An aeroengine inlet casing structure and its assembly method

Abstract

This application belongs to the technical field of aero-engine inlet casing design, and specifically relates to an aero-engine inlet casing structure, which mainly includes an outer casing, a strut, a bearing casing, a cap support, and a cap. Through corresponding structural design, connections are made using nuts, bolts, connecting columns, anti-rotation pins, and plugs to achieve the assembly between structures, and it can be well applied to medium bypass ratio aero-engines. In addition, this application also relates to an assembly method for realizing the above-mentioned aero-engine inlet casing structure.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft engine air intake casing design, and specifically relates to an aircraft engine air intake casing structure and an assembly method thereof. Background Art

[0002] The air intake casing structure is located at the front end of the aircraft engine. It needs to be able to withstand the radial force of a point bearing, adjust the direction of the inlet airflow, make the inlet airflow evenly distributed, improve the fan's low and medium speed performance, and realize a point of oil inlet, oil return, exhaust, lead and other functions.

[0003] The intake casing structure of low-bypass-ratio aircraft engines mostly adopts a welded structure. However, the ratio of radial diameter to axial length of medium-bypass-ratio aircraft engines is larger. Compared with low-bypass-ratio aircraft engines, their intake casing structure is more compact. Some functions need to be achieved by adjusting the relative position relationship between parts and components, and welded structures are difficult to apply.

[0004] This application is proposed in view of the above-mentioned technical defects.

[0005] 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

[0006] The purpose of the present application is to provide an aircraft engine air intake casing structure and an assembly method thereof, so as to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of this application is:

[0008] On the one hand, an aircraft engine air intake casing structure is provided, comprising:

[0009] an outer casing having a plurality of molded holes thereon;

[0010] Multiple support plates are arranged inside the outer casing, with a connecting protrusion at the upper end and a sector at the lower end; each connecting protrusion extends from a corresponding molded hole, a nut is screwed on it, and is fastened to the outer casing; each sector has an anti-rotation hole at the front end, and the sectors are spliced together to form an inner ring; the front end of the inner ring has multiple anti-rotation holes distributed along the circumference;

[0011] The bearing casing is arranged inside the inner ring, and the outer wall of the rear end has an annular folded edge; the annular folded edge has a plurality of connection holes distributed along the circumferential direction;

[0012] Multiple connecting columns, with one end of each connecting column passing through a corresponding connecting hole and being screwed to the rear end of the inner ring, and a nut being screwed onto the other end to fasten the annular folded edge to the inner ring;

[0013] A cap support, having an annular connecting edge at the rear end; the annular connecting edge is fastened to the front end of the bearing casing by a plurality of bolts distributed circumferentially;

[0014] A cap, covering the cap support, having a mounting hole at the front end and a plurality of pin holes distributed circumferentially at the rear end;

[0015] A plurality of anti-rotation pins, with each pin being inserted into a corresponding anti-rotation hole and its pin hole;

[0016] A plug, with its threaded part passing through the mounting hole and being screwed to the front end of the cap support, and the head pressing against the cap.

[0017] According to at least one embodiment of the present application, in the above-mentioned aeroengine inlet casing structure, there are two nuts screwed onto each connecting column to form self-locking, and a gasket is provided between the nut and the outer casing.

[0018] According to at least one embodiment of the present application, in the above-mentioned aeroengine inlet casing structure, one end of each connecting column passing through the corresponding connecting hole is correspondingly screwed to the rear end of a sector segment.

[0019] According to at least one embodiment of the present application, in the above-mentioned aeroengine inlet casing structure, each sector segment has an anti-rotation hole at the front end.

[0020] According to at least one embodiment of the present application, in the above-mentioned aeroengine inlet casing structure, each anti-rotation pin is press-fitted into the corresponding pin hole.

[0021] According to at least one embodiment of the present application, in the above-mentioned aeroengine inlet casing structure, the front end of the cap support has a plurality of stop holes distributed circumferentially;

[0022] The edge of the head of the plug has a plurality of stop grooves;

[0023] The above-mentioned aeroengine inlet casing structure further includes:

[0024] A spacer ring, sleeved on the threaded part of the plug, placed between the head of the plug and the front end of the cap support, having a plurality of stop protrusions on the inner ring and a plurality of stop edges on the outer ring; each stop protrusion is correspondingly snapped into a stop hole; each stop edge is bent outwards and correspondingly snapped into a stop groove.

