An aircraft engine air intake casing inner support plate structure

Abstract

The present application belongs to the technical field of design of support plates inside an aircraft engine air intake casing, and specifically relates to a support plate structure inside an aircraft engine air intake casing, in which an elastic sheet is arranged in the cavity of the support plate, and the two ends of the elastic sheet are bent toward each other, forming a V-shape as a whole, forming two elastic arms. The outer side of each elastic arm relies on the elastic force of the elastic sheet to rest against the side wall of one side of the support plate cavity. When the aircraft engine is working and the support plate is subjected to severe aerodynamic loads, the vibration response amplitude of the support plate can be reduced through joint surface damping and Coulomb friction damping, thereby reducing the vibration stress borne by the support plate, reducing vibration of the support plate, and avoiding cracks and breakage on the support plate.

Description

Technical Field

[0001] The present application belongs to the technical field of design of inner support plates of an aircraft engine air intake casing, and specifically relates to an inner support plate structure of an aircraft engine air intake casing. Background Art

[0002] The inner support plates of aircraft engine casings are mostly thin-walled cavity structures. When the aircraft engine is working, they will be subjected to severe aerodynamic loads, resulting in a large vibration amplitude response and withstand large vibration stress. In severe cases, cracks will occur and even breakage will occur.

[0003] This application is proposed in view of the above-mentioned technical defects.

[0004] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0005] The purpose of the present application is to provide an inner support plate structure of an aircraft engine air intake casing to overcome or alleviate at least one of the existing technical defects.

[0006] The technical solution of this application is:

[0007] An aircraft engine air intake casing inner support plate structure, comprising:

[0008] The support plate is a thin-walled cavity structure;

[0009] The elastic sheet has two ends bent toward each other, forming a V-shape as a whole, forming two elastic arms; the elastic sheet is arranged in the cavity of the support plate, and the outer side of each elastic arm rests against the side wall of one side of the support plate cavity by relying on the elastic force of the elastic sheet.

[0010] According to at least one embodiment of the present application, in the above-mentioned aircraft engine air intake casing inner support plate structure, each elastic arm is cycloid-shaped.

[0011] According to at least one embodiment of the present application, in the above-mentioned aircraft engine air intake casing inner support plate structure, both ends of the elastic sheet have straight sections;

[0012] The two straight sections rest against each other.

[0013] According to at least one embodiment of the present application, in the aforementioned support plate structure within the air intake casing of an aircraft engine, the distance between the side walls of the support plate cavity gradually increases from the leading edge to the trailing edge of the support plate;

[0014] The two ends of the elastic piece face the front edge direction of the support plate.

[0015] According to at least one embodiment of the present application, in the above-mentioned support plate structure within the aircraft engine air intake casing, a gap is left between the elastic sheet and a portion of the support plate cavity near the front edge of the support plate.

[0016] According to at least one embodiment of the present application, in the above-mentioned aircraft engine air intake casing inner support plate structure, the elastic plate has a plurality of vibration-damping holes.

[0017] This application has at least the following beneficial technical effects:

[0018] Provided is a support plate structure within an air intake casing of an aircraft engine. An elastic sheet is disposed within a cavity of the support plate. The two ends of the elastic sheet are bent toward each other, forming a V-shape as a whole, thereby forming two elastic arms. The outer side of each elastic arm rests against a corresponding sidewall of the support plate cavity by virtue of the elastic force of the elastic sheet. When the aircraft engine is operating and the support plate is subjected to severe aerodynamic loads, the vibration response amplitude of the support plate can be reduced through joint surface damping and Coulomb friction damping, thereby reducing the vibration stress borne by the support plate, damping the support plate, and preventing cracks and breakage on the support plate. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 Schematic diagram of the inner support plate structure of the air intake casing of an aircraft engine provided by an embodiment of the present application;

[0020] Figure 2 is a schematic diagram of a support plate provided in an embodiment of the present application;

[0021] Figure 3 is a schematic diagram of an elastic sheet provided in an embodiment of the present application;

[0022] in:

[0023] 1-Support plate; 2-Elastic sheet.

[0024] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limitations on this patent. DETAILED DESCRIPTION

[0025] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0026] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0027] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0028] The following is combined with Figures 1 to 3 This application is described in further detail.

[0029] An aircraft engine air intake casing inner support plate structure, comprising:

[0030] Support plate 1 is a thin-walled cavity structure;

[0031] The elastic sheet 2 has its two ends bent toward each other, forming a V-shape as a whole, forming two elastic arms; the elastic sheet 2 is arranged in the cavity of the support plate 1, and the outer side of each elastic arm relies on the elastic force of the elastic sheet 2 to rest against the side wall of one side of the cavity of the support plate 1.

