JPH0245441Y2 - - Google Patents
Info
- Publication number
- JPH0245441Y2 JPH0245441Y2 JP1983173066U JP17306683U JPH0245441Y2 JP H0245441 Y2 JPH0245441 Y2 JP H0245441Y2 JP 1983173066 U JP1983173066 U JP 1983173066U JP 17306683 U JP17306683 U JP 17306683U JP H0245441 Y2 JPH0245441 Y2 JP H0245441Y2
- Authority
- JP
- Japan
- Prior art keywords
- partition plate
- space
- impeller
- disk
- blade
- 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
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 238000005192 partition Methods 0.000 description 28
- 239000012530 fluid Substances 0.000 description 16
- 230000000694 effects Effects 0.000 description 6
- 238000012856 packing Methods 0.000 description 4
- 230000003068 static effect Effects 0.000 description 4
- 238000007664 blowing Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 210000004907 gland Anatomy 0.000 description 1
- 239000011796 hollow space material Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Description
【考案の詳細な説明】
本考案は蒸気タービン、ガスタービン等の各種
流体機械に応用できる軸流タービンに関するもの
である。[Detailed Description of the Invention] The present invention relates to an axial flow turbine that can be applied to various fluid machines such as steam turbines and gas turbines.
従来の円板形軸流多段タービン段落では、仕切
板ラビリンス部より仕切板と翼車で囲まれた空間
に洩れ込んだ流体は、一部が翼車のバランスホー
ルより翼車下流へ排出されるが、翼車円板表面の
流体は円板に引かれ回転し、この回転運転に伴な
い流体に働く遠心力により外周側へ投げ出され
る。特翼翼根部付近の仕切板および翼車の構造
は、従来、第１図〜第３図のごとくなつているの
で、翼車に沿つて外周側へ投げ出された流体は、
動翼翼根部の仕切板より翼車間の隙間より主流部
へ噴出し、主流を大きく乱す。この結果、段落効
率を著しく低下させる。 In conventional disc-shaped axial flow multi-stage turbine stages, some of the fluid that leaks from the partition plate labyrinth into the space surrounded by the partition plate and the impeller is discharged downstream from the impeller through the balance hole of the impeller. However, the fluid on the surface of the blade wheel disk is drawn by the disk and rotates, and is thrown out toward the outer circumference due to the centrifugal force acting on the fluid accompanying this rotation. Conventionally, the structure of the partition plate near the root of the special wing and the impeller is as shown in Figs. 1 to 3, so the fluid thrown out along the impeller towards the outer circumference is
It is ejected from the partition plate at the root of the rotor blade into the main stream through the gap between the blade wheels, greatly disturbing the main flow. As a result, the stage efficiency is significantly reduced.
本考案は、上記従来例の欠点を解消せんとして
なされたもので、仕切板より翼車間の隙間からの
流体漏洩量と段落効率の関係を調べると、効率が
最も良いのは主流の0.5％程度の流体がノズル翼
根部より仕切板より翼車間の空間へ洩れ出る場合
で、逆に主流部へ吹込む場合は、その吹込量に比
例して落段効率が低下する事が判る。そこで従来
の翼車の動翼翼根部付近の形状を改良し、翼車円
板面に沿つて外周側へ向けて流れる流体を円板外
径付近で反転させ、仕切板面に沿つて仕切板内周
側へ噴出させる事により、主流部への吹出しを防
止し、さらには主流の一部を空間へ吸引させ、段
落効率の向上を計る事を目的とする。 The present invention was developed to overcome the drawbacks of the conventional example described above. When examining the relationship between the amount of fluid leaking from the gap between the blade wheels and the stage efficiency, the best efficiency was found to be around 0.5% of the mainstream. It can be seen that when fluid leaks from the root of the nozzle blade into the space between the blade wheels through the partition plate, and conversely, when it is blown into the main stream, the stage drop efficiency decreases in proportion to the amount of fluid blown. Therefore, by improving the shape of the conventional blade near the root of the rotor blade, the fluid flowing toward the outer circumferential side along the blade wheel disk surface is reversed near the outer diameter of the disk, and the fluid flows inside the partition plate along the partition plate surface. By blowing out to the circumferential side, the purpose is to prevent blowing out to the main stream part, and furthermore, to draw a part of the main stream into the space, thereby improving the stage efficiency.
