Turbine blade having gas film cooling structure with a composite irregular groove and a method of manufacturing the same

Abstract

A turbine blade having a gas film cooling structure with a composite irregular groove. The turbine blade has a hollow structure, and a plurality of first grooves which are recessed grooves are provided on an outer surface thereof. A plurality of discrete holes A extending to an inner surface of the turbine blade are provided at the groove bottom of each first groove. The first groove is an irregular groove, and includes at least two portions in a depth direction. A portion having a depth H.sub.1 from the groove bottom of the first groove is a first portion, and the rest thereof is a second portion. At least one side surface of the second portion is formed by expanding in lateral direction from a corresponding side surface of the first portion.

Claims

1. A turbine blade having a gas film cooling structure with a composite irregular groove, wherein the turbine blade has a hollow structure, and a plurality of first grooves which are irregular grooves are provided on an outer surface of a wall of the turbine blade, wherein each first groove comprises a bottom and two side surfaces parallel to a length direction of the first groove, wherein a plurality of discrete holes A extending to an inner surface of the wall of the turbine blade are provided at the bottom of each first groove, and the discrete holes A are arranged substantially along the length direction of the first groove, wherein a depth of each first groove is H, wherein each first groove includes at least two portions in a depth direction, a portion having a depth of H.sub.1 from the bottom of the first groove is a first portion, and a rest thereof is a second portion, i.e., a depth of the second portion is H.sub.2=H−H.sub.1, wherein at least one side surface of the second portion is a curved surface, and a width of the second portion increases from an end close to the first portion, wherein the maximum diameter of each discrete hole A is d, the depth of each first groove is H, and the minimum width of each first groove is D, and wherein D≥d, H≥2d, and H.sub.1≥H.sub.2.

2. The turbine blade having a gas film cooling structure with a composite irregular groove of claim 1, wherein an angle between an axis of an opening end of each first groove in the depth direction and a normal of the outer surface of the wall of the turbine blade is α, and 10°≤α≤90°.

3. The turbine blade having a gas film cooling structure with a composite irregular groove of claim 1, wherein a connection portion where at least one side surface of the first portion and a corresponding side surface of the second portion are connected is a chamfered transition connection or an arc transition connection.

4. The turbine blade having a gas film cooling structure with a composite irregular groove of claim 1, wherein the maximum diameter of each discrete hole A is d, the depth of each first groove is H, and the minimum width of each first groove is D, and wherein D≥d, and H≥2d.

5. The turbine blade having a gas film cooling structure with a composite irregular groove of claim 1, wherein the discrete holes A are straight circular holes, diffusion holes, or complex composite irregular holes, wherein, an angle between a central axis of each discrete hole A and a normal of surface of the turbine blade is θ, and 0°≤θ≤60°, and wherein, an opening end of each discrete hole A is provided with a chamfered transition, or a rounded transition.

6. The turbine blade having a gas film cooling structure with a composite irregular groove of claim 1, wherein H.sub.1:H.sub.2≥2:1.

7. A turbine blade having a gas film cooling structure with a composite irregular groove, wherein the turbine blade has a hollow structure, a hollow cavity is formed between an inner surface and an outer surface of a wall of the turbine blade, and a plurality of discrete holes B extending to the hollow cavity are provided on the inner surface of a wall of the turbine blade, wherein a plurality of first grooves which are irregular grooves are provided on an outer surface of the wall of the turbine blade, and each first groove comprises a bottom and two side surfaces parallel to a length direction of the first groove, wherein a plurality of discrete holes A extending to the hollow cavity are provided at the bottom of each first groove, and the discrete holes A are arranged substantially along the length direction of the first groove, wherein a depth of each first groove is H, wherein each first groove includes at least two portions in a depth direction, a portion having a depth of H.sub.1 from the bottom of the first groove is a first portion, and a rest thereof is a second portion, i.e., a depth of the second portion is H.sub.2=H−H.sub.1, and wherein at least one side surface of the second portion is a curved surface, and w width of the second portion increase from an end close to the first portion.

