JP5357601B2

JP5357601B2 - Turbine blade

Info

Publication number: JP5357601B2
Application number: JP2009087509A
Authority: JP
Inventors: 剛北村; 大悟藤村; 哲羽田
Original assignee: Mitsubishi Heavy Industries Ltd
Current assignee: Mitsubishi Heavy Industries Ltd
Priority date: 2009-03-31
Filing date: 2009-03-31
Publication date: 2013-12-04
Anticipated expiration: 2029-03-31
Also published as: JP2010236487A

Abstract

<P>PROBLEM TO BE SOLVED: To reduce peeling and pressure loss in a U-turn part of a serpentine flow passage and to improve cooling performance. <P>SOLUTION: This turbine blade includes a semi-circular part 35 at a tip end of a partitioning wall 32 partitioning a cooling passage 6a positioned further upstream of the U-turn part 17 of the serpentine flow passage and a cooling passage 6b positioned downstream and projecting toward the U-turn part 17, and an expansion part 34 projecting toward the inside of the cooling passage 6b positioned downstream and having a linear part 36 for gradually increasing a flow passage cross sectional area and the flow passage width of the cooling passage 6b positioned downstream. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

本発明は、ガスタービンに関し、より詳しくは、ガスタービンのタービン用翼（動翼・静翼）に関するものである。 The present invention relates to a gas turbine, and more particularly to a turbine blade (moving blade / static blade) of a gas turbine.

ガスタービンのタービン用翼としては、例えば、特許文献１に開示されたものが知られている。 As a turbine blade of a gas turbine, for example, one disclosed in Patent Document 1 is known.

特開２００１−２７１６０３号公報JP 2001-271603 A

上記特許文献１に開示されたタービン用翼の冷却通路には、冷却性能を向上させるという観点から、サーペンタイン流路が採用されている。
しかしながら、サーペンタイン流路のＵターン部（反転部）では、上流側の冷却通路と下流側の冷却通路とを仕切る隔壁の先端部における下流側の冷却通路を形成する面の近傍、および、Ｕターン部の隅部（角部）に流体（冷却媒体）の剥離が生じ、圧力損失が増大するとともに、冷却性能が低下してしまうといった問題点があった。 A serpentine flow path is employed in the cooling passage of the turbine blade disclosed in Patent Document 1 from the viewpoint of improving the cooling performance.
However, in the U-turn part (reversal part) of the serpentine flow path, the vicinity of the surface forming the downstream cooling passage at the tip of the partition wall that partitions the upstream cooling passage and the downstream cooling passage, and the U-turn The fluid (cooling medium) is peeled off at the corners (corner portions), increasing the pressure loss and reducing the cooling performance.

本発明は、上記の事情に鑑みてなされたもので、サーペンタイン流路のＵターン部における剥離および圧力損失を低減させることができ、冷却性能を向上させることができるタービン用翼を提供することを目的とする。 The present invention has been made in view of the above circumstances, and provides a turbine blade that can reduce peeling and pressure loss in a U-turn portion of a serpentine flow path and can improve cooling performance. Objective.

本発明は、上記課題を解決するため、以下の手段を採用した。
本発明に係るタービン用翼は、翼根部から供給された冷却媒体を翼の内部に導くサーペンタイン流路を備えたタービン用翼であって、前記サーペンタイン流路のＵターン部よりも上流側に位置する冷却通路と、下流側に位置する冷却通路とを仕切る隔壁の先端部に、前記Ｕターン部に向かって突出する半円部と、下流側に位置する冷却通路内に向かって突出するとともに、下流側に位置する冷却通路の流路断面積および流路幅を徐々に増加させる直線部とを有してなる膨出部を備え、前記隔壁の、前記直線部よりも下流側に位置する冷却通路を形成する表面と、前記直線部の表面との成す角度が５度から１０度までの範囲内に設定され、前記半円部の半径を前記隔壁の前記膨出部を含まない部分の板厚で除した値が１から３までの範囲内に設定されているとともに、前記隔壁の、前記直線部よりも下流側に位置する冷却通路を形成する表面と、前記直線部の表面との成す角度が５度に設定され、前記半円部の半径を前記隔壁の前記膨出部を含まない部分の板厚で除した値が２から３までの範囲内に設定されている。 The present invention employs the following means in order to solve the above problems.
A turbine blade according to the present invention is a turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root part to the inside of the blade, and is located upstream of a U-turn portion of the serpentine flow path. And a semicircular portion projecting toward the U-turn portion, and projecting into the cooling passage located on the downstream side, at the tip of the partition wall that partitions the cooling passage and the cooling passage located on the downstream side, A cooling portion located downstream of the straight portion of the partition wall, the bulging portion having a flow passage cross-sectional area of the cooling passage located on the downstream side and a straight portion gradually increasing the flow passage width. An angle between the surface forming the passage and the surface of the linear portion is set within a range of 5 degrees to 10 degrees, and the radius of the semicircular portion is a portion of the plate not including the bulging portion Set the value divided by thickness within the range of 1 to 3. And an angle formed between the surface of the partition wall forming the cooling passage located downstream of the straight line portion and the surface of the straight line portion is set to 5 degrees, and the radius of the semicircular portion is set. A value obtained by dividing the partition wall by the thickness of the portion not including the bulging portion is set within a range of 2 to 3 .

本発明に係るタービン用翼によれば、Ｕターン部の上流側に位置する冷却通路を隔壁に沿って流れてきた冷却媒体は、膨出部を備えていない従来のタービン用翼の隔壁のように急激に転回されることなく、半円部および直線部の表面にガイドされて（半円部および直線部の表面に沿って）Ｕターン部の下流側に位置する冷却通路に滑らかに流入していくことになるので、Ｕターン部における剥離および圧力損失を低減させることができ、冷却性能を向上させることができる。
また、本発明に係るタービン用翼によれば、Ｕターン部における剥離および圧力損失をさらに低減させることができ、冷却性能をさらに向上させることができる。 According to the turbine blade according to the present invention, the cooling medium flowing along the partition through the cooling passage located on the upstream side of the U-turn portion is like the partition of a conventional turbine blade not provided with the bulging portion. Without being suddenly turned around, it is guided by the surface of the semicircular part and the straight part (along the surface of the semicircular part and the linear part) and smoothly flows into the cooling passage located downstream of the U-turn part. Therefore, peeling and pressure loss in the U-turn portion can be reduced, and cooling performance can be improved.
Moreover, according to the turbine blade according to the present invention, separation and pressure loss in the U-turn portion can be further reduced, and the cooling performance can be further improved.

本発明に係るタービン用翼は、翼根部から供給された冷却媒体を翼の内部に導くサーペンタイン流路を備えたタービン用翼であって、前記サーペンタイン流路のＵターン部よりも上流側に位置する冷却通路と、下流側に位置する冷却通路とを仕切る隔壁の先端部に、前記Ｕターン部に向かって突出する半円部と、下流側に位置する冷却通路内に向かって突出するとともに、下流側に位置する冷却通路の流路断面積および流路幅を徐々に増加させる直線部とを有してなる膨出部を備え、前記直線部の背側に位置して、前記隔壁の、前記上流側に位置する冷却通路を形成する表面に、断面視円弧状の凹みが設けられている。 A turbine blade according to the present invention is a turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root part to the inside of the blade, and is located upstream of a U-turn portion of the serpentine flow path. And a semicircular portion projecting toward the U-turn portion, and projecting into the cooling passage located on the downstream side, at the tip of the partition wall that partitions the cooling passage and the cooling passage located on the downstream side, A bulging portion having a flow passage cross-sectional area and a linear portion that gradually increases the flow passage width of the cooling passage located on the downstream side, located on the back side of the straight portion, The surface forming the cooling passage located on the upstream side is provided with a recess having an arc shape in cross section .