円転中の円板面に引きつけられて回転する流体
は、自らに作用する遠心力で外周方面へ投げ出さ
れるが、その場合の半径方向最大流速は、円板周
速の約２割にも達する。すなわち、直径１米の円
板が3600rpmで回転する場合、外周部より飛び出
す流体の半径方向速度は30数ｍ／ｓになる。 The rotating fluid that is attracted to the disk surface during rotation is thrown toward the outer circumference due to the centrifugal force that acts on itself, but the maximum flow velocity in the radial direction in this case reaches approximately 20% of the circumferential speed of the disk. . That is, when a disk with a diameter of 1 meter rotates at 3,600 rpm, the radial velocity of the fluid ejected from the outer circumference is about 30 m/s.
本考案の新規とする点は、円板形軸流タービン
段落において、翼車円板の上流側翼根部近傍に内
径側の断面形状が逆Ｕ字状の環状の突出棚を有す
る流れ方向転換用ガイド板を付設したことにあ
る。 The novelty of the present invention is that, in a disc-shaped axial flow turbine stage, a flow direction changing guide has an annular protruding shelf with an inverted U-shaped cross section on the inner diameter side near the blade root on the upstream side of the impeller disc. This is due to the addition of a board.
以下、本考案の好適な実施例について、従来形
とともに詳述する。 Hereinafter, preferred embodiments of the present invention will be described in detail together with conventional types.
第１図は代表的な従来形の衝動タービン段落を
示す。第２図、第３図は仕切板および翼車円板の
翼根部付近の従来形状例である。 FIG. 1 shows a typical conventional impulse turbine stage. FIGS. 2 and 3 are examples of conventional shapes of the partition plate and the blade root portion of the impeller disk.
図において、符号１１は仕切板、１２はノズ
ル、１３は仕切板の軸貫通部のラビリンスパツキ
ン、２１は翼車円板、２２は動翼、３１は当該段
落の仕切板と翼車で囲まれた空間、３２は当該段
落の翼車と次段落の仕切板で囲まれた空喰間、３
３は当該段落の翼車円板にあけられたバランスホ
ールで、空間３１と３２を連通する。２３は翼車
円板２１より突き出したグランドで、仕切板１１
に植え込まれたシールフイン１４と対をなし、空
間３１と主流流路部（ノズルおよび動翼で構成）
を区切るシーリング部を構成している。 In the figure, numeral 11 is a partition plate, 12 is a nozzle, 13 is a labyrinth packing of the shaft penetrating part of the partition plate, 21 is a blade wheel disk, 22 is a rotor blade, and 31 is surrounded by the partition plate and blade wheel of the paragraph. 32 is the hollow space surrounded by the impeller of the relevant paragraph and the partition plate of the next paragraph, 3
Reference numeral 3 denotes a balance hole drilled in the impeller disk of the paragraph, which communicates the spaces 31 and 32. 23 is a ground protruding from the impeller disk 21, and is connected to the partition plate 11.
It forms a pair with the seal fin 14 implanted in the space 31 and the main flow path section (consisting of a nozzle and a rotor blade).
It constitutes a sealing part that separates the
第２図の符号１５は仕切板１１より突き出した
アクシヤルフイン、第３図の符号２４は翼車側よ
り突き出したアクシヤルフインで、いずれも主流
流路部と空間３１を円切るシーリング部を構成し
ている。 Reference numeral 15 in FIG. 2 is an axial fin protruding from the partition plate 11, and reference numeral 24 in FIG. 3 is an axial fin protruding from the impeller side, both of which constitute a sealing part that cuts a circle between the main flow path part and the space 31. .
第４図は、本考案になるガイド板２５を付けた
翼車円板を装備するタービン段落例を示す。ガイ
ド板２５は翼車円板２１の上流面側動翼翼根部付
近に設けられ、軸方向の長さは当該段仕切板の側
面に近く迄である。断面は、第４図に示すごと
く、内周側が伏せた椀の縦断面に似た形すなわち
逆Ｕ字状をしている。第４図は、第１図の翼車グ
ランド２３に本考案のガイド板２５の構造を製込
んだ例である。 FIG. 4 shows an example of a turbine stage equipped with a blade wheel disk having a guide plate 25 according to the present invention. The guide plate 25 is provided near the root of the rotor blade on the upstream side of the impeller disc 21, and its length in the axial direction is close to the side surface of the stage partition plate. As shown in FIG. 4, the cross section has a shape resembling the vertical cross section of a bowl with the inner circumferential side facing down, that is, an inverted U-shape. FIG. 4 shows an example in which the structure of the guide plate 25 of the present invention is manufactured into the impeller gland 23 of FIG. 1.
第５図は第３図のアクシヤルフイン２４に本考
案のガイド板２６構造を組合せ、さらに仕切板１
１からのアクシヤルフイン１６と対にした例であ
る。この図では仕切板１１からのフイン１６の外
周側は下流に向つて削り落してあり、ノズル出口
で主流の一部を空間３１へ導入し易い様にした例
である。 FIG. 5 shows a combination of the guide plate 26 structure of the present invention with the axial fin 24 of FIG.