8. The turbine blade having a gas film cooling structure with a composite irregular groove of claim 7, wherein an angle between an axis of an opening end of each first groove in the depth direction and a normal of the outer surface of the wall of the turbine blade is α, and 10°≤α≤90°.

9. The turbine blade having a gas film cooling structure with a composite irregular groove of claim 7, wherein a connection portion where at least one side surface of the first portion and a corresponding side surface of the second portion are connected is a chamfered transition connection or an arc transition connection.

10. The turbine blade having a gas film cooling structure with a composite irregular groove of any one of claim 7, wherein the maximum diameter of each discrete hole A is d, the depth of each first groove is H, and the minimum width of each first groove is D, and wherein D≥d, and H≥2d.

11. The turbine blade having a gas film cooling structure with a composite irregular groove of claim 7, wherein the discrete holes A are straight circular holes, diffusion holes, or complex composite irregular holes, wherein, an angle between a central axis of each discrete hole A and a normal of surface of the turbine blade is θ, and 0°≤θ≤60°, and wherein, an opening end of each discrete hole A is provided with a chamfered transition, or a rounded transition.

12. The turbine blade having a gas film cooling structure with a composite irregular groove of claim 7, wherein H.sub.1:H.sub.2≥2:1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is an aerodynamic simulation diagram of the turbine blade of the present disclosure through which cooling gas passes.

(2) FIG. 2 is a schematic structure diagram of the turbine blade in embodiment 1 of the present disclosure.

(3) FIG. 3 is a schematic structure diagram illustrating a horizontal section of FIG. 2.

(4) FIG. 4 is a schematic structure diagram of a first groove in FIG. 3.

(5) FIG. 5 is a schematic diagram of cooling gas flow in a first groove of FIG. 3.

(6) FIG. 6 is a schematic structure diagram of the turbine blade in embodiment 2 of the present disclosure.

(7) FIG. 7 is a schematic structure diagram illustrating a horizontal section of the turbine blade in embodiment 3 of the present disclosure.

(8) FIG. 8 is a schematic structure diagram of a first groove in FIG. 7.

DETAILED DESCRIPTION OF THE EMBODIMENTS

(9) The present disclosure will be further described in detail below in conjunction with the embodiments. It should be indicated that the following embodiments are intended to facilitate the understanding of the present disclosure but not to limiting the scope of the present disclosure.

Reference Signs in FIGS. 2-8

(10) 14—discrete hole B;

(11) 15—hollow cavity;

(12) 100—turbine blade;

(13) 101—outer surface of the turbine blade;

(14) 102—inner surface of the turbine blade;

(15) 105—first groove;

(16) 106—combining line;

(17) 107—second groove;

(18) 301—second portion of the groove;

(19) 302—first portion of the groove;

(20) 400—discrete hole A;

(21) 500—bottom of the first groove;

(22) 501—bottom of the second groove;

(23) 600, 700—two side surfaces of the first groove; and

(24) 601, 701—two side surfaces of the second groove.

Embodiment 1

(25) In this embodiment, a turbine blade 100 has a hollow structure, and a structural diagram of the turbine blade is shown in FIG. 2, and FIG. 3 is a structural diagram illustrating a horizontal section of FIG. 2.

(26) A plurality of first grooves 105 spaced apart from and parallel to each other are provided on an outer surface 101 of the turbine blade 100, and the first grooves may partially or entirely extend in a length direction of the outer surface 101 of the turbine blade 100.

(27) FIG. 4 is an enlarged structural diagram of a first groove 105 in FIG. 3.

(28) As illustrated in FIG. 4, each first groove includes a bottom 500 and two groove side surfaces 600 and 700. A plurality of discrete holes A 400 extending to an inner surface 102 of the turbine blade are provided at the bottom of each first groove. In the embodiment, the outer surface 101 of the turbine blade and the inner surface 102 of the turbine blade are substantially parallel to each other. As shown in FIG. 1, the discrete holes A 400 are arranged substantially in a length direction of the first groove 105.