本発明に係るタービン用翼によれば、Ｕターン部の上流側に位置する冷却通路を隔壁に沿って流れてきた冷却媒体は、膨出部を備えていない従来のタービン用翼の隔壁のように急激に転回されることなく、半円部および直線部の表面にガイドされて（半円部および直線部の表面に沿って）Ｕターン部の下流側に位置する冷却通路に滑らかに流入していくことになるので、Ｕターン部における剥離および圧力損失を低減させることができ、冷却性能を向上させることができる。
また、本発明に係るタービン用翼によれば、膨出部を設けたことによる隔壁の肉厚の増加を最小限にすることができるので、膨出部の熱容量を小さくでき、膨出部を設けたことによるホットスポットの発生を低減させることができる。また、ホットスポットを冷却するために冷却媒体量を増やす必要性が軽減され、冷却性能をさらに向上させることができる。 According to the turbine blade according to the present invention, the cooling medium flowing along the partition through the cooling passage located on the upstream side of the U-turn portion is like the partition of a conventional turbine blade not provided with the bulging portion. Without being suddenly turned around, it is guided by the surface of the semicircular part and the straight part (along the surface of the semicircular part and the linear part) and smoothly flows into the cooling passage located downstream of the U-turn part. Therefore, peeling and pressure loss in the U-turn portion can be reduced, and cooling performance can be improved.
Further, according to the turbine blade according to the present invention, since the increase in the wall thickness of the partition wall due to the provision of the bulging portion can be minimized, the heat capacity of the bulging portion can be reduced, and the bulging portion can be reduced. Generation of hot spots due to the provision can be reduced. In addition, the necessity of increasing the amount of the cooling medium for cooling the hot spot is reduced, and the cooling performance can be further improved.

本発明に係るタービン用翼は、翼根部から供給された冷却媒体を翼の内部に導くサーペンタイン流路を備えたタービン用翼であって、前記サーペンタイン流路のＵターン部よりも上流側に位置する冷却通路と、下流側に位置する冷却通路とを仕切る隔壁の先端部に、前記Ｕターン部に向かって突出する半円部と、下流側に位置する冷却通路内に向かって突出するとともに、下流側に位置する冷却通路の流路断面積および流路幅を徐々に増加させる直線部とを有してなる膨出部を備え、前記隔壁を貫通して前記上流側に位置する冷却通路と前記下流側に位置する冷却通路とを連通し、前記隔壁の前記上流側に位置する冷却通路を形成する表面に第１の開口を有し、前記直線部の表面に第２の開口を有する第１の連通路を少なくとも一つ以上備え、前記第１の開口が前記第２の開口よりも翼先端の近くに位置する。 A turbine blade according to the present invention is a turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root part to the inside of the blade, and is located upstream of a U-turn portion of the serpentine flow path. And a semicircular portion projecting toward the U-turn portion, and projecting into the cooling passage located on the downstream side, at the tip of the partition wall that partitions the cooling passage and the cooling passage located on the downstream side, A cooling passage located on the upstream side through the partition wall, and having a bulging portion having a flow passage cross-sectional area of the cooling passage located on the downstream side and a linear portion that gradually increases the flow passage width ; A first passage having a first opening on the surface forming the cooling passage located on the upstream side of the partition wall and a second opening on the surface of the linear portion is communicated with the cooling passage located on the downstream side. At least one communication path It said first opening is you close to the blade tip than the second opening.

本発明に係るタービン用翼によれば、Ｕターン部の上流側に位置する冷却通路を隔壁に沿って流れてきた冷却媒体は、膨出部を備えていない従来のタービン用翼の隔壁のように急激に転回されることなく、半円部および直線部の表面にガイドされて（半円部および直線部の表面に沿って）Ｕターン部の下流側に位置する冷却通路に滑らかに流入していくことになるので、Ｕターン部における剥離および圧力損失を低減させることができ、冷却性能を向上させることができる。
また、本発明に係るタービン用翼によれば、第１の連通路の一端に位置する第１の開口が、第１の連通路の他端に位置する第２の開口よりも翼先端に近いので、動翼が回転することによってはたらく翼根部から翼先端方向への遠心力により生じるポンピング効果によって、下流側に位置する冷却通路を形成し第２の開口を有する直線部の表面に沿って流れる冷却媒体の一部が第１の連通路を介して、すなわち、第２の開口から第１の連通路に流入して第１の連通路を通った後、第１の開口から流出して、上流側に位置する冷却通路内に導かれ（吸い出され）ることになるので、Ｕターン部における剥離および圧力損失をさらに低減させることができ、冷却性能をさらに向上させることができる。 According to the turbine blade according to the present invention, the cooling medium flowing along the partition through the cooling passage located on the upstream side of the U-turn portion is like the partition of a conventional turbine blade not provided with the bulging portion. Without being suddenly turned around, it is guided by the surface of the semicircular part and the straight part (along the surface of the semicircular part and the linear part) and smoothly flows into the cooling passage located downstream of the U-turn part. Therefore, peeling and pressure loss in the U-turn portion can be reduced, and cooling performance can be improved.
According to the turbine blade of the present invention, the first opening located at one end of the first communication path is closer to the blade tip than the second opening located at the other end of the first communication path. Therefore, the pumping effect generated by the centrifugal force in the direction from the blade root to the blade tip, which works when the rotor blades rotate, forms a cooling passage located downstream and flows along the surface of the straight portion having the second opening. A part of the cooling medium flows into the first communication path from the second opening through the first communication path, passes through the first communication path, and then flows out of the first opening. Since it is guided (sucked out) into the cooling passage located on the upstream side, separation and pressure loss in the U-turn portion can be further reduced, and the cooling performance can be further improved.

本発明に係るタービン用翼は、翼根部から供給された冷却媒体を翼の内部に導くサーペンタイン流路を備えたタービン用翼であって、前記サーペンタイン流路のＵターン部よりも上流側に位置する冷却通路と、下流側に位置する冷却通路とを仕切る隔壁の先端部に、前記Ｕターン部に向かって突出する半円部と、下流側に位置する冷却通路内に向かって突出するとともに、下流側に位置する冷却通路の流路断面積および流路幅を徐々に増加させる直線部とを有してなる膨出部を備え、前記半円部および前記直線部の表面に、ディンプルが少なくとも一つ以上設けられている。 A turbine blade according to the present invention is a turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root part to the inside of the blade, and is located upstream of a U-turn portion of the serpentine flow path. And a semicircular portion projecting toward the U-turn portion, and projecting into the cooling passage located on the downstream side, at the tip of the partition wall that partitions the cooling passage and the cooling passage located on the downstream side, A bulging portion having a flow passage cross-sectional area of the cooling passage located on the downstream side and a linear portion that gradually increases the flow passage width , and dimples at least on the surfaces of the semicircular portion and the straight portion One or more are provided .

本発明に係るタービン用翼は、翼根部から供給された冷却媒体を翼の内部に導くサーペンタイン流路を備えたタービン用翼であって、前記サーペンタイン流路のＵターン部よりも上流側に位置する冷却通路と、下流側に位置する冷却通路とを仕切る隔壁の先端部に、前記Ｕターン部に向かって突出する半円部と、下流側に位置する冷却通路内に向かって突出するとともに、下流側に位置する冷却通路の流路断面積および流路幅を徐々に増加させる直線部とを有してなる膨出部を備え、前記サーペンタイン流路を２系統以上備え、互いに隣接した一方のサーペンタイン流路と他方のサーペンタイン流路とを仕切るリブの先端部に、一方のサーペンタイン流路と他方のサーペンタイン流路とを連通する第２の連通路が少なくとも一つ以上設けられている。 A turbine blade according to the present invention is a turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root part to the inside of the blade, and is located upstream of a U-turn portion of the serpentine flow path. And a semicircular portion projecting toward the U-turn portion, and projecting into the cooling passage located on the downstream side, at the tip of the partition wall that partitions the cooling passage and the cooling passage located on the downstream side, A bulging portion having a flow passage cross-sectional area of the cooling passage located on the downstream side and a linear portion that gradually increases the flow passage width , two or more serpentine flow passages, and one adjacent to each other the tip portion of the rib partitioning the serpentine flow path and the other serpentine flow path, a second communicating passage communicating the one serpentine flow path and the other serpentine flow path is provided at least one There.

