Aero-engine rotor wheel disc stator inner ring intercellular gill seal structure

Abstract

The application relates to a honeycomb gasket sealing structure between a rotor wheel disc and a stator inner ring in an aero-engine, which comprises a stator inner ring, the inner side of which is connected with a honeycomb, and the stator inner ring can be assembled or integrally formed; a rotor wheel disc is arranged in the stator inner ring, the outer edge of the rotor wheel disc is provided with an annular tenon groove, and the rotor wheel disc is provided with an installation gap which is communicated with the annular tenon groove; a plurality of sector blocks are provided with tenon heads on the inner sides and are provided with gaskets on the outer edges; the tenon heads on the sector blocks are sequentially clamped into the annular tenon groove through the installation gap on the rotor wheel disc, are spliced into a whole ring structure, and the gaskets on the outer edges and the honeycomb on the inner side of the stator inner ring form a sealing structure; the sector blocks and the rotor wheel disc are circumferentially positioned through pins, wherein the heads of the pins are immersed into the side wall of the rotor wheel disc and are flush with the side wall of the rotor wheel disc, the top ends of the pins are hollow structures, the pins are outwardly expanded into horn shapes, and the top ends of the pins are flush with the side wall of the rotor wheel disc.

Description

Technical Field

[0001] This application belongs to the technical field of honeycomb tooth sealing structure design between the inner rings of the rotor disk stator in aero-engines, specifically relating to a honeycomb tooth sealing structure between the inner rings of the rotor disk stator in aero-engines. Background Technology

[0002] In aero engines, honeycomb grates are often used to seal the space between the rotor disk and the stator inner ring. The grates are formed on the outer edge of the rotor disk, and the overall configuration is simple and the structure is highly reliable. However, after long-term operation, the tips of the grates are easily worn, which damages the sealing effect. Moreover, the tips of the grates are difficult to repair, requiring the replacement of the entire rotor disk, which is a complex and costly process.

[0003] This application is made in view of the aforementioned technical deficiencies.

[0004] 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

[0005] The purpose of this application is to provide a honeycomb tooth sealing structure between the inner rings of the rotor disk stator in an aero-engine, so as to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] A honeycomb tooth sealing structure between the inner rings of the rotor disk stator in an aero-engine includes:

[0008] The inner ring of the stator has a honeycomb structure connected to its inner side, and can be assembled or integrally molded.

[0009] The rotor disc is set inside the inner ring of the stator, and its outer edge has an annular tenon groove and an installation notch communicating with the annular tenon groove.

[0010] Multiple fan-shaped blocks, with tenons on the inner side and comb-shaped teeth on the outer edge;

[0011] The tenons on each sector block are sequentially inserted into the annular tenon groove through the mounting notch on the rotor disc, and spliced ​​together to form a complete ring structure. The grates on the outer edge and the honeycomb on the inner side of the stator ring form a sealing structure.

[0012] Each sector block is circumferentially positioned with respect to the rotor disk by pins. The head of the pin is embedded in the side wall of the rotor disk and is flush with the side wall of the rotor disk. The top of the pin is hollow and expands outward into a trumpet shape, which is also flush with the side wall of the rotor disk.

[0013] According to at least one embodiment of this application, in the above-mentioned honeycomb tooth sealing structure between the inner rings of the rotor disk stator in the aero-engine, there are two sets of mounting notches on the rotor disk, which are symmetrically distributed at 180° on the rotor disk.

[0014] Each set of mounting notches on the rotor disc has three, and each corresponding sector block has three tenons.

[0015] There are two pins, which are symmetrically distributed at 180° on the rotor disc.

[0016] According to at least one embodiment of this application, in the above-mentioned honeycomb grate sealing structure between the inner rings of the rotor disk stator in the aero-engine, the sector angle of each sector block is one-equal part of 360°.

