A composite material containment ring anti-scour structure

Abstract

The present application provides a composite material containment ring anti-scour structure, comprising: a containment ring, having a front end face, an outer wall surface and an inner wall surface, the outer wall surface being adhered to the inner wall surface of the fan flow channel of the aircraft engine, the containment ring being formed by stacking multiple fiber layers, the interface of each fiber layer of the containment ring being a cylinder, and the cylinder being coaxial with the containment ring; a guard ring being adhered to the front end face and part of the inner wall surface of the containment ring, the guard ring being formed by stacking multiple fiber layers, the interface of each fiber layer of the guard ring being a plane at the front end face, and the plane being perpendicular to the axis of the containment ring; each fiber layer of the guard ring being adhered along the inner wall surface of the containment ring at the inner wall surface, the present invention avoids secondary damage to the engine caused by abnormal shedding of the metal guard ring, and at the same time brings certain weight reduction benefits.

Description

Technical Field

[0001] The present application belongs to the field of aero-engines, and in particular relates to a composite material containment ring anti-scour structure. Background Art

[0002] The fan stage rotor blades of aircraft engines are large in size. In order to improve the containment capacity of the casing and prevent the blades from flying through the casing and causing secondary damage to the aircraft, a containment ring is designed on the outside of the fan rotor. Currently, the containment ring material is mainly resin-based composite materials. The composite containment ring fiber is circumferentially layered, and the interlayer is filled with resin, such as Figure 1-Figure 2 As shown in the figure, since the containment ring is located in the fan flow path, it is prone to fiber layer separation after being eroded by air for a long time, which reduces the containment capacity and affects the use of the engine. Therefore, the containment ring needs to be designed to resist erosion. Summary of the Invention

[0003] In order to solve the above problems, the present application provides a composite material containment ring anti-scour structure, comprising:

[0004] The containment ring has a front end surface, an outer wall surface, and an inner wall surface. The outer wall surface is in contact with the inner wall surface of the fan flow passage of the aircraft engine. The containment ring is formed by stacking multiple fiber layers. The interface between each fiber layer of the containment ring is a cylindrical surface. The cylindrical surface is coaxial with the containment ring.

[0005] The guard ring is applied to the front end face and part of the inner wall surface of the containment ring. The guard ring is formed by stacking multiple fiber layers. The interface of each fiber layer of the guard ring is a plane at the front end face, and the plane is perpendicular to the axis of the containment ring; each fiber layer of the guard ring is applied along the inner wall surface of the containment ring at the inner wall surface.

[0006] The above technical features have the beneficial effects: the fiber layer of the containment ring is easy to separate mainly because its circumferential laying direction is consistent with the airflow direction. In order to ensure that the containment capacity of the containment ring is not affected, a radially distributed fiber layer is designed on the axial windward surface of the containment ring, namely the guard ring, and the anti-scouring guard ring is integrated into the containment ring, so that the containment ring itself has an anti-scouring function.

[0007] Preferably, the guard ring and the containing ring are integrally formed;

[0008] The above technical features have the beneficial effects that the inclusion ring and the protection ring are fused and applied, which has better mechanical effect, is not easy to fall off, and has good protection.

[0009] Preferably, the containing ring has a step surface for mounting the guard ring at the junction of the outer wall surface and the front end surface, and the end surface of the guard ring is attached to the step surface;

[0010] The above technical features have the beneficial effects that the step surface is more conducive to the application of the guard ring, and the step surface forms a mounting platform connected to the guard ring, so that the end guard ring fully covers the front end surface of the containing ring.

[0011] Preferably, the inner wall surface of the containment ring has an annular groove, the protective coating is accommodated in the groove, and the guard ring is located between the protective coating and the containment ring;

[0012] The above technical features have the beneficial effects: the above grooves are located at the fan blades, the anti-scratch coating can prevent the fan blades from being scratched, and protect the guard ring and the containing ring. At the same time, in order to form a good surface, a groove is provided to accommodate the anti-scratch coating.

