An air intake pressurization intensity test structure for an aeroengine

Abstract

This application belongs to the technical field of the pressurization strength test of an aero-engine inlet duct, and specifically relates to a pressurization strength test structure for an aero-engine inlet duct, including: a bracket; a blanking plate connected to the bracket, located inside the inlet of the inlet duct, with a small gap between it and the inlet duct, and having an installation opening thereon; a cover plate detachably connected to the blanking plate to block the installation opening; a canvas belt bonded to the inner sides of the blanking plate and the inlet duct, with wrinkles at the small gap between the blanking plate and the inlet duct; a balloon cloth belt bonded to the inner sides of the blanking plate and the inlet duct, and also bonded to the inner side of the canvas belt, with wrinkles at the small gap between the blanking plate and the air duct.

Description

Technical Field

[0001] This application belongs to the technical field of aero-engine inlet pressurization strength tests, and particularly relates to a structure for aero-engine inlet pressurization strength tests. Background Art

[0002] Currently, in aero-engine inlet pressurization strength tests, a plug is mostly set in the inlet of the inlet supported by a support device for blocking, and an aero-engine component is connected at the outlet of the inlet. The plug is rigidly connected in the inlet, and polyurethane glue is used for sealing at the connection part. This technical solution has the following defects:

[0003] 1) The plug has a great influence on the stiffness of the inlet, restricts the pressurization deformation of the inlet, and affects the reliability of the test results;

[0004] 2) The polyurethane glue is easily torn when the inlet is pressurized and deformed, making it difficult to ensure the smooth completion of the test;

[0005] 3) Leakage points are likely to occur and are difficult to repair.

[0006] In view of the existence of the above technical defects, this application is proposed.

[0007] It should be noted that the disclosure of the above background art 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 application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background art should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0008] The purpose of this application is to provide a structure for aero-engine inlet pressurization strength tests to overcome or mitigate at least one aspect of the known technical defects.

[0009] The technical solution of this application is as follows:

[0010] A structure for aero-engine inlet pressurization strength tests includes:

[0011] A bracket;

[0012] A plug, connected to the bracket, located inside the inlet of the inlet, having a small gap with the inlet, and having an installation opening thereon;

[0013] A cover plate, detachably connected to the plug to block the installation opening;

[0014] A canvas belt, bonded to the inner sides of the plug and the inlet, having folds at the small gap between the plug and the inlet;

[0015] The balloon cloth belt is bonded to the inner side of the blanking plate and the air inlet duct, and also bonded to the inner side of the canvas belt. There are wrinkles at the small gaps between the blanking plate and the air duct.

[0016] According to at least one embodiment of the present application, in the above-mentioned pressurization strength test structure of the aero-engine air inlet duct, the blanking plate is provided with an inflation hole, a pressure detection hole, and an inflation protection hole, where:

[0017] An inflation nozzle is installed in the inflation hole;

[0018] A pressure detector is installed in the pressure detection hole;

[0019] A pressure relief valve is installed in the inflation protection hole.

[0020] According to at least one embodiment of the present application, in the above-mentioned pressurization strength test structure of the aero-engine air inlet duct, the cover plate is connected to the blanking plate by bolts, with a sealing ring interposed therebetween, and the bolt holes on the blanking plate are blind holes.

[0021] According to at least one embodiment of the present application, in the above-mentioned pressurization strength test structure of the aero-engine air inlet duct, the bracket includes:

[0022] Columns;

[0023] Two cross beams, connected between the two columns;

[0024] Two pairs of support rods, connected to the two cross beams;

[0025] Two pairs of support plates, connected to the two pairs of support rods;

[0026] The above-mentioned pressurization strength test structure of the aero-engine air inlet duct further includes:

[0027] A plurality of blanking plate stiffeners, connected to the outer side of the blanking plate, in a ring shape;

[0028] Two pairs of bracket adapter plates, connected to both ends of each blanking plate stiffener, and bolt-connected to the two pairs of support plates.

