A lightweight aircraft engine blade

Abstract

This utility model relates to the field of engine blade technology, and more particularly to a lightweight aircraft engine blade, comprising a blade body, a hollow cavity formed therein, and a support member fitted into the hollow cavity. The support member is connected to the blade body and includes an upper support strip, a lower support strip, multiple first reinforcing ribs, and multiple second reinforcing ribs. The upper and lower support strips are connected, and a hollow cavity is formed between them. The first and second reinforcing ribs are alternately arranged in the hollow cavity. The upper ends of the first and second reinforcing ribs are connected to the upper support strip, and the lower ends of the first and second reinforcing ribs are connected to the lower support strip. Two adjacent first reinforcing ribs are parallel to each other, and two adjacent second reinforcing ribs are parallel to each other. The blade body is made of carbon fiber reinforced resin matrix composite material or ceramic matrix composite material, and the support member is made of nickel-based high-temperature alloy or cobalt-based high-temperature alloy. The above structural design reduces the weight of the support member while ensuring the strength of the blade, thus achieving lightweighting of the blade.

Description

Technical Field

[0001] This utility model relates to the field of engine blade technology, and in particular to a lightweight aircraft engine blade. Background Technology

[0002] Previously, aero-engine blades mostly used solid nickel-based alloy structures, which not only increased the overall weight of the engine but also led to significant material waste. With technological advancements, the performance requirements for aero-engines have become increasingly demanding. To reduce engine weight, traditional aero-engine blades have achieved lightweighting through purely hollow designs or the replacement of blades with single composite materials. However, purely hollow designs or single composite materials struggle to maintain structural strength. Therefore, it is necessary to improve existing technologies to address these issues. Utility Model Content

[0003] The purpose of this invention is to provide a lightweight aircraft engine blade, which aims to solve the problem that traditional aero-engine blades, which use a purely hollow design or a single composite material, are difficult to maintain structural strength.

[0004] To achieve the above objectives, this utility model provides a lightweight aircraft engine blade, including a blade body, a hollow cavity and a support member that fits into the hollow cavity, the support member being disposed in the hollow cavity and connected to the blade body, the support member including an upper support bar, a lower support bar, multiple first reinforcing ribs and multiple second reinforcing ribs, the upper support bar being connected to the lower support bar and forming a hollow cavity between the upper and lower support bars, the first reinforcing ribs and second reinforcing ribs being alternately disposed in the hollow cavity, the upper ends of the first reinforcing ribs and second reinforcing ribs being connected to the upper support bar, the lower ends of the first reinforcing ribs and second reinforcing ribs being connected to the lower support bar, two adjacent first reinforcing ribs being parallel to each other, two adjacent second reinforcing ribs being parallel to each other, the blade body being made of carbon fiber reinforced resin matrix composite material or ceramic matrix composite material, and the support member being made of nickel-based high-temperature alloy or cobalt-based high-temperature alloy.

[0005] Furthermore, a triangular hollow structure is formed between the first reinforcing rib and the second reinforcing rib.

[0006] Furthermore, the angle formed between the first reinforcing rib and the second reinforcing rib is 50° to 70°.

[0007] Furthermore, the angle formed between the first reinforcing rib and the second reinforcing rib is 60°.

[0008] Furthermore, the leading edge of the blade is provided with reinforcing strips, which are made of titanium alloy or nickel-based high-temperature alloy.

[0009] Furthermore, the leading edge of the blade is provided with a first longitudinal reinforcing rib, a second longitudinal reinforcing rib, and a third longitudinal reinforcing rib at equal intervals. In cross-section, the first longitudinal reinforcing rib, the second longitudinal reinforcing rib, and the third longitudinal reinforcing rib are all trapezoidal in shape that gradually expands toward the support member.

[0010] Furthermore, the length of the first longitudinal stiffener is greater than the length of the second longitudinal stiffener, and the length of the second longitudinal stiffener is greater than the length of the third longitudinal stiffener.

[0011] Furthermore, the trailing edge of the blade is provided with a wear-resistant coating.

[0012] Furthermore, a transverse reinforcing rib is provided at the rear edge. In cross-section, the transverse reinforcing rib is a trapezoidal shape that gradually expands towards the support member.