[0013] Preferably, the retaining ring and the containing ring are of separate design, and the retaining ring is connected to the containing ring by gluing or threading;

[0014] The above technical features have the beneficial effects: since the manufacturing process of the integrated guard ring and the containment ring is difficult, considering the engineering applicability, a composite guard ring anti-scour structure is designed, and the material of the guard ring is selected from the same composite material as the containment ring, but the laying direction is different from that of the containment ring, and it is made into a separate annular guard ring and installed with the containment ring.

[0015] Preferably, the guard ring has an easily breakable area at every preset distance, and each fiber layer in the easily breakable area has a cross section;

[0016] The above technical features have the following beneficial effects: Unlike integrated fusion designs, the guard ring still has the risk of falling off during actual use. Compared with metal guard rings, the falling of the guard ring will not cause impact structural damage to rotating parts such as fan rotor blades. However, due to the large diameter of the aircraft engine containment ring, an overly long guard ring may cause entanglement in rotating parts such as fan rotor blades after falling off, which will also affect the safety of engine use. Therefore, it is necessary to reduce the impact resistance of the guard ring so that it will quickly break apart after falling off to avoid secondary damage. Therefore, the guard ring adopts a reserved defect design, that is, there is a prone to breakage area, fiber sections are reserved during layering, and the axial position of the cross-section between each layer of fiber is staggered.

[0017] Preferably, the cross-section distribution of the easily breakable area is stepped, V-shaped, or staggered.

[0018] Preferably, the retaining ring has a plurality of reserved holes, which are connected to the containing ring by composite screws and increase the breakability of the retaining ring;

[0019] The above technical features have the beneficial effect of: in order to further reduce the impact resistance of the guard ring, reserved holes are designed on the surface of the guard ring to ensure that the guard ring breaks into small pieces after being impacted.

[0020] Preferably, a protective coating is added to the reserved holes, the surface of the containing ring and the surface of the guard ring that are not connected to the composite screw, and the material of the composite screw is a fine-woven puncture three-dimensional carbon-carbon composite material;

[0021] The above technical features have the following beneficial effects: the retaining ring is assembled to the front end of the containment ring using adhesive to ensure axial assembly; the composite screw is designed to ensure radial assembly. The composite screw is made of fine-woven, three-dimensional carbon-carbon composite material, which not only ensures assembly strength but also prevents secondary damage if it falls off. After assembly, a protective coating is applied to the surfaces of the retaining ring and containment ring to enhance corrosion resistance, UV resistance, and long-term reliability.

[0022] The present invention avoids secondary damage to the engine caused by abnormal shedding of the metal guard ring, while bringing certain weight reduction benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a cross-sectional schematic diagram of a traditional composite containment ring;

[0024] Figure 2 This is a schematic diagram of the installation of a traditional containment ring;

[0025] Figure 3 1 is a schematic cross-sectional view of the composite material containment ring anti-scour structure of Example 1;

[0026] Figure 4 is a schematic cross-sectional view of the guard ring of Example 2;

[0027] Figure 5 is a schematic cross-sectional view of a retaining ring with a reserved hole according to the second embodiment;

[0028] Figure 6 It is a schematic cross-sectional view of the anti-scour structure of the composite material containment ring of Example 2. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and should not be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in conjunction with the drawings.

[0030] Example 1:

[0031] like Figure 3 As shown, the present application provides a fiber layer containing ring anti-scour structure, comprising:

[0032] The containment ring 1 has a front face, an outer wall, and an inner wall. The outer wall is in contact with the inner wall of the fan duct of the aircraft engine. The containment ring 1 is formed by stacking multiple fiber layers. The interface between each fiber layer of the containment ring 1 is a cylindrical surface. The cylindrical surface is coaxial with the containment ring 1.

[0033] The guard ring 2 is applied to the front end face and part of the inner wall surface of the containment ring 1. The guard ring 2 is formed by stacking multiple fiber layers. The interface of each fiber layer of the guard ring 2 is a plane at the front end face, and the plane is perpendicular to the axis of the containment ring 1; each fiber layer of the guard ring 2 is applied along the inner wall surface of the containment ring 1 at the inner wall surface.