[0029] According to at least one embodiment of the present application, in the above-mentioned pressurization strength test structure of the aero-engine air inlet duct, it further includes:

[0030] Two lifting rings, connected to two opposite blanking plate stiffeners.

[0031] According to at least one embodiment of the present application, in the above-mentioned pressurization strength test structure of the aero-engine air inlet duct, it further includes:

[0032] Two cover plate adapter plates, connected to two opposite blanking plate stiffeners;

[0033] Cover plate stiffeners, connected to the cover plate;

[0034] The plug plate transfer beam is connected to the cover plate stiffener, and both ends are bolted to two cover plate transfer plates.

[0035] According to at least one embodiment of the present application, in the above-mentioned aero-engine inlet pressurization strength test structure, it further includes:

[0036] The load-bearing floor, on which a bracket is connected. Description of the Drawings

[0037] Figure 1 is a schematic diagram of the aero-engine inlet pressurization strength test structure provided by the embodiment of the present application;

[0038] Figures 2 - 5 is a partial schematic diagram of the aero-engine inlet pressurization strength test structure provided by the embodiment of the present application;

[0039] Wherein:

[0040] 1 - bracket; 2 - plug plate; 3 - inlet; 4 - cover plate; 5 - canvas belt; 6 - balloon cloth belt; 7 - column; 8 - cross beam; 9 - support rod; 10 - support plate; 11 - plug plate stiffener; 12 - bracket transfer plate; 13 - lifting ring; 14 - cover plate stiffener; 15 - plug plate transfer beam; 16 - load-bearing floor; 17 - cover plate transfer plate.

[0041] For better illustration of this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and cannot be construed as a limitation to the present application. Detailed Description of the Embodiment

[0042] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely in conjunction with the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of the present application, which are only used to explain the present application rather than limit the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments and the technical features in the embodiments of the present application can be combined with each other to obtain new embodiments.

[0043] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the ordinary meanings understood by those of ordinary skill in the art to which this application pertains. The words indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application are only used to indicate relative directions or positional relationships, rather than implying that the device or component must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. Therefore, it should not be construed as a limitation to this application. The terms "first", "second", "third" and similar terms used in the description of this application are only for descriptive purposes to distinguish different components and should not be construed as indicating or implying relative importance. The similar words such as "a", "one" or "the" used in the description of this application should not be construed as an absolute limitation on the quantity but should be understood as having at least one. The similar words such as "including" or "comprising" used in the description of this application are intended to mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0044] In addition, it should also be noted that, unless otherwise clearly specified and limited, the similar words such as "installed", "connected" and "joined" used in the description of this application should be understood in a broad sense. For example, "connected" 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 directly connected or indirectly connected through an intermediate medium, and can also be the communication inside two components. Those skilled in the art can understand its specific meaning in this application according to the specific situation.

[0045] The following Figures 1 to 5 will further elaborate on this application in conjunction with the attached

[0046] An aircraft engine inlet pressurization strength test structure, comprising:

[0047] Bracket 1;

[0048] Plug plate 2, which has an installation opening thereon, is connected to bracket 1, is located inside the inlet 3 of the air intake duct, and has a small gap with the air intake duct 3, and this small gap meets the deformation margin of the air intake duct 3 during the stamping strength test;

[0049] Cover plate 4, which is connected to the plug plate 2 in a detachable manner to block the installation opening;

[0050] Canvas belt 5, which is bonded to the inner sides of the plug plate 2 and the air intake duct 3 and has wrinkles at the small gap between the plug plate 2 and the air intake duct 3;

[0051] The balloon cloth belt 6 is bonded to the inner sides of the blocking plate 2 and the air inlet duct 3, and also bonded to the inner side of the canvas belt 5. There are wrinkles at the small gaps between the blocking plate 2 and the air duct 3, and the wrinkles are not bonded.

