Turbine seal and aircraft engine

Abstract

This invention relates to a turbine sealing device and an aero-engine. The turbine sealing device includes a turbine blade (1), a toothed disc (2), a honeycomb structure (3), and an anti-wear device. The toothed disc (2) includes a disc body (21) and sealing teeth (22) disposed on the side of the disc body (21) near the turbine blade (1). The honeycomb structure (3) is disposed on the side of the turbine blade (1) near the toothed disc (2). The anti-wear device is disposed between the turbine blade (1) and the toothed disc (2). The anti-wear device is configured to provide a force that causes the honeycomb structure (3) and the sealing teeth (22) to move away from each other when they are close together. The aero-engine includes a turbine sealing device. The anti-wear device of this invention can provide a force that causes the honeycomb structure and the sealing teeth to move away from each other when they are close together, thereby preventing the honeycomb structure and the sealing teeth from rubbing against each other.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more particularly to a turbine sealing device and an aero-engine. Background Technology

[0002] In civil aviation turbofan engines, air is typically drawn from the compressor, flowing through pipes or internal compressor structures such as discs, shafts, bores, and grates, before reaching the turbine end. After cooling and sealing the turbine and its bearings, the air is discharged into the mains or into the bearing cavity. The grates are a crucial sealing structure; by reducing airflow and pressure, they achieve a seal.

[0003] Currently, in mainstream aero-engine designs, a serrated structure is typically installed below the turbine guide vane to increase the pressure difference between the front and rear sealing chambers of the guide vane, thereby achieving a sealing effect at the front and rear rims of the guide vane. However, due to structural limitations, the honeycomb ring under the guide vane is difficult to design as a single ring structure. It generally needs to be welded to the underside of the guide vane in sections and then assembled to form the honeycomb ring. Even under conditions where consistent machining accuracy is ensured, due to assembly and gravity, it is difficult to guarantee that the assembled honeycomb ring is a standard ring structure. After operation, the serrated teeth and the honeycomb ring are prone to uneven wear, affecting the sealing effect.

[0004] It should be noted that the information disclosed in the background section of this invention is intended only to enhance the understanding of the overall background of this invention, and should not be construed as an admission or in any way implying that such information constitutes prior art known to those skilled in the art. Summary of the Invention

[0005] This invention provides a turbine sealing device and an aero-engine, which can effectively alleviate the friction between the honeycomb structure and the sealing teeth.

[0006] According to one aspect of the present invention, a turbine sealing device is provided, comprising:

[0007] Turbine blades;

[0008] A toothed disc includes a disc body and sealing teeth disposed on the side of the disc body near the turbine blades;

[0009] A honeycomb structure is disposed on the side of the turbine blades near the grating disk; and

[0010] An anti-wear device is disposed between the turbine blades and the grate disc. The anti-wear device is configured to provide a force that causes the honeycomb structure and the sealing grate to move away from each other when they are close to each other.

[0011] In some embodiments, the anti-wear device includes a magnetic device configured to generate a magnetic force that repels the honeycomb structure and the sealing grating when they come into close proximity.

[0012] In some embodiments, the magnetic device includes a first magnet disposed on a turbine blade and a second magnet disposed on a toothed disc, wherein the first magnet and the second magnet have the same magnetic poles.

[0013] In some embodiments, the first magnet is disposed between the turbine blade and the honeycomb structure.

[0014] In some embodiments, a mounting groove is provided on the disk near the sealing teeth, and the second magnet is disposed in the mounting groove.

[0015] In some embodiments, the first magnet is arc-shaped, and a plurality of first magnets are arranged at circumferential intervals; and / or, the second magnet is ring-shaped.

[0016] In some embodiments, the first magnet includes a first surface, the second magnet includes a second surface, and the first and second surfaces are disposed opposite to each other.

[0017] In some embodiments, both the first magnet and the second magnet are permanent magnets.

[0018] In some embodiments, the first magnet is welded to the turbine blade; and / or, the second magnet is welded to the disk.

[0019] In some embodiments, at least one of the first magnet and the second magnet includes an electromagnetic coil, and the turbine sealing device further includes a power supply, a switching valve, and a control device. The switching valve is disposed on the connection line between the power supply and the electromagnetic coil, and the control device is signal-connected to the switching valve. The control device is used to control the opening and closing of the switching valve.

[0020] In some embodiments, the turbine sealing device further includes a detection device connected to the control device, the detection device being used to detect the distance between the cellular structure and the sealing teeth.