本発明に係るタービン用翼によれば、Ｕターン部の上流側に位置する冷却通路を隔壁に沿って流れてきた冷却媒体は、膨出部を備えていない従来のタービン用翼の隔壁のように急激に転回されることなく、半円部および直線部の表面にガイドされて（半円部および直線部の表面に沿って）Ｕターン部の下流側に位置する冷却通路に滑らかに流入していくことになるので、Ｕターン部における剥離および圧力損失を低減させることができ、冷却性能を向上させることができる。
また、本発明に係るタービン用翼によれば、リブの先端部、すなわち、Ｕターン部の隅部（角部）に、一方のサーペンタイン流路から他方のサーペンタイン流路へ、または他方のサーペンタイン流路から一方のサーペンタイン流路への冷却媒体の流れが第２の連通路を介して形成されることになるので、Ｕターン部の隅部におけるホットスポットの発生を低減させることができると共に、ホットスポットを冷却するために冷却媒体量を増やす必要性が軽減され、冷却性能をさらに向上させることができる。また、Ｕターン部の隅部における剥離および圧力損失をさらに低減させることができ、冷却性能をさらに向上させることができる。 According to the turbine blade according to the present invention, the cooling medium flowing along the partition through the cooling passage located on the upstream side of the U-turn portion is like the partition of a conventional turbine blade not provided with the bulging portion. Without being suddenly turned around, it is guided by the surface of the semicircular part and the straight part (along the surface of the semicircular part and the linear part) and smoothly flows into the cooling passage located downstream of the U-turn part. Therefore, peeling and pressure loss in the U-turn portion can be reduced, and cooling performance can be improved.
Further, according to the turbine blade according to the present invention, the tip of the rib, that is, the corner (corner) of the U-turn portion, from one serpentine channel to the other serpentine channel or the other serpentine flow Since the flow of the cooling medium from the passage to the one serpentine passage is formed through the second communication passage, it is possible to reduce the occurrence of hot spots at the corners of the U-turn portion and The need to increase the amount of the cooling medium to cool the spot is reduced, and the cooling performance can be further improved. Further, peeling and pressure loss at the corners of the U-turn portion can be further reduced, and the cooling performance can be further improved.

上記タービン用翼において、前記直線部の背側に位置して、前記隔壁の、前記上流側に位置する冷却通路を形成する表面に、断面視円弧状の凹みが設けられているとさらに好適である。 In the turbine blade, it is more preferable that a concave portion having an arc shape in a sectional view is provided on a surface of the partition wall, which is located on the back side of the straight portion and forms a cooling passage located on the upstream side. is there.

このようなタービン用翼によれば、膨出部を設けたことによる隔壁の肉厚の増加を最小限にすることができるので、膨出部の熱容量を小さくでき、膨出部を設けたことによるホットスポットの発生を低減させることができる。また、ホットスポットを冷却するために冷却媒体量を増やす必要性が軽減され、冷却性能をさらに向上させることができる。 According to such a turbine blade, since the increase in the wall thickness of the partition wall due to the provision of the bulging portion can be minimized, the heat capacity of the bulging portion can be reduced, and the bulging portion is provided. The generation of hot spots due to can be reduced. In addition, the necessity of increasing the amount of the cooling medium for cooling the hot spot is reduced, and the cooling performance can be further improved.

上記タービン用翼において、前記隔壁を貫通して前記上流側に位置する冷却通路と前記下流側に位置する冷却通路とを連通し、前記隔壁の前記上流側に位置する冷却通路を形成する表面に第１の開口を有し、前記直線部の表面に第２の開口を有する第１の連通路を少なくとも一つ以上備え、前記第１の開口が前記第２の開口よりも翼先端の近くに位置しているとさらに好適である。 In the turbine blade, the cooling passage located on the upstream side and the cooling passage located on the downstream side through the partition wall are communicated with each other to form a cooling passage located on the upstream side of the partition wall. At least one first communication path having a first opening and having a second opening on a surface of the linear portion, wherein the first opening is closer to the blade tip than the second opening; It is more preferable that it is located.

このようなタービン用翼によれば、第１の連通路の一端に位置する第１の開口が、第１の連通路の他端に位置する第２の開口よりも翼先端に近いので、動翼が回転することによってはたらく翼根部から翼先端方向への遠心力により生じるポンピング効果によって、下流側に位置する冷却通路を形成し第２の開口を有する直線部の表面に沿って流れる冷却媒体の一部が第１の連通路を介して、すなわち、第２の開口から第１の連通路に流入して第１の連通路を通った後、第１の開口から流出して、上流側に位置する冷却通路内に導かれ（吸い出され）ることになるので、Ｕターン部における剥離および圧力損失をさらに低減させることができ、冷却性能をさらに向上させることができる。 According to such a turbine blade, the first opening located at one end of the first communication path is closer to the blade tip than the second opening located at the other end of the first communication path. The cooling effect of the cooling medium flowing along the surface of the straight portion having the second opening is formed by the pumping effect generated by the centrifugal force from the blade root to the blade tip direction, which is caused by the rotation of the blade. A part flows through the first communication path, that is, from the second opening to the first communication path, passes through the first communication path, and then flows out from the first opening to the upstream side. Since it is guided (sucked out) into the cooling passage located, peeling and pressure loss in the U-turn portion can be further reduced, and the cooling performance can be further improved.

上記タービン用翼において、前記半円部および前記直線部の表面に、ディンプルが少なくとも一つ以上設けられているとさらに好適である。 In the turbine blade, it is more preferable that at least one dimple is provided on the surface of the semicircular portion and the straight portion.

このようなタービン用翼によれば、Ｕターン部における剥離および圧力損失をさらに低減させることができ、冷却性能をさらに向上させることができる。 According to such a turbine blade, separation and pressure loss in the U-turn portion can be further reduced, and the cooling performance can be further improved.

上記タービン用翼において、前記サーペンタイン流路を２系統以上備え、互いに隣接した一方のサーペンタイン流路と他方のサーペンタイン流路とを仕切るリブの先端部に、一方のサーペンタイン流路と他方のサーペンタイン流路とを連通する第２の連通路が少なくとも一つ以上設けられているとさらに好適である。 In the turbine blade, two or more serpentine flow paths are provided, and one serpentine flow path and the other serpentine flow path are provided at the end of a rib that partitions one serpentine flow path and the other serpentine flow path adjacent to each other. It is more preferable that at least one second communication path that communicates with each other is provided.

このようなタービン用翼によれば、リブの先端部、すなわち、Ｕターン部の隅部（角部）に、一方のサーペンタイン流路から他方のサーペンタイン流路へ、または他方のサーペンタイン流路から一方のサーペンタイン流路への冷却媒体の流れが第２の連通路を介して形成されることになるので、Ｕターン部の隅部におけるホットスポットの発生を低減させることができると共に、ホットスポットを冷却するために冷却媒体量を増やす必要性が軽減され、冷却性能をさらに向上させることができる。また、Ｕターン部の隅部における剥離および圧力損失をさらに低減させることができ、冷却性能をさらに向上させることができる。 According to such a turbine blade, at one end of the rib, that is, at a corner (corner) of the U-turn portion, from one serpentine channel to the other serpentine channel or from the other serpentine channel. Since the flow of the cooling medium to the serpentine flow path is formed through the second communication path, the generation of hot spots at the corners of the U-turn portion can be reduced and the hot spots can be cooled. Therefore, the necessity for increasing the amount of the cooling medium is reduced, and the cooling performance can be further improved. Further, peeling and pressure loss at the corners of the U-turn portion can be further reduced, and the cooling performance can be further improved.

本発明に係るガスタービンは、サーペンタイン流路のＵターン部における剥離および圧力損失を低減させることができ、冷却性能を向上させることができるタービン用翼を具備している。 The gas turbine according to the present invention includes turbine blades that can reduce separation and pressure loss in the U-turn portion of the serpentine flow path and can improve cooling performance.