[0025] According to at least one embodiment of the present application, in the above-mentioned aeroengine inlet casing structure, the rear end of the cap support has an annular sealing protrusion;

[0026] The annular seal protrudes into the inner side of the bearing casing, and a sealing groove is formed between the annular seal and the bearing casing;

[0027] The structure of the aero-engine inlet casing further includes:

[0028] A sealing ring, which is arranged in the sealing groove.

[0029] On the other hand, a method for assembling the structure of the aero-engine inlet casing is provided, including:

[0030] Screw the connecting column to the rear section of the corresponding sector segment;

[0031] Arrange each support plate inside the outer casing, so that each connecting protrusion protrudes from the corresponding die hole, arrange gaskets on each connecting protrusion, and tighten by screwing two nuts;

[0032] Push the bearing casing into the inner ring from back to front, so that each connecting hole sleeves onto the corresponding connecting column, and tighten by screwing nuts on each connecting column;

[0033] Arrange the sealing ring in the sealing groove, push the cap housing support from front to back, and fasten the annular connecting edge to the front end of the bearing casing by using bolts;

[0034] Press each anti-rotation pin into the corresponding anti-rotation hole by interference fit, and push the cap housing from front to back, so that each anti-rotation pin inserts into the corresponding pin hole;

[0035] Slip the spacer ring onto the threaded part of the plug, pass the threaded part of the plug through the mounting hole, and screw it to the front end of the cap housing support, so that the head of the plug presses the cap housing, and each anti-stop protrusion correspondingly snaps into a anti-stop hole;

[0036] Bend each anti-stop edge outwards, so that each anti-stop edge snaps into the corresponding anti-stop groove. Description of the Drawings

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

[0038] Wherein:

[0039] 1 - outer casing; 2 - support plate; 3 - bearing casing; 4 - connecting column; 5 - cap housing support; 6 - cap housing; 7 - anti-rotation pin; 8 - plug; 9 - spacer ring; 10 - sealing ring.

[0040] 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 should not be construed as a limitation of this patent. Detailed Embodiment

[0041] To make the technical solutions and their advantages of this application clearer, the following will further describe the technical solutions of this application clearly and completely in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0042] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. 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 represent relative directions or position relationships, rather than implying that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative position relationship may also change accordingly. Therefore, it cannot be understood 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 cannot be understood 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 understood 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 indicate 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.

[0043] In addition, it should be noted that unless otherwise clearly specified and limited, the similar words such as "installed", "connected" and "coupled" 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 directly connected or indirectly connected through an intermediate medium, and it can also be the communication inside two elements. Those skilled in the art can understand their specific meanings in this application according to the specific situation.

[0044] The following will further describe this application in detail Figure 1 in conjunction with the accompanying drawings.

[0045] On the one hand, an aeroengine inlet casing structure is provided, including:

[0046] An outer casing 1, which has a plurality of shaped holes thereon;

[0047] A plurality of support plates 2 are arranged inside the outer casing 1. The upper ends have connecting protrusions, and the lower ends have fan-shaped sections. Each connecting protrusion extends out from a corresponding shaped hole, and a nut is screwed thereon and fastened to the outer casing 1. Each fan-shaped section has an anti-rotation hole at the front end, and the fan-shaped sections are spliced together to form an inner ring. The front end of the inner ring has a plurality of anti-rotation holes distributed circumferentially.

[0048] The bearing casing 3 is arranged inside the inner ring. The outer wall at the rear end has an annular flange. A plurality of connecting holes are distributed circumferentially on the annular flange.

[0049] A plurality of connecting columns 4. One end of each connecting column 3 passes through a corresponding connecting hole and is screwed to the rear end of the inner ring, and a nut is screwed on the other end to fasten the annular flange to the inner ring, realizing the fixation of the bearing casing 3, and using the annular flange on the bearing casing 3 to fix the relative positions between the fan-shaped sections, ensuring the stability of the overall structure of the inner ring.

[0050] The cap support 5 has an annular connecting edge at the rear end. The annular connecting edge is fastened to the front end of the bearing casing 3 by a plurality of bolts distributed circumferentially, and a lock washer can be arranged therebetween.

[0051] The cap 6 covers the cap support 5. The front end has a mounting hole, and the rear end has a plurality of pin holes distributed circumferentially. For the convenience of disassembly and assembly, a threaded hole can be opened at the front end of the cap 6, and a threaded tool is used for fixation and pushing.

[0052] A plurality of anti-rotation pins 7. Each pin 7 is correspondingly inserted into an anti-rotation hole and its pin hole to prevent the cap 6 from rotating circumferentially.

[0053] The plug 8 has its threaded part passing through the mounting hole and is screwed to the front end of the cap support 5, and the head presses against the cap 6 to axially fix the cap 6.

