Aero-engine air intake cowl structure and assembly method thereof

Abstract

The application belongs to the technical field of aero-engine intake frame design, and particularly relates to an aero-engine intake cowl structure and an assembling method thereof, wherein the aero-engine intake cowl structure comprises: an outer cowl, which is provided with a plurality of mounting holes; an inner ring, which is arranged in the outer cowl and is provided with a plurality of mounting grooves; a plurality of support plates, which are arranged in a circumferential direction between the outer cowl and the inner ring, and are provided with support plate heads at top ends and lower edge plates at root portions; each support plate head is inserted into a corresponding mounting hole and is welded to the corresponding mounting hole; each lower edge plate is clamped into a corresponding mounting groove; an annular flow channel plate, which is provided with a plurality of notches at one end and an annular folded edge at the other end; each notch is clamped on a corresponding support plate; and the annular folded edge is bolted to a corresponding end of the inner ring, so that the annular flow channel plate is attached to the inner ring and each lower edge plate is pressed in the corresponding mounting groove.

Description

Technical Field

[0001] This application belongs to the technical field of aero-engine inlet casing structure design, specifically relating to an aero-engine inlet casing structure and its assembly method. Background Technology

[0002] The air intake structure of an aero-engine is the main load-bearing frame of the aero-engine, including an outer casing, an inner ring, and multiple support plates. The inner ring is mostly cast and housed within the outer casing, connecting to the front pivot bearing housing of the aero-engine. The support plates are arranged circumferentially between the outer casing and the inner ring, welded to the inner ring at their roots and welded to their tops with support plate heads. Each support plate head is cast and welded to the outer casing. The radial load borne by the front pivot of the aero-engine is transferred to the air intake frame through the front pivot bearing housing. This technical solution has the following drawbacks:

[0003] 1) There are numerous welds, which can easily lead to substandard welding quality, resulting in problems such as deformation and stress concentration;

[0004] 2) Each support plate head and its inner ring are cast, resulting in poor quality stability and increased welding difficulty, and may even lead to situations where welding is impossible.

[0005] This application is made in view of the aforementioned technical deficiencies.

[0006] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0007] The purpose of this application is to provide an air intake casing structure for an aircraft engine and its assembly method, so as to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] One aspect provides an air intake casing structure for an aircraft engine, comprising:

[0010] The outer casing has multiple mounting holes;

[0011] The inner ring, located inside the outer casing, has multiple mounting slots.

[0012] Multiple support plates, each with a support plate head at the top and a lower edge plate at the base, are arranged circumferentially between the outer casing and the inner ring; each support plate head extends into a corresponding mounting hole and is welded to the corresponding mounting hole; each lower edge plate is snapped into a corresponding mounting groove.

[0013] The annular flow channel plate has multiple notches at one end and an annular folded edge at the other end; each notch is fitted onto a support plate; the annular folded edge is bolted to the corresponding end of the inner ring, so that the annular flow channel plate is attached to the inner ring, pressing each lower edge plate into the corresponding mounting groove.

[0014] According to at least one embodiment of this application, in the above-described aero-engine intake casing structure, each support plate is a cavity structure, which is supported by ribs along its axial direction.

[0015] According to at least one embodiment of this application, in the above-described aero-engine intake casing structure, each support plate and its corresponding support plate and lower edge plate are split structures and are connected by diffusion welding.

[0016] According to at least one embodiment of this application, in the above-described aero-engine intake casing structure, there are multiple bolts connecting the annular flange and the inner ring, and each bolt is screwed onto a corresponding lower edge plate.

[0017] According to at least one embodiment of this application, in the above-described aero-engine intake casing structure, the inner ring is connected to the front pivot bearing casing by a plurality of bolts, and each bolt is screwed onto a corresponding lower edge plate.

[0018] On the other hand, a method for assembling an aero-engine inlet casing structure is provided to achieve the assembly of any of the above-mentioned aero-engine inlet casing structures, including:

[0019] The inner ring is installed inside the outer casing;

[0020] Insert each support plate into the corresponding mounting hole, so that the head of each support plate is locked in the corresponding mounting hole, and each lower edge plate is locked into the corresponding mounting groove;

[0021] Each support plate head is spot-welded to its corresponding mounting hole.