This is an example of a pair with the axial fin 16 from 1. In this figure, the outer circumferential side of the fins 16 from the partition plate 11 is shaved off toward the downstream, making it easier to introduce a part of the mainstream into the space 31 at the nozzle outlet.
第６図は仕切板１１からのアクシヤルフイン１
７と、本考案のガイド板２７を組合せ、狭い通路
３４を設け、ガイド板２７により内周へ向け噴出
する噴流のエジエクタ効果を大きくし、主流の一
部が空間へ流出し易いようにした例である。 Figure 6 shows the axial fin 1 from the partition plate 11.
7 and the guide plate 27 of the present invention are combined, a narrow passage 34 is provided, and the ejector effect of the jet jet jetted toward the inner circumference is increased by the guide plate 27, so that a part of the mainstream flows easily into the space. It is.
次に作用および効果について述べる。 Next, the action and effects will be described.
第１図および第４図により従来形と本考案の翼
車円板２１の作用を説明する。 The functions of the conventional type and the impeller disk 21 of the present invention will be explained with reference to FIGS. 1 and 4.
第１図において、P0は段落入口に全圧、P1は
平均直径上のノズル出口静圧、P1Rはノズル出口
の翼根部静圧、P2は段落出口静圧、P3，P4はそ
れぞれ空間３１，３２の静圧、P3Tは空間３１外
周端の圧力、太い実線矢印は主流、細い実線矢印
は仕切板パツキン部より空間３１へ洩れ込んだ流
体の流動状況を示す。 In Figure 1, P 0 is the total pressure at the stage inlet, P 1 is the static pressure at the nozzle exit on the average diameter, P 1R is the static pressure at the blade root at the nozzle exit, P 2 is the static pressure at the stage exit, P 3 , P 4 P 3T is the static pressure in the spaces 31 and 32, respectively, P 3T is the pressure at the outer peripheral end of the space 31, the thick solid line arrow indicates the mainstream, and the thin solid line arrow indicates the flow situation of the fluid leaking into the space 31 from the partition plate packing.
仕切板パツキンからの空間３１への洩込流体の
うち、翼車円板２１に近い流体は円板の回転運動
に引張られ、円板面に沿つて外周側へ向け螺旋運
動を行ない、一部はバランスホール３３を通り空
間３２へ排出するが、他は第１図の細い実線矢印
のごとき動きとなる。すなわち、翼車円板２１上
を外周へ向け投げ飛ばされた流体はグランド２３
の内周面に沿つて流れ、仕切板１１面上へ衝突す
る。ここで流れは２手に分れ、一つは仕切板１１
面に沿い内径側へ流下する。他の一つは仕切板１
１から出ているラジアルフイン１４の内側空間に
入り、ここの圧力P3Tを大きくする（P3T＞P3）。
そしてフイン部のクリアランスを通り、主流部へ
吹き出す。この現象は例えP1R＞P3であつてもP3T
＞P1R＞P3であれば起る。また、反動度を付与し
P1R＞P3Tにしてもこの螺旋流は主流から空間３１
への洩出しを難かしくする。 Among the fluid leaking into the space 31 from the partition plate packing, the fluid near the impeller disk 21 is pulled by the rotational movement of the disk, performs a spiral movement toward the outer circumference along the disk surface, and some is discharged into the space 32 through the balance hole 33, but otherwise the movement is as shown by the thin solid line arrow in FIG. In other words, the fluid thrown toward the outer periphery on the blade wheel disk 21 is sent to the ground 23.
The liquid flows along the inner peripheral surface of the partition plate 11 and collides with the surface of the partition plate 11. Here, the flow is divided into two, one is the partition plate 11
It flows down along the surface towards the inner diameter side. The other one is partition plate 1
It enters the inner space of the radial fin 14 coming out from 1 and increases the pressure P 3T here (P 3T > P 3 ).
Then, it passes through the clearance of the fin and blows out into the main stream. This phenomenon is true even if P 1R > P 3 , P 3T
It occurs if >P 1R >P 3 . Also, gives recoil degree
Even if P 1R > P 3T , this spiral flow moves from the mainstream to the space 31
Make it difficult for leaks to occur.
そこで第４図に示したガイド板２５を設ける
と、翼車円板２１に沿い外周へ向けて螺旋流は、
半径方向の向きを180度転向し、仕切板１１（静
止）側面に沿い内周側へ吹き出す。従つて主流部
への吹き出しは抑制され、さらには、この内側向
噴流のエゼクタ効果でノズル出口の主流の一部を
空間３１へ吸出す効果を発揮する（第４図中の細
い点線矢印）。 Therefore, if the guide plate 25 shown in FIG. 4 is provided, the spiral flow will flow along the impeller disk 21 toward the outer circumference.
