Turbine blade and gas turbine

Abstract

Provided are a turbine blade and a gas turbine capable of ensuring castability and improving cooling performance. A turbine blade of at least one embodiment of the present disclosure includes a pin fin flow path formed in a trailing edge portion of an airfoil portion and extending toward a trailing edge of the airfoil portion, and a plurality of pin fins connecting a pair of opposing inner walls that constitute the pin fin flow path. The pin fin flow path includes a first region and a second region on the trailing edge side from the first region. The plurality of pin fins includes a plurality of first pin fins provided in the first region and a plurality of second pin fins provided in the second region. A first diameter of the plurality of first pin fins is larger than a second diameter of the plurality of second pin fins. A first pin pitch of the plurality of first pin fins is larger than a second pin pitch of the plurality of second pin fins. A value obtained by dividing the first pin pitch by the first diameter is smaller than a value obtained by dividing the second pin pitch by the second diameter.

Description

Technical Field

[0001] This disclosure relates to turbine blades and gas turbines. Background Technology

[0002] As turbine blades for gas turbines, turbine blades that cool the trailing edge of the blade by means of pin-type fins are known (for example, see Patent Document 1).

[0003] Prior art literature

[0004] Patent documents

[0005] Patent Document 1: Japanese Patent Application Publication No. 2004-60638

[0006] For example, in the turbine blade described in Patent Document 1, a leading-edge passage and a trailing-edge passage are formed inside the airfoil (blade body), and a pin-fin flow path consisting of flow paths between pin-fins is formed on the trailing edge side of the blade body. Furthermore, cooling air that has cooled the leading-edge passage and the trailing-edge passage flows in the pin-fin flow path to cool the pin-fins.

[0007] For example, in a turbine blade with a cooling airflow path structure, such as the turbine blade described in Patent Document 1, the metal temperature is relatively high in the region where the leading-edge passage and the trailing-edge passage are provided, and sometimes it becomes overcooled in the region on the trailing edge side of the blade body where the pin-fin flow path is provided. In such cases, it is considered to suppress the metal temperature by expanding the region of the pin-fin flow path on the leading-edge side.

[0008] However, in the region where the flow path of the pin-type fins is enlarged on the leading edge side, the distance between the pair of opposing inner walls constituting the flow path of the pin-type fins increases, thus the length of the pin-type fins in this region also increases. Therefore, the pin-type fins in this region are prone to breakage during turbine blade casting, making them difficult to cast. Summary of the Invention

[0009] In view of the above, the object of at least one embodiment of the present disclosure is to provide a turbine blade that can ensure castability and improve cooling performance, and a gas turbine having the turbine blade.

[0010] (1) The turbine blade of at least one embodiment of the present disclosure comprises:

[0011] Airfoil;

[0012] A pin-type fin flow path is formed within the trailing edge of the airfoil and extends toward the trailing edge of the airfoil, opening at the trailing edge toward the outside of the airfoil; and

[0013] Multiple pin-shaped fins connect a pair of opposing inner walls that form the flow path of the pin-shaped fins.

[0014] The pin-fin flow path includes a first region and a second region located closer to the trailing edge than the first region.

[0015] The plurality of pin-type fins includes a plurality of first pin-type fins disposed in the first region and a plurality of second pin-type fins disposed in the second region.

[0016] The first diameter of the plurality of first pin-shaped fins is larger than the second diameter of the plurality of second pin-shaped fins.

[0017] The first pin spacing between the plurality of first pin fins is larger than the second pin spacing between the plurality of second pin fins.

[0018] The value obtained by dividing the first pin spacing by the first diameter is smaller than the value obtained by dividing the second pin spacing by the second diameter.

[0019] (2) The gas turbine of at least one embodiment of the present disclosure has turbine blades with the structure described in (1) above.

[0020] Invention Effects

[0021] According to at least one embodiment of the present disclosure, a turbine blade capable of ensuring castability and improving cooling performance, and a gas turbine having the turbine blade, can be provided. Attached Figure Description

[0022] Figure 1 This is a schematic diagram showing the structure of a gas turbine with turbine blades having several embodiments.

[0023] Figure 2 These are cross-sectional views of turbine blades in several embodiments.

[0024] Figure 3 This is a perspective view of the inner shroud of turbine blades in several embodiments, viewed from the bottom side.

[0025] Figure 4 This is a perspective view of the outer shroud of turbine blades in several embodiments, viewed from the top surface side.

[0026] Figure 5 This is a diagram showing the trailing edge of a turbine blade according to several embodiments. The upper section is a cross-sectional view obtained by cutting with a plane that is approximately orthogonal to the vertical axis of the turbine blade, and the lower section is a cross-sectional view obtained by cutting with a plane that is approximately parallel to the vertical axis of the turbine blade.