[0052] For the air inlet duct pressurization strength test structure disclosed in the above embodiments, those skilled in the art can understand that during the pressurization strength test, the air inlet duct 3 can be supported by the supporting device, and air can be filled into the air inlet duct 3 to verify the strength of the air inlet duct 3. When filling air into the air inlet duct 3, the blocking plate 2, the cover plate 4, the canvas belt 5, and the balloon cloth belt 6 form a sealing structure, which can avoid gas leakage. When the air inlet duct 3 is deformed under pressure, due to the small gap between the blocking plate 2 and the air inlet duct 3, and the canvas belt 5 and the balloon cloth belt 6 connected between the blocking plate 2 and the air inlet duct 3 are flexible structures and have wrinkles, they will deform following the air inlet duct 3 and are not easily torn, which can ensure the smooth completion of the test. In addition, it will not affect the deformation of the air inlet duct 3 and accurate test results can be obtained.

[0053] For the air inlet duct pressurization strength test structure disclosed in the above embodiments, those skilled in the art can also understand that in its design, the canvas belt 5 is first bonded to the inner sides of the blocking plate 2 and the air inlet duct 3, and then the balloon cloth belt 6 is bonded. When pressurizing the air inlet duct 3 and the air inlet duct 3 is deformed under pressure, the canvas belt 5 can effectively restrict the deformation of the balloon cloth belt 6 and avoid the canvas belt 5 from being torn. Moreover, the width of the balloon cloth belt 6 is greater than the width of the canvas belt 5, completely covering the canvas belt 5, having reliable sealing performance and being able to effectively prevent gas leakage.

[0054] In some alternative embodiments, in the above air inlet duct pressurization strength test structure of the aeroengine, the blocking plate 2 is provided with an air filling hole, a pressure detection hole, and an air filling protection hole, where:

[0055] An air filling nozzle is installed in the air filling hole, and air can be filled into the air inlet duct 3 through the air filling nozzle to conduct the pressurization strength test;

[0056] A pressure detector is installed in the pressure detection hole to detect the pressure inside the air inlet duct 3;

[0057] A pressure relief valve is installed in the air filling protection hole. When the pressure inside the air inlet duct 3 is too high, it can automatically relieve pressure to provide pressure protection. A pressure gauge with a pressure relief valve contact having a pressure relief protection function can also be installed.

[0058] In some alternative embodiments, in the above air inlet duct pressurization strength test structure of the aeroengine, the cover plate 4 is connected to the blocking plate 2 with an installation opening by bolts, and a sealing ring is padded between them, and the bolt holes on the blocking plate 2 are blind holes to ensure the sealing performance of the air inlet duct 3.

[0059] In some alternative embodiments, in the above air inlet duct pressurization strength test structure of the aeroengine,

[0060] The bracket 1 includes:

[0061] The column 7;

[0062] Two cross beams 8, connected between the two columns 7;

[0063] Two pairs of support rods 9, connected to the two cross beams 8;

[0064] Two pairs of support plates 10, connected to the two pairs of support rods 9;

[0065] The pressurization strength test structure of the aero - engine air intake duct further includes:

[0066] A plurality of blanking plate stiffeners 11, connected to the outside of the blanking plate 2 in a ring shape;

[0067] Two pairs of bracket adapter plates 12, connected to both ends of each blanking plate stiffener 11, and bolt - connected to the two pairs of support plates 10.

[0068] In some alternative embodiments, in the above - mentioned pressurization strength test structure of the aero - engine air intake duct, it further includes:

[0069] Two lifting rings 13, connected to two opposite blanking plate stiffeners 11.

[0070] In some alternative embodiments, in the above - mentioned pressurization strength test structure of the aero - engine air intake duct, it further includes:

[0071] Two cover plate adapter plates 17, connected to two opposite blanking plate stiffeners 11;

[0072] The cover plate stiffener 14, connected to the cover plate 4;

[0073] The blanking plate transfer beam 15, connected to the cover plate stiffener 14, and bolt - connected to the two cover plate adapter plates 17 at both ends.

