An air intake casing support plate for an aeroengine

Abstract

The application belongs to the technical field of aero-engine intake casing support plate design, and particularly relates to an aero-engine intake casing support plate, which comprises a support plate head, a front edge strip, a rear edge strip, a vertical rib, two front edge skins and two rear edge skins.

Description

Technical Field

[0001] This application belongs to the field of aero-engine intake casing support plate design technology, specifically relating to an aero-engine intake casing support plate. Background Technology

[0002] The aero-engine inlet casing is the main load-bearing frame of the aero-engine. It mainly includes the inlet casing, a support plate inner ring installed within the inlet casing, and multiple support plates arranged circumferentially between the inlet casing and the support plate inner ring. Each support plate includes a support plate body and a support plate head at its upper end. The lower end of each support plate is connected to the support plate inner ring, and the upper end of the support plate head is connected to the inlet casing. Figure 1 As shown.

[0003] Currently, to reduce the weight of aero engines, the support plates are often designed as hollow structures with axial ribs within the cavities to enhance their strength. For ease of assembly, the support plates are often designed as split structures, and are manufactured using superplastic forming diffusion welding technology, creating triangular zones at the rib and trailing edge areas. Figure 2-3 As shown, the triangular area is weak and prone to cracking. In addition, the support plate head is mostly made by casting, resulting in low production precision.

[0004] This application is made in view of the aforementioned technical deficiencies.

[0005] 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

[0006] The purpose of this application is to provide an air intake casing support plate for an aircraft engine to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] An air intake casing support plate for an aircraft engine, comprising:

[0009] Support plate head;

[0010] The leading edge strip is connected at its upper end to the support plate head;

[0011] The rear edge strip is connected to the support plate head at its upper end;

[0012] The vertical rib is connected at the upper end to the support plate head and is located between the front edge strip and the rear edge strip, and is integrally formed with the support plate head, the front edge strip, and the rear edge strip;

[0013] Two leading edge skins are connected to the support plate head. One leading edge skin is connected to one side of the leading edge strip and vertical rib, and the other leading edge skin is connected to the other side of the leading edge strip and vertical rib.

[0014] Two rear edge skins are connected to the support plate head. One rear edge skin is connected to one side of the rear edge strip and vertical reinforcement, and the other rear edge skin is connected to the other side of the rear edge strip and vertical reinforcement.

[0015] According to at least one embodiment of this application, in the above-mentioned aero-engine intake casing support plate, the support plate head, leading edge strip, trailing edge strip, and vertical rib are machined together.

[0016] According to at least one embodiment of this application, in the above-mentioned aero-engine intake casing support plate, the support plate head, leading edge strip, trailing edge strip, vertical rib and the two leading edge skins and trailing edge skins are connected by an electron beam welding process.

[0017] According to at least one embodiment of this application, in the above-mentioned aero-engine intake casing support plate, the support plate head, leading edge strip, trailing edge strip, and vertical rib are machined with overlapping parts so that the edge parts of the two leading edge skins and trailing edge skins can overlap.

[0018] According to at least one embodiment of this application, in the above-mentioned aircraft engine intake casing support plate, a leading edge anti-icing air inlet is provided on the support plate head; the leading edge anti-icing air inlet is connected to the space between the leading edge strip and the vertical rib.

[0019] The two leading edge skins have multiple circumferentially distributed leading edge anti-icing vents; each leading edge anti-icing vent is connected to the space between the leading edge strip and the vertical rib.

[0020] The support plate head is provided with a rear edge anti-icing air inlet; the rear edge anti-icing air inlet is connected to the space between the rear edge strip and the vertical rib.

[0021] The trailing edge strip has multiple trailing edge anti-icing vents distributed circumferentially; each trailing edge anti-icing vent is connected to the space between the trailing edge strip and the vertical rib. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the intake casing support plate of an existing aero-engine;

[0023] Figure 2 This is a schematic diagram showing the triangular area formed at the vertical rib of the air intake casing support plate of an existing aero-engine.

[0024] Figure 3 This is a schematic diagram of the triangular area formed at the trailing edge of the air intake casing support plate of an existing aero-engine.

[0025] Figure 4 This is a schematic diagram of the air intake casing support plate of an aircraft engine provided in an embodiment of this application;

[0026] Figure 5 This is a partial cross-sectional view of the air intake casing support plate of the aircraft engine provided in the embodiment of this application;

[0027] in:

[0028] 1-Support head; 2-Front edge strip; 3-Rear edge strip; 4-Vertical rib; 5-Front edge skin; 6-Rear edge skin.

[0029] 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

[0030] 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.

[0031] 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.

[0032] 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.

[0033] The following is in conjunction with the appendix Figures 1 to 5 This application will be described in further detail.

[0034] An air intake casing support plate for an aircraft engine, comprising:

[0035] Support head 1;

[0036] The leading edge strip 2 is connected at its upper end to the support plate head 1;

[0037] The rear edge strip 3 is connected at its upper end to the support plate head 1;

[0038] The vertical rib 4 is connected at its upper end to the support plate head 1 and is located between the front edge strip 2 and the rear edge strip 3. It is integrally formed with the support plate head 1, the front edge strip 2, and the rear edge strip 3.

[0039] Two front edge skins 5 are connected to the support plate head 1. One front edge skin 5 is connected to one side of the front edge strip 2 and the vertical rib 4, and the other front edge skin 5 is connected to the other side of the front edge strip 2 and the vertical rib 4.