[0027] Figure 6 This is a table used to describe the dimensions of pin-type fins.

[0028] Figure 7This diagram illustrates the relationship between the dimensions of pin-type fins and the cooling performance in the pin-type fin flow path.

[0029] Explanation of reference numerals in the attached figures:

[0030] 3... Turbo;

[0031] 10... Turbine blades;

[0032] 11... Blade body (airfoil);

[0033] 11a...front edge;

[0034] 11b... trailing edge;

[0035] 15...posterior margin;

[0036] 16... Pin-type finned flow path;

[0037] 17...Inner wall;

[0038] 26... Pin-type fins;

[0039] 100... gas turbine;

[0040] 161...First region;

[0041] 162...Second region;

[0042] 163...Third region;

[0043] 261...First pin-type fin;

[0044] 262...Second pin fin;

[0045] 263... Third pin-type fin. Detailed Implementation

[0046] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. The dimensions, materials, shapes, and relative arrangements of the constituent components described in the embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0047] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" indicate relative or absolute configurations, not only in a strict sense, but also in a state of relative displacement by angle or distance with tolerance or to the extent that the same function can be obtained.

[0048] For example, expressions such as "same," "equal," and "homogeneous" that indicate the state of equality of things not only indicate a state of strict equality, but also indicate a state of difference in the degree to which the same function can be obtained due to tolerances.

[0049] For example, the descriptions of shapes such as quadrilaterals and cylindrical shapes not only refer to quadrilaterals and cylindrical shapes in a strict geometric sense, but also to shapes that include concave and convex parts, chamfered parts, etc., within the range where the same effect can be obtained.

[0050] On the other hand, expressions such as "possessing," "containing," "equipped with," "including," or "having" a constituent element are not exclusive expressions that exclude the existence of other constituent elements.

[0051] Hereinafter, turbine blades of several embodiments will be described with reference to the figures.

[0052] Figure 1 This is a schematic diagram showing the structure of a gas turbine with turbine blades having several embodiments.

[0053] Figure 2 These are cross-sectional views of turbine blades in several embodiments.

[0054] Figure 3 This is a perspective view of the inner shroud of turbine blades in several embodiments, viewed from the bottom side.

[0055] Figure 4 This is a perspective view of the outer shroud of turbine blades in several embodiments, viewed from the top surface side.

[0056] Figure 5 This is a diagram showing the trailing edge of a turbine blade according to several embodiments. The upper section is a cross-sectional view obtained by cutting with a plane that is approximately orthogonal to the vertical axis of the turbine blade, and the lower section is a cross-sectional view obtained by cutting with a plane that is approximately parallel to the vertical axis of the turbine blade.

[0057] Figure 6 This is a table used to describe the dimensions of pin-type fins.

[0058] Figure 7 This diagram illustrates the relationship between the dimensions of pin-type fins and the cooling performance in the pin-type fin flow path.

[0059] (Gas Turbine 100)

[0060] like Figure 1As shown, the gas turbine 100 in several embodiments includes: a compressor 1 that compresses external gas to generate compressed air; multiple burners 2 that mix and combust fuel supplied from a fuel supply source (not shown) with compressed air to generate combustion gas; and a turbine 3 driven by the combustion gas FG.

[0061] like Figure 2 As shown, the turbine 3 has a rotor 4 that rotates around an axis Ar. A generator 5, for example, is connected to the rotor 4 to generate electricity through the rotation of the rotor 4 (see reference). Figure 1 ).

[0062] Several embodiments of the turbine blade 10 can be adapted, for example, to the stator blade in the turbine 3.

[0063] (Turbine blade 10)

[0064] like Figure 2 As shown, the turbine blade 10 includes a blade body (airfoil) 11, and an inner shield 12 and an outer shield 13 respectively disposed on the inner and outer sides of the blade body 11.

[0065] The blade body 11 has a leading edge passage 42 and a trailing edge passage 44 formed inside it by ribs 40. In the leading edge passage 42 and the trailing edge passage 44, a bottomed cylindrical insert 46 and 47 with multiple cooling air holes 70 and 71 formed on the circumferential surface and the bottom surface are inserted from the outer shield 13 side.

[0066] The blade body 11 has a pin-type fin flow path 16 on its trailing edge 11b side. This pin-type fin flow path 16 is a passageway for a plurality of pin-type fins 26. The pin-type fin flow path 16 will be described in detail later.

[0067] Furthermore, if cooling air CA is supplied to these inserts 46, 47 from the manifold (not shown), the cooling air CA is ejected from the cooling air holes 70, 71 and collides with the inner walls of the leading edge passage 42 and the trailing edge passage 44 to perform so-called impact cooling. In addition, it flows in the pin-fin flow path 16 on the trailing edge side of the blade body 11 to perform pin-fin cooling.