[0022] The inner ring and the front pivot bearing housing are connected by multiple bolts, with each bolt corresponding to a lower edge plate.

[0023] Each notch is snapped onto the corresponding support plate, and the annular folded edge and inner ring are connected with multiple bolts. Each bolt is screwed onto a corresponding lower edge plate, so that the annular flow channel plate is pressed against the inner ring and each lower edge plate is pressed into the corresponding mounting groove.

[0024] Each support plate head is connected to its corresponding mounting hole using electron beam welding. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the air intake casing structure of an aero-engine provided in an embodiment of this application;

[0026] Figure 2 This is a partial schematic diagram of the support plate and lower edge plate provided in the embodiments of this application;

[0027] Figure 3 This is a partial schematic diagram of the annular flow channel plate provided in an embodiment of this application;

[0028] in:

[0029] 1-Outer casing; 2-Inner ring; 3-Support plate; 4-Annular flow channel plate.

[0030] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0031] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0032] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0033] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a 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 or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0034] The following is in conjunction with the appendix Figures 1 to 3 This application will be described in further detail.

[0035] One aspect provides an air intake casing structure for an aircraft engine, comprising:

[0036] The outer casing 1 has multiple mounting holes;

[0037] Inner ring 2, which is disposed inside outer casing 1, has multiple mounting slots;

[0038] Multiple support plates 3, with support plate heads formed at the top and lower edge plates formed at the base, are arranged circumferentially between the outer casing 1 and the inner ring 2; each support plate head extends into a corresponding mounting hole and is welded to the corresponding mounting hole; each lower edge plate is snapped into a corresponding mounting groove.

[0039] The annular flow channel plate 4 has multiple notches at one end and an annular folded edge at the other end; each notch is correspondingly clipped onto a support plate 3; the annular folded edge is bolted to the corresponding end of the inner ring 2, so that the annular flow channel plate 4 is attached to the inner ring 2, and each lower edge plate is pressed into the corresponding mounting groove.

[0040] Regarding the aero-engine intake casing structure disclosed in the above embodiments, those skilled in the art will understand that its design, with each support plate 3 formed on the lower edge plate at the root, in conjunction with the mounting groove on the inner ring 2, and fixed to the inner ring 2 by bolts using the annular flow channel plate 4, and the support plate head directly formed on the top of the support plate, can greatly reduce the number of welds, reduce the probability of substandard welding quality, and avoid problems such as deformation and stress concentration caused by it.

[0041] Regarding the aero-engine intake casing structure disclosed in the above embodiments, those skilled in the art will also understand that the support plate 3, its upper support plate head, lower edge plate, and inner ring can be machined to achieve high machining accuracy.

[0042] Regarding the aero-engine intake casing structure disclosed in the above embodiments, those skilled in the art can also understand that the annular flow channel plate 4 abuts against the inner ring 2, which on the one hand can form the inner surface of the aero-engine intake duct to ensure the aerodynamic configuration of the intake duct, and on the other hand can effectively constrain each lower edge plate in the corresponding mounting groove to prevent each lower edge plate from coming out of the corresponding mounting groove. This can effectively ensure the shape of each support plate 3 and prevent each support plate 3 from deforming due to bearing large aerodynamic loads during operation, thus ensuring the overall performance of the aero-engine.

[0043] In some alternative embodiments, in the above-described aero-engine intake casing structure, each support plate 3 is a cavity structure, which is supported by ribs along its axial direction.

[0044] In some optional embodiments, in the above-described aero-engine intake casing structure, each support plate 3 and its corresponding support plate and lower edge plate are split structures and connected by diffusion welding.

[0045] In some optional embodiments, in the above-described aero-engine intake casing structure, there are multiple bolts connecting the annular flange and the inner ring 2, and each bolt is screwed onto a corresponding lower edge plate to effectively constrain each lower edge plate in the corresponding mounting groove.

