JPS62186004A - Axial flow turbine - Google Patents
Axial flow turbineInfo
- Publication number
- JPS62186004A JPS62186004A JP2583386A JP2583386A JPS62186004A JP S62186004 A JPS62186004 A JP S62186004A JP 2583386 A JP2583386 A JP 2583386A JP 2583386 A JP2583386 A JP 2583386A JP S62186004 A JPS62186004 A JP S62186004A
- Authority
- JP
- Japan
- Prior art keywords
- fins
- scraping
- fin
- eddy current
- tip
- 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.)
- Pending
Links
- 239000012530 fluid Substances 0.000 claims abstract description 16
- 238000003466 welding Methods 0.000 claims description 4
- 239000007779 soft material Substances 0.000 claims description 3
- 238000007790 scraping Methods 0.000 abstract description 34
- 230000000694 effects Effects 0.000 description 6
- 238000007789 sealing Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 210000001520 comb Anatomy 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
（発明の目的）
〔生産上の利用分野〕
本発明は、シュラウドカバー無しの動翼先端における損
失を低減化し、効率を向上しようとした軸流タービンに
関する。DETAILED DESCRIPTION OF THE INVENTION (Objective of the Invention) [Field of Production Application] The present invention relates to an axial flow turbine in which loss at the tip of a rotor blade without a shroud cover is reduced and efficiency is improved.
一般に、蒸気タービンにおける低圧最終段のようにシュ
ラウドカバー無しの動翼先端においては、動翼先端漏洩
損失（以下漏洩損失と略す）および動翼がケーシング上
の流体を掻きとるための掻取損失が大きく、これらの損
失が軸流タービンの効率を著しく悪化している。したが
って、軸流タービンの効率を向上するには、これらの損
失を低減することが重要である。Generally, at the tip of a rotor blade without a shroud cover, such as in the low-pressure final stage of a steam turbine, there is a leakage loss at the tip of the rotor blade (hereinafter referred to as leakage loss) and a scraping loss due to the rotor blade scraping off fluid on the casing. These losses significantly reduce the efficiency of axial flow turbines. Therefore, it is important to reduce these losses to improve the efficiency of axial turbines.
ここで、漏洩損失および掻取損失について説明する。漏
洩損失とは、流体が動翼先端とケーシング内面との間隙
（以下間隙と略す）を仕事せずに圧力側より負圧側へ漏
洩してしまうために起こる損失と漏洩流体と主流との干
渉による損失とを合わせたものである。Here, leakage loss and scraping loss will be explained. Leakage loss is caused by the loss caused by fluid leaking from the pressure side to the negative pressure side without working through the gap between the tip of the rotor blade and the inner surface of the casing (hereinafter referred to as the gap), and the interference between the leaked fluid and the mainstream. This is the sum of losses.
この漏洩損失は１間隙を流体が漏洩するために起こる損
失であるため２間隙の大きさに大きく左右される。すな
わち、間隙が大きくなると漏洩損失は大きくなり１間隙
が小さくなると漏洩損失は小さくなる。掻取損失とは動
翼先端がケーシング上の流体を掻き取るために生じる損
失であり、この掻き取りに要するエネルギ分の損失と、
この掻き取りによって生じる渦が主流を乱すことによっ
て生じる損失を合わせたものである。この掻取損失は、
間隙が小さくなると、掻き取る流体が多くなるために大
きくなり、逆に１間隙が大きくなると掻取損失は小さく
なる。Since this leakage loss is a loss caused by fluid leaking through one gap, it is greatly influenced by the size of the two gaps. That is, as the gap becomes larger, the leakage loss increases, and as the gap becomes smaller, the leakage loss decreases. Scraping loss is the loss caused by the tip of the rotor blade scraping the fluid on the casing, and the loss of energy required for this scraping,
This is the sum of the losses caused by the eddies generated by this scraping that disturb the mainstream. This scraping loss is
The smaller the gap, the larger the amount of fluid to scrape off, and conversely, the larger the gap, the smaller the scraping loss.
これらの動翼先端に生じる損失を低減化するという問題
に対し、漏洩損失を低減化するには、間隙を小さくすれ
ば良いが、そうすると掻取損失が増大してしまい、効率
はそれほど良くはならない。In response to the problem of reducing the loss that occurs at the tip of these rotor blades, the leakage loss can be reduced by making the gap smaller, but this increases the scraping loss and does not improve efficiency that much. .