[0068] It should be noted that a through hole (not shown) is formed on the rib 40, which extends between the end face on the leading edge 11a side and the end face on the trailing edge 11b side, through which cooling air CA can flow from the leading edge passage 42 into the trailing edge passage 44.

[0069] On the inner shroud 12, a front flange 81 and a rear flange 82 are formed on the front edge 11a side and the rear edge 11b side, respectively, and are connected to a sealing support 66 that supports a sealing member 14 that seals the arm portion 48 of the rotor 4. Furthermore, a cavity 45 is formed between the sealing support 66 and the inner shroud 12, and cooling air CA flowing out from the opening end 46a of the insert 46 is also supplied into the cavity 45.

[0070] In the sealing support 66, a flow path 85 is formed on the front side (the upward side in the direction of the axis Ar). Air is supplied from the cavity 45 through the gap between the front stage moving blade 18 side and the seal 14 to the rear stage moving blade 19 side via the flow path 85. The interior is kept at a high pressure higher than the passage of the high-temperature combustion gas FG to prevent the high-temperature combustion gas FG from seeping into the interior.

[0071] (Inner protective cover 12)

[0072] like Figure 3 As shown, a leading edge flow path 88 with multiple needle-shaped fins 89 is formed on the leading edge 11a side of the inner shield 12. In addition, tracks 96 are formed on both sides of the inner shield 12 along the front and rear, and a side flow path 93 is formed in the track 96, one end of which communicates with the leading edge flow path 88 and the other end of which opens into the combustion gas FG at the rear edge of the inner shield 12.

[0073] On the bottom surface of the inner shield 12, collision plates 84 with multiple small holes 101 are provided at intervals relative to the bottom surface. A cavity 83 is formed on the bottom surface side of the inner shield 12 through these collision plates 84 (see reference). Figure 2 ).

[0074] In addition, a plurality of trailing edge flow paths 92 are formed on the trailing edge side of the inner shield 12, one end of which is connected to the side flow path 93 and the other end is discharged into the combustion gas FG.

[0075] Additionally, the cooling air CA supplied to the cavity 45 also flows into the chamber 83 through the small hole 101 of the impact plate 84. As the cooling air CA flows into the chamber 83 through the small hole 101 of the impact plate 84, it collides with the bottom surface of the inner shield 12, thereby performing impact cooling. Furthermore, the cooling air CA supplied to the chamber 83 is fed into the leading edge flow path 88 of the inner shield 12, passing between the needle-shaped fins 89, thereby cooling the leading edge side of the inner shield 12. Then, it is released into the combustion gas FG from the trailing edge of the inner shield 12 through the side flow path 93 and the trailing edge flow path 92.

[0076] (Outer protective shield 13)

[0077] like Figure 4As shown, in the outer shield 13, a collision plate 102 with a plurality of small holes 107 is provided on its upper surface at intervals relative to the upper surface. A chamber 104 is formed on the upper surface side of the outer shield 13 through the collision plate 102 (see reference). Figure 2 ).

[0078] Additionally, a leading edge flow path 105 is formed in the outer outer cover 13, and side flow paths 106 are formed on both sides that communicate with the leading edge flow path 105 on the front side and open at the rear edge of the outer outer cover 13. The leading edge flow path 105 communicates with one of the chambers 104.

[0079] Furthermore, the cooling air CA supplied to the manifold (not shown) flows into the chamber 104 through the small hole 107 of the impact plate 102 and is released from the rear edge of the side flow path 106. As the cooling air CA flows into the chamber 104 through the small hole 107 of the impact plate 102, it collides with the upper surface of the outer shield 13, thereby achieving impact cooling.

[0080] In addition, the cooling air CA flowing into the chamber 104 also flows into the leading edge flow path 105, and through the leading edge flow path 105 and the side flow path 106, the leading edge and the two sides of the outer shield 13 are cooled, and then released from the rear edge of the outer shield 13.

[0081] (Regarding the pin-type fin flow path 16)

[0082] like Figure 2 and Figure 5 As shown, turbine blades 10 in several embodiments include a pin-shaped fin flow path 16 formed within the trailing edge portion 15 of the blade body 11 and extending toward the trailing edge 11b of the blade body 11, opening toward the outside of the blade body 11 at the trailing edge 11b. Turbine blades 10 in several embodiments include a plurality of pin-shaped fins 26 connecting a pair of opposing inner walls 17 constituting the pin-shaped fin flow path 16. The pair of opposing inner walls 17 constituting the pin-shaped fin flow path 16 are a back wall portion 21a and a ventral wall portion 21b of the blade body 11. It should be noted that... Figure 5 The dorsal wall portion 21a and ventral wall portion 21b shown in the upper section are actually curved along the dorsal wall surface 22a and ventral wall surface 22b, but... Figure 5 In the diagram, for the sake of simplification, the dorsal wall portion 21a and the ventral wall portion 21b are not bent and are shown in a simplified manner.

