Gas turbine and turbine blade locking structure and locking plate thereof

Abstract

The invention discloses a gas turbine and a turbine blade locking structure and a locking plate thereof, and relates to the technical field of gas turbines. The lock plate comprises a flat plate body; the flat plate body is a bendable plate; the clamping bulge is arranged on the first surface of the flat plate body; the first surface is perpendicular to the first direction; the first direction is parallel to the thickness direction of the flat plate body; and after the clamping bulge is clamped with the clamping groove, the first end of the flat plate body extends out of the fit clearance. The lock plate is simple in structure, fastening parts such as bolts do not need to be adopted when the lock plate is used, and the machining and manufacturing cost is low. And the lock plate is simple in structure, so that the lock plate does not need to occupy a large structural space, and the reliability of the whole locking structure can be improved.

Description

Technical Field

[0001] The present application relates to the technical field of gas turbines, and in particular to a gas turbine and a turbine blade locking structure and a locking plate thereof. Background Art

[0002] As an important part of the gas turbine device, the reliability of the locking and positioning of the turbine blade is directly related to the safe and stable operation of the gas turbine. Figure 1 and Figure 2 As shown, in the prior art, a gas turbine has a turbine disk, and a plurality of tenons are arranged along the circumference of the turbine disk, and a tenon is arranged on the turbine blade. When in use, the turbine blade is installed on the turbine disk through the tenon and the tenon. In order to lock and position the turbine blade, that is, to prevent the turbine blade from being moved along the axial direction of the turbine disk (perpendicular to the turbine blade) during use. Figure 1 and Figure 2 In the prior art, a positioning plate or a positioning lock plate ( Figure 1 and Figure 2 The turbine blades and the turbine disk are locked and positioned by fastening parts such as bolts. The above locking structure not only has a large number of parts and high processing and manufacturing costs, but also requires a large structural space, resulting in a complex design of the turbine blade locking structure in the gas turbine and reduced reliability. Summary of the invention

[0003] The purpose of the present application is to provide a gas turbine and a turbine blade locking structure and a locking plate thereof, so as to solve the technical problems of complex design and high manufacturing cost of the turbine blade locking structure in the prior art.

[0004] To achieve the above objectives, this application provides the following technical solutions:

[0005] In a first aspect, the present application proposes a technical solution of a lock plate, which is applied to a turbine engine, wherein the turbine engine comprises a turbine disk and a turbine blade; the turbine disk is provided with a tenon; the turbine blade is provided with a tenon; a fitting gap is formed between the tenon and the tenon; a clamping groove is provided in a surface forming the fitting gap; the lock plate comprises:

[0006] A flat plate body; the flat plate body is a bendable plate;

[0007] The clamping protrusion is arranged on the first surface of the flat body; the first surface is perpendicular to the first direction; the first direction is parallel to the thickness direction of the flat body; and after the clamping protrusion is clamped with the clamping groove, the first end of the flat body extends out of the fitting gap.

[0008] As a specific solution in the technical solution of the present application, the clamping groove is arranged on the bottom surface of the mortise of the mortise, and after the clamping protrusion is clamped with the clamping groove, the height of the top surface of the flat plate body along the first direction is less than or equal to the height of the bottom surface of the mortise of the mortise along the first direction.

[0009] As a specific solution in the technical solution of the present application, the clamping protrusion is in the shape of an elongated strip, and the clamping protrusion extends along a second direction; the second direction is parallel to the first surface of the flat plate body.

[0010] As a specific solution in the technical solution of the present application, the first surface of the flat body is also provided with a bending groove, and the bending groove penetrates the flat body along a third direction; the third direction is parallel to the first surface of the flat body and perpendicular to the length direction of the flat body.

[0011] As a specific solution in the technical solution of the present application, the turbine blade includes a blade side; the blade side is perpendicular to the axis of the turbine disk, and the blade side is the side of the turbine blade close to the flat plate body; after the snap-in protrusion is snapped with the snap-in groove, the extension surface of the blade side passes through the bending groove.

[0012] As a specific solution in the technical solution of the present application, the tenon of the turbine blade is provided with at least one hanging hook, and the first end of the flat plate body is provided with a hanging rod corresponding to the hanging hook one by one.

[0013] As a specific solution in the technical solution of the present application, the outer diameter of the clamping protrusion decreases along the first direction; the first direction is from the clamping protrusion to the clamping groove.

[0014] In a second aspect, the present application proposes a technical solution for a turbine blade locking structure, which includes a turbine blade locking structure such as a locking plate as described in any one of the first aspects.