また、間隙をあまりに小さくすると、ケーシングと動翼
との接触事故の危険を増すことになる。また、逆に、間
隙を大きくすると、掻取損失は小さくなるが、漏洩損失
が大きくなってしまう。漏洩損失と掻取損失の両者を低
減化する構造は、まだ考えられていない。Furthermore, if the gap is made too small, the risk of accidental contact between the casing and the rotor blade increases. Conversely, if the gap is made larger, the scraping loss will be smaller, but the leakage loss will be larger. A structure that reduces both leakage loss and scraping loss has not yet been considered.
そこで、本発明は、漏洩損失と掻取損失の両者を同時に
低減せしめた高効率の軸流タービンを提供することにあ
る。SUMMARY OF THE INVENTION Therefore, an object of the present invention is to provide a highly efficient axial flow turbine that simultaneously reduces both leakage loss and scraping loss.
（発明の構成）
〔問題点を解決するための手段およびその作用〕本発明
による軸流タービンは、シュラウドカバー無しの動翼に
おいて、その動翼先端に２枚フィンを設け、その２枚フ
ィンの相互間に渦室を形成したことを特徴とするもので
、動翼先端でケーシング上の流体を掻き取るときに生じ
る掻取溝を渦室内に固定化して掻取溝による損失を低減
し、掻取溝によるシール効果によって漏洩損失を低減し
ようとするものである。(Structure of the Invention) [Means for Solving the Problems and Their Effects] The axial flow turbine according to the present invention has a rotor blade without a shroud cover, and has two fins at the tip of the rotor blade. It is characterized by a vortex chamber formed between them, and the scraping grooves that occur when scraping the fluid on the casing at the tips of the rotor blades are fixed in the vortex chamber to reduce loss due to the scraping grooves, and to reduce the loss caused by the scraping grooves. This is intended to reduce leakage loss through the sealing effect of the grooves.
以下本発明を図面に示す実施例について説明する。まず
第１図において、動翼１の先端には、溝２を有し、この
溝２に２枚フィン３ａ、 ３ｂを有するフィン３が植え
込まれている。この２枚フィン３は、圧力側のフィン３
ａが長くしてケーシング５との間隙が極力小さくなるよ
うにしてあり、負圧側のフィン３ｂは短かくして２枚フ
ィン間に渦室４を形成するようにしである。また、この
植込み部は本実施例を負圧側より見た図である第２図に
示す硝り、フィン３を挿入する側の反対側は閉じた形、
−シ、挿入側は、フィンを挿入後、ビン８を打ち込み、
翼弦方向には抜けないようになっている。The present invention will be described below with reference to embodiments shown in the drawings. First, in FIG. 1, a rotor blade 1 has a groove 2 at its tip, and a fin 3 having two fins 3a and 3b is embedded in this groove 2. These two fins 3 are the fins 3 on the pressure side.
fins 3b on the negative pressure side are shortened to form a vortex chamber 4 between the two fins. In addition, this implanted part has the shape shown in FIG. 2, which is a view of this embodiment from the negative pressure side, and the side opposite to the side where the fin 3 is inserted is closed.
- On the insertion side, after inserting the fin, drive the bottle 8,
It is designed not to come off in the chord direction.
このような構成において、圧力側のフィン３日により漏
洩する流体は極力対ぜられ、また、圧力側のフィンによ
る掻取溝７は２枚フィン間の渦室４内に固定され、主流
を乱さない。この渦室４内に固定された掻取溝は、漏洩
流体の漏洩方向とは逆向きに回転しているため、漏洩す
る流体をシールする効果も期待できる。−力負圧側のフ
ィン３ｂは短かくしであるため、このフィン３ｂにょる
掻取損失の発生は極めて小さい。したがって、漏洩損失
と掻取損失の両者を低減化せしめることが可能となる。In such a configuration, the leaking fluid due to the fins on the pressure side is collected as much as possible, and the scraping groove 7 formed by the fins on the pressure side is fixed in the vortex chamber 4 between the two fins to prevent the mainstream from being disturbed. do not have. Since the scraping groove fixed in the vortex chamber 4 rotates in the opposite direction to the leaking direction of the leaking fluid, it can also be expected to have the effect of sealing the leaking fluid. - Since the fins 3b on the negative pressure side are short combs, the scraping loss caused by these fins 3b is extremely small. Therefore, it is possible to reduce both leakage loss and scraping loss.