[0017] According to at least one embodiment of this application, in the above-mentioned honeycomb grate sealing structure between the inner rings of the rotor disk stator in the aero-engine, the sector angle of each sector block is 1 / 5 or 1 / 6 of 360°.

[0018] According to at least one embodiment of this application, in the above-mentioned honeycomb tooth sealing structure between the inner rings of the rotor disk stator in the aero-engine, the width of each set of mounting notches on the rotor disk is greater than the distance between the mounting notches.

[0019] The width of the tenon on each sector block is smaller than the spacing between the corresponding mounting notches on the rotor disc;

[0020] The distance from the tenon to the end on each sector block is half the width of the corresponding mounting notch on the rotor disc. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the honeycomb tooth sealing structure between the inner rings of the rotor disk stator in an aero-engine provided in the embodiments of this application;

[0022] Figure 2 This is a schematic diagram of the rotor disk provided in an embodiment of this application;

[0023] Figure 3 This is a schematic diagram of a sector block provided in an embodiment of this application;

[0024] Figure 4 This is a schematic diagram of the assembly of the sector-shaped blocks on the rotor disk according to an embodiment of this application;

[0025] Figure 5 This is a schematic diagram of the various sector blocks assembled onto the rotor disk according to the embodiments of this application;

[0026] Figure 6 This is a schematic diagram of the pin tip before flaring, provided in an embodiment of this application.

[0027] in:

[0028] 1-Stator inner ring; 2-Rotor disc; 3-Sector block; 4-Pin.

[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] The following is in conjunction with the appendix Figures 1 to 6 This application will be described in further detail.

[0034] A honeycomb tooth sealing structure between the inner rings of the rotor disk stator in an aero-engine includes:

[0035] The inner ring 1 of the stator has a honeycomb structure connected to its inner side;

[0036] The rotor disk 2 is set inside the stator inner ring 1, and its outer edge has an annular tenon groove and an installation notch communicating with the annular tenon groove.

[0037] Multiple fan-shaped blocks 3, with tenons on their inner sides and comb-shaped teeth on their outer edges;

[0038] The tenons on each sector block 3 are sequentially inserted into the annular tenon groove through the mounting notch on the rotor disc 2, and are assembled by rotating circumferentially. They are spliced ​​together to form a complete ring structure, and the grating teeth on the outer edge and the honeycomb on the inner side of the stator inner ring 1 form a sealing structure.

[0039] Each sector block 3 is circumferentially positioned with respect to the rotor disk 2 by a pin 4. The head of the pin 4 is embedded in the side wall of the rotor disk 2 and is flush with the side wall of the rotor disk 2. The top of the pin is hollow and expands outward into a trumpet shape, which is also flush with the side wall of the rotor disk 2.

[0040] Regarding the honeycomb tooth sealing structure between the inner rings of the rotor disk stator in the aero-engine disclosed in the above embodiments, those skilled in the art will understand that its design involves forming the teeth on multiple sector blocks 3. Each sector block 3 is installed by inserting it into the annular tenon groove through the mounting notch on the rotor disk 2 via the tenon on its inner side. It is a detachable structure. When the tooth tips of the teeth are worn, only the corresponding sector block 3 needs to be replaced, without the need to replace the entire rotor disk 3. The process is simple and can reduce costs.

[0041] Regarding the honeycomb tooth sealing structure between the inner rings of the rotor disk stator in the aero-engine disclosed in the above embodiments, those skilled in the art will understand that the design uses pins 4 to circumferentially position each sector block 3 and the rotor disk 2. Considering that the axial load on the pin 4 is limited during operation, the top of the pin 4 is designed to be hollow, and anti-detachment is achieved by flaring. This can reduce the weight of the structure while ensuring structural reliability, facilitate assembly, and ensure that it is flush with the side wall of the rotor disk 2, thereby reducing the possibility of collision damage.