[0015] As a specific solution in the technical solution of this application, it also includes:

[0016] Turbine discs and interstage grate rings;

[0017] A plurality of turbine blades; one side of each turbine blade is positioned by the locking plate, and the other side of each turbine blade is positioned by the interstage grate ring.

[0018] In a third aspect, the present application proposes a technical solution for a gas turbine, which includes a locking plate as described in any one of the first aspects, or includes a turbine blade locking structure as described in any one of the second aspects.

[0019] Compared with the prior art, the beneficial effects of this application are:

[0020] The lock plate proposed in the present application has a simple structure, does not require fastening parts such as bolts when in use, and has a low manufacturing cost. In addition, since the lock plate has a simple structure, it does not need to occupy a large structural space, and can improve the reliability of the overall locking structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a partial schematic diagram of a turbine disc in the prior art;

[0022] Figure 2 It is a schematic diagram of the mortise and tenon joint between the turbine blade and the mortise and tenon groove in the turbine disc in the prior art;

[0023] Figure 3 A three-dimensional schematic diagram of a locking plate proposed in an embodiment of the present application;

[0024] Figure 4 A schematic front view of a locking plate proposed in an embodiment of the present application;

[0025] Figure 5 for Figure 3 A bottom view of the middle locking plate;

[0026] Figure 6 A schematic front view of another locking plate proposed in an embodiment of the present application;

[0027] Figure 7 A front view schematic diagram of another locking plate proposed in an embodiment of the present application;

[0028] Figure 8 A cross-sectional schematic diagram of a turbine blade locking structure proposed in an embodiment of the present application;

[0029] Fig. 9 for Figure 8 A schematic cross-sectional view with turbine blades removed;

[0030] Fig.10 This is a schematic structural diagram of a turbine blade locking structure proposed in an embodiment of the present application.

[0031] In the figure: 1, turbine disc; 11, mortise and tenon; 111, snap-fit ​​groove; 112, mortise and tenon bottom; 2, turbine blade; 21, hook; 22, blade side; 3, interstage grate ring; 4, locking plate; 41, flat plate body; 411, flat plate top; 42, snap-fit ​​protrusion; 43, bending groove; 44, hooking rod. DETAILED DESCRIPTION

[0032] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0033] It should be noted that, in the description of the present application, the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation on the present application.

[0034] Furthermore, it should be understood that for the sake of ease of description, the sizes of the various components shown in the drawings are not drawn according to actual proportions. For example, the thickness or width of certain layers may be exaggerated relative to other layers.

[0035] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined or described in one drawing, it will not require further detailed discussion and description in the description of the subsequent drawings.

[0036] In order to solve the technical problem of the complicated design of the locking structure of the turbine blades in the prior art mentioned in the background technology, the present application proposes a locking plate 4, which is applied to a turbine engine, and the turbine engine includes a turbine disk 1 and a turbine blade 2. The turbine disk 1 is provided with a mortise 11, and the turbine blade 2 is provided with a tenon. When in use, a fitting gap is formed between the mortise 11 and the tenon. It should be noted that in the embodiments of the present application, the fitting gap refers to the gap formed after the tenon and the mortise 11 are connected. In other words, the surface forming the fitting gap includes both the surface on the tenon and the surface on the mortise 11 opposite to the surface on the tenon.

[0037] It should be noted that, in the embodiment of the present application, a snap-in groove 111 is provided in the surface forming the fitting gap. As can be seen from the foregoing, the fitting gap includes both the surface on the tenon and the surface on the tenon 11 opposite to the surface on the tenon. That is to say, in the present embodiment, the snap-in groove 111 can be provided on the surface on the tenon, and can also be provided on the surface on the tenon 11 opposite to the surface on the tenon. In the following, in order to avoid redundancy, only the snap-in groove 11 is provided on the surface on the tenon 11 (that is, the tenon bottom surface 112 hereinafter) to describe the embodiment of the present application, which does not mean that the snap-in groove 111 can only be provided on the tenon bottom surface 112. It should be understood that the snap-in groove 111 can also be provided on other surfaces forming the fitting gap, which will not be described in detail later.

[0038] It should be noted that, in the embodiments of the present application, the turbine engine may be any engine having a turbine disk 1 and turbine blades 2, for example, the turbine engine may be an automobile engine, an aircraft engine, or a gas turbine.