[0074] In some alternative embodiments, in the above - mentioned pressurization strength test structure of the aero - engine air intake duct, it further includes:

[0075] The load - bearing floor 16, to which the bracket 1 is connected, has a T - shaped groove on it, and the bracket 1 can be fixed by bolts and the position of the bracket 1 can be adjusted adaptively.

[0076] In the description of the specification, each embodiment is described in a progressive manner. Each embodiment focuses on the differences from other embodiments. The same or similar parts among the embodiments can be referred to each other.

[0077] So far, the technical solutions of this application have been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of this application is obviously not limited to these specific embodiments. Without departing from the principle of this application, those skilled in the art can make equivalent changes or substitutions to relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of this application.

Claims

1. An air intake pressurization intensity test structure for an aeroengine, characterized in that Comprising: A bracket (1); A blanking plate (2), connected to the bracket (1), located inside the inlet of the air inlet duct (3), having a small gap with the air inlet duct (3), and having an installation opening thereon; A cover plate (4), detachably connected to the blanking plate (2) to block the installation opening; A canvas belt (5), bonded to the inner sides of the blanking plate (2) and the air inlet duct (3), having wrinkles at the small gap between the blanking plate (2) and the air inlet duct (3); A balloon cloth belt (6), bonded to the inner sides of the blanking plate (2) and the air inlet duct (3), and also bonded to the inner side of the canvas belt (5), having wrinkles at the small gap between the blanking plate (2) and the air duct (3); When inflating the air inlet duct (3), the blanking plate (2), the cover plate (4), the canvas belt (5), and the balloon cloth belt (6) form a sealing structure to prevent gas leakage. When the air inlet duct (3) is deformed under pressure, due to the small gap between the blanking plate (2) and the air inlet duct (3), and the canvas belt (5) and the balloon cloth belt (6) connected between the blanking plate (2) and the air inlet duct (3) are flexible structures and have wrinkles, they will deform following the air inlet duct (3), are not easily torn, and will not affect the deformation of the air inlet duct (3).

2. The air inlet duct pressurization strength test structure of an aero-engine according to claim 1, wherein: The blanking plate (2) has an inflation hole, a pressure detection hole, and an inflation protection hole, where: An inflation nozzle is installed in the inflation hole; A pressure detector is installed in the pressure detection hole; A pressure relief valve is installed in the inflation protection hole.

3. The air inlet duct pressurization strength test structure of an aero-engine according to claim 1, wherein: The cover plate (4) is connected to the blanking plate (2) by bolts, with a sealing ring padded between them, and the bolt holes on the blanking plate (2) are blind holes.

4. The air inlet duct pressurization strength test structure of an aero-engine according to claim 1, wherein: The bracket (1) includes: A column (7); Two cross beams (8), connected between the two columns (7); Two pairs of support rods (9), connected to the two cross beams (8); Two pairs of support plates (10), connected to the two pairs of support rods (9); The air inlet duct pressurization strength test structure of the aero-engine further includes: A plurality of blanking plate stiffeners (11), connected to the outer side of the blanking plate (2) and in a ring shape; Two pairs of bracket adapter plates (12), connected to both ends of each blanking plate stiffener (11), and connected to the two pairs of support plates (10) by bolts.

5. The air inlet duct pressurization strength test structure of an aero-engine according to claim 4, wherein: It further includes: Two lifting rings (13), connected to two opposite blanking plate stiffeners (11).

6. The air inlet duct pressurization strength test structure of an aero-engine according to claim 4, wherein: It further includes: Two cover plate adapter plates (17), connected to two opposite blanking plate stiffeners (11); A cover plate stiffener (14), connected to the cover plate (4); A blanking plate transfer beam (15), connected to the cover plate stiffener (14), and both ends are connected to the two cover plate adapter plates (17) by bolts.

7. The air inlet duct pressurization strength test structure of an aero-engine according to claim 1, wherein: It further includes: Load-bearing floor (16), to which a support (1) is connected.

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