JPS6125882B2 - - Google Patents
Info
- Publication number
- JPS6125882B2 JPS6125882B2 JP2321079A JP2321079A JPS6125882B2 JP S6125882 B2 JPS6125882 B2 JP S6125882B2 JP 2321079 A JP2321079 A JP 2321079A JP 2321079 A JP2321079 A JP 2321079A JP S6125882 B2 JPS6125882 B2 JP S6125882B2
- Authority
- JP
- Japan
- Prior art keywords
- refrigerant passage
- stator blade
- tip side
- refrigerant
- stator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 239000003507 refrigerant Substances 0.000 claims description 23
- 239000003595 mist Substances 0.000 claims description 8
- 239000000110 cooling liquid Substances 0.000 claims description 5
- 238000001816 cooling Methods 0.000 description 9
- 239000002826 coolant Substances 0.000 description 6
- 239000012809 cooling fluid Substances 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005553 drilling Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000009834 vaporization Methods 0.000 description 2
- 230000008016 vaporization Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
【発明の詳細な説明】
本発明は、少量の冷却液で良好に冷却できるよ
うにしたガスタービンの静翼に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a stator blade for a gas turbine that can be cooled well with a small amount of cooling fluid.
周知のように、ガスタービンは、往復機関に比
較して小形軽量で大馬力が得られるなどの多くの
利点を有している。 As is well known, gas turbines have many advantages over reciprocating engines, such as being smaller, lighter, and more powerful.
このようなガスタービン、たとえば等圧燃焼式
のものを例にとると、通常、第１図に示すように
筒状のケーシング１内に軸２を回転自在に設け、
この軸２の両端部とクケーシング１との間にそれ
ぞれ圧縮機３とパワータービン４とを構成し、圧
縮機３で圧縮された高圧空気で燃焼器５内の圧力
を高め、この状態で燃料を噴射させて燃焼させ、
この燃焼によつて生じた超高圧の高温ガスをパワ
ータービン４に導いて膨張させることにより軸２
の回転動力を得るように構成されている。そし
て、圧縮機３は、図の場合では案内羽根６と回転
羽根７とを軸方向へ配列して軸流型とし、また、
パワータービン４は軸２に固定された動翼８とケ
ーシング１に固定された静翼９とで構成されてい
る。 Taking such a gas turbine, for example, an isobaric combustion type, as shown in FIG.
A compressor 3 and a power turbine 4 are constructed between both ends of the shaft 2 and the casing 1, respectively, and the high pressure air compressed by the compressor 3 increases the pressure inside the combustor 5, and in this state, the fuel inject and burn it,
The ultra-high-pressure high-temperature gas generated by this combustion is guided to the power turbine 4 and expanded, and the shaft 2
It is configured to obtain rotational power of. In the case shown in the figure, the compressor 3 is of an axial flow type with guide vanes 6 and rotary vanes 7 arranged in the axial direction, and
The power turbine 4 includes rotor blades 8 fixed to the shaft 2 and stator blades 9 fixed to the casing 1.
ところで、上記のようなガスタービンにおい
て、効率を向上させるためには、パワータービン
４の入口におけるガス温度を高めることが最も有
効な手段であると云われている。しかし、パワー
タービン４を構成する金属材料の許容温度は、一
般的に800℃程度であり、これ以上にガス温度を
上げることはできない。したがつて、上記の値以
上にガス温度を上げるには、パワータービン４を
構成する部材、特に翼を効率よく冷却する必要が
ある。 By the way, in order to improve the efficiency of the gas turbines mentioned above, the power turbine
It is said that increasing the gas temperature at the inlet of No. 4 is the most effective means. However, the permissible temperature of the metal material constituting the power turbine 4 is generally about 800° C., and the gas temperature cannot be increased beyond this. Therefore, in order to raise the gas temperature above the above value, it is necessary to efficiently cool the members constituting the power turbine 4 , especially the blades.
翼を冷却する手段としては、従来、種々考えら
れており、たとえば静翼を冷却する方式として
は、液冷却方式を採用したものもある。 Conventionally, various means for cooling blades have been considered, and for example, a liquid cooling method has been adopted as a method for cooling stationary blades.