[0083] like Figure 5 As shown in the upper section, the passage width W of the pin-fin flow path 16, that is, the distance between a pair of opposing inner walls 17, is formed to gradually narrow from the leading edge 11a side toward the trailing edge 11b side (the front end becomes thinner).

[0084] In addition, such as Figure 5As shown in the upper and lower sections, the pin-fin flow path 16 extends from the leading edge 11a side toward the trailing edge 11b side and includes, for example, a first region 161, a second region 162, and a third region 163.

[0085] The plurality of pin fins 26 disposed in the pin fin flow path 16 include a plurality of first pin fins 261 disposed in the first region 161, a plurality of second pin fins 262 disposed in the second region 162, and a plurality of third pin fins 263 disposed in the third region 163.

[0086] In several embodiments of the turbine blade 10, the diameter d of the plurality of pin-type fins 26 is set as follows. For example, the diameter d of the first pin-type fin 261 is a first diameter d1, the diameter d of the second pin-type fin 262 is a second diameter d2, and the diameter d of the third pin-type fin 263 is a third diameter d3.

[0087] In several embodiments of the turbine blade 10, the first diameter d1 is larger than the second diameter d2 (d2 < d1), and the third diameter d3 is equal to the second diameter d2 (d2 = d3).

[0088] In several embodiments of the turbine blade 10, the pin fins 26 are formed such that the first pin spacing p1 of the first pin fin 261 (the arrangement spacing in a direction approximately parallel to the vertical setting direction axis AX of the blade body 11, i.e., the center-to-center distance of the pin fins 26 along the vertical setting direction axis AX, and the arrangement spacing in a direction approximately orthogonal to the vertical setting direction axis AX of the blade body 11, i.e., the row-to-row distance of the pin fin rows (a plurality of pin fins 26 arranged along the vertical setting direction axis AX) is larger than the second pin spacing p2 of the second pin fin 262 (p2 < p1), and the second pin spacing p2 of the second pin fin 262 is smaller than the third pin spacing p3 of the third pin fin 263 (p2 < p3).

[0089] It should be noted that for the pin spacing p of the pin-type fins 26 within the same region, the arrangement spacing in the direction approximately parallel to the vertical setting direction axis AX of the blade body 11 and the arrangement spacing in the direction approximately orthogonal to the vertical setting direction axis AX of the blade body 11 are set to the same spacing (or the first pin spacing p1 if it is the first region 161). However, the arrangement spacing in the approximately parallel direction and the arrangement spacing in the approximately orthogonal direction may not be the same, but different. However, regarding the proportion of change in the arrangement spacing compared between regions, it is preferable that the arrangement spacing in the direction approximately parallel to the vertical setting direction axis AX and the arrangement spacing in the direction approximately orthogonal to the vertical setting direction axis AX change at the same proportion.

[0090] In several embodiments of the turbine blade 10, the cooling performance in the pin-fin flow path 16 varies according to the value p / d, which is obtained by dividing the pin pitch p by the diameter d of the pin-fin 26. In the following description, the value p / d obtained by dividing the pin pitch p by the diameter d of the pin-fin 26 is also referred to as the diameter-pitch ratio p / d.

[0091] For example, Figure 7 As shown, in several embodiments of the turbine blade 10, the cooling performance in the pin-fin flow path 16 is maximized when the diameter-to-pitch ratio p / d is between 1.0 and 2.0, and more specifically between 1.5 and 2.0. It should be noted that when the diameter-to-pitch ratio p / d is 1.0, there is no gap between adjacent pin-fins, therefore cooling air CA cannot flow in the pin-fin flow path 16.

[0092] like Figure 7 As shown, the cooling performance of the pin-fin flow path 16 increases when the diameter-to-pitch ratio p / d is small. However, as mentioned above, the cooling performance of the pin-fin flow path 16 is maximized when the diameter-to-pitch ratio p / d is between 1.5 and 2.0. Therefore, if the diameter-to-pitch ratio p / d is too small, the cooling performance of the pin-fin flow path 16 decreases as the diameter-to-pitch ratio p / d becomes smaller. In other words, the cooling performance of the pin-fin flow path 16 increases when the diameter-to-pitch ratio p / d is relatively small, provided that the diameter-to-pitch ratio p / d is not too small.

