Turbine blade fixing structure

Abstract

The invention belongs to the field of turbine rotor blades, and particularly relates to a turbine blade fixing structure. According to the structure, an annular groove is formed in the disc edge of the turbine disc; a plurality of turbine rotor blades are arranged in the circumferential direction of the turbine disc, tenons of the turbine rotor blades are installed in mortises of the turbine disc, edge plates of the turbine rotor blades are provided with grooves, the axial positions of the grooves and the annular grooves are opposite, and the grooves of the turbine rotor blades and the annular grooves of the turbine disc jointly form an annular space; the blade baffles are in a fan shape, the multiple blade baffles are arranged in the circumferential direction of the annular space, each blade baffle comprises a radial outer side baffle section, a radial middle baffle section and a radial inner side baffle section, the radial outer side baffle sections and the radial inner side baffle sections are each provided with a bending angle, and small holes for cooling airflow to pass through are formed in the radial middle baffle sections. The turbine rotor blade can be axially fixed on the turbine disc in a narrow space, the size of an engine is greatly reduced, and the mass of the engine is reduced.

Description

Technical Field

[0001] The present application belongs to the field of turbine rotor blades, and in particular relates to a turbine blade fixing structure. Background Art

[0002] The turbine rotor blade is one of the important parts that determines the life of the engine. When the turbine rotor blade is installed in the tenon of the turbine disc, a fixing structure must be used to firmly fix the blade to prevent the blade from flying out of the tenon during the operation of the engine and penetrating the casing, causing serious or even catastrophic consequences. It is very important to reasonably design the turbine rotor blade fixing structure to ensure the reliable operation of the engine.

[0003] The existing turbine rotor blade fixing structure adopts a full-ring baffle structure, which uses front and rear baffles with bolts to achieve the groove fixation of the turbine rotor blade on the turbine disk and limit the axial movement of the turbine rotor blade. However, the full-ring baffle structure is large, requires a certain installation space, has a complex structure, is heavy, has a large centrifugal load, is complex to produce, process, and assemble, and is costly.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide a turbine blade fixing structure to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A turbine blade fixing structure, comprising:

[0008] A turbine disk, wherein an annular groove is provided at the disk edge of the turbine disk;

[0009] A turbine rotor blade, wherein a plurality of turbine rotor blades are arranged along the circumference of the turbine disk, a tenon of the turbine rotor blade is installed in a tenon groove of the turbine disk, a groove is provided on an edge plate of the turbine rotor blade, the groove is opposite to the annular groove in axial direction, and the grooves of the plurality of turbine rotor blades and the annular groove of the turbine disk jointly form an annular space;

[0010] The blade baffle is fan-shaped, and multiple blade baffles are arranged along the circumference of the annular space. The blade baffle includes a radially outer baffle segment, a radially middle baffle segment and a radially inner baffle segment. The radially outer baffle segment and the radially inner baffle segment both have a bending angle, and the radially middle baffle segment is provided with a small hole for cooling airflow to pass through.

[0011] In at least one embodiment of the present application, the annular groove and the groove have the same axial groove width.

[0012] In at least one embodiment of the present application, the outer wall thickness of the annular groove and the groove is the same, and both are twice the axial thickness of the blade baffle.

[0013] In at least one embodiment of the present application, the mating position between the tenon of the turbine rotor blade and the tenon groove of the turbine disk is completely blocked by the blade baffle, and the edge of the blade baffle is at least 3 mm away from the edge of the mating position.

[0014] In at least one embodiment of the present application, the blade baffle is made of sheet metal material.

[0015] In at least one embodiment of the present application, the number of the blade baffles is 1 / 3 of the number of the turbine rotor blades.

[0016] In at least one embodiment of the present application, there is a gap of 0.3 mm to 2 mm between two adjacent blade baffles.

[0017] In at least one embodiment of the present application, the bending angles of the radially outer baffle segment and the radially inner baffle segment are 10° to 20°.

[0018] In at least one embodiment of the present application, the radial height of the blade baffle in an unbent state is smaller than the radial height of the annular space, and the height difference is 0.2 mm to 1 mm.