本発明に係るガスタービンによれば、タービン用翼における冷却性能の向上により、冷却通路に流入する冷却空気量を減少させることができ、ガスタービンの性能を向上させることができる。
また、タービン用翼の内部を通過してタービン用翼を冷却した冷却媒体（蒸気等）を回収するタイプのガスタービンでは、タービン用翼における圧力損失が低減することにより、コンバインド・サイクル効率が向上することになる。 According to the gas turbine of the present invention, the amount of cooling air flowing into the cooling passage can be reduced by improving the cooling performance of the turbine blades, and the performance of the gas turbine can be improved.
In addition, in the type of gas turbine that collects the cooling medium (steam, etc.) that has passed through the turbine blades and cooled the turbine blades, the combined cycle efficiency is improved by reducing the pressure loss in the turbine blades. Will do.

本発明に係るタービン用翼によれば、サーペンタイン流路のＵターン部における剥離および圧力損失を低減させることができ、冷却性能を向上させることができるという効果を奏する。 According to the turbine blade according to the present invention, it is possible to reduce peeling and pressure loss in the U-turn portion of the serpentine flow path, and it is possible to improve the cooling performance.

本発明の第１実施形態に係るタービン用翼の縦断面図である。It is a longitudinal cross-sectional view of the blade for turbines concerning 1st Embodiment of this invention. 図１の要部を拡大した図である。It is the figure which expanded the principal part of FIG. 図１の要部を拡大した図であって、図２と同様の図である。It is the figure which expanded the principal part of FIG. 1, Comprising: It is a figure similar to FIG. 本発明の第１実施形態に係るタービン用翼を用いて行った実験の結果を示す図表である。It is a graph which shows the result of the experiment conducted using the turbine blade | wing which concerns on 1st Embodiment of this invention. 本発明の第２実施形態に係るタービン用翼の要部を拡大した図であって、図２および図３と同様の図である。It is the figure which expanded the principal part of the blade for turbines concerning 2nd Embodiment of this invention, Comprising: It is a figure similar to FIG. 2 and FIG. 本発明の第３実施形態に係るタービン用翼の要部を拡大した図であって、図２および図３と同様の図である。It is the figure which expanded the principal part of the blade for turbines concerning 3rd Embodiment of this invention, Comprising: It is a figure similar to FIG. 2 and FIG. 本発明の第４実施形態に係るタービン用翼の要部を拡大した図であって、図２および図３と同様の図である。It is the figure which expanded the principal part of the blade for turbines concerning 4th Embodiment of this invention, Comprising: It is a figure similar to FIG. 2 and FIG. 本発明の第５実施形態に係るタービン用翼の要部を拡大した図であって、図２および図３と同様の図である。It is the figure which expanded the principal part of the blade for turbines concerning 5th Embodiment of this invention, Comprising: It is a figure similar to FIG. 2 and FIG.

以下、本発明に係るタービン用翼の第１実施形態について、図１から図４を参照しながら説明する。
図１は本実施形態に係るタービン用翼の縦断面図、図２は図１の要部を拡大した図、図３は図１の要部を拡大した図であって、図２と同様の図、図４は本実施形態に係るタービン用翼を用いて行った実験の結果を示す図表である。 Hereinafter, a first embodiment of a turbine blade according to the present invention will be described with reference to FIGS. 1 to 4.
1 is a longitudinal sectional view of a turbine blade according to the present embodiment, FIG. 2 is an enlarged view of the main part of FIG. 1, and FIG. 3 is an enlarged view of the main part of FIG. FIG. 4 and FIG. 4 are tables showing the results of experiments conducted using the turbine blades according to the present embodiment.

本実施形態に係るタービン用翼１は、例えば、燃焼用空気を圧縮する圧縮部（図示せず）と、この圧縮部から送られてきた高圧空気中に燃料を噴射して燃焼させ、高温燃焼ガスを発生させる燃焼部（図示せず）と、この燃焼部の下流側に位置し、燃焼部を出た燃焼ガスにより駆動されるタービン部（図示せず）とを主たる要素として構成されたガスタービンの、タービン部における動翼（例えば、１段動翼）に適用され得るものである。 The turbine blade 1 according to the present embodiment includes, for example, a compression section (not shown) that compresses combustion air, and injects and burns fuel into high-pressure air sent from the compression section to perform high-temperature combustion. A gas composed mainly of a combustion section (not shown) that generates gas and a turbine section (not shown) that is located on the downstream side of the combustion section and is driven by the combustion gas exiting the combustion section The turbine can be applied to a moving blade (for example, a one-stage moving blade) in a turbine section.

図１において、符号２は翼根部、３はプラットフォームである。タービン用翼１の内部には、冷却通路４ａ、および、冷却通路５ａ，５ｂ，５ｃ，６ａ，６ｂ，６ｃからなるサーペンタイン冷却流路が形成されている。翼根部２には冷却通路４，５，６、７がそれぞれ独立して設けられている。冷却通路４は前縁側（図１において左側）に位置し、翼内の冷却通路４ａに連通している。冷却通路４には冷却空気１０がロータ側から流入し、冷却通路４ａを通過する過程で翼の前縁部を冷却した後、冷却孔１９から流出して前縁部をシャワーヘッドフィルム冷却する。冷却通路５には冷却空気１１が流入し、翼内の冷却通路５ａを通り、タービン外径側（図１において上方）のＵターン部１５で１８０°転回して冷却通路５ｂに流入する。そして、タービン内径側（図１において下方）のＵターン部１６で再び上方に転回して冷却通路５ｃに流入し、翼先端部より流出する。この過程において冷却穴（図示せず）より翼表面へ流出してフィルム冷却を行う。 In FIG. 1, reference numeral 2 denotes a blade root portion, and 3 denotes a platform. Inside the turbine blade 1, a cooling passage 4a and a serpentine cooling passage including cooling passages 5a, 5b, 5c, 6a, 6b, and 6c are formed. The blade root 2 is provided with cooling passages 4, 5, 6, and 7 independently. The cooling passage 4 is located on the leading edge side (left side in FIG. 1) and communicates with the cooling passage 4a in the blade. Cooling air 10 flows into the cooling passage 4 from the rotor side, cools the leading edge of the blade in the process of passing through the cooling passage 4a, and then flows out of the cooling hole 19 to cool the leading edge of the shower head film. The cooling air 11 flows into the cooling passage 5, passes through the cooling passage 5 a in the blade, turns 180 ° at the U-turn portion 15 on the turbine outer diameter side (upper side in FIG. 1), and flows into the cooling passage 5 b. Then, the U-turn part 16 on the turbine inner diameter side (downward in FIG. 1) turns upward again to flow into the cooling passage 5c, and flows out from the blade tip. In this process, the film is cooled by flowing out from the cooling hole (not shown) to the blade surface.

冷却通路６には冷却空気１２が、冷却通路７には冷却空気１３がそれぞれ流入し、合流して冷却通路６ａを流れる。そして、外径側のＵターン部１７にて１８０°転回した後、冷却通路６ｂに入り、そして、内径側のＵターン部１８にて再び上方に転回して冷却流路６ｃに流入する。この過程において冷却穴（図示せず）より翼表面に流出してフィルム冷却を行い、残りの空気は翼後縁２０に至る領域をピンフィン冷却した後、排出孔２１より流出する。 The cooling air 12 flows into the cooling passage 6 and the cooling air 13 flows into the cooling passage 7 and merges to flow through the cooling passage 6a. Then, after turning 180 ° at the U-turn portion 17 on the outer diameter side, it enters the cooling passage 6b and then turns upward again at the U-turn portion 18 on the inner diameter side and flows into the cooling flow path 6c. In this process, the film is cooled by flowing out from the cooling hole (not shown) to the blade surface, and the remaining air flows out from the discharge hole 21 after the pin fin cooling is performed in the region reaching the blade trailing edge 20.