(29) The maximum diameter of the discrete holes A is d, the depth of the first groove is H, and the minimum width of the first groove is D, wherein D≥d, and H≥2d.

(30) In the embodiment, as shown in FIG. 4, the first groove includes two portions in the depth direction. A portion having a depth H.sub.1 from the bottom of the first groove is a first portion 302, and the rest thereof is a second portion 302. In other words, the depth of the second portion is H.sub.2=H−H.sub.1.

(31) In the embodiment, the first portion 302 of the groove has an inclined cylinder shape, and in a vertical section as shown in FIG. 4, two side surfaces of the first portion 302 of the groove are two straight line segments spaced apart from each other, the two straight line segments are parallel to each other, and an angle between each straight line segment of the first portion and the bottom of the first groove is 70°; one side surface of the second portion is also a straight line segment and is formed by extending from a corresponding side surface of the first portion, and the other side surface of the second portion is an arc line segment and is formed by expanding in lateral direction from the other side surface of the first portion. In the embodiment, an angle α between an axis of an opening end of each second portion in the depth direction and a normal of the outer surface 101 of the turbine blade is 30°.

(32) In the embodiment, H.sub.1 is slightly larger than H.sub.2.

(33) In the embodiment, an angle θ between a central axis of the discrete hole and a normal of the inner surface 102 of the turbine blade is 15°, and an opening end of the hole is provided with a rounded transition to avoid the stress concentration phenomenon due to sharp angles.

(34) FIG. 5 is a schematic diagram of cooling gas flow in a first groove of FIG. 3. After the cooling gas inside the inner surface 102 of the turbine blade enters the first groove through the discrete holes A, the gas from each discrete hole A may not only diffuse and mix in the length direction of the first groove, but also diffuse, mix, and superimpose on each other in the depth direction of the first groove. That is, the gas may sufficiently spread in the first portion of the first groove to form a continuous and uniform gas with positive pressure, and then flows, via the second portion of the first groove, to an opening end at the outer surface of the turbine blade and flows out, to form a continuous and uniform gas film adhered on the outer surface 101 of the turbine blade. Since the first groove has a relatively larger depth, the gas flowing out from the opening end of the first groove has a higher air pressure, and thus the continuous and uniform gas film formed on the outer surface of the turbine blade strongly attaches to the outer surface of the turbine blade.

(35) In the embodiment, a method of manufacturing the above-mentioned turbine blade includes: first, separately preparing the turbine blade 100 in two parts, i.e., as shown in FIG. 2, part I and part II, wherein part I and part II are combined at the combining line 106 to obtain a complete turbine blade 100; second, forming the first grooves 105 on an outer surface of part I, forming the discrete holes A on an inner surface of part I, forming the first grooves 105 on an outer surface of part II, and forming the discrete holes A on an inner surface of part II; and third, combining part I and part II at the combining line 106 to obtain a complete turbine blade 100.

Embodiment 2

(36) In this embodiment, a turbine blade 100 has a hollow structure, and a structural diagram of the turbine blade is shown in FIG. 2, and FIG. 3 is a structural diagram illustrating a horizontal section of FIG. 2.

(37) A plurality of first grooves 105 spaced apart from and parallel to each other are provided on an outer surface 101 of the turbine blade 100, the first grooves may partially or entirely extend in a length direction of the outer surface 101 of the turbine blade 100. A plurality of second grooves 107 spaced apart from and parallel to each other are provided on an inner surface 102 of the turbine blade 100.

(38) FIG. 6 is an enlarged structural diagram of a first groove 105 and a second groove 107 in FIG. 3.