[0019] In at least one embodiment of the present application, the small hole is at least 5 mm away from the edge of the blade baffle, and the small hole is at least 3 mm away from the edge of the mating position of the tenon of the turbine rotor blade and the tenon groove of the turbine disk.

[0020] The invention has at least the following beneficial technical effects:

[0021] The turbine blade fixing structure of the present application can realize axial fixation of the turbine rotor blades on the turbine disk in a narrow space; it simplifies the blade baffle structure, reduces the mass, reduces the load, is easy to produce, process and assemble, and reduces the cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a cross-sectional view of a turbine blade fixing structure according to an embodiment of the present application;

[0023] Figure 2 It is a schematic diagram of a turbine blade fixing structure according to an embodiment of the present application.

[0024] Figure 3 is a schematic diagram of a blade baffle according to an embodiment of the present application;

[0025] Figure 4 is a cross-sectional view of a blade baffle according to an embodiment of the present application;

[0026] in:

[0027] 1-Blade baffle; 2-Turbine disc; 3-Turbine rotor blade. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0029] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0030] The following is combined with Figures 1 to 4 This application is described in further detail.

[0031] The present application provides a turbine blade fixing structure, comprising: a turbine disk 2, a turbine rotor blade 3 and a blade baffle 1.

[0032] Specifically, Figure 1As shown, the turbine disk 2 is a full ring structure, and a plurality of tenons for installing the turbine rotor blades 3 are opened along the circumferential direction on the radial outer side thereof, and an annular groove structure is opened at the disk edge of the turbine disk 2; a plurality of turbine rotor blades 3 are evenly arranged along the circumference of the turbine disk 2, and the tenons of each turbine rotor blade 3 are installed in the corresponding tenons of the turbine disk 2, and a groove structure is opened on the inner side of the edge plate of the turbine rotor blade 3, and the axial position of the groove and the annular groove are opposite, and the grooves of the plurality of turbine rotor blades 3 and the annular groove of the turbine disk 2 jointly form an annular space. The blade baffle 1 is a fan-shaped thin plate structure, and the blade baffle 1 is installed in the annular space to limit the axial movement of the turbine rotor blades 3 relative to the turbine disk 2. The blade baffle 1 is arranged along the circumferential direction of the annular space, and the plurality of blade baffles 1 form a full ring structure, and the blade baffle 1 includes a radial outer baffle section, a radial middle baffle section and a radial inner baffle section, and the radial outer baffle section and the radial inner baffle section both have a certain bending angle relative to the radial middle baffle section, and a small hole for cooling airflow to pass through is opened on the radial middle baffle section.

[0033] In a preferred embodiment of the present application, the annular groove of the turbine disk 2 and the groove of the turbine rotor blade 3 have the same axial groove width, and are slightly larger than the axial thickness of the blade baffle 1. Preferably, the outer wall thickness of the annular groove and the groove is the same, and both are twice the axial thickness of the blade baffle 1.

[0034] In the preferred embodiment of the present application, in order to reliably fix the turbine rotor blades 3 and ensure the safety of the engine operation, after assembly is completed, the mating position between the tenon of the turbine rotor blade 3 and the tenon groove of the turbine disk 2 is completely blocked by the blade baffle 1, and the edge of the blade baffle 1 is at least 3 mm away from the edge of the mating position.

[0035] In the preferred embodiment of the present application, the designed blade baffle 1 is made of sheet metal material, replacing the existing forging material, which is easy to process and greatly reduces the processing cost of the engine. In this embodiment, in order to ensure the cooling effect of the turbine rotor blades 3, the number of blade baffles 1 is 1 / 3 of the number of turbine rotor blades 3.

[0036] Advantageously, if Figure 2 As shown, in order to extend the service life of the blade baffle 1 and ensure the reliable operation of the blade baffle 1, a gap of 0.3mm to 2mm is left between two adjacent blade baffles 1 after assembly, which is beneficial to the coordination of thermal deformation of the blade baffle 1 at high temperature.