さて、本実施形態に係るタービン用翼１には、冷却通路５ａと冷却通路５ｂとを仕切る隔壁（仕切壁）３１の先端部（翼先端側の端部）、および冷却通路６ａと冷却通路６ｂとを仕切る隔壁（仕切壁）３２の先端部（翼先端側の端部）に、膨出部３３，３４が設けられている。
図１に示すように、膨出部３３は、Ｕターン部１５に向かって突出するとともに、下流側に位置する冷却通路５ｂ内に向かって突出する膨らみであり、膨出部３４は、Ｕターン部１７に向かって突出するとともに、下流側に位置する冷却通路６ｂ内に向かって突出する膨らみである。
膨出部３３と膨出部３４とは、図１において左右対称を成す同一の構成要素からなるものであるので、以下、膨出部３４のみを説明する。 Now, in the turbine blade 1 according to the present embodiment, the tip (part on the blade tip side) of the partition wall (partition wall) 31 that partitions the cooling passage 5a and the cooling passage 5b, and the cooling passage 6a and the cooling passage 6b. Swelling portions 33 and 34 are provided at the tip end portion (end portion on the blade tip side) of the partition wall (partition wall) 32.
As shown in FIG. 1, the bulging portion 33 is a bulge that protrudes toward the U-turn portion 15 and also protrudes into the cooling passage 5 b located on the downstream side. The bulge protrudes toward the portion 17 and protrudes into the cooling passage 6b located on the downstream side.
Since the bulging portion 33 and the bulging portion 34 are composed of the same components that are symmetrical in FIG. 1, only the bulging portion 34 will be described below.

図２に示すように、膨出部３４は、Ｕターン部１７に向かって突出する半円部３５と、下流側に位置する冷却通路６ｂ内に向かって突出する直線部３６とを備えている。
半円部３５の上流端は、冷却通路６ａに面する隔壁３２の一面３２ａの下流端と接続され、半円部３５の下流端は、直線部３６の上流端と接続されており、直線部３６の下流端は、冷却通路６ｂに面する隔壁３２の他面３２ｂの上流端と接続されている。 As shown in FIG. 2, the bulging portion 34 includes a semicircular portion 35 that protrudes toward the U-turn portion 17 and a linear portion 36 that protrudes into the cooling passage 6 b located on the downstream side. .
The upstream end of the semicircular portion 35 is connected to the downstream end of the one surface 32a of the partition wall 32 facing the cooling passage 6a, and the downstream end of the semicircular portion 35 is connected to the upstream end of the straight portion 36, The downstream end of 36 is connected to the upstream end of the other surface 32b of the partition wall 32 that faces the cooling passage 6b.

半円部３５および直線部３６は、５度≦θ≦１０度の式、および１≦Ｒ／Ｔ≦３の式を満たすように形成されている。ここで、θは隔壁３２の他面３２ｂと直線部３６の表面との成す角度（傾斜角度）、Ｒは半円部３５の半径、Ｔは隔壁３２の板厚（一面３２ａと他面３２ｂとの間の距離）である。
また、半円部３５および直線部３６は、Ａ_２／Ａ_１＝０．４〜１．８、Ａ_３／Ａ_１＝０．４〜１．０、Ｌ_２／Ｌ_１＝１．０〜１．５、およびＬ_３／Ｌ_１＝０．６〜１．０となるように形成されている。ここで、Ａ_１およびＬ_１は図３中に符号１０１で示す場所の流路断面積および流路幅（半円部３５の上流端と、この上流端に対向する面３７との間の距離）、Ａ_２およびＬ_２は図３中に符号１０２で示す場所の流路断面積および流路幅（半円部３５の頂点と、この頂点に対向する面３８との間の距離）、Ａ_３およびＬ_３は図３中に符号１０３で示す場所の流路断面積および流路幅（半円部３５の下流端と、この下流端に対向する面３９との間の距離）である。 The semicircular portion 35 and the straight portion 36 are formed so as to satisfy the formula of 5 degrees ≦ θ ≦ 10 degrees and the formula of 1 ≦ R / T ≦ 3. Here, θ is an angle (inclination angle) formed between the other surface 32b of the partition wall 32 and the surface of the linear portion 36, R is a radius of the semicircular portion 35, and T is a plate thickness of the partition wall 32 (one surface 32a and the other surface 32b). Distance).
Further, the semicircular portion 35 and the straight portion _{_{_{_{36, A 2 / A 1 = 0.4~1.8}}}} , A 3 / A 1 = 0.4~1.0, L 2 / L 1 = 1.0~ 1.5, and L ₃ / L ₁ = 0.6 to 1.0. Here, A ₁ and L ₁ are the channel cross-sectional area and the channel width at the location indicated by reference numeral 101 in FIG. 3 (the distance between the upstream end of the semicircular portion 35 and the surface 37 facing the upstream end). ), A ₂ and L ₂ are the channel cross-sectional area and the channel width (the distance between the apex of the semicircular portion 35 and the surface 38 facing this apex) at the location indicated by reference numeral 102 in FIG. ₃ and L ₃ are the channel cross-sectional area and the channel width (the distance between the downstream end of the semicircular portion 35 and the surface 39 facing the downstream end) at the location indicated by reference numeral 103 in FIG.

そして、Ａ_２／Ａ_１＝１．０、Ａ_３／Ａ_１＝０．７〜１．０、Ｌ_２／Ｌ_１＝１．０、Ｌ_３／Ｌ_１＝０．７〜１．０とし、θ＝５°として、Ｒ／Ｔ＝１，２，３のときの圧力損失係数と、Ａ_２／Ａ_１＝１．０、Ａ_３／Ａ_１＝０．７〜１．０、Ｌ_２／Ｌ_１＝１．０、Ｌ_３／Ｌ_１＝０．７〜１．０とし、θ＝１０°として、Ｒ／Ｔ＝１，２，３のときの圧力損失係数とを実験で求め、図４に示す実験結果を得た。なお、図４中に示す「ベースケース」とは、本実施形態に係る半円部３５および直線部３６からなる膨出部３４を備えていない従来のタービン用翼（Ｒ／Ｔ＝１．０）を用いて行った実験結果であり、図４はこのベースケースの圧力損失係数を１．０としたときの各々の実験結果を相対値として示している。
図４からθ＝５°、Ｒ／Ｔ＝２のときに圧力損失係数が最も小さくなり、Ｒ／Ｔ＝２，３のとき、すなわち、半円部３５のＲが大きいときには、θを小さくすると圧力損失係数が小さくなることがわかる。
ここで、圧力損失係数は、ΔＰ／（（１／２）×ρ×Ｖ^２）であらわすことができる。なお、ΔＰは、半円部３５の上流端と、この上流端に対向する面３７との間を通過する流体（本実験では室温の空気）の圧力Ｐ_１（図３参照）と、直線部３６の下流端よりも下流側に位置する隔壁３２の他面３２ｂと、この他面３２ｂに対向する面３９との間を通過する流体の圧力Ｐ_２（図３参照）との差（Ｐ_１−Ｐ_２）である。また、ρは、空気の粘性計数、Ｖは半円部３５の上流端と、この上流端に対向する面３７との間を通過する流体の速度である。 _{_{_{_{Then, A 2 / A 1 = 1.0}}}} , A 3 / A 1 = 0.7~1.0, L 2 / L 1 = 1.0, and L 3 / L 1 = 0.7~1.0 and , Θ = 5 °, pressure loss coefficient when R / T = 1, 2, 3 and A ₂ / A ₁ = 1.0, A ₃ / A ₁ = 0.7 to 1.0, L ₂ / L ₁ = 1.0, L ₃ / L ₁ = 0.7 to 1.0, θ = 10 °, and the pressure loss coefficient when R / T = 1, 2, 3 is experimentally determined. The experimental result shown in FIG. 4 was obtained. Note that the “base case” shown in FIG. 4 is a conventional turbine blade (R / T = 1.0) that does not include the bulging portion 34 including the semicircular portion 35 and the straight portion 36 according to the present embodiment. ), And FIG. 4 shows each experimental result as a relative value when the pressure loss coefficient of this base case is 1.0.
From FIG. 4, when θ = 5 ° and R / T = 2, the pressure loss coefficient becomes the smallest. When R / T = 2, 3, that is, when R of the semicircular portion 35 is large, θ is reduced. It can be seen that the pressure loss coefficient is small.
Here, the pressure loss coefficient can be expressed by ΔP / ((1/2) × ρ × V ² ). ΔP is the pressure P ₁ (see FIG. 3) of the fluid (room temperature air in this experiment) passing between the upstream end of the semicircular portion 35 and the surface 37 facing the upstream end, and the straight portion. The difference (P ₁ ) between the pressure P ₂ (see FIG. 3) of the fluid passing between the other surface 32b of the partition wall 32 located on the downstream side of the downstream end of 36 and the surface 39 facing the other surface 32b. is -P _2). Further, ρ is the viscosity coefficient of air, and V is the velocity of the fluid passing between the upstream end of the semicircular portion 35 and the surface 37 facing the upstream end.

