A turbine rotor blade

Abstract

The present application provides a turbine rotor blade, belonging to the technical field of gas turbines, including a blade body and a blade crown. The side of the blade crown located on the suction side of the blade body is the first side, and the side of the blade crown located on the pressure side of the blade body is the second side. A sealing labyrinth structure is provided on the side of the blade crown facing away from the blade body. The sealing labyrinth structure includes a strip-shaped first labyrinth tooth and a second labyrinth tooth. One end of the first labyrinth tooth and one end of the second labyrinth tooth are both within the range corresponding to the blade tip of the blade body. The first labyrinth tooth extends from within the range of the blade tip towards the first side, and the second labyrinth tooth extends from within the range of the blade tip towards the second side. In the axial direction of the turbine, there is a gap between the ends of the first labyrinth tooth and the second labyrinth tooth within the range of the blade tip. In the circumferential direction of the turbine, at least a part of the ends of the first labyrinth tooth and the second labyrinth tooth within the range of the blade tip overlap each other. The present application reduces the stress generated by the bending of the labyrinth structure due to the blade crown, and improves the performance and service life of the blade.

Description

Technical Field

[0001] This application relates to the field of gas turbines, and particularly to a turbine rotor blade. Background Art

[0002] A gas turbine is a mechanical device that utilizes the energy of gas to generate power. In a gas turbine, the gas is compressed by a compressor and then mixed with air, and burns at a high temperature in a combustion chamber. The high-temperature gas generated by combustion flows through a turbine, causing the turbine to rotate, and thus driving the rotation of the entire rotor through a main shaft. The working blades of the turbine in many engines, especially relatively advanced engines, often adopt a crowned structure to improve turbine efficiency and solve vibration problems. This is because, after the blades are crowned, the leakage of gas from the blade basin to the blade back at the blade tip can be reduced, the secondary loss can be lowered, and the efficiency can be improved. There are labyrinth teeth for sealing on the crown to prevent the leakage of gas from the front to the back in the blade tip clearance, further reducing the leakage loss.

[0003] As Figure 1 shown, currently there are usually two parallel continuous labyrinth teeth 5 on the crown 2 of the turbine blade. Each continuous labyrinth tooth 5 spans across the entire crown in the circumferential direction to ensure its sealing effect on the gas. Under the action of high rotational speed, due to the mass of the crown itself, the crown will undergo bending deformation. For this traditional labyrinth tooth structure, the bent crown will exert extrusion on the labyrinth tooth structure on the crown, resulting in concentrated stress on the continuous labyrinth tooth 5. This phenomenon of stress concentration will greatly affect the performance and service life of the blade. Summary of the Invention

[0004] In view of this, this application provides a turbine rotor blade, which solves the problems in the prior art, reduces the stress generated by the crown bending on the labyrinth tooth structure, and improves the performance and service life of the blade.

[0005] A turbine rotor blade provided by this application adopts the following technical solution:

[0006] A turbine rotor blade includes a blade body and a crown connected to the blade tip of the blade body. The side of the crown located on the side of the blade back of the blade body is the first side, and the side of the crown located on the side of the blade basin of the blade body is the second side. A sealing labyrinth tooth structure is provided on the side of the crown facing away from the blade body. The sealing labyrinth tooth structure includes a strip-shaped first labyrinth tooth and a second labyrinth tooth. One end of the first labyrinth tooth and one end of the second labyrinth tooth are both within the range of the blade tip corresponding to the blade body. The first labyrinth tooth extends from the range of the blade tip towards the first side, and the second labyrinth tooth extends from the range of the blade tip towards the second side;

[0007] Wherein, in the axial direction of the turbine, there is a gap between the ends of the first labyrinth seal and the second labyrinth seal within the tip range; in the circumferential direction of the turbine, the ends of the first labyrinth seal and the second labyrinth seal within the tip range at least partially overlap each other.

[0008] Optionally, the extending directions of the first labyrinth seal and the second labyrinth seal are parallel to each other.

[0009] Optionally, the first side and the second side are parallel to each other, the first end face of the end of the first labyrinth seal within the tip range and the second end face of the end of the second labyrinth seal within the tip range are parallel to the first side, and the end faces of the first labyrinth seal and the second labyrinth seal away from the tip are parallel to the first side.