(39) As illustrated in FIG. 6, each first groove includes a bottom 500 and two side surfaces 600 and 700. Each second groove 107 includes a bottom 501 and two side surfaces 601 and 701 parallel to a length direction of the second groove. A plurality of discrete holes A 400 extending to the bottom of the second groove are provided at the bottom of each first groove, and the discrete holes A 400 are arranged substantially along a length direction of the first groove 105.

(40) The maximum diameter of the discrete holes A is d, the depth of the first groove is H, and the minimum width of the first groove is D, wherein D≥d, and H≥2d.

(41) In the embodiment, the first groove 105 includes two portions in the depth direction. As shown in FIG. 6, a portion having a depth of H.sub.1 from the bottom of the first groove is a first portion 302, and the rest thereof is a second portion 302. In other words, the depth of the second portion is H.sub.2=H−H.sub.1.

(42) In the embodiment, the first portion 302 of the groove has an inclined cylinder shape, and in a vertical section as shown in FIG. 6, two side surfaces of the first portion 302 of the groove are two straight line segments spaced apart from each other, the two straight line segments are parallel to each other, and an angle between each straight line segment of the first portion and the bottom of the first groove is 70°; one side surface of the second portion is also a straight line segment and is formed by extending from a corresponding side surface of the first portion, and the other side surface is an arc line segment and is formed by expanding in lateral direction from the other side surface of the first portion. In the embodiment, an angle α between an axis of an opening end of each second portion in the depth direction and a normal of the surface 101 of the turbine blade is 30°.

(43) In the embodiment, H.sub.1 is slightly larger than H.sub.2.

(44) In the embodiment, an angle θ between a central axis of the discrete hole A and a normal of the inner surface 102 of the turbine blade is 15°, and an opening end of the hole is provided with a rounded transition to avoid the stress concentration phenomenon due to sharp angles.

(45) In the embodiment, the flow path of the cooling gas at the wall of the turbine blade includes: the cooling gas inside the inner surface 102 of the turbine blade is transmitted to the second groove, and efficiently flows along the second groove and generates a positive pressure, and then enters the first groove via the discrete holes A; and the cooling gas from each discrete hole A may not only diffuse and mix in the length direction of the first groove, but also diffuse, mix, and superimpose on each other in the depth direction of the first groove. That is, the gas may sufficiently spread in the first portion of the first groove to form a continuous and uniform gas with positive pressure, and then flows, via the second portion of the first groove, to an opening end at the outer surface of the turbine blade and flows out, to form a continuous and uniform gas film adhered on the outer surface of the turbine blade. Since the first groove has a relatively larger depth, the gas flowing out from the opening end of the first groove has a higher air pressure, and thus the continuous and uniform gas film formed on the outer surface of the turbine blade strongly attaches to the outer surface of the turbine blade.

(46) In the embodiment, a method of manufacturing the above-mentioned turbine blade includes: first, separately preparing the turbine blade 100 in two parts, i.e., as shown in FIG. 2, part I and part II, wherein part I and part II are combined at the combining line 106 to obtain a complete turbine blade 100; second, forming the first grooves 105 on an outer surface of part I, forming the second grooves 107 and the discrete holes A on an inner surface of part I, forming the first grooves 105 on an outer surface of part II, and forming the second grooves 107 and the discrete holes A on an inner surface of part II; and third, combining part I and part II at the combining line 106 to obtain a complete turbine blade 100.

Embodiment 3

(47) In this embodiment, a turbine blade 100 has a hollow structure, and a structural diagram of the turbine blade is shown in FIG. 2, and FIG. 7 is a structural diagram illustrating a horizontal section of FIG. 2.

(48) As shown in FIG. 7, a hollow cavity 15 is formed between an inner surface 102 and an outer surface 101 of the turbine blade 100. A plurality of discrete holes B 14 extending to the hollow cavity 15 are provided on the inner surface 102 of the turbine blade.

(49) A plurality of first grooves 105 spaced apart from and parallel to each other are provided on an outer surface 101 of the turbine blade 100, the first grooves may have a length partially or entirely extending in a length direction of the outer surface 101 of the turbine blade 100.