[0040] Two rear edge skins 6 are connected to the support plate head 1. One rear edge skin 6 is connected to one side of the rear edge strip 3 and the vertical rib 4, and the other rear edge skin 6 is connected to the other side of the rear edge strip 3 and the vertical rib 4.

[0041] Regarding the aero-engine intake casing support plate disclosed in the above embodiments, those skilled in the art will understand that its design uses an integrally formed support plate head 1, front edge strip 2, rear edge strip 3, and vertical rib 4 to form the load-bearing support structure of the support plate, which is stable and reliable. Moreover, the two front edge skins 5 and rear edge skins 6 covering it form the shape of the support plate, which can avoid the weak parts of strength caused by the triangular area formed by the superplastic molding diffusion welding process.

[0042] In some optional embodiments, the support plate of the above-mentioned aero-engine intake casing is machined with high precision, wherein the support plate head 1, the leading edge strip 2, the trailing edge strip 3, and the vertical rib 4 are machined together.

[0043] In some optional embodiments, in the above-mentioned aero-engine intake casing support plate, the support plate head 1, leading edge strip 2, trailing edge strip 3, vertical rib 4 and the two leading edge skins 5 and trailing edge skins 6 are connected by an electron beam welding process.

[0044] In some optional embodiments, the above-mentioned aero-engine intake casing support plate has overlapping parts processed on the support plate head 1, front edge strip 2, rear edge strip 3, and vertical rib 4, so that the edge parts of the two front edge skins 5 and rear edge skins 6 can overlap to make the support plate surface flat.

[0045] In some optional embodiments, the aforementioned aero-engine intake casing support plate has a leading edge anti-icing air inlet hole on the support plate head 1; the leading edge anti-icing air inlet hole is connected to the space between the leading edge strip 2 and the vertical rib 4.

[0046] The two leading edge skins 5 have multiple leading edge anti-icing vents distributed circumferentially; each leading edge anti-icing vent is connected to the space between the leading edge strip 2 and the vertical rib 4.

[0047] The support plate head 1 is provided with a rear edge anti-icing air inlet; the rear edge anti-icing air inlet is connected to the space between the rear edge strip 3 and the vertical rib 4;

[0048] The rear edge strip 3 has multiple rear edge anti-icing vents distributed circumferentially; each rear edge anti-icing vent is connected to the space between the rear edge strip 3 and the vertical rib 4.

[0049] In some optional embodiments, the above-mentioned aero-engine intake casing support plate also includes a bottom block connected to the lower end of the front edge strip 2, the rear edge strip 3, and the vertical rib 4, integrally formed with the front edge strip 2, the rear edge strip 3, and the vertical rib 4, and overlapping with the edge parts of the two front edge skins 5 and the rear edge skins 6, together forming a support plate, and the overall structure is stable.

[0050] 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.

[0051] 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 support plate for an aircraft engine, characterized in that, include: Support plate head (1); The front edge strip (2) is connected at its upper end to the support plate head (1); The rear edge strip (3) is connected at its upper end to the support plate head (1); The vertical rib (4) is connected at the upper end to the support plate head (1), located between the front edge strip (2) and the rear edge strip (3), and is integrally formed with the support plate head (1), the front edge strip (2) and the rear edge strip (3); Two front edge skins (5) are connected to the support plate head (1), wherein one front edge skin (5) is connected to one side of the front edge strip (2) and the vertical rib (4), and the other front edge skin (5) is connected to the other side of the front edge strip (2) and the vertical rib (4); Two rear edge skins (6) are connected to the support plate head (1), wherein one rear edge skin (6) is connected to one side of the rear edge strip (3) and the vertical rib (4), and the other rear edge skin (6) is connected to the other side of the rear edge strip (3) and the vertical rib (4); The bottom block is connected to the lower end of the front edge strip (2), the rear edge strip (3), and the vertical rib (4), and is integrally formed with the front edge strip (2), the rear edge strip (3), and the vertical rib (4), and is connected to the edge parts of the two front edge skins (5) and the rear edge skins (6); Support plate head (1), front edge strip (2), rear edge strip (3), vertical rib (4), bottom end block machined; The support plate head (1), front edge strip (2), rear edge strip (3), vertical rib (4) are connected to the two front edge skins (5) and rear edge skins (6) by electron beam welding process.

2. The aero-engine intake casing support plate according to claim 1, characterized in that, The support plate head (1), front edge strip (2), rear edge strip (3), and vertical rib (4) are machined with overlapping parts so that the edges of the two front edge skins (5) and rear edge skins (6) can be overlapped.

3. The aero-engine intake casing support plate according to claim 1, characterized in that, The support plate head (1) is provided with a front edge anti-icing air inlet; the front edge anti-icing air inlet is connected to the space between the front edge strip (2) and the vertical rib (4); The two leading edge skins (5) have multiple leading edge anti-icing vents distributed circumferentially; each leading edge anti-icing vent is connected to the space between the leading edge strip (2) and the vertical rib (4); The support plate head (1) is provided with a rear edge anti-icing air inlet; the rear edge anti-icing air inlet is connected to the space between the rear edge strip (3) and the vertical rib (4); The rear edge strip (3) has multiple rear edge anti-icing vents distributed along the circumference; each rear edge anti-icing vent is connected to the space between the rear edge strip (3) and the vertical rib (4).

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