[0010] Optionally, in the circumferential direction of the turbine, there is a gap between the sides of the first end face and the second end face that are close to each other, the side of the first end face away from the second end face coincides with the area of the second labyrinth seal, and the side of the second end face away from the first end face coincides with the area of the first labyrinth seal.

[0011] Optionally, in the circumferential direction of the turbine, the distance between the sides of the first end face and the second end face that are close to each other is less than the length of the first end face or the second end face.

[0012] Optionally, the extending directions of the first labyrinth seal and the second labyrinth seal are parallel to the circumferential section of the turbine.

[0013] Optionally, a plurality of the seal labyrinth seal structures are provided on the shroud, and the plurality of seal labyrinth seal structures are arranged at intervals in the axial direction of the turbine.

[0014] In summary, the present application includes the following beneficial technical effects:

[0015] This application divides an entire labyrinth seal into two segments, and there is a gap between the ends of the first labyrinth seal and the second labyrinth seal within the tip range in the axial direction of the turbine; that is, when viewed from a direction perpendicular to the airflow direction, there is a gap between the ends of the first labyrinth seal and the second labyrinth seal that are close to each other. When the shroud deforms, in the circumferential direction of the turbine, the ends of the first labyrinth seal and the second labyrinth seal within the tip range approach each other. During the approaching process, due to the gap between the first labyrinth seal and the second labyrinth seal in the axial direction of the turbine, the ends of the first labyrinth seal and the second labyrinth seal within the tip range are staggered, and the first labyrinth seal and the second labyrinth seal will not squeeze each other and can deform freely, thereby reducing the stress generated by the bending of the shroud in the labyrinth seal structure. In the circumferential direction of the turbine, at least part of the ends of the first labyrinth seal and the second labyrinth seal within the tip range overlap each other; that is, when viewed along the direction parallel to the airflow direction, there is an overlapping area between the ends of the first labyrinth seal and the second labyrinth seal that are close to each other, ensuring the continuity of a labyrinth seal structure in the circumferential direction of the turbine, thereby guaranteeing the sealing effect of the labyrinth seal and preventing gas from leaking from front to back. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of this application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0017] Figure 1 Schematic diagram of the shroud structure in the prior art;

[0018] Figure 2 Partial structural schematic diagram of the blade of this application near the tip;

[0019] Figure 3 Schematic diagram of the labyrinth seal structure and the shroud in Embodiment 1 of this application;

[0020] Figure 4 Schematic diagram of the labyrinth seal structure and the shroud in Embodiment 2 of this application.

[0021] Description of the reference numerals: 1, blade body; 2, shroud; 21, first side; 22, second side; 4, labyrinth seal structure; 41, first labyrinth seal; 42, second labyrinth seal; 43, first end face; 44, second end face; 5, continuous labyrinth seal. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0022] The embodiments of this application will be described in detail below with reference to the drawings.

[0023] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand the other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all embodiments. The present application can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope protected by the present application.

[0024] It should be noted that the following describes various aspects of the embodiments within the scope of the appended claims. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is illustrative only. Based on the present application, those skilled in the art should understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. Additionally, this device and / or this method can be implemented using other structures and / or functions in addition to one or more of the aspects described herein.

[0025] It should also be noted that the drawings provided in the following embodiments only illustrate the basic concept of the present application schematically. The components shown in the drawings only show the components related to the present application and are not drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and ratio of each component in its actual implementation can be arbitrarily changed, and the component layout type may also be more complex.

[0026] In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0027] An embodiment of the present application provides a turbine rotor blade.