しかしながら、液冷却方式を採用した従来の静
翼にあつては、多量の冷却液を必要としたり、冷
却によつて局部的な応力集中現象が生じたりする
問題があつた。また、過熱蒸気を使つて冷却する
方式も考えられているが、この方式を採用すると
多量の蒸気を必要とする問題があつた。 However, conventional stationary blades employing a liquid cooling system have problems such as requiring a large amount of cooling liquid and causing local stress concentration phenomenon due to cooling. A method of cooling using superheated steam has also been considered, but this method has the problem of requiring a large amount of steam.
本発明は、このような事情に鑑みてなされたも
ので、その目的とするところは、少ない冷却液で
翼全体を効率よく冷却でき、しかも翼の製作の容
易化も図り得るガスタービンの静翼を提供するこ
とにある。 The present invention has been made in view of the above circumstances, and its purpose is to provide a stator blade for a gas turbine that can efficiently cool the entire blade with a small amount of cooling fluid and that also facilitates the manufacture of the blade. Our goal is to provide the following.
以下、本発明の詳細を図示の実施例によつて説
明する。 Hereinafter, details of the present invention will be explained with reference to illustrated embodiments.
第２図は、本発明に係る静翼をパワータービン
に組込んだ状態の一部分だけを示すもので、図中
１１はケーシングを、１２は動翼を、１３はケー
シング１１の内面に固定された静翼本体を示して
いる。 FIG. 2 shows only a part of the stator vane according to the present invention incorporated into a power turbine. In the figure, 11 is a casing, 12 is a rotor blade, and 13 is fixed to the inner surface of the casing 11. The stator blade body is shown.
静翼本体１３は、その全体形状が公知のものと
ほぼ同様に形成されているが、内部に次のような
冷媒通路が形成されている。すなわち、静翼本体
１３の内部で、かつほぼ中央部には第３図にも示
すように根本部側から先端部側に亘つて比較的大
径の第１の冷媒通路１４が形成されている。この
第１の冷媒通路１４は穴開け加工等によつて形成
されたもので、その根本部側の端部はケーシング
１１を貫通して設けられた孔１５を介して冷却液
供給管１６に通じている。またこの第１の冷媒通
路１４の先端部側に位置する端部は第３図にも示
すように静翼本体１３の先端内部に形成された接
続路１７に通じている。また、静翼本体１３の表
面近傍内部にも根本部側から先端部側へかけて、
かつ静翼本体１３の周面に沿つてほぼ等間隔に複
数の第２の冷媒通路１８が形成されている。この
第２の冷媒通路１８も穴開け加工等によつて形成
されたもので、前記第１の冷媒通路１４より小径
に形成されている。そして各第２の冷媒通路１８
の先端部側の端部は第４図に示すように流路を十
分に狭めたノズル部１９を介してそれぞれ前記接
続路１７に接続されている。また、各第２の冷媒
通路１８の根本部側に位置する端部は、ケーシン
グ１１の壁内に形成された部屋２０に共通に接続
され、この部屋２０は排出管２１に接続されてい
る。 The stator vane main body 13 has an overall shape substantially similar to that of a known one, but the following refrigerant passages are formed inside. That is, as shown in FIG. 3, inside the stator vane body 13 and approximately in the center, a first refrigerant passage 14 having a relatively large diameter is formed from the root side to the tip side. . This first refrigerant passage 14 is formed by drilling or the like, and its base end communicates with the coolant supply pipe 16 through a hole 15 provided through the casing 11. ing. Further, the end of the first refrigerant passage 14 located on the tip side communicates with a connection path 17 formed inside the tip of the stator blade body 13, as shown in FIG. Also, inside the stator blade body 13 near the surface, from the root side to the tip side,
A plurality of second refrigerant passages 18 are formed at approximately equal intervals along the circumferential surface of the stator blade body 13. This second refrigerant passage 18 is also formed by drilling or the like, and is formed to have a smaller diameter than the first refrigerant passage 14. and each second refrigerant passage 18
As shown in FIG. 4, the ends on the tip side are respectively connected to the connection passages 17 via nozzle parts 19 whose flow passages are sufficiently narrowed. Further, the end portions of the second refrigerant passages 18 located on the root side are commonly connected to a chamber 20 formed within the wall of the casing 11, and this chamber 20 is connected to a discharge pipe 21.