[0046] In some optional embodiments, in the above-described aero-engine intake casing structure, the inner ring 2 and the front pivot bearing casing 5 are connected by multiple bolts, each bolt being screwed onto a lower edge plate to effectively constrain each lower edge plate in the corresponding mounting groove.

[0047] On the other hand, a method for assembling an aero-engine inlet casing structure is provided to achieve the assembly of any of the above-mentioned aero-engine inlet casing structures, including:

[0048] The inner ring 2 is installed inside the outer casing 1;

[0049] Insert each support plate 3 into the corresponding mounting hole, so that each support plate head is locked in the corresponding mounting hole and each lower edge plate is locked into the corresponding mounting groove;

[0050] Each support plate head is spot-welded to its corresponding mounting hole to initially fix each support plate 3 to the outer casing 1;

[0051] The inner ring 2 and the front support bearing housing 5 are connected by multiple bolts, with each bolt screwed onto a corresponding lower edge plate to position each support plate 3 and the inner ring 2.

[0052] Each notch is snapped onto the corresponding support plate 3, and the annular folded edge and inner ring 2 are connected by multiple bolts. Each bolt is screwed onto a corresponding lower edge plate, so that the annular flow channel plate 4 is attached to the inner ring 2. Each lower edge plate is pressed into the corresponding mounting groove to achieve reliable fixation between each support plate 3 and the inner ring 2.

[0053] Each support plate head is connected to its corresponding mounting hole using electron beam welding.

[0054] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0055] The technical solution of this 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 this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. An air intake casing structure for an aircraft engine, characterized in that, include: The outer casing (1) has multiple mounting holes; The inner ring (2) is provided inside the outer casing (1) and has multiple mounting slots thereon; Multiple support plates (3) are arranged circumferentially between the outer casing (1) and the inner ring (2), with support plate heads formed at the top and lower edge plates formed at the base. Each support plate head extends into a corresponding mounting hole and is welded to the corresponding mounting hole. Each lower edge plate is inserted into a corresponding mounting groove. The annular flow channel plate (4) has multiple notches at one end and an annular folded edge at the other end; each notch is correspondingly clamped on a support plate (3); the annular folded edge is bolted to the corresponding end of the inner ring (2), so that the annular flow channel plate (4) is attached to the inner ring (2), and each lower edge plate is pressed into the corresponding mounting groove. There are multiple bolts connecting the annular fold and the inner ring (2), and each bolt is screwed onto a lower edge plate.

2. The aero-engine inlet casing structure according to claim 1, characterized in that, Each support plate (3) is a hollow structure, which is supported by ribs along its axial direction.

3. The aero-engine inlet casing structure according to claim 2, characterized in that, There are multiple bolts connecting the annular fold and the inner ring (2), and each bolt is screwed onto a lower edge plate.

4. The aero-engine inlet casing structure according to claim 3, characterized in that, The inner ring (2) is connected to the front pivot bearing housing (5) by multiple bolts, and each bolt is screwed onto a lower edge plate.

5. A method for assembling an aero-engine inlet casing structure, used to assemble the aero-engine inlet casing structure as described in claim 4, characterized in that, include: The inner ring (2) is installed inside the outer casing (1); Insert each support plate (3) into the corresponding mounting hole, so that the head of each support plate is locked in the corresponding mounting hole and the lower edge plate is locked into the corresponding mounting groove; Each support plate head is spot-welded to its corresponding mounting hole for initial fixation; The inner ring (2) and the front pivot bearing housing (5) are connected by multiple bolts, with each bolt corresponding to a lower edge plate; Each notch is attached to the corresponding support plate (3), and the annular folded edge and inner ring (2) are connected by multiple bolts. Each bolt is screwed onto a corresponding lower edge plate, so that the annular flow channel plate (4) is attached to the inner ring (2), and each lower edge plate is pressed into the corresponding mounting groove. Each support plate head is connected to its corresponding mounting hole using electron beam welding, thus reliably fixing the support plate head in the mounting hole.

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