[0034] The above technical features have the beneficial effects: the fiber layer of the containment ring is easy to separate mainly because its circumferential laying direction is consistent with the airflow direction. In order to ensure that the containment capacity of the containment ring is not affected, a radially distributed fiber layer is designed on the axial windward surface of the containment ring, namely the guard ring, and the anti-scouring guard ring is integrated into the containment ring, so that the containment ring itself has an anti-scouring function.

[0035] Preferably, the retaining ring 2 and the containing ring 1 are integrally formed;

[0036] The above technical features have the beneficial effects that the containing ring 1 and the protecting ring 2 are fused and applied, which has better mechanical effect, is not easy to fall off, and has good protection.

[0037] Preferably, the containing ring 1 has a step surface for mounting the guard ring 2 at the junction of the outer wall surface and the front end surface, and the end surface of the guard ring 2 is attached to the step surface;

[0038] The above technical features have the beneficial effects that the step surface is more conducive to the application of the guard ring 2, and the step surface forms a mounting platform connected to the guard ring 2, so that the end guard ring 2 fully covers the front end surface of the containing ring 1.

[0039] Preferably, the inner wall surface of the containment ring 1 has an annular groove, the protective coating 3 is accommodated in the groove, and the guard ring 2 is located between the protective coating 3 and the containment ring 1;

[0040] The above technical features have the beneficial effects: the above grooves are located at the fan blades, the anti-scratch coating can prevent the fan blades from being scratched, and protect the guard ring 2 and the containing ring 1. At the same time, in order to form a good surface, a groove is provided to accommodate the anti-scratch coating.

[0041] Example 2:

[0042] A fiber layer containing ring anti-scour structure, comprising:

[0043] The containment ring 1 has a front face, an outer wall, and an inner wall. The outer wall is in contact with the inner wall of the fan duct of the aircraft engine. The containment ring 1 is formed by stacking multiple fiber layers. The interface between each fiber layer of the containment ring 1 is a cylindrical surface. The cylindrical surface is coaxial with the containment ring 1.

[0044] The guard ring 2 is applied to the front end face and part of the inner wall surface of the containment ring 1. The guard ring 2 is formed by stacking multiple fiber layers. The interface of each fiber layer of the guard ring 2 is a plane at the front end face, and the plane is perpendicular to the axis of the containment ring 1; each fiber layer of the guard ring 2 is applied along the inner wall surface of the containment ring 1 at the inner wall surface.

[0045] The above technical features have the beneficial effects: the fiber layer of the containment ring is easy to separate mainly because its circumferential laying direction is consistent with the airflow direction. In order to ensure that the containment capacity of the containment ring is not affected, a radially distributed fiber layer is designed on the axial windward surface of the containment ring, namely the guard ring, and the anti-scouring guard ring is integrated into the containment ring, so that the containment ring itself has an anti-scouring function.

[0046] Preferably, the retaining ring 2 and the containing ring 1 are of separate design, and the retaining ring 2 is connected to the containing ring 1 by gluing or threading;

[0047] The above technical features have the beneficial effects: since the manufacturing process of the integrated guard ring 2 and the containment ring 1 is difficult, considering the engineering applicability, the composite guard ring 2 is designed to have an anti-scour structure. The material of the guard ring 2 is selected from the same composite material as the containment ring 1, but the laying direction is different from that of the containment ring, and it is made into a separate annular guard ring 2 and installed with the containment ring.

[0048] Preferably, the guard ring 2 has an easy-to-break area at every preset distance, and each fiber layer in the easy-to-break area has a cross section, such as Figure 4 ;

[0049] The above technical features have the following beneficial effects: Unlike an integrated fusion design, the guard ring 2 still has the risk of falling off during actual use. Compared with metal guard rings, the falling of the guard ring 2 will not cause impact structural damage to rotating parts such as fan rotor blades. However, due to the large diameter of the aircraft engine containment ring 1, an excessively long guard ring 2 may cause entanglement in rotating parts such as fan rotor blades after falling off, which will also affect the safety of engine use. Therefore, it is necessary to reduce the impact resistance of the guard ring 2 so that it will quickly break apart after falling off to avoid secondary damage. Therefore, the guard ring 2 adopts a reserved defect design, that is, there is a prone to breakage area, and fiber sections are reserved during layering, and the axial position of the cross-section between each layer of fibers is staggered.