[0013] The lightweight aircraft engine blade provided by this utility model, compared with the prior art, can significantly reduce the overall weight of the blade by combining a hollow blade body of composite material with a hollow support component of high-temperature alloy material. At the same time, the support component, through the layout of the first and second reinforcing ribs, can reduce the material used in the support component while ensuring the strength of the blade, further reducing the weight of the support component, thereby reducing the overall weight of the blade and realizing the lightweighting of the blade. Attached Figure Description

[0014] Figure 1 This is a cross-sectional view of the present invention;

[0015] Figure 2 yes Figure 1 A magnified structural diagram of part A in the middle.

[0016] Explanation of reference numerals in the attached figures:

[0017] 1. Blade; 11. Leading edge; 111. First longitudinal reinforcing rib; 112. Second longitudinal reinforcing rib; 113. Third longitudinal reinforcing rib; 12. Trailing edge; 121. Wear-resistant coating; 122. Transverse reinforcing rib; 2. Support component; 21. Upper support bar; 22. Lower support bar; 23. First reinforcing rib; 24. Second reinforcing rib; 25. Hollow cavity; 3. Reinforcing strip. Detailed Implementation

[0018] The present invention will be described in detail below with reference to specific embodiments.

[0019] In this utility model, unless otherwise explicitly specified and limited, when terms such as "set in," "connected," or "linked" appear, these terms should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or a connection through one or more intermediate media. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances. The directional terms appearing in this utility model are for the purpose of better describing the characteristics of the features and the relationships between them. It should be understood that when the placement direction of this utility model changes, the direction of the characteristics of the features and the relationships between them also changes accordingly. Therefore, directional terms do not constitute an absolute limitation on the characteristics of the features and the relationships between them in space, but only a relative limitation.

[0020] This invention provides a lightweight aircraft engine blade, such as... Figures 1 to 2 As shown, it includes a blade body 1, which has a hollow cavity and a support member 2 that fits into the hollow cavity. The support member 2 is disposed in the hollow cavity and connected to the blade body 1. The support member 2 includes an upper support bar 21, a lower support bar 22, multiple first reinforcing ribs 23 and multiple second reinforcing ribs 24. The upper support bar 21 is connected to the lower support bar 22, and a hollow cavity 25 is formed between the upper support bar 21 and the lower support bar 22. The first reinforcing ribs 23 and the second reinforcing ribs 24 are alternately disposed in the hollow cavity 25. The upper ends of the first reinforcing ribs 23 and the second reinforcing ribs 24 are connected to the upper support bar 21, and the lower ends of the first reinforcing ribs 23 and the second reinforcing ribs 24 are connected to the lower support bar 22. Two adjacent first reinforcing ribs 23 are parallel to each other, and two adjacent second reinforcing ribs 24 are parallel to each other. The blade body 1 is made of carbon fiber reinforced resin matrix composite material or ceramic matrix composite material, and the support member 2 is made of nickel-based high-temperature alloy or cobalt-based high-temperature alloy.

[0021] Based on the above structural design, the combination of the hollow blade 1 made of composite material and the hollow support 2 made of high-temperature alloy material can significantly reduce the overall weight of the blade. At the same time, the support 2, through the arrangement of the first reinforcing rib 23 and the second reinforcing rib 24, can reduce the material used in the support 2 while ensuring the strength of the blade, further reducing the weight of the support 2, thereby reducing the overall weight of the blade and achieving lightweighting of the blade.

[0022] In this embodiment, a triangular hollow structure is formed between the first reinforcing rib 23 and the second reinforcing rib 24. The triangular hollow structure has good mechanical properties, can effectively disperse and transfer stress, and improve the load-bearing capacity of the support member 2.

[0023] In this embodiment, the angle between the first reinforcing rib 23 and the second reinforcing rib 24 is 50° to 70°. Within this angle range, the triangular hollow structure has high rigidity and can effectively resist bending and shear deformation. More preferably, the angle between the first reinforcing rib 23 and the second reinforcing rib 24 is 60°, at which point the triangular hollow structure has the strongest supporting force.

[0024] In this embodiment, a reinforcing strip 3 is provided on the leading edge 11 of the blade 1. The reinforcing strip 3 is made of titanium alloy or nickel-based high-temperature alloy. The reinforcing strip 3 improves the impact resistance of the leading edge 11 of the blade and ensures the durability of the blade.

[0025] In this embodiment, the leading edge 11 of the blade 1 is provided with a first longitudinal reinforcing rib 111, a second longitudinal reinforcing rib 112 and a third longitudinal reinforcing rib 113 at equal intervals. In cross-section, the first longitudinal reinforcing rib 111, the second longitudinal reinforcing rib 112 and the third longitudinal reinforcing rib 113 are all trapezoidal in shape that gradually expands toward the support member 2.