[0032] As for the support plate structure in the air intake casing of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that an elastic sheet 2 is provided in the cavity of the support plate 1, and the two ends of the elastic sheet 2 are bent toward each other, forming a V-shape as a whole, forming two elastic arms. The outer side of each elastic arm is pressed against the side wall of one side of the cavity of the support plate 1 by the elastic force of the elastic sheet 2. When the aircraft engine is working and the support plate 1 is subjected to severe aerodynamic loads, the vibration response amplitude of the support plate 1 can be reduced through joint surface damping and Coulomb friction damping, thereby reducing the vibration stress borne by the support plate 1, reducing the vibration of the support plate 1, and avoiding cracks and breakage on the support plate 1.

[0033] In some optional embodiments, in the above-mentioned support plate structure in the air intake casing of the aircraft engine, each elastic arm is cycloid-shaped and has a locally outward protruding portion. The protruding portion can rely on the elastic force of the elastic sheet 2 to remain against the side wall on the corresponding side of the cavity of the support plate 1. Even when it is worn, it can still effectively rest against the side wall on the corresponding side of the cavity of the support plate 1. Therefore, when the aircraft engine is working and the support plate 1 is subjected to severe aerodynamic loads, the vibration reduction effect of the support plate 1 can be ensured through the joint surface damping and Coulomb friction damping, thereby avoiding cracks and breakage on the support plate 1.

[0034] In some optional embodiments, in the above-mentioned support plate structure inside the air intake casing of the aircraft engine, both ends of the elastic sheet 2 have straight sections, and the two straight sections are pressed against each other so that the elastic sheet 2 maintains sufficient elasticity, so that the two elastic arms can effectively remain pressed against the side walls on the corresponding sides of the cavity of the support plate 1, thereby ensuring the vibration reduction effect on the support plate 1.

[0035] In some optional embodiments, in the above-mentioned support plate structure in the air intake casing of the aircraft engine, the distance between the side walls on both sides of the cavity of the support plate 1 gradually increases from the leading edge to the trailing edge of the support plate 1;

[0036] The two ends of the elastic sheet 2 are facing the front edge of the support plate 1. Constrained by the space size between the side walls of the cavity of the support plate 1, the bent part of the elastic sheet 2 naturally rests against the part of the cavity of the support plate 1 close to the rear edge of the support plate 1, so that the entire elastic sheet 2 leans against the rear edge of the support plate 1, that is, against the part of the support plate that is subjected to greater vibration stress, thereby ensuring the vibration reduction effect on the support plate 1.

[0037] In some optional embodiments, in the above-mentioned support plate structure in the air intake casing of the aircraft engine, a gap is left between the elastic sheet 2 and the portion of the support plate 1 cavity near the front edge of the support plate 1. On the one hand, it is convenient to assemble the elastic sheet 2 into the cavity of the support plate 1. On the other hand, it allows the elastic sheet 2 to have a certain amount of movement margin in the cavity of the support plate 1, thereby ensuring the vibration reduction effect on the support plate 1 when the aircraft engine is working.

[0038] In some optional embodiments, in the above-mentioned support plate structure within the air intake casing of the aircraft engine, a plurality of vibration-damping holes are provided on the elastic sheet 2. On the one hand, the weight of the elastic sheet 2 can be reduced, thereby reducing the mass of the support plate 1 and the aircraft engine as a whole. On the other hand, the stiffness of the elastic sheet 2 can be reduced, and the deformation capacity of the elastic sheet 2 can be enhanced, thereby ensuring the vibration-damping effect on the support plate 1.

[0039] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0040] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. An aircraft engine air intake casing inner support plate structure, characterized in that: include: The support plate (1) is a thin-walled hollow structure; The elastic sheet (2) has two ends bent toward each other, forming a V-shape as a whole, forming two elastic arms; the elastic sheet (2) is arranged in the cavity of the support plate (1), and the outer side of each elastic arm is pressed against the side wall of one side of the cavity of the support plate (1) by the elastic force of the elastic sheet (2); Each of the elastic arms is cycloid-shaped and has a partially outwardly protruding portion, which can be kept against the side wall of the corresponding side of the cavity of the support plate (1) by relying on the elastic force of the elastic sheet (2); Both ends of the elastic sheet (2) have straight sections; the two straight sections abut against each other.

2. The aircraft engine air intake casing inner support plate structure according to claim 1, characterized in that: The distance between the side walls of the support plate (1) cavity gradually increases from the front edge to the rear edge of the support plate (1); The two ends of the elastic sheet (2) face the front edge of the support plate (1), and are constrained by the space size between the side walls of the support plate (1). The bent portion of the elastic sheet (2) naturally abuts against a portion of the support plate (1) cavity near the rear edge of the support plate (1).

3. The aircraft engine air intake casing inner support plate structure according to claim 1, characterized in that: A gap is left between the elastic sheet (2) and a portion of the support plate (1) cavity close to the front edge of the support plate (1).

4. The aircraft engine air intake casing inner support plate structure according to claim 1, characterized in that: The elastic sheet (2) is provided with a plurality of vibration-damping holes.

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