[0042] In some optional embodiments, in the above-mentioned honeycomb tooth sealing structure between the inner rings of the rotor disk stator in the aero-engine, there are two sets of mounting notches on the rotor disk 2, which are symmetrically distributed at 180° on the rotor disk 2, so as to reduce the unbalance of the rotor structure.

[0043] Each set of mounting notches on the rotor disc 2 has three notches, and each corresponding sector block 3 has three tenons, which can increase the stability of the assembly of each sector block 3 on the rotor disc 2.

[0044] There are two pins 4, which are symmetrically distributed at 180° on the rotor disk 2 to reduce the imbalance of the rotor structure.

[0045] In some optional embodiments, in the honeycomb grate sealing structure between the inner rings of the rotor disk stator in the above-mentioned aero-engine, the sector angle of each sector block 3 is one-equal part of 360°.

[0046] In some optional embodiments, in the above-described honeycomb grate sealing structure between the inner rings of the rotor disk stator in the aero-engine, the sector angle of each sector block 3 is 1 / 5 or 1 / 6 of 360°.

[0047] In some optional embodiments, in the above-mentioned honeycomb tooth sealing structure between the inner rings of the rotor disk stator in the aero-engine, the width of each set of mounting notches on the rotor disk 2 is greater than the distance between the mounting notches;

[0048] The width of the tenon on each sector block 3 is smaller than the spacing between the corresponding mounting notches on the rotor disc 2, so as to ensure that the tenons on each sector block 3 can easily be inserted into the annular mortise through the mounting notches on the rotor disc 2 to achieve assembly.

[0049] The distance from the tenon to the end of each sector block 3 is half the width of the corresponding mounting notch on the rotor disc 2. This allows the tenon of the sector block 3, which is finally assembled at the mounting notch, to be completely locked in the annular mortise. This helps to increase the mating area between the tenon and the annular mortise, reduce compressive stress, and improve service life.

[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. A honeycomb tooth sealing structure between the inner rings of the rotor disk stator in an aero-engine, characterized in that, include: The inner ring of the stator (1) has a honeycomb structure connected to its inner side; The rotor disk (2) is set inside the stator inner ring (1), and its outer edge has an annular tenon groove and an installation notch communicating with the annular tenon groove; Multiple fan-shaped blocks (3) have tenons on their inner sides and comb teeth formed on their outer edges; The tenons on each sector block (3) are inserted into the annular tenon groove through the installation notch on the rotor disc (2) and spliced ​​together to form a complete ring structure. The grating teeth on the outer edge and the honeycomb on the inner side of the stator inner ring (1) form a sealing structure. Each sector block (3) is circumferentially positioned with respect to the rotor disk (2) by a pin (4). The head of the pin (4) is inserted into the side wall of the rotor disk (2) and is flush with the side wall of the rotor disk (2). The top is hollow and expands outward into a trumpet shape, and is flush with the side wall of the rotor disk (2). The width of each set of mounting notches on the rotor disc (2) is greater than the distance between the mounting notches; The width of the tenon on each sector block (3) is smaller than the spacing between the corresponding mounting notches on the rotor disc (2); The distance from the tenon to the end of each sector block (3) is half the width of the corresponding mounting notch on the rotor disc (2).

2. The honeycomb tooth sealing structure between the inner rings of the rotor disk stator in an aero-engine according to claim 1, characterized in that, There are two sets of mounting notches on the rotor disk (2), which are symmetrically distributed at 180° on the rotor disk (2); There are three mounting notches on each set of rotor discs (2), and three tenons on each corresponding sector block (3); There are two pins (4), which are symmetrically distributed at 180° on the rotor disk (2).

3. The honeycomb tooth sealing structure between the inner rings of the rotor disk stator in an aero-engine according to claim 1, characterized in that, The sector angle of each sector block (3) is one-equal part of 360°.

4. The honeycomb tooth sealing structure between the inner rings of the rotor disk stator in an aero-engine according to claim 1, characterized in that, The sector angle of each sector block (3) is 1 / 5 or 1 / 6 of 360°.

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