[0021] According to another aspect of the invention, an aircraft engine is provided, including the turbine sealing device described above.

[0022] Based on the above technical solution, the embodiments of the present invention provide an anti-wear device between the turbine blade and the sealing grating. When the honeycomb structure installed on the turbine blade and the sealing grating on the sealing grating are close to each other, the anti-wear device can provide a force to keep the honeycomb structure and the sealing grating away from each other, thereby avoiding the honeycomb structure and the sealing grating from rubbing against each other and effectively improving the service life of the sealing device. Attached Figure Description

[0023] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this application, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings:

[0024] Figure 1 This is a schematic diagram of one embodiment of the turbine sealing device of the present invention.

[0025] Figure 2 This is a partial structural schematic diagram of one embodiment of the turbine sealing device of the present invention.

[0026] In the picture:

[0027] 1. Turbine blade; 2. Grate disc; 21. Disc body; 22. Sealing grate; 23. Mounting groove; 3. Honeycomb structure; 4. Fixing ring; 5. Front casing; 6. Connecting part; 7. First magnet; 8. Second magnet. Detailed Implementation

[0028] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0029] In the description of this invention, it should be understood that the terms "center," "lateral," "longitudinal," "front," "rear," "left," "right," "upper," "lower," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this invention.

[0030] like Figure 1 and Figure 2 As shown, in some embodiments of the turbine sealing device provided by the present invention, the turbine sealing device includes a turbine blade 1, a toothed disc 2, a honeycomb structure 3, and an anti-wear device. The toothed disc 2 includes a disc body 21 and sealing teeth 22 disposed on the side of the disc body 21 near the turbine blade 1. The honeycomb structure 3 is disposed on the side of the turbine blade 1 near the toothed disc 2. The anti-wear device is disposed between the turbine blade 1 and the toothed disc 2. The anti-wear device is configured to provide a force that causes the honeycomb structure 3 and the sealing teeth 22 to move away from each other when they approach each other.

[0031] In this embodiment of the invention, an anti-wear device is provided between the turbine blade 1 and the grate disk 2. When the honeycomb structure 3 installed on the turbine blade 1 and the sealing grate 22 on the grate disk 2 approach each other, the anti-wear device can provide a force that keeps the honeycomb structure 3 and the sealing grate 22 away from each other, thereby avoiding collision and wear between the honeycomb structure 3 and the sealing grate 22 and effectively improving the service life of the sealing device.

[0032] There are several ways to implement anti-wear devices, such as using elastic devices or magnetic devices.

[0033] In some embodiments, the anti-wear device includes a magnetic device configured to generate a magnetic force that causes the honeycomb structure 3 and the sealing teeth 22 to repel each other when they come close together.

[0034] As the distance between the honeycomb structure 3 and the sealing teeth 22 gradually decreases, the magnetic device will gradually generate a magnetic force that causes the honeycomb structure 3 and the sealing teeth 22 to repel each other, thereby moving the honeycomb structure 3 and the sealing teeth 22 away from each other and preventing them from rubbing against each other.

[0035] In some embodiments, the magnetic device includes a first magnet 7 disposed on the turbine blade 1 and a second magnet 8 disposed on the grate disk 2, wherein the first magnet 7 and the second magnet 8 have the same magnetic poles. By setting the first magnet 7 and the second magnet 8 with the same magnetic poles, according to the principle that opposite poles attract and like poles repel, when the honeycomb structure 3 and the sealing grate 22 approach each other, the distance between the first magnet 7 and the second magnet 8 will gradually decrease, and the repulsive force between the first magnet 7 and the second magnet 8 will gradually increase, so as to maintain the distance between the first magnet 7 and the second magnet 8 and avoid the honeycomb structure 3 and the sealing grate 22 from rubbing against each other.

[0036] In some embodiments, the first magnet 7 is disposed between the turbine blade 1 and the honeycomb structure 3. Disposing the first magnet 7 between the turbine blade 1 and the honeycomb structure 3 can provide a stable mounting position for the first magnet 7 and can prevent the first magnet 7 from squeezing the honeycomb structure, thus affecting the function and stability of the honeycomb structure.

[0037] In some embodiments, a mounting groove 23 is provided on the disc body 21 near the sealing teeth 22, and the second magnet 8 is disposed in the mounting groove 23. By providing the mounting groove 23, installation space can be provided for the second magnet 8, avoiding compression of the second magnet 8 and effectively ensuring the safety of the second magnet 8.

