An intermediate casing splitter ring segment for an aeroengine

Abstract

The application belongs to the technical field of intermediate casing splitter ring segment design of an aero-engine, and particularly relates to an intermediate casing splitter ring segment of an aero-engine, which comprises: an arc segment with a V-shaped cross section; a reinforcing rib with a U-shaped cross section arranged in the arc segment, two side walls of the reinforcing rib being brazed to the inner side of the arc segment, a brazing filler being used to fill a gap between the two side walls of the reinforcing rib and the inner side of the arc segment after being liquefied, and the two side walls of the reinforcing rib and the inner side of the arc segment being smoothly connected after solidification to eliminate sharp gaps between the two side walls of the reinforcing rib and the inner side of the arc segment; an auxiliary rib welded to the inner side of the arc segment to form a damping cavity with the reinforcing rib; damping particles wrapped by a cylinder mesh and filled in the damping cavity; and an arc plate with two convex edges welded to the rear end faces of the two side walls of the arc segment by argon arc welding.

Description

Technical Field

[0001] This application belongs to the field of design technology of intermediate casing shunt ring section for aero-engines, and specifically relates to an intermediate casing shunt ring section for aero-engines. Background Technology

[0002] An aircraft engine intermediate casing includes an outer casing, an inner casing disposed within the outer casing, and multiple support plates that circumferentially support the outer casing and the inner casing.

[0003] The intermediate casing of the aircraft engine is located behind the fan. To divide the fan outlet airflow into inner and outer bypass airflow, a flow-splitting ring is installed in the intermediate casing. Currently, the flow-splitting ring is divided into multiple flow-splitting ring segments, each of which includes:

[0004] The arc-shaped section has a V-shaped cross-section and is secured on the convex fins in the middle of the adjacent support plates on both sides.

[0005] The reinforcing ribs have a U-shaped cross-section and are installed within the arc-shaped section. The two side walls are spot-welded to the inner side of the arc-shaped section.

[0006] An arc-shaped plate with two protruding edges is welded to the rear end face of the two side walls of the arc-shaped section by argon arc welding to seal the rear end of the arc-shaped section.

[0007] The arc-shaped plates in each flow distribution ring can be bolted to the connecting ring, which is located at the rear end of each support plate. This allows the flow distribution ring to be combined into a stable whole in the intermediate casing, enhancing the overall structural stability.

[0008] Because the inner side of the arc-shaped section and the side walls of the reinforcing ribs in each flow divider are spot-welded, sharp gaps are easily left, such as... Figure 1 As shown, the shunt ring section mainly bears radial force during operation, which is prone to radial uncoordinated deformation, causing stress concentration at sharp gaps and generating large local stress. This makes it easy for fatigue cracks to form at the weld points. Under vibration, the fatigue cracks will propagate rapidly, resulting in local chipping and damage to aero-engine components.

[0009] This application is made in view of the aforementioned technical deficiencies.

[0010] 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 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

[0011] The purpose of this application is to provide an intermediate casing shunt ring section for an aircraft engine to overcome or mitigate at least one of the known technical defects.

[0012] The technical solution of this application is:

[0013] An intermediate casing shunt ring section for an aero-engine includes:

[0014] The arc-shaped segment has a V-shaped cross-section;

[0015] The reinforcing rib has a U-shaped cross-section and is set inside the arc segment. The two side walls are brazed to the inside of the arc segment. After the brazing filler metal liquefies, it fills the gap between the two side walls of the reinforcing rib and the inside of the arc segment. After curing, it makes the transition between the two side walls of the reinforcing rib and the inside of the arc segment smooth, eliminating the sharp gap between the two side walls of the reinforcing rib and the inside of the arc segment.

[0016] The auxiliary ribs are welded to the inside of the arc-shaped section, forming a vibration damping cavity between them and the reinforcing ribs.

[0017] Damping particles, wrapped in a cylindrical mesh, are filled into the vibration damping cavity;

[0018] An arc-shaped plate with two convex edges, which are welded to the rear end faces of the two side walls of the arc-shaped section by argon arc welding.