本実施形態に係るタービン用翼１によれば、Ｕターン部１７の上流側に位置する冷却通路６ａを隔壁３２に沿って流れてきた冷却媒体は、膨出部３４を備えていない従来のタービン用翼の隔壁のように急激に転回されることなく、半円部３５および直線部３６の表面にガイドされて（半円部３５および直線部３６の表面に沿って）Ｕターン部１７の下流側に位置する冷却通路６ｂに滑らかに流入していくことになるので、Ｕターン部１７における剥離および圧力損失を低減させることができ、冷却性能を向上させることができる。 According to the turbine blade 1 according to the present embodiment, the cooling medium flowing along the partition wall 32 in the cooling passage 6 a located on the upstream side of the U-turn portion 17 is a conventional turbine that does not include the bulging portion 34. It is guided by the surfaces of the semicircular portion 35 and the straight portion 36 (along the surfaces of the semicircular portion 35 and the straight portion 36) without being rapidly turned like the partition wall of the blade, and downstream of the U-turn portion 17. Since the air smoothly flows into the cooling passage 6b located on the side, peeling and pressure loss in the U-turn portion 17 can be reduced, and the cooling performance can be improved.

本発明に係るタービン用翼の第２実施形態について、図５を参照しながら説明する。
図５は本実施形態に係るタービン用翼の要部を拡大した図であって、図２および図３と同様の図である。
本実施形態に係るタービン用翼５１は、直線部３６の裏側（背側）に位置する隔壁３２の一面３２ａに、断面視円弧状の凹み（窪み）５２が設けられているという点で上述した第１実施形態のものと異なる。その他の構成要素については前述した第１実施形態のものと同じであるので、ここではそれら構成要素についての説明は省略する。
なお、前述した第１実施形態と同一の部材には同一の符号を付している。 A second embodiment of a turbine blade according to the present invention will be described with reference to FIG.
FIG. 5 is an enlarged view of the main part of the turbine blade according to the present embodiment, which is the same as FIG. 2 and FIG.
The turbine blade 51 according to the present embodiment is described above in that a recess 52 having a circular arc shape in cross section is provided on one surface 32a of the partition wall 32 located on the back side (back side) of the straight portion 36. Different from that of the first embodiment. Since other components are the same as those of the first embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 1st Embodiment mentioned above.

図５に示すように、凹み５２は、直線部３６の裏側において冷却通路６ａの流路断面積および流路幅を徐々に増加させた後、徐々に減少させて、隔壁３２の一面３２ａと直線部３６の表面との距離（すなわち、膨出部３４における隔壁３２の板厚）をタービン用翼５１の翼厚方向（図５において紙面に直交する方向）に沿って、上述した第１実施形態のものよりも減少させる凹所であり、直線部３６の下流端裏側近傍から半円部３５の上流端近傍にかけて形成されている。
また、凹み５２の上流端および下流端における接線と、隔壁３２の一面３２ａとの成す角度θ２は、おおよそ５°以下になるように、すなわち、凹み５２の上流端および下流端に剥離が生じないように設定されている。 As shown in FIG. 5, the recess 52 is formed so that the channel cross-sectional area and the channel width of the cooling passage 6 a are gradually increased on the back side of the straight portion 36, and then gradually decreased to form a straight line with the one surface 32 a of the partition wall 32. In the first embodiment described above, the distance from the surface of the portion 36 (that is, the plate thickness of the partition wall 32 in the bulging portion 34) is along the blade thickness direction of the turbine blade 51 (the direction perpendicular to the paper surface in FIG. 5). It is a recess that is reduced more than that of the straight portion 36 and is formed from the vicinity of the back end of the straight line portion 36 to the vicinity of the upstream end of the semicircular portion 35.
Further, the angle θ2 formed between the tangent line at the upstream end and the downstream end of the recess 52 and the one surface 32a of the partition wall 32 is approximately 5 ° or less, that is, no separation occurs at the upstream end and the downstream end of the recess 52. Is set to

本実施形態に係るタービン用翼５１によれば、膨出部３４を設けたことによる隔壁３２の肉厚の増加を最小限にすることができるので、膨出部３４の熱容量を小さくでき、膨出部３４を設けたことによるホットスポットの発生を低減させることができる。また、ホットスポットを冷却するために冷却媒体量を増やす必要性が軽減され、冷却性能をさらに向上させることができる。 According to the turbine blade 51 according to the present embodiment, the increase in the wall thickness of the partition wall 32 due to the provision of the bulging portion 34 can be minimized, so that the heat capacity of the bulging portion 34 can be reduced, and the swelling is increased. The generation of hot spots due to the provision of the protruding portion 34 can be reduced. In addition, the necessity of increasing the amount of the cooling medium for cooling the hot spot is reduced, and the cooling performance can be further improved.

本発明に係るタービン用翼の第３実施形態について、図６を参照しながら説明する。
図６は本実施形態に係るタービン用翼の要部を拡大した図であって、図２および図３と同様の図である。
本実施形態に係るタービン用翼６１は、隔壁３２を貫通して上流側に位置する冷却通路６ａと下流側に位置する冷却通路６ｂとを連通し、隔壁３２の上流側に位置する冷却通路６ａを形成する表面３２ａに第１の開口６３を有し、直線部３６の表面に第２の開口６４を有する第１の連通路６２を少なくとも一つ以上備え、第１の開口６３が第２の開口６４よりも翼先端の近くに位置しているという点で上述した第１実施形態のものと異なる。その他の構成要素については前述した第１実施形態のものと同じであるので、ここではそれら構成要素についての説明は省略する。
なお、前述した第１実施形態と同一の部材には同一の符号を付している。 A third embodiment of a turbine blade according to the present invention will be described with reference to FIG.
FIG. 6 is an enlarged view of the main part of the turbine blade according to the present embodiment, which is the same as FIG. 2 and FIG. 3.
The turbine blade 61 according to the present embodiment communicates a cooling passage 6a positioned upstream through the partition wall 32 and a cooling passage 6b positioned downstream, and a cooling passage 6a positioned upstream of the partition wall 32. The surface 32a forming the first portion 63 has at least one first communication passage 62 having a first opening 63 and a second opening 64 on the surface of the straight portion 36, and the first opening 63 is a second opening 63. It differs from that of the first embodiment described above in that it is positioned closer to the blade tip than the opening 64. Since other components are the same as those of the first embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 1st Embodiment mentioned above.

図６に示すように、第１の連通路６２は、その中心軸線（延在方向）が、冷却通路６ａを流れる流体の向きと鋭角を成すように形成された孔状またはスリット状のものであり、タービン用翼６１の翼厚方向（図６において紙面に直交する方向）に沿って少なくとも一つ以上形成されている。
なお、中心軸線と流体の向きとが成す角度は鋭角に限定されるものではなく、第１の開口６３が第２の開口６４よりも翼先端の近くに位置しておれば、直角でも鈍角でも構わない。 As shown in FIG. 6, the first communication passage 62 is a hole or slit having a central axis (extending direction) that forms an acute angle with the direction of the fluid flowing through the cooling passage 6a. And at least one is formed along the blade thickness direction of the turbine blade 61 (the direction perpendicular to the paper surface in FIG. 6).
The angle formed by the central axis and the direction of the fluid is not limited to an acute angle. If the first opening 63 is located closer to the blade tip than the second opening 64, the angle may be perpendicular or obtuse. I do not care.