(50) FIG. 8 is an enlarged structural diagram of a first groove 105 in FIG. 7.

(51) As illustrated in FIG. 8, each first groove 105 includes a bottom 500 and two side surfaces 600 and 700. A plurality of discrete holes A 400 extending to the hollow cavity 15 are provided at the bottom of each first groove.

(52) In the embodiment, the outer surface 101 of the turbine blade and the inner surface 102 of the turbine blade are substantially parallel to each other. As shown in FIG. 1, the discrete holes A 400 are arranged substantially along a length direction of the first groove.

(53) The maximum diameter of the discrete holes A is d, the depth of the first groove is H, and the minimum width of the first groove is D, wherein D≥d, and H≥2d.

(54) In the embodiment, the first groove includes two portions in the depth direction. As shown in FIG. 4, a portion having a depth of H.sub.1 from the bottom of the first groove is a first portion 302, and the rest thereof is a second portion 302. In other words, the depth of the second portion is H.sub.2=H−H.sub.1.

(55) In the embodiment, the first portion 302 of the groove has an inclined cylinder shape, and in a vertical section as shown in FIG. 4, two side surfaces of the first portion 302 of the groove are two straight line segments spaced apart from each other, the two straight line segments are parallel to each other, and an angle between each straight line segment of the first portion and the bottom of the first groove is 70°; one side surface of the second portion is also a straight line segment and is formed by extending from a corresponding side surface of the first portion, and the other side surface is an arc line segment and is formed by expanding in lateral direction from the other side surface of the first portion. In the embodiment, an angle α between an axis of an opening end of each second portion in the depth direction and a normal of the surface 101 of the turbine blade is 30°.

(56) In the embodiment, H.sub.1 is slightly larger than H.sub.2.

(57) In the embodiment, an angle θ between a central axis of the discrete hole A and a normal of the inner surface 102 of the turbine blade is 15°, and an opening end of the hole is provided with a rounded transition to avoid the stress concentration phenomenon due to sharp angles.

(58) In the embodiment, the flow path of the cooling gas at the wall of the turbine blade includes: the cooling gas inside the inner surface 102 of the turbine blade enters the hollow cavity 15 via the discrete holes B, efficiently flows in the hollow cavity 15 and generates a positive pressure, and then enters the first groove via the discrete holes A; and the cooling gas from each discrete hole A may not only diffuse and mix in the length direction of the first groove, but also diffuse, mix, and superimpose on each other in the depth direction of the first groove. That is, the gas may sufficiently spread in the first portion of the first groove to form a continuous and uniform gas with positive pressure, and then flows, via the second portion of the first groove, to an opening end at the outer surface of the turbine blade and flows out, to form a continuous and uniform gas film adhered on the outer surface of the turbine blade. Since the first groove has a relatively larger depth, the gas flowing out from the opening end of the first groove has a higher air pressure, and thus the continuous and uniform gas film formed on the outer surface of the turbine blade strongly attaches to the outer surface of the turbine blade.

(59) In the embodiment, a method of manufacturing the above-mentioned turbine blade includes: first, separately preparing the turbine blade 100 in two parts, i.e., as shown in FIG. 2, part I and part II, wherein part I and part II are combined at the combining line 106 to obtain a complete turbine blade 100; second, forming the first grooves 105 and the discrete holes A on an outer surface of part I, forming the discrete holes B on an inner surface of part I, forming the first grooves 105 and the discrete holes A on an outer surface of part II, and forming the discrete holes B on an inner surface of part II; and third, combining part I and part II at the combining line 106 to obtain a complete turbine blade 100.

(60) The above-mentioned embodiments are detailed descriptions of the technical solution of the present disclosure. It is understood that the above-mentioned embodiments are only specific embodiments of the present disclosure and are not intended to limit the scope of the present disclosure. Any modifications, supplements, or substitutions within the scope of the principles of the present disclosure shall be included in the protection scope of the appended claims.