このように構成されているので、次のようにし
て良好な冷却が行なわれる。すなわち、タービン
の運転時には、冷却液供給管１６を図示しない圧
縮液供給系に接続し、排出管２１を図示しない低
圧排気系に接続する。 With this configuration, good cooling can be achieved in the following manner. That is, during operation of the turbine, the coolant supply pipe 16 is connected to a compressed liquid supply system (not shown), and the discharge pipe 21 is connected to a low-pressure exhaust system (not shown).
しかして、圧縮液供給系から高圧（10〜100Kg/
cm2）の冷却液が第１の冷媒通路１４に送り込まれ
たとき、上記通路１４への熱侵入が所定に設定さ
れているものとすると、送り込まれた高圧冷却液
は沸騰しない程度に温度が上昇する。そして、昇
温した高圧冷却液は接続路１７およびノズル部１
９を介してそれぞれ第２の冷媒通路１８へ流れ込
む。この場合、冷却液は高圧でかつ高温、つまり
飽和に近い状態となつているのでノズル部１９を
通過して急激に膨張すると１〜50μのミストとな
る。したがつて第２の冷媒通路１８にはミストが
通流することになり、このミストが第２の冷媒通
路１８の内面全体に接触し、上記内面全体から熱
を奪つて気化し、このときの気化熱によつて静翼
１３が冷却される。そして、残りのミストを含ん
だ蒸気は一旦部屋２０へ導かれ、その後、排出管
２１を介して排出され、たとえば蒸気タービンな
どの蒸気として使用される。 However, high pressure (10~100Kg/
cm 2 ) of coolant is sent into the first refrigerant passage 14, assuming that the heat infiltration into the passage 14 is set to a predetermined value, the temperature of the high-pressure coolant that is sent is such that it does not boil. Rise. Then, the heated high-pressure coolant flows through the connection path 17 and the nozzle part 1.
9 into the second refrigerant passages 18, respectively. In this case, since the cooling liquid is under high pressure and high temperature, that is, in a state close to saturation, when it passes through the nozzle portion 19 and rapidly expands, it becomes a mist of 1 to 50 microns. Therefore, the mist flows through the second refrigerant passage 18, and this mist contacts the entire inner surface of the second refrigerant passage 18, absorbs heat from the entire inner surface, and vaporizes. The stator blade 13 is cooled by the heat of vaporization. Then, the remaining mist-containing steam is once led to the room 20, and then discharged through the exhaust pipe 21, and is used as steam for, for example, a steam turbine.
このように冷却液を静翼本体１３内で一旦ミス
ト状にし、このミスト流体を静翼本体１３の表面
近傍内部に形成された第２の冷媒通路１８へ流
し、上記流路１８の内面に接触させて気化させ、
この気化熱で静翼本体１３を冷却するようにして
いる。したがつて、少ない冷却液で効率良く冷却
することができる。また、冷媒をミスト状にして
いるので通流時の混合が良好に行なわれることに
なり、この結果根本部から先端部まで一様に冷却
でき、これによつて応力集中現象の発生を防止で
きるので、応力集中を緩和させるための複雑な構
造を採用する必要がなく、結局、静翼１３の製作
の容易化も図ることができる。 In this way, the coolant is once made into a mist within the stator blade body 13, and this mist fluid is flowed into the second refrigerant passage 18 formed inside near the surface of the stator blade body 13, and comes into contact with the inner surface of the passage 18. Let it vaporize,
The stator blade main body 13 is cooled by this heat of vaporization. Therefore, efficient cooling can be achieved with a small amount of cooling liquid. In addition, since the refrigerant is in a mist form, it is well mixed during flow, resulting in uniform cooling from the root to the tip, which prevents stress concentration from occurring. Therefore, there is no need to adopt a complicated structure for alleviating stress concentration, and as a result, manufacturing of the stationary blade 13 can be facilitated.