[0093] In the region on the leading edge 11a side of the pin-fin flow path 16, the distance (passage width W) between the pair of opposing inner walls 17 constituting the pin-fin flow path 16 is larger than that on the trailing edge 11b side. Therefore, the length of the pin fins 26 in the region on the leading edge 11a side of the pin-fin flow path 16 becomes longer, making the pin fins 26 in this region prone to breakage and difficult to cast during the casting of the turbine blade 10.

[0094] To improve castability, the diameter d of the pin fin 26 in this region is considered to be increased. However, if the pin spacing p of the pin fin 26 is not changed and only the diameter d of the pin fin 26 is increased, the diameter-spacing ratio p / d becomes too small, which may reduce the cooling performance in this region.

[0095] Therefore, in several embodiments of the turbine blade 10, the first diameter d1 is made larger than the second diameter d2 (d2 < d1).

[0096] By making the first diameter d1 larger than the second diameter d2, castability can be ensured even if the length of the first pin fin 261 increases.

[0097] In several embodiments of the turbine blade 10, the diameter-to-pitch ratio p / d (p1 / d1) of the first pin fin 261 is smaller than the diameter-to-pitch ratio p / d (p2 / d2) of the second pin fin 262.

[0098] By making the diameter-to-spacing ratio p / d (p1 / d1) of the first pin fin 261 smaller than the diameter-to-spacing ratio p / d (p2 / d2) of the second pin fin 262, the cooling performance in the first region 161 can be greater than that in the second region 162.

[0099] In several embodiments of the turbine blade 10, the first pin spacing p1 is made larger than the second pin spacing p2 (p2 < p1).

[0100] By making the first pin spacing p1 larger than the second pin spacing p2, it is possible to avoid a decrease in cooling performance in the first region 161 due to the diameter-spacing ratio p / d becoming too small.

[0101] Therefore, the turbine blades 10 according to several embodiments can ensure castability in the first region 161 and improve cooling performance. Furthermore, the turbine blades 10 according to several embodiments can improve cooling performance, thereby reducing the flow rate of cooling air CA.

[0102] In several embodiments of the gas turbine 100, turbine blades 10 are provided in several embodiments, so the flow rate of cooling air CA in the turbine blades 10 can be suppressed, and the performance of the gas turbine 100 can be improved.

[0103] In several embodiments of the turbine blade 10, the first region 161 is preferably the region closest to the leading edge 11a of the blade body 11 in the pin-fin flow path 16.

[0104] In the region closest to the leading edge 11a of the blade body 11 in the pin-fin flow path 16, the distance (passage width W) between the pair of opposing inner walls 17 constituting the pin-fin flow path 16 is larger than in other regions. Therefore, the length of the pin-fin 26 is longer and more difficult to cast compared to other regions.

[0105] According to several embodiments of the turbine blade 10, in the first region 161 where the length of the pin fin 26 is longer and difficult to cast, compared to other regions, castability in the first region 161 can be ensured and cooling performance can be improved.

[0106] In several embodiments of the turbine blade 10, the second region 162 may also be adjacent to the first region 161.

[0107] Thus, in the region (first region 161) adjacent to the leading edge 11a relative to the second region 162, castability can be ensured and cooling performance can be improved.

[0108] In several embodiments of the turbine blade 10, the diameter-to-pitch ratio p / d (p3 / d3) of the third pin fin 263 may also be larger than the diameter-to-pitch ratio p / d (p2 / d2) of the second pin fin 262.

[0109] In the third region 163, which is located on the trailing edge 11b side of the second region 162, the cooling performance can also be suppressed compared to the second region 162. Therefore, the diameter-pitch ratio p / d (p3 / d3) of the third pin fin 263 can also be larger than the diameter-pitch ratio p / d (p2 / d2) of the second pin fin 262.

[0110] Therefore, by increasing the diameter-spacing ratio p / d (p3 / d3) of the third pin fin 263, the size of the third pin spacing p3 relative to the third diameter d3 becomes larger. As a result, the proportion of the third pin fin 263 in the third region 163 becomes smaller, which can suppress the pressure loss of the cooling air CA in the third region 163.

[0111] In several embodiments of the turbine blade 10, the third diameter d3 may also be equal to the second diameter d2 (d3 = d2).

[0112] In the third region 163, located on the trailing edge 11b side of the second region 162, the distance (passage width W) between the pair of opposing inner walls 17 constituting the pin-fin flow path 16 is smaller than that in the second region 162. Therefore, it is not necessary to make the third diameter d3 of the third pin-fin 263 larger than the second diameter d2 of the second pin-fin 262, as in the first region 161. As mentioned above, the diameter-pitch ratio p / d has a significant impact on cooling performance. Furthermore, regarding the relationship between the diameter-pitch ratio p / d (p2 / d2) of the second pin-fin 262 and the diameter-pitch ratio p / d (p3 / d3) of the third pin-fin 263, if the third diameter d3 is made equal to the second diameter d2, it is possible to set the value using only the relationship between the second pin pitch p2 and the third pin pitch p3. Therefore, if the third diameter d3 is made equal to the second diameter d2, it becomes easier to set the cooling performance of the third region 163 during the design phase of the turbine blade 10.

