted into the composite material body;

the blade further comprises a second metal body, the second metal body is embedded in the composite material body, and the second metal body and the first metal body are arranged at intervals.

In the technical scheme, the second metal body arranged at a distance from the first metal body is embedded in the composite material body, so that the rigidity and the shock resistance of the composite material body can be improved, the integral rigidity and the shock resistance of the blade are improved, and the design requirement of the blade on bird impact resistance is met; meanwhile, the second metal bodies are inserted into different parts of the blade, so that the rigidity and the mode of the blade can be adjusted.

Preferably, the first metal body comprises a main body and an extension connected, the extension being inserted into the composite body;

the dimension of the composite body in the chordwise direction is greater than or equal to twice the dimension of the body in the chordwise direction;

the extension has a dimension in the chordwise direction that is less than or equal to half the dimension of the composite body in the chordwise direction.

In the technical scheme, the weight of the whole blade is reduced as much as possible by setting the specific size of the first metal body.

Preferably, the second metal body is a sheet structure.

In the technical scheme, the second metal body is of a sheet structure, so that the weight of the whole blade is reduced while the rigidity and the shock resistance of the composite material body are improved.

Preferably, the second metal body comprises a first sub-metal body, the outer periphery of the first sub-metal body and the outer periphery of the composite material body at least partially coincide; and/or the presence of a gas in the gas,

the second metal body includes a second sub-metal body having an outer peripheral edge spaced apart from an outer peripheral edge of the composite material body.

In the technical scheme, the rigidity and the shock resistance of the outer periphery of the composite material body are improved by arranging the first sub-metal body; the rigidity and the impact resistance of the middle position of the composite material body are improved by arranging the second sub-metal body.

Preferably, the first sub-metal body comprises a first part and a second part, the first part is arranged along the span direction of the blade, and the outer periphery of one side of the first part is coincided with the outer periphery of the tail edge of the blade;

the second portion is arranged along the chord direction of the blade, and the outer periphery of one side of the second portion is coincided with the outer periphery of the blade tip of the blade.

In the technical scheme, the rigidity and the impact resistance of the tail edge position of the blade where the composite material body is located and the rigidity and the impact resistance of the tip position of the blade are improved by arranging the specific structure of the first sub-metal body.

Preferably, one end of the first portion is connected to one end of the second portion;

the joint of the first part and the second part is arranged at a right angle; alternatively, the first and second electrodes may be,

the junction of the first part and the second part is arranged in a round angle mode.

In this technical scheme, through setting up the one end of first part and being connected with the one end of second part to strengthen the intensity of the first sub-metal body itself.

Preferably, the first portion and the second portion are spaced apart.

In the technical scheme, the first part and the second part are arranged at intervals, so that the rigidity and the shock resistance of the composite material body are improved, and meanwhile, the using amount of the first sub-metal body is saved, and the technical effect of reducing the weight of the whole blade is achieved.

Preferably, the first sub-metal body and the second sub-metal body are arranged at an interval.

In the technical scheme, the first sub-metal body and the second sub-metal body are arranged at intervals, so that the rigidity and the impact resistance of the composite material body are improved at different positions of the composite material body.

Preferably, the number of the second sub-metal bodies is one or more, and the plurality of the second sub-metal bodies are arranged at intervals.

In the technical scheme, the rigidity and the impact resistance of the composite material body are improved at different positions of the composite material body by arranging the plurality of second sub-metal bodies at intervals.

Preferably, a plurality of the second sub-metal bodies are arranged at intervals along the chord direction of the blade; or, a plurality of the second sub-metal bodies are arranged at intervals along the spanwise direction of the blade.

In the technical scheme, the rigidity and the impact resistance of the composite material body are improved in different directions by limiting the direction in which the plurality of second sub-metal bodies are arranged at intervals.

The positive progress effects of the utility model are as follows:

according to the blade, the second metal body arranged at a distance from the first metal body is embedded in the composite material body, so that the rigidity and the shock resistance of the composite material body can be improved, the integral rigidity and the shock resistance of the blade are improved, and the design requirement of the blade on bird impact resistance is met; meanwhile, the second metal bodies are inserted into different parts of the blade, so that the rigidity and the mode of the blade can be adjusted.

Drawings

Fig. 1 is a schematic structural view of a blade according to embodiment 1 of the present invention.

Fig. 2 is a schematic sectional view in the direction of a-a in fig. 1.

Fig. 3 is a cross-sectional structural view in the thickness direction of a blade according to an embodiment of example 1 of the present invention.

Fig. 4 is a cross-sectional structural view in the thickness direction of a blade according to another embodiment of example 1 of the present invention.

Fig. 5 is a schematic cross-sectional structure in the thickness direction of a blade according to still another embodiment of example 1 of the present invention.