本実施形態に係るタービン用翼６１によれば、第１の連通路６２の一端に位置する第１の開口６３が、第１の連通路６２の他端に位置する第２の開口６４よりも翼先端に近いので、動翼６１が回転することによってはたらく翼根部２から翼先端方向への遠心力により生じるポンピング効果によって、下流側に位置する冷却通路６ｂを形成し第２の開口６４を有する直線部３６の表面に沿って流れる冷却媒体の一部が第１の連通路６２を介して、すなわち、第２の開口６４から第１の連通路６２に流入して第１の連通路６２を通った後、第１の開口６３から流出して、上流側に位置する冷却通路６ａ内に導かれ（吸い出され）ることになるので、Ｕターン部１７における剥離および圧力損失をさらに低減させることができ、冷却性能をさらに向上させることができる。 According to the turbine blade 61 according to the present embodiment, the first opening 63 positioned at one end of the first communication path 62 is more than the second opening 64 positioned at the other end of the first communication path 62. Since it is close to the blade tip, the cooling passage 6b located downstream is formed by the pumping effect generated by the centrifugal force in the blade tip direction from the blade root 2 that works when the rotor blade 61 rotates, and has the second opening 64. A part of the cooling medium flowing along the surface of the straight portion 36 flows into the first communication path 62 from the second opening 64 through the first communication path 62, that is, through the first communication path 62. After passing, it flows out from the first opening 63 and is guided (sucked out) into the cooling passage 6a located on the upstream side, so that the separation and pressure loss in the U-turn portion 17 are further reduced. Can further improve the cooling performance. It can be.

本発明に係るタービン用翼の第４実施形態について、図７を参照しながら説明する。
図７は本実施形態に係るタービン用翼の要部を拡大した図であって、図２および図３と同様の図である。
本実施形態に係るタービン用翼７１は、半円部３５および直線部３６の表面に、ディンプル７２が少なくとも一つ以上設けられているという点で上述した第１実施形態のものと異なる。その他の構成要素については前述した第１実施形態のものと同じであるので、ここではそれら構成要素についての説明は省略する。
なお、前述した第１実施形態と同一の部材には同一の符号を付している。 A fourth embodiment of a turbine blade according to the present invention will be described with reference to FIG.
FIG. 7 is an enlarged view of the main part of the turbine blade according to the present embodiment, which is the same as FIG. 2 and FIG.
The turbine blade 71 according to this embodiment is different from that of the first embodiment described above in that at least one dimple 72 is provided on the surfaces of the semicircular portion 35 and the straight portion 36. Since other components are the same as those of the first embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 1st Embodiment mentioned above.

図７に示すように、ディンプル７２は、断面視半円状（または円弧状）の凹み（窪み）であり、タービン用翼７１の翼厚方向（図７において紙面に直交する方向）に沿って多数形成されているとともに、半円部３５上流端近傍から直線部３６の下流端近傍にかけても少なくとも一つ以上形成されている。 As shown in FIG. 7, the dimple 72 is a semicircular (or arc-shaped) dent (dent) in cross section, and extends along the blade thickness direction of the turbine blade 71 (a direction perpendicular to the paper surface in FIG. 7). A large number are formed, and at least one is formed from the vicinity of the upstream end of the semicircular portion 35 to the vicinity of the downstream end of the straight portion 36.

本実施形態に係るタービン用翼７１によれば、ディンプル７２によっても剥離および圧力損失が低減されることになるので、Ｕターン部１７における剥離および圧力損失をさらに低減させることができ、冷却性能をさらに向上させることができる。 According to the turbine blade 71 according to the present embodiment, the separation and pressure loss are also reduced by the dimple 72. Therefore, the separation and pressure loss in the U-turn portion 17 can be further reduced, and the cooling performance can be improved. Further improvement can be achieved.

本発明に係るタービン用翼の第５実施形態について、図８を参照しながら説明する。
図８は本実施形態に係るタービン用翼の要部を拡大した図であって、図２および図３と同様の図である。
本実施形態に係るタービン用翼８１は、サーペンタイン流路を２系統以上備え、互いに隣接した一方のサーペンタイン流路と他方のサーペンタイン流路とを仕切るリブ８２の先端部に、一方のサーペンタイン流路と他方のサーペンタイン流路とを連通する第２の連通路８３が少なくとも一つ以上設けられているという点で上述した第１実施形態のものと異なる。その他の構成要素については前述した第１実施形態のものと同じであるので、ここではそれら構成要素についての説明は省略する。
なお、前述した第１実施形態と同一の部材には同一の符号を付している。 A fifth embodiment of a turbine blade according to the present invention will be described with reference to FIG.
FIG. 8 is an enlarged view of a main part of the turbine blade according to the present embodiment, which is the same as FIG. 2 and FIG.
The turbine blade 81 according to the present embodiment includes two or more serpentine flow paths, and one serpentine flow path is provided at the tip of a rib 82 that partitions one serpentine flow path and the other serpentine flow path adjacent to each other. It differs from that of the first embodiment described above in that at least one second communication path 83 communicating with the other serpentine flow path is provided. Since other components are the same as those of the first embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 1st Embodiment mentioned above.

図８に示すように、第２の連通路８３は、一方のサーペンタイン流路を形成する冷却通路５ａと他方のサーペンタイン流路を形成する冷却通路６ａを仕切るリブ８２の先端部に位置し、冷却通路６ａを形成する面３７の翼先端側の隅部８５と、この裏側（背側）に位置して冷却通路５ａを形成する面８４の翼先端側の隅部８６とを連通する孔状またはスリット状のものであり、タービン用翼８１の翼厚方向（図８において紙面に直交する方向）に沿って少なくとも一つ以上形成されている。 As shown in FIG. 8, the second communication passage 83 is located at the tip of the rib 82 that partitions the cooling passage 5a that forms one serpentine passage and the cooling passage 6a that forms the other serpentine passage. A hole 85 communicating with the corner 85 on the blade tip side of the surface 37 forming the passage 6a and the corner 86 on the blade tip side of the surface 84 forming the cooling passage 5a located on the back side (back side) One or more slits are formed along the blade thickness direction of the turbine blade 81 (the direction perpendicular to the paper surface in FIG. 8).

本実施形態に係るタービン用翼８１によれば、リブ８２の先端部、すなわち、Ｕターン部１５，１７の隅部（角部）８５，８６に、一方のサーペンタイン流路から他方のサーペンタイン流路へ、または他方のサーペンタイン流路から一方のサーペンタイン流路への冷却媒体の流れが第２の連通路８３を介して形成されることになるので、Ｕターン部１５，１７の隅部８５，８６近傍におけるホットスポットの発生を低減させることができると共に、ホットスポットを冷却するために冷却媒体量を増やす必要性が軽減され、冷却性能をさらに向上させることができる。また、Ｕターン部の隅部における剥離および圧力損失をさらに低減させることができ、冷却性能をさらに向上させることができる。 According to the turbine blade 81 according to this embodiment, the tip of the rib 82, that is, the corners (corner portions) 85 and 86 of the U-turn portions 15 and 17, from one serpentine channel to the other serpentine channel. Or the other serpentine flow path to the one serpentine flow path is formed through the second communication path 83, so that the corner portions 85, 86 of the U-turn portions 15, 17 are formed. The occurrence of hot spots in the vicinity can be reduced, and the necessity of increasing the amount of the cooling medium to cool the hot spots is reduced, and the cooling performance can be further improved. Further, peeling and pressure loss at the corners of the U-turn portion can be further reduced, and the cooling performance can be further improved.