[0019] According to at least one embodiment of this application, in the above-mentioned intermediate casing shunt ring section of the aero-engine, the auxiliary rib has a U-shaped cross-section, and its two side walls are brazed to the inner side of the arc section. After the brazing filler metal liquefies, it fills the gap between the two side walls of the auxiliary rib and the inner side of the arc section. After curing, it makes the transition between the two side walls of the auxiliary rib and the inner side of the arc section smooth, eliminating the sharp gap between the two side walls of the auxiliary rib and the inner side of the arc section.

[0020] According to at least one embodiment of this application, in the above-mentioned intermediate casing shunt ring section of the aero-engine, the two side walls of the reinforcing rib and the two side walls of the auxiliary rib are connected.

[0021] According to at least one embodiment of this application, in the aforementioned intermediate casing shunt ring section of the aero-engine, the damping particles are specifically wrapped with multiple cylindrical meshes, and each cylindrical mesh is stacked and placed in the vibration damping cavity.

[0022] According to at least one embodiment of this application, in the aforementioned intermediate casing shunting ring section of the aero-engine, the arc-shaped plate in each shunting ring section is bolted to the connecting ring. Attached Figure Description

[0023] Figure 1 This is a schematic diagram showing the sharp gaps created by spot welding on the inner side of the arc-shaped section and the two side walls of the reinforcing rib in the intermediate casing of an existing aero-engine.

[0024] Figure 2 This is a cross-sectional view of the airflow splitter ring section of the intermediate casing of an aero-engine provided in an embodiment of this application;

[0025] Figure 3 This is a partial structural schematic diagram of the airflow splitter ring section of the intermediate casing of an aero-engine provided in an embodiment of this application;

[0026] Figure 4 This is a schematic diagram showing that the inner side of the arc-shaped section and the two side walls of the reinforcing rib in the intermediate casing of the aero-engine provided in this application embodiment are eliminated by brazing.

[0027] in:

[0028] 1-Arc-shaped segment; 2-Reinforcing rib; 3-Auxiliary rib; 4-Damping particles; 5-Arc-shaped plate.

[0029] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. 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] Brazing is a process that uses a metal material with a lower melting point than the component as a filler metal. The component and the filler metal are heated to a temperature higher than the melting point of the filler metal. The liquid filler metal wets the component, fills the gap between the components, and diffuses between the components to achieve a connection.

[0034] The vibration reduction mechanism of particle damping is that there is a coupled motion between the component and the damping particles inside it. There are relative collisions and frictions between the damping particles and between the damping particles and the component, which can quickly consume the vibration energy of the component and cause the amplitude to decay rapidly. It has a series of advantages such as wide vibration reduction frequency band, good effect, good structural motion stability, small impact force, light added weight, and suitability for harsh environments.

[0035] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.

[0036] A type of intermediate casing shunt ring section for an aero-engine, such as Figures 2-3 As shown, it includes:

[0037] Arc segment 1 has a V-shaped cross-section;

[0038] Reinforcing rib 2, with a U-shaped cross-section, is installed within the arc-shaped segment. Its two side walls are brazed to the inner side of the arc-shaped segment 1, reinforcing the segment 1. The brazing filler metal, after liquefaction, fills the gaps between the two side walls of reinforcing rib 2 and the inner side of arc-shaped segment 1 through capillary action. Simultaneously, the liquid brazing filler metal has wettability, and after solidification, it creates a smooth transition between the two side walls of reinforcing rib 2 and the inner side of arc-shaped segment 1, eliminating sharp gaps between them. Figure 4 As shown, this can reduce the likelihood of fatigue cracks.

[0039] The auxiliary rib 3 is welded to the inside of the arc segment 1, which can further strengthen the arc segment 1 and form a vibration damping cavity between it and the reinforcing rib 2;

[0040] Damping particles 4 are wrapped in a cylindrical mesh, which allows them to be easily filled into the vibration damping cavity for efficient vibration damping and reduces the possibility of fatigue cracks.