[0113] In several embodiments of the turbine blade 10, the third pin spacing p3 may also be larger than the second pin spacing p2 (p2 < p3).

[0114] As described above, in the third region 163, which is located on the trailing edge 11b side of the second region 162, the cooling performance can also be suppressed compared to the second region. Therefore, the diameter-pitch ratio p / d (p3 / d3) of the third pin fin 263 can also be larger than the diameter-pitch ratio p / d (p2 / d2) of the second pin fin 262.

[0115] To increase the diameter-to-pitch ratio p / d (p3 / d3) of the third pin fin 263, the third pin pitch p3 can be increased, or the third diameter d3 can be decreased. However, if the third diameter d3 is decreased, the castability of the third pin fin 263 may be reduced.

[0116] Therefore, if the third pin spacing p3 is made larger than the second pin spacing p2, the diameter-spacing ratio p / d(p3 / d3) of the third pin fin 263 can be increased, and the castability of the third pin fin 263 can be ensured.

[0117] In several embodiments of the turbine blade 10, the third pin spacing p3 can also be greater than or equal to the first pin spacing p1 (p1≤p3).

[0118] As described above, the diameter-to-pitch ratio p / d (p1 / d1) of the first pin-type fin 261 is smaller than the diameter-to-pitch ratio p / d (p2 / d2) of the second pin-type fin 262. Furthermore, the diameter-to-pitch ratio p / d (p3 / d3) of the third pin-type fin 263 can also be larger than the diameter-to-pitch ratio p / d (p2 / d2) of the second pin-type fin 262. Therefore, the diameter-to-pitch ratio p / d (p3 / d3) of the third pin-type fin 263 can also be larger than the diameter-to-pitch ratio p / d (p1 / d1) of the first pin-type fin 261. Therefore, the third pin pitch p3 can also be greater than or equal to the first pin pitch p1.

[0119] It should be noted that in the turbine blades 10 of several embodiments, the third pin spacing p3 may also be smaller than the first pin spacing p1 (p3 < p1).

[0120] That is, if the diameter-pitch ratio p / d (p3 / d3) of the third pin fin 263 is larger than the diameter-pitch ratio p / d (p1 / d1) of the first pin fin 261, then the third pin pitch p3 can also be smaller than the first pin pitch p1.

[0121] This disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations thereof.

[0122] For example, the cross-sectional shape of the pin-type fins 26 in the above-described embodiments is not limited to a circle; it can also be any shape such as a blade, streamline, polygon, or ellipse. It should be noted that when the cross-sectional shape of the pin-type fin 26 is not circular, the diameter d of the pin-type fin 26 can also be the equivalent circle diameter of the cross-sectional shape. Furthermore, the pin spacing p can also be the distance between the centers of view of two adjacent pin-type fins 26.

[0123] The turbine blades 10 described above can be applied to the stationary blades in the turbine 3, but can also be applied to the moving blades.

[0124] The contents described in the above embodiments should be understood as follows.

[0125] (1) A turbine blade according to at least one embodiment of the present disclosure comprises: an airfoil (blade body 11); a pin-type fin flow path 16 formed within the trailing edge portion 15 of the airfoil (blade body 11) and extending toward the trailing edge 11b of the airfoil (blade body 11), opening at the trailing edge 11b toward the outside of the airfoil (blade body 11); and a plurality of pin-type fins 26 connecting a pair of opposing inner walls 17 constituting the pin-type fin flow path 16. The pin-type fin flow path 16 includes a first region 161 and a second region 162 located on the trailing edge 11b side of the first region 161. The plurality of pin-type fins 26 includes a plurality of first pin-type fins 261 disposed in the first region 161 and a plurality of second pin-type fins 262 disposed in the second region 162. The first diameter d1 of the plurality of first pin-type fins 261 is larger than the second diameter d2 of the plurality of second pin-type fins 262. The first pin spacing p1 between the multiple first pin fins 261 is larger than the second pin spacing p2 between the multiple second pin fins 262. The value (p1 / d1) obtained by dividing the first pin spacing p1 by the first diameter d1 is smaller than the value (p2 / d2) obtained by dividing the second pin spacing p2 by the second diameter d2.