[0026] In this embodiment, the length of the first longitudinal reinforcing rib 111 is greater than the length of the second longitudinal reinforcing rib 112, and the length of the second longitudinal reinforcing rib 112 is greater than the length of the third longitudinal reinforcing rib 113.

[0027] Through the above structural design, the first longitudinal stiffener 111, the second longitudinal stiffener 112 and the third longitudinal stiffener 113 can significantly enhance the strength and impact resistance of the leading edge 11 and extend the service life of the blade.

[0028] In this embodiment, the trailing edge 12 of the blade 1 is provided with a wear-resistant coating 121. The wear-resistant coating 121 can prevent the trailing edge 12 of the blade 1 from deforming due to wear, thereby improving the wear resistance of the blade and extending its service life.

[0029] In this embodiment, the trailing edge 12 is also provided with a transverse reinforcing rib 122. In cross-section, the transverse reinforcing rib 122 is a trapezoidal shape that gradually expands towards the support member 2. The transverse reinforcing rib 122 can improve the structural stability of the trailing edge 12 and reduce the generation of vibration and fatigue cracks.

[0030] In summary, this lightweight aircraft engine blade can solve the problem that traditional aero-engine blades, which use purely hollow designs or single composite materials, are difficult to maintain structural strength.

[0031] Where there is no conflict, the above embodiments and features can be combined with each other.

[0032] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit the scope of protection of this utility model. Although this utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of this utility model without departing from the essence and scope of the technical solutions of this utility model.

Claims

1. A lightweight aircraft engine blade, characterized in that: The blade (1) includes a blade body (1), which has a hollow cavity and a support member (2) that fits into the hollow cavity. The support member (2) is located in the hollow cavity and connected to the blade body (1). The support member (2) includes an upper support bar (21), a lower support bar (22), multiple first reinforcing ribs (23), and multiple second reinforcing ribs (24). The upper support bar (21) is connected to the lower support bar (22), and a hollow cavity (25) is formed between the upper support bar (21) and the lower support bar (22). The first reinforcing ribs (23) and the second reinforcing ribs (24) 24) Alternately arranged in the hollow cavity (25), the upper ends of the first reinforcing rib (23) and the second reinforcing rib (24) are connected to the upper support strip (21), and the lower ends of the first reinforcing rib (23) and the second reinforcing rib (24) are connected to the lower support strip (22). Two adjacent first reinforcing ribs (23) are parallel to each other, and two adjacent second reinforcing ribs (24) are parallel to each other. The blade (1) is made of carbon fiber reinforced resin matrix composite material or ceramic matrix composite material, and the support (2) is made of nickel-based high temperature alloy or cobalt-based high temperature alloy.

2. The lightweight aircraft engine blade according to claim 1, characterized in that: A triangular hollow structure is formed between the first reinforcing rib (23) and the second reinforcing rib (24).

3. The lightweight aircraft engine blade according to claim 1, characterized in that: The angle between the first reinforcing rib (23) and the second reinforcing rib (24) is 50° to 70°.

4. The lightweight aircraft engine blade according to claim 3, characterized in that: The angle between the first reinforcing rib (23) and the second reinforcing rib (24) is 60°.

5. The lightweight aircraft engine blade according to claim 1, characterized in that: The leading edge (11) of the blade (1) is provided with a reinforcing strip (3), which is made of titanium alloy or nickel-based high-temperature alloy.

6. The lightweight aircraft engine blade according to claim 5, characterized in that: The leading edge (11) of the blade (1) is provided with a first longitudinal reinforcing rib (111), a second longitudinal reinforcing rib (112) and a third longitudinal reinforcing rib (113) at equal intervals. In the cross section, the first longitudinal reinforcing rib (111), the second longitudinal reinforcing rib (112) and the third longitudinal reinforcing rib (113) are all trapezoidal shapes that gradually expand towards the support member (2).

7. The lightweight aircraft engine blade according to claim 6, characterized in that: The length of the first longitudinal stiffener (111) is greater than the length of the second longitudinal stiffener (112), and the length of the second longitudinal stiffener (112) is greater than the length of the third longitudinal stiffener (113).

8. The lightweight aircraft engine blade according to claim 1, characterized in that: The trailing edge (12) of the blade (1) is provided with a wear-resistant coating (121).

9. The lightweight aircraft engine blade according to claim 8, characterized in that: The rear edge (12) is also provided with a transverse reinforcing rib (122). In cross-section, the transverse reinforcing rib (122) is a trapezoidal shape that gradually expands towards the support member (2).

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