Fig. 6 is a cross-sectional structural view in the thickness direction of a blade according to an embodiment of example 2 of the present invention.

Fig. 7 is a cross-sectional structural view in the thickness direction of a blade according to another embodiment of example 2 of the present invention.

Fig. 8 is a cross-sectional structural view in the thickness direction of a blade according to still another embodiment of example 2 of the present invention.

Fig. 9 is a schematic cross-sectional structure view in the chord direction of a blade according to still another embodiment of example 2 of the present invention.

Detailed Description

The present invention will be more clearly and completely described in the following description of preferred embodiments, taken in conjunction with the accompanying drawings.

Example 1

As shown in fig. 1-5, the present embodiment provides a blade 100, the structure of which blade 100 may be connected together in some manner by a variety of materials or substructures. The blades 100 are generally mounted on a fan, for example a turbofan, constituting an element of the turbofan engine responsible for compressing air.

The blade 100 includes a composite material body 10 made of a composite material and a first metal body 20 made of a metal material.

The composite material used for the composite material body 10 may be, for example, a fiber-reinforced material with an organic polymer as a matrix, wherein the fiber-reinforced material may include glass fibers, carbon fibers, basalt fibers, aramid fibers, or the like, and the organic polymer as the matrix may be, for example, various resins, such as epoxy resins, unsaturated polyester resins, or the like. The resin-based composite material can effectively reduce the weight of the blade and improve the hollow rate, and the specific components and the fiber direction of the resin-based composite material can improve the mechanical property of the blade through design, so that the blade has considerable strength and can bear the impact force possibly applied to part of the blade, and the manufacturing cost can be reduced through design. Resin-based composite materials refer to fibrous reinforcement materials based on organic polymers. The metal material used for the first metal body 20 may be titanium alloy, other metals or alloys.

In fig. 1, in order to make the structure clearer, the hatched area indicates the composite material body 10, and the white area indicates the first metal body 20. Referring to fig. 2, the blade leading edge 1 is a point having the maximum curvature at the front of the blade 100, and a front portion including the blade leading edge 1 may be referred to as a leading edge portion. Similarly defined, the blade trailing edge 2 is the point of maximum curvature at the trailing portion of the blade 100, and the trailing side portion including the blade trailing edge 2 may be referred to as the trailing edge portion. A chord line C1 is a straight line connecting the blade leading edge 1 and the blade trailing edge 2, and the chord direction D1 is also in the direction of chord line C1. That is, the chord direction D1 of the blade 100 is generally parallel to the left-right direction in fig. 1 to 5, which is the direction of the connecting line from the blade leading edge 1 to the blade trailing edge 2.

The thickness direction or thickness direction D2 of blade 100 may be defined as a direction perpendicular to chord direction D1. That is, the thickness direction D2 of the blade 100 is substantially parallel to the up-down direction in fig. 2.

The span direction D3 of the blade 100 is generally parallel to the up-down direction in fig. 1, or the direction from the root 3 to the tip 4.

Further, in the airfoil shape shown in FIG. 2, the lower surface of the blade 100 may be referred to as the pressure surface 5; and the upper surface of the blade 100 may be referred to as the suction surface 6.

The first metal body 20 constitutes the leading edge portion of the blade. The leading edge portion comprises the blade leading edge 1, part of the pressure surface 51 and part of the suction surface 61. The front edge part is made of metal materials, and has strong impact resistance to foreign objects, so that the impact load on the composite material part can be reduced. The composite body 10 configures the trailing edge portion of the blade including the trailing edge 2 of the blade, the remaining pressure surface 52 and the remaining suction surface 62, and an end of the first metal body 20 adjacent the composite body 10 is inserted into the composite body 10. That is, the surface of the first metal body 20 on the pressure surface 5 is continuous with the surface of the composite material body 10 on the pressure surface 5 to form the pressure surface 5 of the blade; likewise, the surface of the first metal body 20 on the suction side 6 is continuous with the surface of the composite body 10 on the suction side 6, forming the pressure side 5 of the blade.

The first metal body 20 comprises a main body 21 and an extension 22 connected, the extension 22 being inserted into the composite body 10; the dimension of the composite body 10 in the chordwise direction D1 is greater than or equal to twice the dimension of the body 21 in the chordwise direction D1; the extension 22 has a dimension in the chordwise direction D1 that is less than or equal to half the dimension of the composite body 10 in the chordwise direction D1. Thus, by providing the first metal body 20 with specific dimensions, the weight of the entire blade 100 is minimized.