[0126] According to the structure described in (1) above, by making the first diameter d1 of the plurality of first pin fins 261 larger than the second diameter d2 of the plurality of second pin fins 262, castability can be ensured even if the length of the plurality of first pin fins 261 increases. According to the structure described in (1) above, by making the value (p1 / d1) obtained by dividing the first pin spacing p1 by the first diameter d1 smaller than the value (p2 / d2) obtained by dividing the second pin spacing p2 by the second diameter d2, the cooling performance in the first region 161 can be greater than the cooling performance in the second region 162. Furthermore, according to the structure described in (1) above, by making the first pin spacing p1 between the plurality of first pin fins 261 larger than the second pin spacing p2 between the plurality of second pin fins 262, the reduction in cooling performance in the first region 161 due to the diameter-spacing ratio p / d becoming too small can be avoided. Therefore, according to the structure described in (1) above, castability in the first region 161 can be ensured and cooling performance can be improved. Furthermore, based on the structure described in (1) above, the flow rate of cooling air CA can be reduced by improving cooling performance.

[0127] (2) In several embodiments, based on the structure described in (1) above, it is preferable that the first region 161 is the region closest to the leading edge 11a of the airfoil (blade body 11) in the pin fin flow path 16.

[0128] In the region of the pin-fin flow path 16 closest to the leading edge 11a of the airfoil (blade body 11), the distance (passage width W) between the pair of opposing inner walls 17 constituting the pin-fin flow path 16 is larger than in other regions. Therefore, the length of the pin-fin 26 is longer and more difficult to cast compared to other regions.

[0129] Based on the structure described in (2) above, compared to the other regions, in the first region 161 where the length of the pin fin 26 is longer and difficult to cast, the castability of the first region 161 can be ensured and the cooling performance can be improved.

[0130] (3) In several embodiments, based on the structure of (1) or (2) above, the second region 162 may be adjacent to the first region 161.

[0131] According to the structure described above (3), in the region (first region 161) adjacent to the second region 162 on the leading edge 11a side, castability can be ensured and cooling performance can be improved.

[0132] (4) In several embodiments, based on any of the structures in (1) to (3) above, the pin-fin flow path 16 may also include a third region 163 located on the trailing edge 11b side of the second region 162. The plurality of pin-fins 26 preferably include a plurality of third pin-fins 263 disposed in the third region 163. The value (p3 / d3) obtained by dividing the third pin spacing p3 of the plurality of third pin-fins 263 by the third diameter d3 of the plurality of third pin-fins 263 may also be larger than the value (p2 / d2) obtained by dividing the second pin spacing p2 by the second diameter d2.

[0133] In the third region 163, which is located on the rear edge 11b side of the second region 162, the cooling performance can also be suppressed compared to the second region 162. Therefore, the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3 can also be larger than the value (p2 / d2) obtained by dividing the second pin spacing p2 by the second diameter d2.

[0134] According to the structure of (4) above, by increasing the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3, the size of the third pin spacing p3 relative to the third diameter d3 becomes larger. Therefore, the proportion of the third pin fin 263 in the pin fin flow path 16 becomes smaller, which can suppress the pressure loss of cooling air in the third region 163.

[0135] (5) In several embodiments, based on the structure of (4) above, the third diameter d3 may be equal to the second diameter d2.

[0136] In the third region 163, located on the trailing edge 11b side of the second region 162, the distance (passage width W) between the pair of opposing inner walls 17 constituting the pin-fin flow path 16 is smaller than that in the second region 162. Therefore, it is not necessary to make the third diameter d3 of the plurality of third pin-fins 263 larger than the second diameter d2 of the plurality of second pin-fins 262, as in the first region 161. According to the structure described above (5), the third diameter d3 is equal to the second diameter d2, so the diameter-pitch ratio p / d, which has a significant impact on cooling performance, can be set using only the relationship between the second pin pitch p2 and the third pin pitch p3. As a result, setting the cooling performance of the third region 163 in the design phase of the turbine blade 10 becomes easier.

[0137] (6) In several embodiments, based on the structure of (4) or (5) above, the third pin spacing p3 may be larger than the second pin spacing p2.

[0138] In the third region 163, which is located on the rear edge 11b side of the second region 162, the cooling performance can also be suppressed compared to the second region 162. Therefore, the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3 can also be larger than the value (p2 / d2) obtained by dividing the second pin spacing p2 by the second diameter d2.

[0139] To increase the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3, the third pin spacing p3 can be increased or the third diameter d3 can be decreased. However, decreasing the third diameter d3 may reduce the castability of the third pin fin 263.

[0140] According to the structure described in (6) above, if the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3 is increased by making the third pin spacing p3 larger than the second pin spacing p2, then even if the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3 is increased, the castability of the third pin fin 263 can still be ensured.

[0141] (7) In several embodiments, based on any of the structures in (4) to (6) above, the third pin spacing p3 may be greater than or equal to the first pin spacing p1.