[0037] Furthermore, in this embodiment, the bending angles of the radially outer baffle section and the radially inner baffle section of the blade baffle 1 are maintained at 10° to 20°. The radial height of the blade baffle 1 in the unbent state is slightly smaller than the height of the annular space. Generally, the height difference between the two is 0.2mm to 1mm. During assembly, the blade baffle 1 is pressed into the annular space with force. During operation, the blade baffle 1 is deformed, straightened, and lengthened under the action of high temperature and centrifugal force to clamp the turbine rotor blade 3.

[0038] like Figure 3-4 As shown, in this embodiment, in order to facilitate the circulation of cooling air in the turbine rotor blade 3 and ensure reliable operation, the small hole structure designed on the blade baffle 1 is at least 5 mm away from the edge of the blade baffle 1, and the small hole is at least 3 mm away from the edge of the matching position of the tenon of the turbine rotor blade 3 and the tenon groove of the turbine disk 2.

[0039] The turbine blade fixing structure of the present application can realize the axial fixation of the turbine rotor blades on the turbine disk in a narrow space, greatly reducing the size of the engine and reducing the engine weight; it has a simple structure and a small weight, and is about 90% lighter than the commonly used full-annular baffle structure in China, reducing the centrifugal load brought by the baffle structure, and is simple to produce, process and assemble, greatly reducing the cost.

[0040] The above is only a specific implementation 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 a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A turbine blade fixing structure, characterized in that: include: A turbine disk (2), wherein an annular groove is provided at the disk edge of the turbine disk (2); A turbine rotor blade (3), wherein a plurality of the turbine rotor blades (3) are arranged along the circumference of the turbine disk (2), the tenon of the turbine rotor blade (3) is installed in the tenon groove of the turbine disk (2), a groove is provided on the edge plate of the turbine rotor blade (3), the groove is opposite to the annular groove in axial direction, and the grooves of the plurality of turbine rotor blades (3) and the annular groove of the turbine disk (2) together form an annular space; The blade baffle (1) is fan-shaped, and a plurality of blade baffles (1) are arranged along the circumference of the annular space. The blade baffle (1) comprises a radially outer baffle segment, a radially middle baffle segment, and a radially inner baffle segment. The radially outer baffle segment and the radially inner baffle segment both have a bending angle, and the radially middle baffle segment is provided with a small hole for cooling airflow to pass through.

2. The turbine blade fixing structure according to claim 1, characterized in that: The annular groove and the groove have the same axial groove width.

3. The turbine blade fixing structure according to claim 1, characterized in that: The outer wall thickness of the annular groove and the groove is the same, and both are twice the axial thickness of the blade baffle (1).

4. The turbine blade fixing structure according to claim 1, characterized in that: The mating position between the tenon of the turbine rotor blade (3) and the tenon groove of the turbine disc (2) is completely blocked by the blade baffle (1), and the edge of the blade baffle (1) is at least 3 mm away from the edge of the mating position.

5. The turbine blade fixing structure according to claim 1, characterized in that: The blade baffle (1) is made of sheet metal material.

6. The turbine blade fixing structure according to claim 1, characterized in that: The number of the blade baffles (1) is 1 / 3 of the number of the turbine rotor blades (3).

7. The turbine blade fixing structure according to claim 1, characterized in that: There is a gap of 0.3 mm to 2 mm between two adjacent blade baffles (1).

8. The turbine blade fixing structure according to claim 1, characterized in that: The bending angles of the radially outer baffle section and the radially inner baffle section are 10° to 20°.

9. The turbine blade fixing structure according to claim 1, characterized in that: The radial height of the blade baffle (1) in an unbent state is smaller than the radial height of the annular space, and the height difference is 0.2 mm to 1 mm.

10. The turbine blade fixing structure according to claim 1, characterized in that: The small hole is at least 5 mm away from the edge of the blade baffle (1), and at least 3 mm away from the edge of the matching position of the tenon of the turbine rotor blade (3) and the tenon groove of the turbine disk (2).

Images