The blade 100 further comprises a second metal body 30, the second metal body 30 is embedded in the composite material body 10, and the second metal body 30 and the first metal body 20 are arranged at intervals. In this way, the second metal body 30 arranged at a distance from the first metal body 20 is embedded in the composite material body 10, so that the rigidity and the shock resistance of the composite material body 10 can be increased, the integral rigidity and the shock resistance of the blade 100 are improved, and the bird impact resistance design requirement of the fan blade 100 is met; while inserting the second metal body 30 at different portions of the blade 100 may be used to adjust the stiffness and mode shape of the blade 100. That is, by adding the second metal body 30 inside the position of the blade 100 to be adjusted, the rigidity and the shock resistance are enhanced at the local position of the blade 100 without increasing the weight of the blade 100, so as to keep the blade 100 from being damaged under the bird strike load, meet the bird strike resistance design requirement of the blade 100, and change and adjust the rigidity, the resonance frequency and the vibration mode of the blade 100 by the arrangement.

The metal material of the second metal body 30 may be titanium alloy, other metals or alloys. The material of the second metal body 30 may be the same as or different from that of the first metal body 20.

The second metal body 30 located within the composite body 10 may be machined by 3D printing, machining, stamping or forging forming, etc.

In the present embodiment, the second metal body 30 has a sheet structure. In this way, by providing the second metal body 30 as a sheet-like structure, the weight of the entire blade 100 is reduced while the rigidity and impact resistance of the composite material body 10 are improved. The second metal body 30 is located in a plane substantially perpendicular to the thickness direction D2 of the blade 100 to maximize the impact resistance on the pressure side 5 and the suction side 6 of the blade 100.

The second metal body 30 comprises a first sub-metal body 31, the outer periphery of the first sub-metal body 31 at least partially coinciding with the outer periphery of the composite body 10. In this way, the rigidity and the impact resistance of the outer peripheral edge of the composite material body 10 are improved by providing the first sub-metal body 31.

Preferably, the first sub-metal body 31 includes a first portion 311 and a second portion 312, the first portion 311 is disposed along the span direction D3 of the blade 100, and the outer periphery of one side of the first portion 311 coincides with the outer periphery of the trailing edge (blade trailing edge 2) of the blade 100; the second portion 312 is disposed along the chord direction D1 of the blade 100, and the outer periphery of the second portion 312 side coincides with the outer periphery of the tip 4 of the blade 100. In this way, the specific structure of the first sub-metal body 31 is provided to improve the rigidity and impact resistance of the composite material body 10 at the position of the trailing edge of the blade 100, and the rigidity and impact resistance at the position of the blade tip 4 of the blade 100. Under the impact load of bird strike, the blade tip 4 and the tail edge of the blade 100 are weak positions due to small thickness, and the first sub-metal body 31 is embedded in the positions, so that the rigidity of the blade 100 can be increased, the deformation of the blade 100 can be reduced, and the damage to the blade 100 can be reduced. Meanwhile, the first sub-metal body 31 can generate large plastic deformation and large damage strain, so that even if the composite material of the blade 100 is damaged, the first sub-metal body 31 cannot be damaged, and the whole blade 100 cannot fall off. The width, length, thickness and shape of the first sub-metal body 31 can be changed, the first sub-metal body 31 can be arranged at the middle position along the thickness direction of the blade 100, and can also be biased to the pressure surface 5 or the suction surface 6, under the impact load, the sheet can generate larger plastic deformation, and the first sub-metal body 31 can absorb more energy. The first sub-metal body 31 inserted into the composite material body 10 and the composite material body 10 may be connected by sewing, gluing, or the like. If the first sub-metal body 31 and the composite material body 10 are connected by means of sewing, the first sub-metal body 31 needs to be perforated.

As shown in fig. 3, in one embodiment of the present embodiment, one end of the first portion 311 is connected to one end of the second portion 312. The junction of the first portion 311 and the second portion 312 is arranged at a right angle. In this way, by providing that one end of the first portion 311 is connected to one end of the second portion 312, the strength of the first sub-metal body 31 itself is reinforced.

But not limited thereto, as shown in fig. 4, in another embodiment of the present embodiment, a joint between the first portion 311 and the second portion 312 may also be a rounded corner. In this way, the joint of the first portion 311 and the second portion 312 is formed in a circular arc shape to increase the entire area of the first sub-metal body 31, thereby enhancing the strength and impact resistance of the blade 100.

In yet another embodiment of the present embodiment, as shown in fig. 5, the first portion 311 is spaced apart from the second portion 312. In this way, by providing the first portion 311 spaced apart from the second portion 312, the amount of the first sub-metal body 31 is saved while the rigidity and the impact resistance of the composite material body 10 are improved, thereby achieving a technical effect of reducing the weight of the entire blade 100.

Example 2

As shown in fig. 6 to 9, the overall structure of the vane of the present embodiment is substantially the same as that of embodiment 1, except that the second metal body does not include the first sub-metal body 31 but includes the second sub-metal body 32, and the outer peripheral edge of the second sub-metal body 32 has a distance from the outer peripheral edge of the composite material body 10. In this way, the rigidity and the impact resistance of the composite material body 10 at the intermediate position are improved by providing the second sub-metal body 32.