また、圧力側フィン３ａを長くしてケーシング５との間
隙を極力小さくしたため、このフィン３ａとケーシング
５とが接触する危険性は大きくなるが、フィン３ａは軟
質材であり、また翼長方向には完全には固定されていな
いので、たとえフィン３ａとケーシング５とが接触して
も大きな事故には到らない。Furthermore, since the pressure side fins 3a are lengthened to minimize the gap between them and the casing 5, the risk of contact between the fins 3a and the casing 5 increases; however, the fins 3a are made of a soft material, and are not completely fixed, so even if the fins 3a and the casing 5 come into contact, no major accident will occur.
第３図は、植込み部形状をフィン側に溝を有するように
した他の実施例であり、他の構成は上記発明の実施例と
全く同じであり、作用も全く同じである。FIG. 3 shows another embodiment in which the implanted portion has a groove on the fin side, and the other structure is exactly the same as the embodiment of the invention described above, and the operation is also exactly the same.
第４図は、２枚フィン３ａ、 ３ｂを動翼先端にＥＢ溶
接等の溶接あるいはピン打ち等により完全に固定する構
成にしたもので、他の構成は上記発明の実施例と同様で
ある。この構成の場合には、圧カ速フィン３ａとケーシ
ング５との間隙はフィンとケーシングとが接触しないよ
うに、上記の実施例よりも大きくなるようにしである。FIG. 4 shows a configuration in which two fins 3a and 3b are completely fixed to the tip of the rotor blade by welding such as EB welding or by pinning, and the other configurations are the same as the embodiments of the invention described above. In this configuration, the gap between the pressure fins 3a and the casing 5 is made larger than in the above embodiments so that the fins and the casing do not come into contact with each other.
このような構成にした場合においても、掻取溝７が渦室
内に固定化されることにより、従来よりも、掻取溝７が
主流を乱すための損失は小さく、また、この掻取溝７に
よるシール効果により漏洩損失をも低減化されることが
期待できる。Even in the case of such a configuration, since the scraping groove 7 is fixed in the vortex chamber, the loss due to the scraping groove 7 disturbing the mainstream is smaller than in the past, and the scraping groove 7 It is expected that the leakage loss will also be reduced due to the sealing effect.
第５図は、２枚フィン３ａ、３ｂおよび渦室４を動翼１
よりの削り出しにより形成したことを特徴とする他の実
施例であり、フィン部を溶接等により完全に固定する上
記実施例と同様、圧力側フィンとケーシング５との間隙
は、フィン３とケーシング５の接触を避ける必要上大き
くしであるが、掻取溝７を渦室４内に固定化することに
より、掻取損失および漏洩損失を従来の構造によるより
大きく低減化することが期待できる。FIG.
This is another embodiment characterized in that the fins are formed by cutting out the fins, and similar to the above embodiment in which the fins are completely fixed by welding or the like, the gap between the pressure side fins and the casing 5 is the same as that between the fins 3 and the casing. Although it is necessary to avoid contact with the scraping groove 7, by fixing the scraping groove 7 within the vortex chamber 4, it is expected that the scraping loss and leakage loss can be reduced more than in the conventional structure.
（発明の効果）
以上説明したように、本発明によれば、動翼先端部に２
枚フィンを設け、圧力側を長く、負圧側を小さくし、２
枚フィン間に渦室を形成することにより、掻取溝を渦室
内に固定させ、掻取溝ガ主流を乱すための損失を低減化
し、また、掻取溝のシール効果により、漏洩損失をも同
時に低減化し、高効率の軸流タービンを提供することが
可能となる。(Effects of the Invention) As explained above, according to the present invention, there are two
Two fins are provided, the pressure side is long and the negative pressure side is small.
By forming a vortex chamber between the fins, the scraping groove is fixed within the vortex chamber, reducing loss due to the scraping groove disturbing the main flow, and the sealing effect of the scraping groove also reduces leakage loss. At the same time, it becomes possible to provide a highly efficient axial flow turbine.