[0050] Preferably, the cross-section distribution of the easily breakable area is stepped, V-shaped, or staggered.

[0051] Preferably, the retaining ring 2 has a plurality of reserved holes, which are connected to the containing ring 1 through composite screws and increase the easy breakability of the retaining ring 2, such as Figure 5 As shown;

[0052] The above technical features have the beneficial effect of: in order to further reduce the impact resistance of the guard ring, reserved holes are designed on the surface of the guard ring to ensure that the guard ring breaks into small pieces after being impacted.

[0053] Preferably, a protective coating 3 is added to the reserved holes, the surface of the containing ring 1 and the surface of the retaining ring 2 that are not connected to the composite screws, such as Figure 6 As shown, the material of the composite screw is a fine-woven puncture three-way carbon-carbon composite material;

[0054] The above technical features have the following beneficial effects: the retaining ring 2 is assembled to the front end of the containment ring 1 using adhesive to ensure axial assembly; the composite screws are designed to ensure radial assembly. The composite screws are made of fine-woven, three-dimensional carbon-carbon composite material, which not only ensures assembly strength but also prevents secondary damage caused by disengagement. After assembly, a protective coating is applied to the surfaces of the retaining ring and containment ring 1 to enhance corrosion resistance, UV resistance, and long-term reliability.

[0055] The advantages of the present application include: both solutions of the present invention avoid secondary damage to the engine caused by abnormal shedding of the metal guard ring, while bringing certain weight reduction benefits.

[0056] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A composite material containment ring anti-scour structure, characterized in that: include: The containment ring (1) has a front end face, an outer wall face, and an inner wall face, wherein the outer wall face is attached to the inner wall face of the fan flow passage of the aircraft engine, and the containment ring (1) is formed by stacking multiple fiber layers, and the interface of each fiber layer of the containment ring (1) is a cylindrical surface, and the cylindrical surface is coaxial with the containment ring (1); The retaining ring (2) is applied to the front end face and part of the inner wall surface of the containing ring (1). The retaining ring (2) is formed by stacking multiple fiber layers. The interface of each fiber layer of the retaining ring (2) is a plane at the front end face, and the plane is perpendicular to the axis of the containing ring (1). Each fiber layer of the retaining ring (2) is applied along the inner wall surface of the containing ring (1). The guard ring (2) has easy-to-break areas at predetermined intervals, and each fiber layer in the easy-to-break area has a cross section; The cross-section distribution of the easily fractured area is stepped, V-shaped, or staggered.

2. The composite material containment ring anti-scour structure according to claim 1, characterized in that: The guard ring (2) and the containing ring (1) are integrally formed.

3. The composite material containment ring anti-scour structure according to claim 1, characterized in that: The containing ring (1) has a step surface for mounting the guard ring (2) at the junction of the outer wall surface and the front end surface, and the end surface of the guard ring (2) is attached to the step surface.

4. The composite material containment ring anti-scour structure according to claim 1, characterized in that: The inner wall surface of the containing ring (1) has an annular groove, the protective coating (3) is accommodated in the groove, and the protective ring (2) is located between the protective coating (3) and the containing ring (1).

5. The composite material containment ring anti-scour structure according to claim 1, characterized in that: The guard ring (2) and the containing ring (1) are of split design, and the guard ring (2) is connected to the containing ring (1) by gluing or threading.

6. The composite material containment ring anti-scour structure according to claim 1, characterized in that: The retaining ring (2) has a plurality of reserved holes, and the reserved holes are connected to the containing ring (1) via composite screws and increase the breakability of the retaining ring (2).

7. The composite material containment ring anti-scour structure according to claim 6, characterized in that: A protective coating (3) is added to a portion of the reserved holes that are not connected to the composite screws, the surface of the containing ring (1), and the surface of the guard ring (2).

8. The composite material containment ring anti-scour structure according to claim 6, characterized in that: The composite screw is made of a fine-woven puncture three-dimensional carbon-carbon composite material.

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