The number of the second sub-metal bodies 32 may be one or plural. Preferably, the second sub-metal bodies 32 are plural, and the plural second sub-metal bodies 32 are disposed at intervals. In this way, the rigidity and the impact resistance of the composite material body 10 are improved at different positions of the composite material body 10 by the spaced arrangement of the plurality of second sub-metal bodies 32. In the present embodiment, the number of the second sub-metal bodies 32 is five, but is not limited thereto, and in other embodiments, the number of the second sub-metal bodies 32 may also be two, three, four, six, and other values.

As shown in fig. 6, in one embodiment of the present embodiment, five second sub-metal bodies 32 are arranged at intervals along the chord direction D1 of the blade 100.

In another embodiment of the present embodiment, as shown in fig. 7, five second sub-metal bodies 32 are arranged at intervals along the span direction D3 of the blade 100.

But not limited to the above two embodiments, as shown in fig. 8, in another embodiment of the present embodiment, five second sub-metal bodies 32 are spaced in different directions forming an included angle therebetween.

In this way, by defining the direction in which the plurality of second sub-metal bodies 32 are arranged at intervals, the rigidity and the impact resistance of the composite material body 10 are improved in different directions.

In a further embodiment of this embodiment, as shown in fig. 9, the second sub-metal body 32 has two or more pieces in the thickness direction D2, one of which is biased toward the pressure surface 5 of the blade 100 and the other of which is biased toward the suction surface 6 of the blade 100, so as to further improve the rigidity and impact resistance of the composite material body 10 at the thickness position.

The number, shape, thickness, width, and length of the second sub-metal bodies 32 in the above embodiment may be different, and the arrangement and the spacing of the second sub-metal bodies 32 may be adjusted according to the design requirements of the blade 100. Through the change of the geometric dimension and the arrangement mode, the second sub-metal body 32 can be positioned at the key position of the blade 100 and the position needing to be adjusted, the strength of the blade 100 is increased, the rigidity of the blade 100 is adjusted, and meanwhile, the resonance frequency and the mode shape of the blade 100 can be changed.

It is noted that, in other embodiments, the second metal body 30 may include both the first sub-metal body 31 and the second sub-metal body 32, i.e., both the first sub-metal body 31 and the second sub-metal body 32 are provided in the composite material body 10. The first sub-metal body 31 and the second sub-metal body 32 are disposed at an interval. In this way, by providing the first sub-metal body 31 and the second sub-metal body 32 at the same time, the rigidity and the impact resistance of the composite material body 10 are improved at different positions of the composite material body 10. The first sub-metal body 31 and the second sub-metal body 32 are arranged at intervals to improve the rigidity and the impact resistance of the composite material body 10 at different positions of the composite material body 10.

The present invention is not intended to be limited to the particular embodiments shown and described, but is to be accorded the widest scope consistent with the principles and novel features herein disclosed.

Claims

1. A blade, characterized in that the blade comprises in chord direction a composite body and a first metal body connected, the first metal body constituting a leading edge portion of the blade, the leading edge portion comprising a blade leading edge, a part of a pressure surface and a part of a suction surface; the composite material body constructs a tail edge part of the blade, the tail edge part comprises a tail edge of the blade, the pressure surface of the rest part and the suction surface of the rest part, and one end of the first metal body close to the composite material body is inserted into the composite material body;

2. The blade of claim 1 wherein said first metal body comprises a joined main body and extension, said extension being inserted into said composite body;

3. The blade of claim 1 wherein said second metal body is a sheet-like structure.

4. The blade according to claim 1, wherein the second metal body comprises a first sub-metal body having an outer circumference at least partially coinciding with an outer circumference of the composite body; and/or the presence of a gas in the gas,

5. The blade according to claim 4, wherein the first sub-metallic body comprises a first portion and a second portion, the first portion being disposed in a span-wise direction of the blade, an outer periphery of a side of the first portion coinciding with an outer periphery of a trailing edge of the blade;

6. The blade of claim 5, wherein one end of said first portion is connected to one end of said second portion;

7. The blade of claim 5 wherein said first portion is spaced from said second portion.

8. The blade of claim 5, wherein the first sub-metallic body is spaced apart from the second sub-metallic body.

9. The blade according to claim 5, wherein the second sub-metal bodies are one or more, and a plurality of the second sub-metal bodies are arranged at intervals.

10. The blade according to claim 9, wherein a plurality of said second sub-metallic bodies are arranged at intervals in a chord direction of said blade; or, a plurality of the second sub-metal bodies are arranged at intervals along the spanwise direction of the blade.