Turbine stator blade, turbine stator blade ring and gas turbine

Abstract

The invention discloses a turbine stator blade, a turbine stator blade ring and a gas turbine, the turbine stator blade comprises a blade body and a margin plate, the blade body is connected with the margin plate and is arranged along the height direction of the blade body, the margin plate is provided with periodic surfaces opposite to each other along the thickness direction of the blade body, the periodic surfaces are provided with sealing grooves, and the sealing grooves extend along the length direction of the blade body. An inner cavity of the sealing groove comprises a sealing section and a cooling section which are arranged in the depth direction of the sealing groove, the sealing section is suitable for being matched with a sealing piece, a first cooling hole communicated with the cooling section is formed in the side, away from the blade body, of the margin plate, and a second cooling hole communicated with the cooling section is further formed in the periodic surface. And the low-cycle fatigue life of the margin plate is long.

Description

Technical Field

[0001] The invention relates to the technical field of gas turbines, and in particular to a turbine stator blade, a turbine stator blade ring and a gas turbine. Background Art

[0002] In the related art, it is usually necessary to set cooling holes on the edge plates of turbine stator blades, and to extend one end opening of the cooling holes to the periodic surface of the edge plates to achieve cooling of the periodic surface. But at the same time, a sealing groove is also required to be set on the periodic surface of the edge plates, so as to achieve the connection and sealing between the two edge plates in two adjacent turbine stator blades by matching the sealing groove in the sealing groove. However, in view of the size limitation of the edge plates, if the cooling holes and the sealing grooves are set at a close distance, there is a possibility that the two will penetrate during processing, affecting the cooling of the periodic surface. If the cooling holes and the sealing grooves are set at a far distance, there is a poor orthogonality between the cooling holes and the surface where the holes are located, which in turn affects the low-cycle fatigue life of the edge plates. Summary of the invention

[0003] The present invention aims to solve one of the technical problems in the related art at least to a certain extent.

[0004] To this end, an embodiment of the present invention provides a turbine stator blade having the advantages of high cooling reliability and high low-cycle fatigue life of the edge plate.

[0005] The embodiments of the present invention also provide a turbine vane ring and a gas turbine.

[0006] The turbine static blade of an embodiment of the present invention includes a blade body and an edge plate, wherein the blade body is connected to the edge plate and is arranged along the height direction of the blade body, the edge plate has periodic surfaces opposite to each other along the thickness direction of the blade body, a sealing groove is provided on the periodic surface, the sealing groove extends along the length direction of the blade body, the inner cavity of the sealing groove includes a sealing section and a cooling section arranged along the depth direction of the sealing groove, the sealing section is suitable for cooperation with a sealing sheet; a first cooling hole connected to the cooling section is provided on the side of the edge plate away from the blade body, and a second cooling hole connected to the cooling section is also provided on the periodic surface.

[0007] According to the turbine static blade of the embodiment of the present invention, by reserving part of the chamber of the sealing groove to form a cooling section connecting the first cooling hole and the second cooling hole, the hidden danger of the sealing sheet in the sealing groove blocking the cooling hole due to the penetration of the cooling hole and the sealing groove in the related technology is avoided, and the cooling reliability of the periodic surface of the edge plate is ensured. At the same time, without considering the design that the first cooling hole and the second cooling hole are far away from the sealing groove, the processing flexibility of the first cooling hole and the second cooling hole on the edge plate is higher, and the orthogonality of the first cooling hole and the second cooling hole to their respective processing surfaces is higher, so that the low-cycle fatigue life of the edge plate at the first cooling hole and the second cooling hole is higher.

[0008] In some embodiments, the first cooling hole and the second cooling hole are both in plurality and are arranged at intervals along the length direction of the blade body;

[0009] An extending direction of the first cooling hole is perpendicular to an extending direction of the sealing groove, and / or an extending direction of the second cooling hole is perpendicular to an extending direction of the sealing groove.

[0010] In some embodiments, an inner wall surface of the sealing segment is provided with an opening connected to the second cooling hole, and along the depth direction of the sealing groove, the opening extends from an edge adjacent to the cooling segment to an edge away from the cooling segment.

[0011] In some embodiments, the width of the opening in the length direction of the blade gradually increases in a direction away from the cooling section.

