Nacelles and aircraft engines

Abstract

This invention discloses a nacelle and an aero-engine. The lip is formed from a composite laminate, which includes fiberglass layers and aluminum alloy layers, which are alternately laid and cured to form the lip. By using a composite laminate to make the lip, and setting the composite laminate to include fiberglass and aluminum alloy layers, which are alternately laid and cured, the lip made of the composite laminate has high structural rigidity and can effectively resist bird strikes. Even if a foreign object penetrates through one layer of fiberglass or aluminum alloy, the other layers of fiberglass or aluminum alloy underneath can effectively block the foreign object, preventing it from entering the fan nacelle. The manufacturing process of the lip made of composite laminate is simple, does not require milling of internal surfaces, and improves the utilization rate of raw materials.

Description

Technical Field

[0001] This invention relates to the field of aircraft engines, and particularly to a nacelle and an aircraft engine. Background Technology

[0002] Aircraft engines are crucial components of aircraft. Turbofan engines are a common type of aircraft engine. For example... Figure 1 As shown in the figure, the nacelle of a mainstream high-bypass turbofan engine is illustrated. The nacelle typically includes an air intake 101, a fan shroud 102, thrust reversers 103, and nozzles 104. The air intake 101 primarily serves to ensure the quality of airflow into the engine's flow path; its internal flow path design is a major factor affecting the engine's aerodynamic performance and structural weight, while its external profile design is a crucial component influencing the overall engine drag performance.

[0003] The nacelle typically needs to meet the requirements for bird strike resistance. Under the impact of a foreign object with a certain speed, mass and volume, the structure of the air intake 101 should have sufficient structural rigidity to ensure that the foreign object does not pass through the rear bulkhead 202, thereby preventing the foreign object from entering the fan compartment.

[0004] like Figure 2 As shown in the figure, a conventional air intake 101 is illustrated. The conventional air intake 101 structure mainly includes a metal lip 205, a front bulkhead 201, a rear bulkhead 202, and an inner wall panel 206. The air intake 101 is connected to the fan casing 105 via a docking ring 204 and is mounted on the aircraft engine body. The conventional air intake 101 configuration typically includes two cylindrical structures, inner and outer, with a U-shaped ring structure formed at the front end by the metal lip 205 and the inner and outer skins. Considering structural rigidity and deformation, resistance to foreign object impacts, hot gas de-icing function, and fan compartment fire protection requirements, the front bulkhead 201 and rear bulkhead 202 can also be arranged within the U-shaped ring structure. The front bulkhead 201 and rear bulkhead 202 provide structural support for the inner and outer cylinders, constituting the air intake 101 structure.

[0005] like Figure 3 As shown in the figure, a cross-sectional schematic diagram of a typical metal lip 205 is displayed. The metal lip 205 is a structural component at the leading edge of an aero-engine. The shape and profile of the metal lip 205 have a significant impact on the aero-engine's aerodynamic performance. As the first line of defense against bird strikes, the metal lip 205 also requires corresponding reinforcement.

[0006] Currently, the metal lip 205 of the mainstream air intake duct 101 is typically formed from aluminum alloy or titanium alloy sheet metal. The forming process for aluminum alloy metal lips 205 is mainly liquid-filled deep drawing, while the forming process for titanium alloy metal lips 205 is mainly hot forming. Metal lips 205 formed from aluminum alloy or titanium alloy sheet metal have poor impact resistance. The metal lip 205 usually also requires local structural thickening in the connection area 94 to increase connection strength. Furthermore, metal lips 205 made of metal materials usually require machining or milling of internal surfaces after forming. This manufacturing method for metal lips 205 is technically challenging, difficult to control dimensions, prone to part deformation, and has a very low utilization rate of raw materials. Summary of the Invention

[0007] The technical problem to be solved by the present invention is to overcome the above-mentioned defects of low raw material utilization caused by the need to mill the inner surface after forming the metal lip made of metal material in the prior art, and to provide a nacelle and an aero engine.

[0008] The present invention solves the above-mentioned technical problems through the following technical solution:

[0009] A lip for an air intake of an aircraft engine, the lip being formed from a composite laminate comprising a fiberglass layer and an aluminum alloy layer, the fiberglass layer and the aluminum alloy layer being alternately laid and cured to form the lip.