[0054] For the aeroengine inlet casing structure disclosed in the above embodiments, in specific applications, the bearing casing 3 can be sleeved onto a support bearing to be able to bear radial forces, and the support plates 2 are used to adjust the inlet air flow direction, so that the inlet air flow is evenly distributed, improving the performance of the fan at medium and low speeds, and corresponding functional channels are opened in the outer casing 1 and the support plates 2 to ensure functions such as oil inlet, oil return, air intake and exhaust, and wire leading for a single support point.

[0055] For the aeroengine inlet casing structure disclosed in the above embodiments, those skilled in the art can understand that the designed aeroengine inlet casing structure mainly includes the outer casing 1, the support plates 2, the bearing casing 3, the cap support 5, and the cap 6. Through corresponding structural designs, nuts, bolts, connecting columns 4, anti-rotation pins 7, and plugs 8 are used for connection to realize the assembly between structures, and it can be well applied to aeroengines with medium bypass ratios.

[0056] In some alternative embodiments, in the above-described aero-engine inlet casing structure, there are two nuts screwed onto each connecting column to form self-locking, and a gasket is provided between the nut and the outer casing 1.

[0057] In some alternative embodiments, in the above-described aero-engine inlet casing structure, one end of each connecting column 4 passing through the corresponding connecting hole is screwed to the rear end of a corresponding sector segment.

[0058] In some alternative embodiments, in the above-described aero-engine inlet casing structure, each front end of the sector segment has an anti-rotation hole.

[0059] In some alternative embodiments, in the above-described aero-engine inlet casing structure, each anti-rotation pin 7 is press-fitted in the corresponding pin hole.

[0060] In some alternative embodiments, in the above-described aero-engine inlet casing structure, the front end of the cap support 5 has a plurality of circumferentially distributed stop holes;

[0061] The edge of the head of the plug 8 has a plurality of stop grooves;

[0062] The aero-engine inlet casing structure further includes:

[0063] A spacer ring 9, sleeved on the threaded portion of the plug 8, is provided between the head of the plug 8 and the front end of the cap support 5. The inner ring has a plurality of stop protrusions, and the outer ring has a plurality of stop edges; each stop protrusion is correspondingly snapped into a stop hole; each stop edge is bent outwards and correspondingly snapped into a stop groove, thereby effectively preventing the plug from rotating. In a specific embodiment, there are two sets of stop protrusions and their corresponding stop holes, and three sets of stop edges and their corresponding stop grooves.

[0064] In some alternative embodiments, in the above-described aero-engine inlet casing structure, the rear end of the cap support 5 has an annular sealing protrusion;

[0065] The annular sealing protrusion extends into the inner side of the bearing casing 3, and a sealing groove is formed between the annular sealing protrusion and the bearing casing 3;

[0066] The aero-engine inlet casing structure further includes:

[0067] A sealing ring 10, disposed in the sealing groove.

[0068] On the other hand, a method for assembling an aero-engine inlet casing structure is provided, including:

[0069] Screwing the connecting column 4 to the rear section of the corresponding sector segment;

[0070] Arrange each support plate 2 inside the outer casing 1 so that each connecting protrusion extends out of the corresponding hole, set gaskets on each connecting protrusion, and fasten with two screwed nuts;

[0071] Push the bearing casing 3 into the inner ring from back to front so that each connecting hole is sleeved on the corresponding connecting column 4, and fasten with screwed nuts on each connecting column 4;

[0072] Set the sealing ring 10 in the sealing groove, push the cap support 5 from front to back, and fasten the annular connecting edge to the front end of the bearing casing 3 with bolts;

[0073] Press fit each anti-rotation pin 7 into the corresponding anti-rotation hole, push the cap 6 from front to back so that each anti-rotation pin 7 is inserted into the corresponding pin hole;

[0074] Set the spacer ring 9 on the threaded part of the plug 8, pass the threaded part of the plug 8 through the mounting hole, and screw it to the front end of the cap support 5, with the head of the plug 8 pressing against the cap 6 so that each stop protrusion is correspondingly snapped into a stop hole;

[0075] Bend each stop edge outwards so that each stop edge is snapped into the corresponding stop groove.

[0076] Regarding the assembly method of the aero-engine inlet casing structure disclosed in the above embodiments, those skilled in the art can understand that it is used to realize the assembly of the aero-engine inlet casing structure disclosed in the above embodiments. The description is relatively simple. For specific relevant parts, reference can be made to the relevant descriptions of the aero-engine inlet casing structure. Its technical effects can also refer to the technical effects of the relevant parts of the aero-engine inlet casing structure, which will not be elaborated here.