[0012] In some embodiments, the edge plate includes a middle portion and an edge portion arranged along the thickness direction of the blade body, part of the edge portion protrudes from a side of the middle portion away from the blade body, and the first cooling hole and the sealing groove are arranged on the edge portion.

[0013] In some embodiments, an extension direction of the first cooling hole forms an angle with an extension direction of the second cooling hole.

[0014] In some embodiments, an extension direction of the first cooling hole forms an angle a with a thickness direction of the blade airfoil, and an extension direction of the second cooling hole forms an angle b with the thickness direction of the blade airfoil, wherein a>b.

[0015] In some embodiments, the blade is provided with the edge plate at the first end and / or the second end in the height direction.

[0016] According to an embodiment of the present invention, a turbine static blade ring comprises a holding ring, a sealing sheet and a turbine static blade as described in any of the above embodiments, wherein there are a plurality of turbine static blades which are arranged in sequence along the circumference of the holding ring, the plurality of turbine static blades are located on the inner side of the holding ring, the sealing sheet is provided between any two adjacent turbine static blades, and the two ends of the sealing sheet are respectively fitted in the sealing grooves on the two adjacent turbine static blades.

[0017] The technical advantages of the turbine stator ring according to the embodiment of the present invention are the same as the technical advantages of the turbine stator in the above-mentioned embodiment, which will not be described in detail here.

[0018] A gas turbine according to an embodiment of the present invention includes the turbine vane ring according to the above-described embodiment.

[0019] The technical advantages of the gas turbine according to the embodiment of the present invention are the same as the technical advantages of the turbine stator ring in the above-mentioned embodiment, which will not be described in detail here. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 Schematic diagram of a turbine static blade according to an embodiment of the present invention.

[0021] Figure 2 is a cross-sectional view of a turbine vane according to an embodiment of the present invention.

[0022] Reference numerals:

[0023] 1. Edge plate; 11. Middle section; 12. Edge section; 121. First cooling hole; 122. Second cooling hole; 123. Sealing groove; 1231. Cooling section; 1232. Sealing section; 2. Sealing sheet. DETAILED DESCRIPTION

[0024] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0025] Combine the following Figure 1 and Figure 2 A turbine static blade according to an embodiment of the present invention is described.

[0026] The turbine static blade of the embodiment of the present invention includes a blade body and an edge plate 1. The blade body is connected to the edge plate 1 and arranged along the height direction of the blade body. The edge plate 1 has periodic surfaces opposite to each other along the thickness direction of the blade body. A sealing groove 123 is provided on the periodic surface. The sealing groove 123 extends along the length direction of the blade body. The inner cavity of the sealing groove 123 includes a sealing section 1232 and a cooling section 1231 arranged along the depth direction of the sealing groove 123. The sealing section 1232 is suitable for being matched with a sealing sheet 2. A first cooling hole 121 connected to the cooling section 1231 is provided on the side of the edge plate 1 away from the blade body, and a second cooling hole 122 connected to the cooling section 1231 is also provided on the periodic surface.

[0027] According to the turbine static blade of the embodiment of the present invention, by reserving part of the chamber of the sealing groove 123 to form a cooling section 1231 connecting the first cooling hole 121 and the second cooling hole 122, the hidden danger of the sealing sheet 2 fitted in the sealing groove 123 blocking the cooling hole due to the penetration of the cooling hole and the sealing groove 123 in the related art is avoided, and the cooling reliability of the periodic surface of the edge plate 1 is ensured. At the same time, without considering the design of the first cooling hole 121 and the second cooling hole 122 being far away from the sealing groove 123, the processing flexibility of the first cooling hole 121 and the second cooling hole 122 on the edge plate 1 is higher, and the orthogonality of the first cooling hole 121 and the second cooling hole 122 to their respective processing surfaces is higher, and thus the low-cycle fatigue life of the edge plate 1 at the first cooling hole 121 and the second cooling hole 122 is higher.

[0028] It should be noted that the sealing groove 123 passes through the edge plate 1 along the length direction of the blade body. The sealing section 1232 in the sealing groove 123 is closer to the opening of the sealing groove 123 than the cooling section 1231. The width of the cooling section 1231 can be smaller than the width of the sealing section 1232, thereby ensuring that the sealing sheet 2 will not mistakenly enter the cooling section 1231 after being inserted into the sealing section 1232, thereby affecting the reliable connection between the first cooling hole 121 and the second cooling hole 122.