[0038] In some embodiments, the mounting slot 23 has an opening, and the opening has an openable and closable closure structure. After the second magnet 8 is inserted into the mounting slot 23 through the opening, the closure structure can be closed to seal the mounting slot 23 and prevent the second magnet 8 from falling out.

[0039] In other embodiments, the opening can be welded shut after the second magnet 8 is inserted into the mounting slot 23 through the opening to prevent the second magnet 8 from falling out.

[0040] In some embodiments, the first magnet 7 is arc-shaped, and a plurality of first magnets 7 are arranged at circumferential intervals; and / or, the second magnet 8 is ring-shaped.

[0041] The first magnet 7 is set to be arc-shaped, which can match the segmented honeycomb structure 3, so that each first magnet 7 is set to correspond with the honeycomb structure 3.

[0042] The second magnet 8 is set as a ring, which matches the ring structure of the disk body 21. Correspondingly, the mounting groove 23 can also be ring-shaped.

[0043] In some embodiments, the first magnet 7 includes a first surface, and the second magnet 8 includes a second surface, with the first and second surfaces disposed opposite to each other. By disposing the first and second surfaces opposite to each other, a mutual repulsive force can be formed between the first magnet 7 and the second magnet 8 when they approach each other, avoiding the impact of the lack of opposing surfaces on the generation of the mutual repulsive force and the function of preventing wear.

[0044] In some embodiments, both the first magnet 7 and the second magnet 8 are permanent magnets. Using permanent magnets for both the first magnet 7 and the second magnet 8 improves ease of operation and prevents the first magnet 7 and the second magnet 8 from failing and thus unable to provide repulsive force.

[0045] In other embodiments, at least one of the first magnet 7 and the second magnet 8 includes an electromagnetic coil. The turbine sealing device also includes a power supply, a switching valve, and a control device. The switching valve is disposed on the connection line between the power supply and the electromagnetic coil. The control device is signal-connected to the switching valve and is used to control the opening and closing of the switching valve to control the electrical connection or disconnection between the power supply and the electromagnetic coil. The advantage of this arrangement is that the electrical connection or disconnection between the power supply and the electromagnetic coil can be controlled by the controller to connect the power supply and the electromagnetic coil when it is necessary to provide a force to move the honeycomb structure 3 and the sealing teeth 22 away from each other, and to disconnect the electrical connection between the power supply and the electromagnetic coil when it is not necessary to provide a force to move the honeycomb structure 3 and the sealing teeth 22 away from each other.

[0046] Furthermore, the turbine sealing device also includes a detection device connected to the control device. This detection device is used to detect the distance between the honeycomb structure 3 and the sealing grates 22. By setting the detection device, when the distance between the honeycomb structure 3 and the sealing grates 22 is detected to be less than or equal to a preset distance, the control device can connect the power supply and the electromagnetic coil; conversely, when the distance between the honeycomb structure 3 and the sealing grates 22 is detected to be greater than the preset distance, the control device can disconnect the power supply and the electromagnetic coil.

[0047] In some embodiments, the first magnet 7 is welded to the turbine blade 1; and / or, the second magnet 8 is welded to the disk 21. Welding the first magnet 7 to the turbine blade 1 improves the stability of the first magnet 7 and prevents it from shifting. Welding the second magnet 8 to the disk 21 improves the stability of the second magnet 8 and prevents it from shifting.

[0048] In one embodiment of the present invention, such as Figure 1 As shown, turbine blade 1 is a guide vane, and a honeycomb structure 3 is provided below turbine blade 1. The grating disk 2 below turbine blade 1 includes a disk body 21 and sealing grates 22 disposed on the disk body 21. A fixing ring 4 for sealing is provided above turbine blade 1, a front casing 5 for fixing turbine blade 1 is provided in front of turbine blade 1, and a connecting part 6 is provided behind turbine blade 1. The connecting part 6 is fixed to the rear casing by a bolt structure. Among them, the grating disk 2 is a complete ring structure, and turbine blade 1 is a discrete structure. It is composed of multiple sets of guide vanes forming a ring structure, thereby forming a complete ring honeycomb with multiple honeycomb structures 3.

[0049] like Figure 2 As shown, an arc-shaped first magnet 7 is placed below each set of turbine blades 1 and above the honeycomb structure 3. An annular mounting groove 23 is provided below the sealing grates 22 of the grate disc 2. An annular second magnet 8 is placed in the mounting groove 23, and the mounting groove 23 is then welded to enclose the second magnet 8 within it. The first magnet 7 and the second magnet 8 are of the same polarity, and their magnetic surfaces are arranged opposite each other.