なお、上述した実施例においては第１の冷媒通
路を１つだけ設けているが、複数に分割してもよ
い。 In addition, in the embodiment described above, only one first refrigerant passage is provided, but it may be divided into a plurality of passages.
以上詳述したように、本発明によれば少ない冷
却液で良好に冷却でき、しかも製作の容易化も図
れるガスタービンの静翼を提供できる。 As described in detail above, according to the present invention, it is possible to provide a stator blade for a gas turbine that can be cooled well with a small amount of cooling fluid and can be manufactured easily.
第１図はガスタービンを一部切欠して示す側面
図、第２図は本発明の一実施例に係る静翼の側面
図、第３図ａは第２図におけるＡ−Ａ線切断失視
図、同図ｂは第２図におけるＢ−Ｂ線切断失視
図、第４図は第２図におけるＸ部分を取り出して
示す縦断面図である。
１１……ケーシング、１３……静翼、１４……
第１の冷媒通路、１７……接続路、８……第２の
冷媒通路、２０……ノズル部。
FIG. 1 is a partially cutaway side view of a gas turbine, FIG. 2 is a side view of a stator blade according to an embodiment of the present invention, and FIG. FIG. 4B is an asymmetrical view taken along the line BB in FIG. 2, and FIG. 4 is a vertical cross-sectional view showing the portion X in FIG. 2. 11...Casing, 13...Stator blade, 14...
1st refrigerant passage, 17... connection path, 8... second refrigerant passage, 20... nozzle section.
Claims (1)
この静翼本体内に設けられ外部より導かれた高圧
力の冷却液を上記静翼本体の根本部側から先端部
側へ導く第１の冷媒通路と、前記静翼本体の表面
近傍内部に上記静翼本体の根本部側から先端部側
へ亘つて複数設けられ上記先端部側に位置する端
部がそれぞれ前記第１の冷媒通路の先端部側の端
部に共通に接続されるとともに根本部側に位置す
る端部が外部の排出路に共通に通じる第２の冷媒
通路と、前記第１の冷媒通路と前記各第２の冷媒
通路との間に介在し通流する冷却液をミスト流に
変換するノズル機構とを具備したことを特徴とす
るガスタービンの静翼。1 The stator blade itself fixed to the inner surface of the casing,
A first refrigerant passage is provided in the stator vane body and guides a high-pressure cooling liquid led from the outside from the root side of the stator blade body to the tip side; A plurality of stator vane bodies are provided extending from the root side to the tip side, and the ends located on the tip side are each commonly connected to the end on the tip side of the first refrigerant passage, and A second refrigerant passage whose end located on the side commonly communicates with an external discharge passage, and a cooling liquid interposed between and flowing between the first refrigerant passage and each of the second refrigerant passages in a mist flow. A stator blade for a gas turbine, characterized in that it is equipped with a nozzle mechanism that converts into a nozzle mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2321079A JPS55117010A (en) | 1979-02-28 | 1979-02-28 | Stator blade for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2321079A JPS55117010A (en) | 1979-02-28 | 1979-02-28 | Stator blade for gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS55117010A JPS55117010A (en) | 1980-09-09 |
| JPS6125882B2 true JPS6125882B2 (en) | 1986-06-18 |
Family
ID=12104293
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2321079A Granted JPS55117010A (en) | 1979-02-28 | 1979-02-28 | Stator blade for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS55117010A (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5968504A (en) * | 1982-10-13 | 1984-04-18 | Hitachi Ltd | Heat recovery system of gas turbine cooling medium |
| JPH04119303U (en) * | 1991-04-09 | 1992-10-26 | 三菱重工業株式会社 | nozzle |
-
1979
- 1979-02-28 JP JP2321079A patent/JPS55117010A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS55117010A (en) | 1980-09-09 |
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