[0039] Specifically, in the embodiment of the present application, the locking plate 4 includes a flat plate body 41 and a clamping protrusion 42. Specifically, the flat plate body 41 is a bendable plate. The clamping protrusion 42 is arranged on a first surface of the flat plate body 41, the first surface is perpendicular to a first direction, and the first direction is parallel to a thickness direction of the flat plate body 41 (i.e., Figures 6 to 9 In the direction B), after the engaging protrusion 42 is engaged with the engaging groove 111, the first end of the flat body 41 extends out of the fitting gap.

[0040] When using, Figure 8 As shown, the portion of the flat plate body 41 extending out of the fitting gap (i.e. Figure 8 The locking plate 4 is bent along the dotted line portion shown in the figure, so that the bent portion fits the side surface of the turbine blade 2. It is easy to understand that under the limiting effect of the clamping protrusion 42 and the clamping groove 111, the locking plate 4 cannot be moved along the axial direction of the turbine disk 1 (that is, as shown in the figure). Figures 8 to 10 If the lock plate 4 cannot move in the axial direction of the turbine disk 1, then the turbine blade 2 cannot move in the axial direction of the turbine disk 1 toward the lock plate 4 due to the restriction of the bent portion of the lock plate 4.

[0041] As can be seen from the foregoing, the engaging groove 111 can be provided on any surface of the fitting gap. Fig. 9As shown, the engaging groove 111 can be provided at the bottom surface 112 of the tenon 11. In order to smoothly engage the tenon of the turbine blade 2 into the tenon 11, in one embodiment of the present application, after the engaging protrusion 42 engages with the engaging groove 111, the height of the flat plate top surface 411 of the flat plate body 41 along the first direction is less than or equal to the height of the bottom surface 112 of the tenon 11 along the first direction. It should be noted that, since the height of the flat plate top surface 411 of the flat plate body 41 along the first direction is less than or equal to the height of the bottom surface 112 of the tenon 11 along the first direction, when the turbine blade 2 is installed, the tenon of the turbine blade 2 will not interfere with the flat plate body 41, that is, the tenon of the turbine blade 2 can be smoothly engaged into the tenon 11.

[0042] In the embodiment of the present application, there is no restriction on the shape and structure of the clamping protrusion 42, as long as it can cooperate with the clamping groove 111 to limit the movement of the lock plate 4. For example, the clamping protrusion 42 can be block-shaped or hemispherical. In order to cooperate with the clamping groove 111 to form a better limiting effect, in one embodiment of the present application, it can be as follows Figure 3 and Figure 5 As shown, the clamping protrusion 42 is in the shape of a long strip, and the clamping protrusion 42 extends along the second direction, and the second direction is parallel to the first surface of the flat body 41. In this embodiment, compared with the block-shaped or hemispherical clamping protrusion 42, the long strip-shaped clamping protrusion 42 has a longer extension length, so it can form a better limiting effect. Figure 3 and Figure 5 As shown, the second direction may be parallel to the width direction of the locking plate 4 .

[0043] In the embodiments of the present application, Figure 4 As shown, the clamping protrusion 42 can be in the shape of a rectangular strip. It should be noted that the use environment of the turbine blade 2 is a high temperature environment. In order to avoid the clamping protrusion 42 and the clamping groove 111 being deformed and stuck in a high temperature environment for a long time, and thus making it difficult to separate the clamping protrusion 42 from the clamping groove 111, in one embodiment of the present application, the outer diameter of the clamping protrusion 42 along the first direction can be gradually reduced, and the first direction is parallel to the thickness direction of the flat plate body 41, and is directed from the clamping protrusion 42 to the clamping groove 111.

[0044] In the embodiment of the present application, there is no limitation on the shape of the clamping protrusion 42 with decreasing outer diameter, for example: Figure 6 As shown, the cross section of the clamping protrusion 42 can be an isosceles trapezoid; or Figure 7 As shown, the cross section of the clamping protrusion 42 can be semicircular. In this embodiment, the cross section is perpendicular to the extending direction of the clamping protrusion 42.

[0045] As can be seen from the foregoing, when the lock plate 4 is used, the portion of the flat plate body 41 extending out of the matching gap needs to be bent so that the lock plate 4 can play a limiting role. In order to facilitate the bending of the flat plate body 41, in one embodiment of the present application, Figures 3 to 5 As shown, the first surface of the flat plate body 41 is further provided with a bending groove 43, and the bending groove 43 penetrates the flat plate body 41 along the third direction. The third direction is parallel to the first surface of the flat plate body 41, and is perpendicular to the length direction of the flat plate body 41. Since the thickness of the flat plate body 41 at the bending groove 43 is relatively thin, it is convenient for the user to bend the flat plate body 41 through the bending groove 43. In order to ensure the overall strength of the flat plate body 41, the depth of the bending groove 43 can be relatively shallow, so that the strength of the bent flat plate body 41 at the bending groove 43 is slightly lower than the strength at other places.