[0050] Due to assembly and gravity, it is difficult to guarantee that the assembled honeycomb ring is a standard ring structure. After operation, the grating teeth and the honeycomb ring are prone to uneven wear, affecting the sealing effect. In the embodiment provided by the present invention, by setting the first magnet 7 and the second magnet 8, when the engine is running, due to the influence of gravity and thermal imbalance, the gap between the honeycomb structure 3 under different turbine blades 1 and the sealing grating teeth 22 of the grating disk 2 is inconsistent. The closer the distance between the honeycomb structure 3 of a certain turbine blade 1 and the corresponding sealing grating teeth 22, the greater the force it receives. This can appropriately alleviate the influence of local uneven wear, eliminate the effects of assembly and gravity, and ensure the roundness of the honeycomb structure under the turbine blade as much as possible, reducing the friction between the sealing grating teeth and the honeycomb structure.

[0051] Based on the turbine sealing device described above, the present invention also proposes an aero-engine that includes the turbine sealing device described above.

[0052] The positive technical effects of the turbine sealing device in the above embodiments are also applicable to aero engines, and will not be elaborated here.

[0053] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of the present invention or equivalent substitutions can still be made to some technical features without departing from the principle of the present invention, and such modifications and equivalent substitutions should all be covered within the scope of the technical solutions claimed in the present invention.

Claims

1. A turbine sealing device, characterized in that, include: Turbine blade (1); The toothed disc (2) includes a disc body (21) and sealing teeth (22) disposed on the side of the disc body (21) near the turbine blade (1). A honeycomb structure (3) is disposed on the side of the turbine blade (1) near the toothed disc (2); A wear-resistant device is disposed between the turbine blade (1) and the toothed disc (2). The wear-resistant device includes a magnetic device, which includes a first magnet (7) disposed on the turbine blade (1) and a second magnet (8) disposed on the toothed disc (2). The first magnet (7) and the second magnet (8) have the same magnetic poles. The magnetic device is configured to generate a magnetic force that causes the honeycomb structure (3) and the sealing toothed disc (22) to repel each other when the honeycomb structure (3) and the sealing toothed disc (22) are close to each other, so as to provide a force that causes the honeycomb structure (3) and the sealing toothed disc (22) to move away from each other when the honeycomb structure (3) and the sealing toothed disc (22) are close to each other. At least one of the first magnet (7) and the second magnet (8) includes an electromagnetic coil. power supply; A switching valve is installed on the connection line between the power supply and the electromagnetic coil; A detection device for detecting the distance between the honeycomb structure (3) and the sealing teeth (22); and A control device is connected to the switching valve and the detection device. The control device is used to control the opening and closing of the switching valve to control the electrical connection or disconnection between the power supply and the electromagnetic coil. When the detection device detects that the distance between the honeycomb structure (3) and the sealing teeth (22) is less than or equal to a preset distance, the control device is configured to control the electrical connection between the power supply and the electromagnetic coil. When the detection device detects that the distance between the honeycomb structure (3) and the sealing teeth (22) is greater than the preset distance, the control device is configured to control the electrical connection between the power supply and the electromagnetic coil to be disconnected.

2. The turbine sealing device according to claim 1, characterized in that, The first magnet (7) is disposed between the turbine blade (1) and the honeycomb structure (3).

3. The turbine sealing device according to claim 1, characterized in that, The disk body (21) is provided with a mounting groove (23) near the sealing teeth (22), and the second magnet (8) is disposed in the mounting groove (23).

4. The turbine sealing device according to claim 1, characterized in that, The first magnet (7) is arc-shaped, and a plurality of the first magnets (7) are arranged at intervals along the circumference; and / or, the second magnet (8) is ring-shaped.

5. The turbine sealing device according to claim 1, characterized in that, The first magnet (7) includes a first surface, and the second magnet (8) includes a second surface, with the first surface and the second surface disposed opposite to each other.

6. The turbine sealing device according to claim 1, characterized in that, Both the first magnet (7) and the second magnet (8) are permanent magnets.

7. The turbine sealing device according to claim 1, characterized in that, The first magnet (7) is welded to the turbine blade (1); and / or the second magnet (8) is welded to the disk (21).

8. An aircraft engine, characterized in that, Includes the turbine sealing device as described in any one of claims 1 to 7.

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