[0010] In this solution, the above structure is adopted, using composite laminates to create the lip. These composite laminates consist of alternating layers of fiberglass and aluminum alloy, which are then cured and molded. The lip made of composite laminates has high structural rigidity, effectively resisting bird strikes. Even if a foreign object penetrates one fiberglass or aluminum alloy layer, the other inner fiberglass or aluminum alloy layers can effectively block it, preventing it from entering the fan compartment. The manufacturing process of the lip made of composite laminates is simple, requiring no milling of internal surfaces, thus improving raw material utilization.

[0011] Preferably, a localized area of ​​the lip opening is provided with localized ply and / or drop layers, the localized ply and the drop layers being used to increase the localized thickness of the lip opening.

[0012] In this scheme, by adopting the above structure, local plying and de-plying can effectively improve the stiffness of the local area of ​​the lip.

[0013] Preferably, the partial layup is disposed along the circumferential and / or axial direction of the lip.

[0014] Preferably, the shape of a single local ply is a rectangular block, and a plurality of rectangular blocks are spaced apart circumferentially and / or axially along the lip.

[0015] Preferably, the partial layup is provided in the connection area or non-connection area of ​​the lip.

[0016] Preferably, the number of glass fiber layers is n, and the number of aluminum alloy lay-up layers is n+1, where n is a natural number greater than or equal to 2.

[0017] In this solution, by adopting the above structure, the glass fiber layup is placed between the aluminum alloy layup, and the innermost and outermost sides of the lip are both aluminum alloy layup, which can effectively improve the rigidity of the lip and also improve the corrosion resistance of the lip.

[0018] Preferably, the glass fiber layer includes unidirectional tape, the main load-bearing direction of the composite laminate is 0°, and the angle between the direction of the unidirectional tape and the main load-bearing direction is 0°, 45°, -45° or 90°.

[0019] Alternatively, the glass fiber layer includes a braid, the main load-bearing direction of the composite laminate is 0°, and the angle between the braid and the main load-bearing direction is 0° or 45°;

[0020] And / or, the material type of the aluminum alloy layer includes 7075, 2024, and 2219.

[0021] Preferably, the lip is an integral lip;

[0022] And / or, the composite laminate includes a thermosetting composite laminate or a thermoplastic composite laminate.

[0023] In this solution, by adopting the above structure, the integrated lip structure has stronger integrity and higher rigidity.

[0024] Preferably, the lip includes multiple segments and connecting strips, with adjacent segments connected by the connecting strips.

[0025] In this solution, by adopting the above structure, the connecting strip can easily and reliably connect the segments, improving the integrity and reliability of the lip.

[0026] An aircraft engine, the aircraft engine including the lip as described above.

[0027] In this design, by adopting the above structure, the lip stiffness of the aero-engine is higher, which can effectively resist bird strikes. Even if foreign objects penetrate through one layer of fiberglass or aluminum alloy, the other layers of fiberglass or aluminum alloy inside can also effectively block foreign objects and prevent them from entering the fan compartment.

[0028] Based on common knowledge in the field, the above-mentioned preferred conditions can be combined arbitrarily to obtain various preferred embodiments of the present invention.

[0029] The positive and progressive effects of this invention are as follows:

[0030] This invention utilizes a composite laminate to create a lip, comprising alternating layers of fiberglass and aluminum alloy, which are then cured and molded. The lip made from the composite laminate exhibits high structural rigidity, effectively resisting bird strikes. Even if a foreign object penetrates one fiberglass or aluminum alloy layer, the subsequent fiberglass or aluminum alloy layers effectively block it, preventing entry into the fan compartment. The manufacturing process for the lip made from the composite laminate is simple, eliminating the need for milling internal surfaces and improving raw material utilization. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the nacelle structure of an aero-engine in the prior art.

[0032] Figure 2 for Figure 1 A schematic diagram of the cross-section of the air intake duct of the mid-short section.

[0033] Figure 3 for Figure 2 A schematic diagram of the cross-section of the lip of the middle air intake.

[0034] Figure 4 This is a schematic diagram of the cross-section of a first type of lip of an aero-engine according to a preferred embodiment of the present invention, wherein a layer is disposed in the connection area.

[0035] Figure 5 This is a schematic diagram of the cross-section of a second type of lip of an aero-engine according to a preferred embodiment of the present invention, wherein partial plying is provided in the connection area.

[0036] Figure 6 This is a structural schematic diagram of the cross-section of a third type of lip of an aero-engine according to a preferred embodiment of the present invention, wherein the missing layer is disposed in the non-connection region.

[0037] Figure 7 This is a structural schematic diagram of the cross-section of a fourth type of lip of an aero-engine according to a preferred embodiment of the present invention, wherein partial lay-up is provided in the non-connecting region.