[0029] In some embodiments, Figure 1 As shown, there are multiple first cooling holes 121 and second cooling holes 122, which are arranged at intervals along the length direction of the blade. The extension direction of the first cooling hole 121 is perpendicular to the extension direction of the sealing groove 123, and / or the extension direction of the second cooling hole 122 is perpendicular to the extension direction of the sealing groove 123.

[0030] That is, the extension direction of at least one of the first cooling hole 121 and the second cooling hole 122 is perpendicular to the length direction of the edge plate 1 , so that the arrangement of at least one of the first cooling hole 121 and the second cooling hole 122 is more flexible, and the low-cycle fatigue life of the edge plate 1 is better improved.

[0031] Specifically, the number of the first cooling holes 121 and the second cooling holes 122 are equal, the multiple first cooling holes 121 are arranged at equal intervals along the length direction of the blade body, the multiple second cooling holes 122 are arranged at equal intervals along the length direction of the blade body, and the extension direction of each of the first cooling holes 121 and the second cooling holes 122 is perpendicular to the extension direction of the sealing groove 123.

[0032] In some embodiments, Figure 1 and Figure 2 As shown, the inner wall surface of the sealing section 1232 is provided with an opening connected to the second cooling hole 122 , and along the depth direction of the sealing groove 123 , the opening extends from the edge adjacent to the cooling section 1231 to the edge away from the cooling section 1231 .

[0033] This further improves the connectivity reliability between the second cooling hole 122 and the cooling section 1231 , and also further improves the orthogonality between the second cooling hole 122 and the periodic surface, so that the low-cycle fatigue life of the edge plate 1 at the second cooling hole 122 is higher.

[0034] Specifically, the second cooling hole 122 is located below the sealing groove 123 , and the opening of the second cooling hole 122 is formed on the lower side surface of the inner wall surface of the sealing groove 123 .

[0035] In some embodiments, Figure 1 and Figure 2 As shown, the width of the opening in the length direction of the blade gradually increases in the direction away from the cooling section 1231.

[0036] That is, the cross-sectional area of ​​the second cooling hole 122 gradually increases in the direction away from the cooling section 1231, thereby effectively increasing the air outlet area of ​​the second cooling hole 122, further improving the cooling effect of the cold air on the periodic surface.

[0037] Specifically, the maximum width of the opening of the second cooling hole 122 is less than or equal to the diameter of the second cooling hole 122 .

[0038] In some embodiments, the edge plate 1 includes a middle portion and an edge portion arranged along the thickness direction of the blade body, part of the edge portion protrudes from the side of the middle portion away from the blade body, and the first cooling hole 121 and the sealing groove 123 are arranged on the edge portion.

[0039] That is, the thickness of the edge portion is greater than that of the middle portion, and the processing surface of the first cooling hole 121 is the side surface of the edge portion facing the middle portion rather than the upper surface of the middle portion. As a result, a larger angle can be formed between the extension direction of the first cooling hole 121 and the thickness direction of the blade body, further increasing the angle between the first cooling hole 121 and the processing surface, and the low-cycle fatigue life of the edge plate 1 is higher.

[0040] Specifically, the number of the edge portion can be one and located at any side of the middle portion in the thickness direction of the vehicle body. The number of the edge portion can also be two and located at two opposite sides of the middle portion in the thickness direction of the vehicle body.

[0041] In some embodiments, Figure 2 As shown, the extension direction of the first cooling hole 121 forms an angle with the extension direction of the second cooling hole 122 .

[0042] At this time, the first cooling hole 121 and the second cooling hole 122 are processed independently, and the processing method and processing position of the two on the edge plate 1 are more flexible.

[0043] Specifically, the extending direction of the first cooling hole 121 forms an angle a with the thickness direction of the blade body, and the extending direction of the second cooling hole 122 forms an angle b with the thickness direction of the blade body, wherein a>b.

[0044] In some embodiments, a blade is provided with an edge plate 1 at a first end and / or a second end in the height direction.