第１図は本発明による軸流タービンの動翼先端の一実施
例を説明するための構成図、第２図はその動翼を負圧側
より観た正面図、第３図、第４図。
および第５図はそれぞれ本発明の異なる他の実施例を説
明するための構成図である。
１ 動翼
２溝
３ ２枚フィン
４ 渦室
５ ケーシング
６ 漏洩流体
７ 掻取溝
８ ビン
（８７３３）代理人 弁理士 猪 股 祥 晃（はが１
名）第１図
第２図
第３図 第４図
第５図FIG. 1 is a configuration diagram for explaining one embodiment of the rotor blade tip of an axial flow turbine according to the present invention, FIG. 2 is a front view of the rotor blade as seen from the negative pressure side, and FIGS. 3 and 4. and FIG. 5 are configuration diagrams for explaining other different embodiments of the present invention. 1 2 rotor blade grooves 3 2 fins 4 Vortex chamber 5 Casing 6 Leakage fluid 7 Scraping groove 8 Bin (8733) Agent Patent attorney Yoshiaki Inomata (Haga 1
Figure 1 Figure 2 Figure 3 Figure 4 Figure 5
Claims (5)
先端に２枚フィンを形成し、その２枚フィン間に動翼先
端でケーシング上の流体を掻き取るときに生じる渦を貯
める渦室を設けたことを特徴とする軸流タービン。(1) In a rotor blade without a shroud cover, two fins are formed at the tip of the rotor blade, and a vortex chamber is provided between the two fins to store the vortex generated when the fluid on the casing is scraped at the tip of the rotor blade. An axial flow turbine characterized by:
、負圧側のフィンは短かくした事を特徴とする特許請求
の範囲第１項記載の軸流タービン。(2) The axial flow turbine according to claim 1, wherein of the two fins, the fin on the pressure side of the rotor blade is made long, and the fin on the negative pressure side is made short.
込んだことを特徴とする特許請求の範囲第１項記載の軸
流タービン。(3) The axial flow turbine according to claim 1, characterized in that two fins are formed of a soft material and embedded at the tips of the rotor blades.
溶接あるいはピン打ち等により固定したことを特徴とす
る特許請求の範囲第１項記載の軸流タービン。(4) Two fins are formed from a soft material, and at the tip of the rotor blade,
The axial flow turbine according to claim 1, wherein the axial flow turbine is fixed by welding or pinning.
ことを特徴とする特許請求の範囲第１項記載の軸流ター
ビン。(5) The axial flow turbine according to claim 1, wherein the two fins are formed by cutting out the rotor blades.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2583386A JPS62186004A (en) | 1986-02-10 | 1986-02-10 | Axial flow turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2583386A JPS62186004A (en) | 1986-02-10 | 1986-02-10 | Axial flow turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS62186004A true JPS62186004A (en) | 1987-08-14 |
Family
ID=12176856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2583386A Pending JPS62186004A (en) | 1986-02-10 | 1986-02-10 | Axial flow turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62186004A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007085344A (en) * | 2005-09-19 | 2007-04-05 | General Electric Co <Ge> | Steam cooling type gas turbine bucket for reducing blade-end leak loss |
| JP2011012682A (en) * | 2009-07-02 | 2011-01-20 | General Electric Co <Ge> | System and device relating to turbine engine, and seal for turbine engine |
| WO2016080136A1 (en) * | 2014-11-20 | 2016-05-26 | 三菱重工業株式会社 | Turbine rotor blade and gas turbine |
| CN107002556A (en) * | 2014-10-24 | 2017-08-01 | 三菱重工业株式会社 | Axial-flow turbine and supercharger |
| FR3070424A1 (en) * | 2017-08-29 | 2019-03-01 | Safran Aircraft Engines | TURBOMACHINE WHEEL, SUCH AS A TURBO AIRBORNE OR TURBOPROPULSER |
-
1986
- 1986-02-10 JP JP2583386A patent/JPS62186004A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007085344A (en) * | 2005-09-19 | 2007-04-05 | General Electric Co <Ge> | Steam cooling type gas turbine bucket for reducing blade-end leak loss |
| JP2011012682A (en) * | 2009-07-02 | 2011-01-20 | General Electric Co <Ge> | System and device relating to turbine engine, and seal for turbine engine |
| CN107002556A (en) * | 2014-10-24 | 2017-08-01 | 三菱重工业株式会社 | Axial-flow turbine and supercharger |
| CN107002556B (en) * | 2014-10-24 | 2021-06-08 | 三菱重工业株式会社 | Axial flow turbine and supercharger |
| WO2016080136A1 (en) * | 2014-11-20 | 2016-05-26 | 三菱重工業株式会社 | Turbine rotor blade and gas turbine |
| JP2016098695A (en) * | 2014-11-20 | 2016-05-30 | 三菱重工業株式会社 | Turbine rotor blade and gas turbine |
| CN106661947A (en) * | 2014-11-20 | 2017-05-10 | 三菱重工业株式会社 | Turbine rotor blade and gas turbine |
| US10697311B2 (en) | 2014-11-20 | 2020-06-30 | Mitsubishi Heavy Industries, Ltd. | Turbine blade and gas turbine |
| FR3070424A1 (en) * | 2017-08-29 | 2019-03-01 | Safran Aircraft Engines | TURBOMACHINE WHEEL, SUCH AS A TURBO AIRBORNE OR TURBOPROPULSER |
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