[0038] Figure 8 This is a structural schematic diagram of the cross-section of a fifth type of lip of an aero-engine according to a preferred embodiment of the present invention, wherein rectangular block-shaped partial plying is disposed in the non-connected area.

[0039] Figure 9This is a structural schematic diagram of the cross-section of a sixth type of lip of an aero-engine according to a preferred embodiment of the present invention, wherein the lip is an integral lip.

[0040] Figure 10 This is a structural schematic diagram of the cross-section of a sixth type of lip of an aero-engine according to a preferred embodiment of the present invention, wherein the lip is segmented.

[0041] Figure 11 This is a schematic diagram of the cross-section of a sixth type of lip of an aero-engine according to a preferred embodiment of the present invention, wherein the lip is segmented and a connecting strip is provided between the segments.

[0042] Explanation of reference numerals in the attached figures:

[0043] Intake 101

[0044] Fan cover 102

[0045] Reverse calculation 103

[0046] Nozzle 104

[0047] Fan housing 105

[0048] Metal lip 205

[0049] Front partition 201

[0050] Rear partition 202

[0051] Docking ring 204

[0052] Metal lip 205

[0053] Inner wall panel 206

[0054] lip 90

[0055] Partial layup 91

[0056] Lost 92 layers

[0057] Rectangular block 93

[0058] Connection area 94

[0059] Non-connection area 95

[0060] Segment 96

[0061] Connecting plate 97

[0062] Composite laminate 80

[0063] Glass fiber layer 81

[0064] Aluminum alloy layer 82 Detailed Implementation

[0065] The present invention will be described more clearly and completely below by way of embodiments and in conjunction with the accompanying drawings, but the present invention is not limited to the scope of the embodiments.

[0066] like Figures 3 to 11 As shown, this embodiment is an aircraft engine, which includes a lip 90 as described below. The lip 90 of the aircraft engine has higher rigidity and can effectively resist bird strikes. Even if foreign objects penetrate through a fiberglass layer 81 or an aluminum alloy layer 82, the other fiberglass layers 81 or aluminum alloy layers 82 inside can also effectively block foreign objects and prevent them from entering the fan compartment.

[0067] exist Figures 3-11 In this design, the lip 90, as mentioned above, is formed from a composite laminate 80, which includes a fiberglass layer 81 and an aluminum alloy layer 82. The fiberglass layers 81 and aluminum alloy layers 82 are alternately laid and cured to form the lip 90. By using the composite laminate 80 to create the lip 90, and configuring the composite laminate 80 to include fiberglass layers 81 and aluminum alloy layers 82, which are alternately laid and cured, the lip 90 made from the composite laminate 80 has high structural rigidity and can effectively resist bird strikes. Even if a foreign object penetrates through one layer of fiberglass layer 81 or aluminum alloy layer 82, the other layers of fiberglass layer 81 or aluminum alloy layer 82 inside can effectively block the foreign object, preventing it from entering the fan compartment. The manufacturing process of the lip 90 made from the composite laminate 80 is simple, requiring no milling of the internal surface, thus improving the utilization rate of raw materials.

[0068] As one implementation method, the composite laminate 80 can be a composite material made by alternately laying and curing glass fiber and high-strength aluminum alloy sheet under specific temperature and pressure using adhesive technology, and combining the advantages of glass fiber and high-strength aluminum alloy sheet.

[0069] The lip 90 has one or both of the following in a local area: local ply 91 and ply 92. The local ply 91 and ply 92 are used to increase the local thickness of the lip 90. The local ply 91 and ply 92 can effectively improve the stiffness of the local area of ​​the lip 90.

[0070] Partial lay-up 91 is set in one or two circumferential or axial directions along the lip 90.

[0071] A single partial layup 91 is shaped like a rectangular block 93, and multiple rectangular blocks 93 are spaced apart along the circumference and / or axial direction of the lip 90. In other embodiments, the partial layup 91 may also be shaped like other shapes, such as regular or irregular shapes like triangles, circles, or ellipses.

[0072] Partial lay-up 91 is provided in the connection area 94 or non-connection area 95 of the lip 90.

[0073] The number of glass fiber layers 81 is n, and the number of aluminum alloy layers is n+1, where n is a natural number greater than or equal to 2. This allows the glass fiber layers to be placed between the aluminum alloy layers, and the innermost and outermost sides of the lip 90 are both aluminum alloy layers, which can effectively improve the stiffness of the lip 90 and also improve its corrosion resistance.