[0028] Such as Figure 2 and Figure 3As shown in the figure, a turbine rotor blade includes a blade body 1, a shroud 2 connected to the tip of the blade body 1, and a tenon. The tenon is connected to one end of the blade body 1 away from the tip. The side of the shroud 2 located on the suction side of the blade body 1 is the first side 21, and the side of the shroud 2 located on the pressure side of the blade body 1 is the second side 22. A sealing labyrinth structure 4 is provided on the side of the shroud 2 facing away from the blade body 1. The sealing labyrinth structure 4 includes a strip-shaped first labyrinth tooth 41 and a second labyrinth tooth 42. One end of the first labyrinth tooth 41 and one end of the second labyrinth tooth 42 are both within the range of the tip of the blade body 1 corresponding to the shroud 2. The first labyrinth tooth 41 extends from within the range of the tip towards the first side 21, and the second labyrinth tooth 42 extends from within the range of the tip towards the second side 22. Among them, in the axial direction of the turbine, there is a gap between the ends of the first labyrinth tooth 41 and the second labyrinth tooth 42 within the range of the tip. In the circumferential direction of the turbine, at least part of the ends of the first labyrinth tooth 41 and the second labyrinth tooth 42 within the range of the tip overlap each other.

[0029] During the high-speed movement of the blade, since the middle of the shroud 2 is connected to the tip, and the parts of the shroud 2 outside the tip range, close to the first side 21 and the second side 22, are cantilever structures. When the shroud 2 is subjected to centrifugal force, in the circumferential direction of the turbine, the first side 21 and the second side 22 of the shroud 2 will deflect outward compared with the part connecting the tip, making the shape of the part of the shroud 2 connecting the tip closer to the turbine axis than the two sides. That is, the shroud 2 is prone to deformation in the axial direction of the turbine and the first side 21 and the second side 22 bend away from the turbine axis.

[0030] In this application, an entire labyrinth tooth is divided into two sections, and there is a gap between the ends of the first labyrinth tooth 41 and the second labyrinth tooth 42 within the range of the tip in the axial direction of the turbine; that is, when viewed from the direction perpendicular to the airflow direction, there is a gap between the ends of the first labyrinth tooth 41 and the second labyrinth tooth 42 that are close to each other. When the shroud 2 deforms, in the circumferential direction of the turbine, the ends of the first labyrinth tooth 41 and the second labyrinth tooth 42 within the range of the tip approach each other. During the approaching process, due to the gap between the first labyrinth tooth 41 and the second labyrinth tooth 42 in the axial direction of the turbine, the ends of the first labyrinth tooth 41 and the second labyrinth tooth 42 within the range of the tip are staggered, and the first labyrinth tooth 41 and the second labyrinth tooth 42 will not squeeze each other and can deform freely, thereby reducing the stress generated by the bending of the sealing labyrinth structure 4 due to the bending of the shroud 2. In the circumferential direction of the turbine, at least part of the ends of the first labyrinth tooth 41 and the second labyrinth tooth 42 within the range of the tip overlap each other; that is, when viewed along the direction parallel to the airflow direction, there is an overlapping area part at the ends of the first labyrinth tooth 41 and the second labyrinth tooth 42 that are close to each other, ensuring the continuity of a sealing labyrinth structure 4 in the circumferential direction of the turbine, thereby ensuring the sealing effect of the sealing labyrinth and preventing gas from leaking from front to back.

[0031] The extending directions of the first labyrinth teeth 41 and the second labyrinth teeth 42 are parallel to each other, and the extending directions of the first labyrinth teeth 41 and the second labyrinth teeth 42 are parallel to the circumferential section of the turbine. The change in the interval between the first labyrinth teeth 41 and the second labyrinth teeth 42 when the shroud 2 deforms can be reduced, and it can be avoided that the ends of the first labyrinth teeth 41 and the second labyrinth teeth 42 start to abut after a certain deformation of the shroud 2; the degree of free deformation of the first labyrinth teeth 41 and the second labyrinth teeth 42 can be further improved.

[0032] Example 1, as Figure 3 shown, the first end face 43 of the end of the first labyrinth teeth 41 within the blade tip range and the second end face 44 of the end of the second labyrinth teeth 42 within the blade tip range are perpendicular to the extending direction of the first labyrinth teeth 41, and the interval between the first end face 43 and the second end face 44 is: there is an interval between the ends of the first labyrinth teeth 41 and the second labyrinth teeth 42 within the blade tip range in the axial direction of the turbine.