[0046] It should be noted that, during the use of the lock plate 4, the closer the bent portion of the plate body 41 fits with the side of the turbine blade 2, the better the limiting effect of the lock plate 4. In order to make the portion of the plate body 41 extending out of the matching gap fit closely with the blade side 22 of the turbine blade 2 after being bent, in one embodiment of the present application, Figure 8 As shown, the blade side surface 22 is perpendicular to the axis of the turbine disk 1, and the blade side surface 22 is the side surface of the turbine disk 1 close to the flat plate body 41. After the clamping protrusion 42 is clamped with the clamping groove 111, the infinitely extended surface of the blade side surface 22 passes through the bending groove 43. Figure 8 As shown, since the extended surface of the blade side surface 22 passes through the bending groove 43 , after the flat plate body 41 is bent through the bending groove 43 , the bent portion can fit tightly with the blade side surface 22 of the turbine blade 2 .

[0047] In order to prevent the bent portion of the flat plate body 41 from returning to its original state during long-term use (i.e. Figure 8 The dotted line portion shown in the figure) will lose the limiting effect on the turbine blade 2. In one embodiment of the present application, Figure 8 As shown, the tenon of the turbine blade 2 is provided with at least one hook 21. Figure 3 and Figure 5 As shown, the first end of the flat plate body 41 is provided with a hooking rod 44 corresponding to the hooking hook 21. When in use, the hooking rod 44 on the flat plate body 41 is inserted into the corresponding hook 21 on the turbine blade 2, thereby effectively preventing the bent portion of the flat plate body 41 from returning to its original state, that is, the locking plate 4 can maintain a limiting effect for a long time.

[0048] It should be noted that, in the embodiment of the present application, in order to enable the hooking rod 44 to be smoothly inserted into the hooking hook 21 , the hooking rod 44 may be a rod capable of plastic deformation or a rod capable of elastic deformation.

[0049] It should be clear that the lock plate proposed in the embodiment of the present application has a simple structure, does not require bolts or other fastening parts when in use, and has a low manufacturing cost. In addition, since the lock plate has a simple structure, it does not need to occupy a large structural space, which can improve the reliability of the overall locking structure.

[0050] After introducing the embodiment of the locking plate proposed in the present application, an embodiment of a turbine blade locking structure proposed in the present application is introduced below. The turbine blade locking structure includes the locking plate proposed in any one of the above embodiments.

[0051] It should be noted that in the turbine blade locking structure, both sides of the turbine blade 2 need to be locked and positioned. In the embodiment of the present application, both sides of the turbine blade 2 can be locked and positioned by the locking plate 4 mentioned above. In order to further simplify the turbine blade locking structure proposed in the present application, in one embodiment of the present application, Fig.10 As shown, the turbine blade locking structure may include a turbine disk 1, an interstage grate ring 3 and a plurality of turbine blades 2. Among them, one side of each turbine blade 2 is positioned by a locking plate 4, and the other side of each turbine blade 2 is positioned by an interstage grate ring 3. It should be noted that the interstage grate ring 3 is an indispensable part for sealing between turbine disks at each stage in a gas turbine, and is not a newly added part. The present application only cleverly utilizes the grate sealing ring to lock and position the other side of the turbine blade, so as to further simplify the turbine blade locking structure.

[0052] Specifically, using the turbine blade locking structure proposed in the embodiment of the present application, the steps of locking and positioning each turbine blade 2 include steps S100 to S300.

[0053] Step S100: Fig. 9 As shown, the locking plate 4 is placed into the engaging groove 111 in the tenon groove 11;

[0054] Step S200: Fig.10 As shown, the turbine blade 2 is pushed into the tongue groove 11, so that the turbine blade 2 is in contact with the interstage grate ring 3;

[0055] Step S300: Figure 8 As shown, the portion of the locking plate 4 extending out of the fitting gap is bent by 90° so that the bent portion fits tightly against the blade side surface 22 of the turbine blade 2 .