[0074] The glass fiber layer 81 includes a unidirectional strip, the main load-bearing direction of the composite laminate 80 is 0°, and the angle between the direction of the unidirectional strip and the direction of the main load-bearing direction is 0°, 45°, -45° or 90°.

[0075] The glass fiber layer 81 includes a braid, the main load-bearing direction of the composite laminate 80 is 0°, and the angle between the braid and the main load-bearing direction is 0° or 45°.

[0076] The aluminum alloy layer 82 is made of materials including 7075, 2024, and 2219. The composite material laminate 80 includes thermosetting composite material laminate 80 or thermoplastic composite material laminate 80.

[0077] exist Figure 9 In the middle, the lip 90 is a one-piece lip 90, which has stronger structural integrity and higher rigidity.

[0078] exist Figure 10 and Figure 11 In the lip 90, multiple segments 96 and connecting plates 97 are included, with adjacent segments 96 connected by the connecting plates 97. The connecting plates 97 can easily and reliably connect the segments 96, improving the overall integrity and reliability of the lip 90. The connecting plates 97 can be made of lightweight, high-strength materials such as aluminum alloy.

[0079] The lip 90 is formed by laying and curing a composite laminate 80. The main materials of the composite laminate 80 include a glass fiber layer 81 and an aluminum alloy layer 82. Specifically, the aluminum alloy layer 82 can be a high-strength aluminum alloy plate. As one implementation, the aerodynamic flow channel surface can use the aluminum alloy layer 82, and the glass fiber layer 81 and the aluminum alloy layer 82 can be alternately laid and cured. In the connection area 94 of the lip 90, a localized thickening of the layup 91 can be added, which can effectively avoid the blade effect of countersunk fasteners.

[0080] The lip 90 can also be thickened by adding circumferential and axial localized layers 92 in the non-connection area 95, which can increase structural stiffness and further improve resistance to bird strikes. The circumferential and axial directions can also be the circumferential and axial directions of the lip 90, respectively.

[0081] The lip 90 utilizes the excellent damage tolerance properties of the composite laminate 80 to improve its resistance to impacts from foreign objects such as bird strikes and hail. At the same time, the composite laminate 80 has a lower density than aluminum alloy, and the lip 90 made of composite laminate 80 is lighter in weight and has greater specific strength and specific stiffness.

[0082] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A lip for an air intake of an aircraft engine, characterized in that, The lip is formed by a composite material laminate, which includes a fiberglass layer and an aluminum alloy layer. The fiberglass layer and the aluminum alloy layer are alternately laid and cured to form the lip. The number of glass fiber layers is n, and the number of aluminum alloy layers is n+1, where n is a natural number greater than or equal to 2. The aluminum alloy layers are located at the innermost and outermost sides of the lip, and the outermost layer on the pneumatic flow channel side of the lip is an aluminum alloy layer. The lip opening has local ply and drop layers in a local area, the local ply and drop layers being used to increase the local thickness of the lip opening; The partial lay-up is applied to the connection area of ​​the lip to avoid the blade effect of the countersunk fastener; The missing layer is located in the non-connection area of ​​the lip to increase structural rigidity.

2. The lip opening as described in claim 1, characterized in that, The partial layup is disposed along the circumferential and / or axial direction of the lip.

3. The lip opening as described in claim 2, characterized in that, The shape of a single local layup is a rectangular block, and multiple rectangular blocks are spaced apart along the circumference and / or axial direction of the lip.

4. The lip opening as described in claim 1, characterized in that, The glass fiber layer includes unidirectional tapes, the main load-bearing direction of the composite material laminate is 0°, and the angle between the direction of the unidirectional tapes and the main load-bearing direction is 0°, 45°, -45° or 90°. Alternatively, the glass fiber layer includes a braid, the main load-bearing direction of the composite laminate is 0°, and the angle between the braid and the main load-bearing direction is 0° or 45°; And / or, the material type of the aluminum alloy layer includes 7075, 2024, and 2219.

5. The lip opening as described in claim 1, characterized in that, The lip opening is a one-piece lip opening; And / or, the composite laminate includes a thermosetting composite laminate or a thermoplastic composite laminate.

6. The lip opening as described in claim 1, characterized in that, The lip includes multiple segments and connecting plates, and adjacent segments are connected by the connecting plates.

7. An aircraft engine, characterized in that, The aircraft engine includes a lip as described in any one of claims 1-6.

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