なお、本発明は上述した実施形態に限定されるものではなく、本発明の要旨を逸脱しない範囲で各種変更・変形が可能である。
例えば、第２実施形態と第３実施形態とを組み合わせて実施したり、第２実施形態または第３実施形態と第４実施形態とを組み合わせて実施したり、第２実施形態から第４実施形態のいずれかと第５実施形態とを組み合わせて実施することもできる。 The present invention is not limited to the above-described embodiments, and various changes and modifications can be made without departing from the gist of the present invention.
For example, the second embodiment may be combined with the third embodiment, the second embodiment or the third embodiment may be combined with the fourth embodiment, or the second embodiment to the fourth embodiment. Any of the above and the fifth embodiment may be combined.

また、本発明は１系統のサーペンタイン流路を有するタービン用翼１に設けられた隔壁の先端部１箇所においてのみ適用されるものではなく、２系統以上のサーペンタイン流路を有するタービン用翼１に設けられた少なくとも一つ以上の隔壁における少なくとも１箇所以上の先端部においても適用することができる。
また、本発明は翼先端側（チップ側）に位置するＵターン部１５，１７においてのみ適用され得るものではなく、翼根元側（ハブ側）に位置するＵターン部１６，１８においても適用することができる。
さらに、上述した実施形態では、タービン部における動翼（例えば、１段動翼）に適用したものを一具体例として説明したが、本発明はタービン部における動翼（例えば、１段動翼）のみに適用され得るものではなく、その他の段の動翼にも適用することができる。
さらにまた上述した第１実施形態、第２実施形態、第４実施形態、および第５実施形態については、タービン部における静翼にも適用することができる。 In addition, the present invention is not applied only to one tip of the partition wall provided in the turbine blade 1 having one system serpentine flow path, but to the turbine blade 1 having two or more system serpentine flow paths. The present invention can also be applied to at least one tip portion of at least one provided partition wall.
Further, the present invention can be applied not only to the U-turn portions 15 and 17 located on the blade tip side (tip side) but also to the U-turn portions 16 and 18 located on the blade root side (hub side). be able to.
Furthermore, in the above-described embodiment, the description has been given by taking as an example a case where it is applied to a moving blade (for example, a first stage moving blade) in a turbine section. The present invention can be applied not only to the blades of the other stages but also to the blades of other stages.
Furthermore, the first embodiment, the second embodiment, the fourth embodiment, and the fifth embodiment described above can also be applied to a stationary blade in a turbine section.

１タービン用翼
５ａ冷却通路
５ｂ冷却通路
６ａ冷却通路
６ｂ冷却通路
１５Ｕターン部
１７Ｕターン部
３１隔壁
３２隔壁
３２ａ一面（表面）
３２ｂ他面（表面）
３３膨出部
３４膨出部
３５半円部
３６直線部
５１タービン用翼
５２凹み
６１タービン用翼
６２第１の連通路
６３第１の開口
６４第２の開口
７１タービン用翼
７２ディンプル
８１タービン用翼
８２リブ
８３第２の連通路
８５隅部
８６隅部 DESCRIPTION OF SYMBOLS 1 Turbine blade 5a Cooling passage 5b Cooling passage 6a Cooling passage 6b Cooling passage 15 U turn part 17 U turn part 31 Partition 32 Partition 32a One surface (surface)
32b Other side (surface)
33 bulging portion 34 bulging portion 35 semicircular portion 36 linear portion 51 turbine blade 52 dent 61 turbine blade 62 first communication path 63 first opening 64 second opening 71 turbine blade 72 dimple 81 for turbine Wing 82 Rib 83 Second communication path 85 Corner 86 Corner

Claims

A turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root to the inside of the blade,
A semicircular portion protruding toward the U-turn portion at the tip of the partition wall that partitions the cooling passage located upstream of the U-turn portion of the serpentine channel and the cooling passage located downstream; A bulging portion that protrudes into the cooling passage located on the side and has a linear section that gradually increases the flow passage cross-sectional area and the flow passage width of the cooling passage located on the downstream side ,
An angle formed between a surface of the partition wall that forms a cooling passage located downstream of the linear portion and a surface of the linear portion is set within a range of 5 degrees to 10 degrees, and the semicircular portion The value obtained by dividing the radius by the thickness of the part not including the bulging part of the partition wall is set within a range of 1 to 3,
The angle formed between the surface of the partition wall forming the cooling passage located downstream of the straight line portion and the surface of the straight line portion is set to 5 degrees, and the radius of the semicircular portion is set to the expansion of the partition wall. A turbine blade, wherein a value divided by a plate thickness of a portion not including a protruding portion is set within a range of 2 to 3 .

A turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root to the inside of the blade,
A semicircular portion protruding toward the U-turn portion at the tip of the partition wall that partitions the cooling passage located upstream of the U-turn portion of the serpentine channel and the cooling passage located downstream; A bulging portion that protrudes into the cooling passage located on the side and has a linear section that gradually increases the flow passage cross-sectional area and the flow passage width of the cooling passage located on the downstream side ,
A turbine blade characterized in that a recess having an arc shape in cross section is provided on a surface of the partition wall, which is located on the back side of the straight portion and forms a cooling passage located on the upstream side .

A turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root to the inside of the blade,
A semicircular portion protruding toward the U-turn portion at the tip of the partition wall that partitions the cooling passage located upstream of the U-turn portion of the serpentine channel and the cooling passage located downstream; A bulging portion that protrudes into the cooling passage located on the side and has a linear section that gradually increases the flow passage cross-sectional area and the flow passage width of the cooling passage located on the downstream side ,
The cooling passage located on the upstream side and the cooling passage located on the downstream side through the partition are communicated with each other, and a first opening is provided on a surface forming the cooling passage located on the upstream side of the partition. and, the first communication path having a second opening on the surface of the linear portion includes at least one, characterized that you close to the blade tip than the first opening and the second opening Turbine blades.

A turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root to the inside of the blade,
A semicircular portion protruding toward the U-turn portion at the tip of the partition wall that partitions the cooling passage located upstream of the U-turn portion of the serpentine channel and the cooling passage located downstream; A bulging portion that protrudes into the cooling passage located on the side and has a linear section that gradually increases the flow passage cross-sectional area and the flow passage width of the cooling passage located on the downstream side ,
At least one dimple is provided on the surface of the semicircular portion and the straight portion, and the turbine blade is characterized in that:

A turbine blade having a serpentine flow path that guides a cooling medium supplied from a blade root to the inside of the blade,
A semicircular portion protruding toward the U-turn portion at the tip of the partition wall that partitions the cooling passage located upstream of the U-turn portion of the serpentine channel and the cooling passage located downstream; A bulging portion that protrudes into the cooling passage located on the side and has a linear section that gradually increases the flow passage cross-sectional area and the flow passage width of the cooling passage located on the downstream side ,
The second serpentine flow path is provided with two or more serpentine flow paths, and the first serpentine flow path and the other serpentine flow path are communicated with a tip portion of a rib that partitions one serpentine flow path and the other serpentine flow path adjacent to each other. A turbine blade characterized in that at least one communication passage is provided .

Located on the back side of the straight portion, of the partition wall, the surface to form a cooling passage located at the upstream side, according to claim 1, characterized in that cross section arcuate recess is provided, 3 The blade for turbines according to any one of claims 4 and 5 .

The cooling passage located on the upstream side and the cooling passage located on the downstream side through the partition are communicated with each other, and a first opening is provided on a surface forming the cooling passage located on the upstream side of the partition. And at least one first communication passage having a second opening on the surface of the straight portion, wherein the first opening is located closer to the blade tip than the second opening. The turbine blade according to any one of claims 1, 2 , 4, 5 , and 6 .

8. The turbine according to claim 1 , wherein at least one dimple is provided on a surface of the semicircular portion and the linear portion. Wings.

The second serpentine flow path is provided with two or more serpentine flow paths, and the first serpentine flow path and the other serpentine flow path are communicated with a tip portion of a rib that partitions one serpentine flow path and the other serpentine flow path adjacent to each other. The turbine blade according to any one of claims 1 , 2, 3, 4, 6 , 7 , and 8 , wherein at least one communication passage is provided.

A gas turbine comprising the turbine blade according to any one of claims 1 to 9 .