[0142] As described above, the value (p1 / d1) obtained by dividing the first pin spacing p1 by the first diameter d1 is smaller than the value (p2 / d2) obtained by dividing the second pin spacing p2 by the second diameter d2. Furthermore, the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3 can also be larger than the value (p2 / d2) obtained by dividing the second pin spacing p2 by the second diameter d2. Therefore, the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3 can also be larger than the value (p1 / d1) obtained by dividing the first pin spacing p1 by the first diameter d1. Therefore, as in the structure described in (7) above, the third pin spacing p3 can also be greater than or equal to the first pin spacing p1.

[0143] (8) In several embodiments, based on any of the structures in (4) to (6) above, the third pin spacing p3 may be smaller than the first pin spacing p1.

[0144] As described above, the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3 can also be larger than the value (p1 / d1) obtained by dividing the first pin spacing p1 by the first diameter d1. It should be noted that if the value (p3 / d3) obtained by dividing the third pin spacing p3 by the third diameter d3 is larger than the value (p1 / d1) obtained by dividing the first pin spacing p1 by the first diameter d1, then as in the structure described above (8), the third pin spacing p3 can also be smaller than the first pin spacing p1.

[0145] (9) The gas turbine 100 of at least one embodiment of the present disclosure has turbine blades 10 with any of the structures described in (1) to (8) above.

[0146] According to the structure described above (9), the flow rate of cooling air CA in the turbine blades 10 can be suppressed, thereby improving the performance of the gas turbine 100.

Claims

1. A turbine blade, wherein, The turbine blades have: Airfoil; A pin-type fin flow path is formed within the trailing edge of the airfoil and extends toward the trailing edge of the airfoil, opening at the trailing edge toward the outside of the airfoil; and Multiple pin-shaped fins connect a pair of opposing inner walls that form the flow path of the pin-shaped fins. The pin-fin flow path includes a first region and a second region located closer to the trailing edge than the first region. The distance between the pair of opposing inner walls of the pin-fin flow path is greater in the first region than in the second region. The plurality of pin-type fins includes a plurality of first pin-type fins disposed in the first region and a plurality of second pin-type fins disposed in the second region. The first diameter of the plurality of first pin-shaped fins is larger than the second diameter of the plurality of second pin-shaped fins. The first pin spacing between the plurality of first pin fins is larger than the second pin spacing between the plurality of second pin fins. The value obtained by dividing the first pin spacing by the first diameter is smaller than the value obtained by dividing the second pin spacing by the second diameter.

2. The turbine blade according to claim 1, wherein, The first region is the region closest to the leading edge of the airfoil in the pin-fin flow path.

3. The turbine blade according to claim 1 or 2, wherein, The second region is adjacent to the first region.

4. The turbine blade according to claim 1 or 2, wherein, The pin-fin flow path includes a third region located closer to the trailing edge than the second region. The plurality of pin-type fins includes a plurality of third pin-type fins disposed in the third region. The value obtained by dividing the third pin spacing of the plurality of third pin fins by the third diameter of the plurality of third pin fins is greater than the value obtained by dividing the second pin spacing by the second diameter.

5. The turbine blade according to claim 4, wherein, The third diameter is equal to the second diameter.

6. The turbine blade according to claim 4, wherein, The third pin spacing is larger than the second pin spacing.

7. The turbine blade according to claim 4, wherein, The third pin spacing is greater than or equal to the first pin spacing.

8. The turbine blade according to claim 4, wherein, The third pin spacing is smaller than the first pin spacing.

9. The turbine blade according to claim 1, wherein, The value obtained by dividing the first pin spacing by the first diameter and the value obtained by dividing the second pin spacing by the second diameter are both greater than 1.5 and less than 2.

0.

10. The turbine blade according to claim 1, wherein, The first pin spacing between the plurality of first pin-type fins in a direction parallel to the vertical orientation axis of the airfoil is larger than the second pin spacing between the plurality of second pin-type fins in a direction parallel to the vertical orientation axis of the airfoil. The first pin spacing between the plurality of first pin-type fins in a direction orthogonal to the vertical axis of the airfoil is greater than the second pin spacing between the plurality of second pin-type fins in a direction orthogonal to the vertical axis of the airfoil. The value obtained by dividing the first pin spacing in the direction parallel to the vertical axis of the airfoil by the first diameter is smaller than the value obtained by dividing the second pin spacing in the direction parallel to the vertical axis of the airfoil by the second diameter. The value obtained by dividing the first pin spacing in the direction orthogonal to the vertical setting axis of the airfoil by the first diameter is smaller than the value obtained by dividing the second pin spacing in the direction orthogonal to the vertical setting axis of the airfoil by the second diameter.

11. A gas turbine, wherein, The gas turbine includes turbine blades as described in any one of claims 1 to 10.

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