[0041] The arc-shaped plate 5 has two protruding edges, which are welded to the rear end faces of the two side walls of the arc-shaped segment 1 by argon arc welding to seal the rear end of the arc-shaped segment 1.

[0042] In some optional embodiments, in the aforementioned intermediate casing shunt ring section of the aero-engine, the auxiliary rib 3 has a U-shaped cross-section, and its two side walls are brazed to the inner side of the arc-shaped section 1. After the brazing filler metal liquefies, it fills the gap between the two side walls of the auxiliary rib 3 and the inner side of the arc-shaped section 1 based on capillary filling effect. At the same time, the liquid brazing filler metal has wettability, and after solidification, it will make the transition between the two side walls of the auxiliary rib 3 and the inner side of the arc-shaped section 1 smooth, eliminating the sharp gap between the two side walls of the auxiliary rib 3 and the inner side of the arc-shaped section 1, which can significantly reduce the possibility of fatigue cracks.

[0043] In some optional embodiments, the two side walls of the reinforcing rib 2 and the two side walls of the auxiliary rib 3 in the above-mentioned intermediate casing of the aero-engine are connected to each other to enhance structural stability.

[0044] In some optional embodiments, in the aforementioned intermediate casing shunt ring section of the aero-engine, the damping particles 4 are specifically wrapped with multiple cylindrical meshes, which are stacked in the vibration damping cavity to constrain the damping particles 4, thereby dispersing the damping particles 4 in the vibration damping cavity and preventing them from being biased to a local area. This enables efficient and uniform vibration damping, and the vibration damping effect can be further enhanced by the mutual friction between the cylindrical meshes.

[0045] In some optional embodiments, in the aforementioned intermediate casing of the aero-engine, the arc-shaped plate 5 in each intermediate casing is bolted to the connecting ring, thereby enabling the intermediate casing to combine the intermediate casing into a stable whole and enhance the stability of the structure.

[0046] 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.

[0047] 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. A flow divider ring section for an aero-engine intermediate casing, characterized in that, include: Arc-shaped segment (1), with a V-shaped cross-section; The reinforcing rib (2) has a U-shaped cross-section and is set in the arc segment. The two side walls are brazed to the inside of the arc segment (1). After the brazing filler metal liquefies, it fills the gap between the two side walls of the reinforcing rib (2) and the inside of the arc segment (1). After solidification, it makes the transition between the two side walls of the reinforcing rib (2) and the inside of the arc segment (1) smooth, eliminating the sharp gap between the two side walls of the reinforcing rib (2) and the inside of the arc segment (1). The auxiliary rib (3) is welded to the inside of the arc segment (1) and forms a vibration damping cavity with the reinforcing rib (2); Damping particles (4) are wrapped in a cylindrical mesh and filled into the vibration damping cavity; The arc plate (5) has two protruding edges, which are welded to the rear end faces of the two side walls of the arc segment (1) by argon arc welding. The damping particles (4) are specifically wrapped with multiple cylindrical meshes, and each cylindrical mesh is stacked in the vibration damping cavity.

2. The aero-engine intermediate casing shunt ring section according to claim 1, characterized in that, The auxiliary rib (3) has a U-shaped cross-section. The two sides are brazed to the inside of the arc segment (1). After the brazing filler metal liquefies, it fills the gap between the two sides of the auxiliary rib (3) and the inside of the arc segment (1). After solidification, it makes the transition between the two sides of the auxiliary rib (3) and the inside of the arc segment (1) smooth, eliminating the sharp gap between the two sides of the auxiliary rib (3) and the inside of the arc segment (1).

3. The aero-engine intermediate casing shunt ring section according to claim 2, characterized in that, Reinforcing ribs (2) on both sides of the wall, auxiliary ribs (3) between the two sides of the wall.

4. The aero-engine intermediate casing shunt ring section according to claim 2, characterized in that, In each diversion ring section, the arc plate (5) is bolted to the connecting ring.

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