[0045] That is, the structure of at least one of the upper edge plate and the lower edge plate in the turbine stator blade is the same as the structure of the edge plate 1 of this embodiment, thereby ensuring the cooling reliability and low-cycle fatigue life of the periodic surface on at least one edge plate 1.

[0046] Specifically, there are two edge plates 1 in this embodiment and they are respectively arranged at the upper end and the lower end of the blade body.

[0047] The turbine static blade ring according to an embodiment of the present invention comprises a holding ring, a sealing sheet 2 and a turbine static blade as in any of the above embodiments. There are multiple turbine static blades and they are arranged in sequence along the circumference of the holding ring. The multiple turbine static blades are located on the inner side of the holding ring. A sealing sheet 2 is provided between any two adjacent turbine static blades. Both ends of the sealing sheet 2 are respectively fitted in the sealing grooves 123 on the two adjacent turbine static blades.

[0048] The technical advantages of the turbine stator ring according to the embodiment of the present invention are the same as the technical advantages of the turbine stator in the above-mentioned embodiment, which will not be described in detail here.

[0049] A gas turbine according to an embodiment of the present invention includes the turbine vane ring according to the above-described embodiment.

[0050] The technical advantages of the gas turbine according to the embodiment of the present invention are the same as the technical advantages of the turbine stator ring in the above-mentioned embodiment, which will not be described in detail here.

[0051] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0052] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0053] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0054] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0055] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0056] Although the above embodiments have been shown and described, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those of ordinary skill in the art are all within the scope of protection of the present invention.

Claims

1. A turbine static blade, characterized in that: It comprises a blade body and an edge plate, wherein the blade body is connected to the edge plate and arranged along the height direction of the blade body, the edge plate has periodic surfaces opposite to each other along the thickness direction of the blade body, a sealing groove is arranged on the periodic surface, the sealing groove extends along the length direction of the blade body, the inner cavity of the sealing groove comprises a sealing section and a cooling section arranged along the depth direction of the sealing groove, and the sealing section is suitable for being matched with a sealing sheet; A first cooling hole communicating with the cooling section is disposed on a side of the edge plate away from the blade body, and a second cooling hole communicating with the cooling section is also disposed on the periodic surface.

2. The turbine vane according to claim 1, characterized in that: There are a plurality of the first cooling holes and the second cooling holes, which are arranged at intervals along the length direction of the blade body; An extending direction of the first cooling hole is perpendicular to an extending direction of the sealing groove, and / or an extending direction of the second cooling hole is perpendicular to an extending direction of the sealing groove.

3. The turbine vane according to claim 1, characterized in that: The inner wall surface of the sealing section is provided with an opening connected with the second cooling hole, and along the depth direction of the sealing groove, the opening extends from an edge adjacent to the cooling section to an edge away from the cooling section.

4. The turbine static blade according to claim 3, characterized in that: The width of the opening in the length direction of the blade gradually increases in a direction away from the cooling section.

5. The turbine vane according to claim 1, characterized in that: The edge plate includes a middle portion and an edge portion arranged along the thickness direction of the blade body, a portion of the edge portion protrudes from a side of the middle portion away from the blade body, and the first cooling hole and the sealing groove are arranged on the edge portion.

6. The turbine vane according to claim 1, characterized in that: An extending direction of the first cooling hole forms an angle with an extending direction of the second cooling hole.

7. The turbine vane according to claim 6, characterized in that: The extending direction of the first cooling hole forms an angle a with the thickness direction of the blade airfoil, and the extending direction of the second cooling hole forms an angle b with the thickness direction of the blade airfoil, wherein a>b.

8. The turbine vane according to claim 1, characterized in that: The blade is provided with the edge plate at the first end and / or the second end in the height direction.

9. A turbine stator ring, characterized in that: It comprises a holding ring, a sealing sheet and a turbine static blade according to any one of claims 1 to 8, wherein there are a plurality of turbine static blades which are arranged in sequence along the circumference of the holding ring, the plurality of turbine static blades are located on the inner side of the holding ring, a sealing sheet is provided between any two adjacent turbine static blades, and both ends of the sealing sheet are respectively fitted in the sealing grooves on the two adjacent turbine static blades.

10. A gas turbine, characterized in that: The invention comprises the turbine stator ring according to claim 9.

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