[0056] After assembly is completed, the turbine blade 2, the turbine disk 1 and the locking plate 4 form a whole. When the turbine blade 2 moves toward the locking plate 4, the locking plate 4 limits it; when the turbine blade moves toward the interstage grate ring 3, the interstage grate ring 3 limits it, ensuring that the turbine blade 2 can always be reliably locked in the tenon groove 11 of the turbine disk 1 in both static and working states, thereby ensuring safe and stable operation of the gas turbine.

[0057] It should be clear that the turbine blade locking structure proposed in the present application has a locking plate with a simple structure, which does not require fastening parts such as bolts when in use, and has a low processing and manufacturing cost. In addition, since the locking plate has a simple structure, it does not need to occupy a large structural space, which can improve the reliability of the overall locking structure.

[0058] After introducing the embodiments of the turbine blade locking structure proposed in the present application, a gas turbine proposed in the present application is introduced below, including a locking plate as proposed in any one of the above embodiments, or including a turbine blade locking structure as proposed in any one of the above embodiments.

[0059] It should be clear that the gas turbine proposed in the present application has a lock plate with a simple structure, which does not require fastening parts such as bolts when in use, and has a low processing and manufacturing cost. In addition, since the lock plate has a simple structure, it does not need to occupy a large structural space, which can improve the reliability of the overall locking structure.

[0060] Although the embodiments of the present application have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present application, and that the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A lock plate (4), applied to a turbine engine, the turbine engine comprising a turbine disk (1) and a turbine blade (2); the turbine disk (1) is provided with a tenon (11); the turbine blade (2) is provided with a tenon; a matching gap is formed between the tenon (11) and the tenon; characterized in that: A clamping groove (111) is provided in the surface forming the fitting gap; the locking plate (4) comprises: A flat plate body (41); the flat plate body (41) is a bendable plate; A clamping protrusion (42) is arranged on a first surface of the flat plate body (41); the first surface is perpendicular to a first direction; the first direction is parallel to a thickness direction of the flat plate body (41); and after the clamping protrusion (42) is clamped with the clamping groove (111), the first end of the flat plate body (41) extends out of the fitting gap.

2. The locking plate (4) according to claim 1, characterized in that: The clamping groove (111) is arranged on the bottom surface (112) of the tenon groove (11); after the clamping protrusion (42) is clamped with the clamping groove (111), the height of the flat plate top surface (411) of the flat plate body (41) along the first direction is less than or equal to the height of the bottom surface (112) of the tenon groove (11) along the first direction.

3. The locking plate (4) according to claim 1, characterized in that: The clamping protrusion (42) is in the shape of an elongated strip, and the clamping protrusion (42) extends along a second direction; the second direction is parallel to the first surface of the flat plate body (41).

4. The locking plate (4) according to claim 1, characterized in that: The first surface of the flat plate body (41) is also provided with a bending groove (43), and the bending groove (43) penetrates the flat plate body (41) along a third direction; the third direction is parallel to the first surface of the flat plate body (41) and perpendicular to the length direction of the flat plate body (41).

5. The locking plate (4) according to claim 4, characterized in that: The turbine blade (2) comprises a blade side surface (22); the blade side surface (22) is perpendicular to the axis of the turbine disk (1), and the blade side surface (22) is the side surface of the turbine blade (2) close to the flat plate body (41); after the engaging protrusion (42) is engaged with the engaging groove (111), the extension surface of the blade side surface (22) passes through the bending groove (43).

6. The locking plate (4) according to any one of claims 1 to 5, characterized in that: The tenon of the turbine blade (2) is provided with at least one hanging hook (21), and the first end of the flat plate body (41) is provided with a hanging rod (44) corresponding one-to-one to the hanging hook (21).

7. The locking plate (4) according to any one of claims 1 to 5, characterized in that: The outer diameter of the clamping protrusion (42) decreases gradually along a first direction; the first direction is directed from the clamping protrusion (42) to the clamping groove (111).

8. A turbine blade locking structure, characterized in that: Comprising a locking plate (4) as claimed in any one of claims 1 to 7.

9. The turbine blade locking structure according to claim 8, characterized in that: Also includes: A turbine disk (1) and an interstage grate ring (3); A plurality of turbine blades (2); one side of each turbine blade (2) is positioned by the locking plate (4), and the other side of each turbine blade (2) is positioned by the interstage grate ring (3).

10. A gas turbine, characterized in that: It comprises a locking plate (4) as claimed in any one of claims 1 to 7, or comprises a turbine blade locking structure as claimed in claim 8 or 9.

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