[0033] Example 2, as Figure 4 shown, the first side edge 21 and the second side edge 22 are parallel to each other, and the first end face 43 of the end of the first labyrinth teeth 41 within the blade tip range and the second end face 44 of the end of the second labyrinth teeth 42 within the blade tip range are parallel to the first side edge 21. The two end faces of the first labyrinth teeth 41 and the second labyrinth teeth 42 are parallel to the first side edge 21 or the second side edge 22, so that the structures at both ends of the seal labyrinth teeth structure 4 are consistent with the structure of the shroud 2, improving the sealing performance. The end faces of the first labyrinth teeth 41 and the second labyrinth teeth 42 that are close to each other are also parallel to the first side edge 21, that is, the two end faces of the first labyrinth teeth 41 and the two end faces of the second labyrinth teeth 42 are parallel to each other, which is convenient for the machining of the first labyrinth teeth 41 and the second labyrinth teeth 42.

[0034] In the circumferential direction of the turbine, a gap is provided between the side edges of the first end face 43 and the second end face 44 that are close to each other, which is convenient for the rounding machining of the parts of the first end face 43 and the second end face 44 that are close to each other. The side of the first end face 43 away from the second end face 44 coincides with the area of the second labyrinth teeth 42, and the side of the second end face 44 away from the first end face 43 coincides with the area of the first labyrinth teeth 41, ensuring the continuity of the seal labyrinth teeth structure 4.

[0035] In the circumferential direction of the turbine, the distance between the side edges of the first end face 43 and the second end face 44 that are close to each other is less than the length of the first end face 43 or the second end face 44.

[0036] In one embodiment, a plurality of the seal labyrinth teeth structures 4 are provided on the shroud 2, and the plurality of seal labyrinth teeth structures 4 are arranged at intervals in the axial direction of the turbine.

[0037] As described above, it is only the specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A turbine rotor blade, comprising a blade body and a shroud connected to the tip of the blade body, characterized in that, The side of the shroud located on the suction side of the blade is the first side, and the side of the shroud located on the pressure side of the blade is the second side. A sealing labyrinth structure is provided on the side of the shroud facing away from the blade. The sealing labyrinth structure includes strip-shaped first labyrinth teeth and second labyrinth teeth. One end of the first labyrinth teeth and one end of the second labyrinth teeth are both within the range corresponding to the blade tip of the blade. The first labyrinth teeth extend from the range of the blade tip towards the first side, and the second labyrinth teeth extend from the range of the blade tip towards the second side; Wherein, in the axial direction of the turbine, there is a gap between the ends of the first labyrinth teeth and the second labyrinth teeth within the range of the blade tip; in the circumferential direction of the turbine, the ends of the first labyrinth teeth and the second labyrinth teeth within the range of the blade tip at least partially overlap each other.

2. The turbine rotor blade according to claim 1, characterized in that, The extending directions of the first labyrinth teeth and the second labyrinth teeth are parallel to each other.

3. The turbine rotor blade according to claim 1, characterized in that, The first side and the second side are parallel to each other. The first end face of the end of the first labyrinth teeth within the range of the blade tip and the second end face of the end of the second labyrinth teeth within the range of the blade tip are parallel to the first side, and the end faces of the first labyrinth teeth and the second labyrinth teeth away from the blade tip are parallel to the first side.

4. The turbine rotor blade according to claim 3, characterized in that, In the circumferential direction of the turbine, a gap is provided between the sides of the first end face and the second end face that are close to each other. The side of the first end face away from the second end face coincides with the area of the second labyrinth teeth, and the side of the second end face away from the first end face coincides with the area of the first labyrinth teeth.

5. The turbine rotor blade according to claim 4, characterized in that, In the circumferential direction of the turbine, the distance between the sides of the first end face and the second end face that are close to each other is less than the length of the first end face or the second end face.

6. The turbine rotor blade according to claim 1, characterized in that, The extending directions of the first labyrinth teeth and the second labyrinth teeth are parallel to the circumferential section of the turbine.

7. The turbine rotor blade according to claim 2, characterized in that, A plurality of the sealing labyrinth structures are provided on the shroud, and the plurality of sealing labyrinth structures are arranged at intervals in the axial direction of the turbine.

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