[0077] The embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same or similar parts between the embodiments, reference can be made to each other.

[0078] So far, the technical solutions of the present application have been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present 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 fall within the protection scope of the present application.

Claims

1. An air intake casing structure of an aeroengine, characterized in that Comprising: An outer casing (1) having a plurality of shaped holes thereon; A plurality of support plates (2) disposed within the outer casing (1), having a connecting protrusion at the upper end and a fan-shaped section at the lower end; each connecting protrusion correspondingly protrudes from one of the shaped holes, and a nut is screwed thereon and fastened to the outer casing (1); each fan-shaped section has an anti-rotation hole at the front end, and the respective fan-shaped sections are spliced together to form an inner ring; the inner ring has a plurality of circumferentially distributed anti-rotation holes at the front end; A bearing casing (3) disposed within the inner ring, having an annular flange on the outer wall at the rear end; the annular flange has a plurality of circumferentially distributed connecting holes; A plurality of connecting columns (4), one end of each connecting column (3) correspondingly passes through a connecting hole and is screwed to the rear end of the inner ring, and a nut is screwed on the other end to fasten the annular flange to the inner ring; A cap support (5) having an annular connecting edge at the rear end; the annular connecting edge is fastened to the front end of the bearing casing (3) by a plurality of circumferentially distributed bolts; A cap (6) covering the cap support (5), having a mounting hole at the front end and a plurality of circumferentially distributed pin holes at the rear end; A plurality of anti-rotation pins (7), each pin (7) is correspondingly inserted into an anti-rotation hole and its pin hole; A plug (8), the threaded portion thereof passes through the mounting hole and is screwed to the front end of the cap support (5), and the head presses against the cap (6).

2. The structure of the aeroengine inlet casing according to claim 1, wherein There are two nuts screwed on each connecting column to form self-locking, and a gasket is provided between the nut and the outer casing (1).

3. The structure of the aeroengine inlet casing according to claim 1, wherein One end of each connecting column (4) passing through the corresponding connecting hole is correspondingly screwed to the rear end of a fan-shaped section.

4. The structure of the aeroengine inlet casing according to claim 1, wherein Each fan-shaped section has one anti-rotation hole at the front end.

5. The structure of the aeroengine inlet casing according to claim 1, wherein Each anti-rotation pin (7) is press-fitted in the corresponding pin hole.

6. The structure of the aeroengine inlet casing according to claim 1, wherein The front end of the cap support (5) has a plurality of circumferentially distributed stop holes; The head edge of the plug (8) has a plurality of stop grooves; The structure of the aeroengine inlet casing further comprises: A spacer ring (9) sleeved on the threaded portion of the plug (8), padded between the head of the plug (8) and the front end of the cap support (5), having a plurality of stop protrusions on the inner ring and a plurality of stop edges on the outer ring; each stop protrusion is correspondingly snapped into a stop hole; each stop edge is bent outwards and correspondingly snapped into a stop groove.

7. The structure of the aeroengine inlet casing according to claim 1, wherein The rear end of the cap support (5) has an annular sealing protrusion; The annular sealing protrusion extends into the inner side of the bearing casing (3) and forms a sealing groove with the bearing casing (3); The structure of the aeroengine inlet casing further comprises: A sealing ring (10) disposed in the sealing groove.

8. An assembly method for an aeroengine inlet casing structure, characterized in that, Comprising: Screwing the connecting column (4) to the rear section of the corresponding fan-shaped section; Arrange each support plate (2) inside the outer casing (1) so that each connecting protrusion extends out of the corresponding shaped hole, set gaskets on each connecting protrusion, and fasten with two nuts screwed together; Push the bearing casing (3) into the inner ring from back to front so that each connecting hole is sleeved on the corresponding connecting post (4), and fasten with nuts screwed on each connecting post (4); Arrange the sealing ring (10) in the sealing groove, push the cap support (5) from front to back, and fasten the annular connecting edge to the front end of the bearing casing (3) with bolts; Press-fit each anti-rotation pin (7) into the corresponding anti-rotation hole, push the cap (6) from front to back so that each anti-rotation pin (7) is inserted into the corresponding pin hole; Slip the spacer ring (9) onto the threaded part of the plug (8), pass the threaded part of the plug (8) through the mounting hole, and screw it onto the front end of the cap support (5), with the head of the plug (8) pressing against the cap (6) so that each stop protrusion is correspondingly snapped into a stop hole; Bend each stop edge outwards so that each stop edge snaps into the corresponding stop groove.

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