The radial direction is turned 180 degrees and the air is blown out along the side of the partition plate 11 (stationary) toward the inner circumference. Therefore, the blowout to the main flow part is suppressed, and furthermore, the ejector effect of this inward jet flow has the effect of sucking out a part of the main flow at the nozzle outlet into the space 31 (thin dotted line arrow in FIG. 4).
第５図、第６図の構造についての効果は上記構
成の記述の後半部で述べた通りである。 The effects of the structures shown in FIGS. 5 and 6 are as described in the second half of the description of the above structure.
本考案によると空間３１から主流部への吹出し
が低減ないしは無くなり、さらに好条件の場合
は、主流の極く一部が空間３１へ洩出し、タービ
ン段落性能の向上をもたらす効果がある。 According to the present invention, the blowout from the space 31 to the main stream part is reduced or eliminated, and under favorable conditions, a small portion of the main stream leaks into the space 31, which has the effect of improving the turbine stage performance.
第１図は従来形の衝動タービン段落を示す断面
図、第２図は仕切板の翼根部付近の断面図、第３
図は翼車円板の翼根部付近の断面図、第４図は本
考案のガイド板を付けた歯車円板を装備するター
ビン段落例を示く断面図、第５図は第３図の例に
本考案のガイド板を組合せ、仕切板からのアクシ
ヤルフインと対にした例の断面図、第６図は仕切
板からのアクシヤルフインと本考案のガイド板を
組合せた例の断面図である。
１１……仕切板、１２……ノズル、１３……ラ
ビリンスパツキン、１５，１７……アクシヤルフ
イン、１６……フイン、２１……翼車円板、２２
……動翼、２５，２６，２７……ガイド板、３１
……空間、３２……通り空間、３３……バランス
ホール、３４……通路。
Figure 1 is a cross-sectional view showing a conventional impulse turbine stage, Figure 2 is a cross-sectional view of the partition plate near the blade root, and Figure 3 is a cross-sectional view of a conventional impulse turbine stage.
The figure is a cross-sectional view of the vicinity of the blade root of the blade wheel disk, Figure 4 is a cross-sectional view showing an example of a turbine stage equipped with a gear disk equipped with the guide plate of the present invention, and Figure 5 is an example of the blade shown in Figure 3. FIG. 6 is a sectional view of an example in which the guide plate of the present invention is combined with an axial fin from the partition plate, and FIG. 6 is a sectional view of an example in which the axial fin from the partition plate is combined with the guide plate of the present invention. 11... Partition plate, 12... Nozzle, 13... Labyrinth packing, 15, 17... Axial fin, 16... Fin, 21... Impeller disk, 22
... Moving blade, 25, 26, 27 ... Guide plate, 31
...space, 32...street space, 33...balance hall, 34...passage.
Claims (1)
上流側翼根部近傍に内径側の断面形状が逆Ｕ字状
の環状の突出棚を有する流れ方向転換用ガイド板
を付設したことを特徴とする軸流タービン。 The disc-shaped axial flow turbine stage is characterized in that a flow direction changing guide plate having an annular protruding shelf with an inverted U-shaped cross section on the inner diameter side is attached near the blade root on the upstream side of the impeller disc. axial flow turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17306683U JPS6081202U (en) | 1983-11-10 | 1983-11-10 | axial turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17306683U JPS6081202U (en) | 1983-11-10 | 1983-11-10 | axial turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS6081202U JPS6081202U (en) | 1985-06-05 |
| JPH0245441Y2 true JPH0245441Y2 (en) | 1990-12-03 |
Family
ID=30377105
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17306683U Granted JPS6081202U (en) | 1983-11-10 | 1983-11-10 | axial turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6081202U (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005240727A (en) * | 2004-02-27 | 2005-09-08 | Mitsubishi Heavy Ind Ltd | Impulse axial flow turbine |
| JP5172424B2 (en) * | 2008-03-28 | 2013-03-27 | 株式会社東芝 | Axial flow turbine |
| JP5972374B2 (en) * | 2012-07-11 | 2016-08-17 | 三菱日立パワーシステムズ株式会社 | Axial fluid machine |
| JP6638938B2 (en) * | 2016-03-25 | 2020-02-05 | 三菱日立パワーシステムズ株式会社 | Rotating machinery |
| JP6858032B2 (en) * | 2017-02-17 | 2021-04-14 | 三菱重工業株式会社 | Axial rotating machine |
| JP7202259B2 (en) * | 2019-05-31 | 2023-01-11 | 三菱重工業株式会社 | steam turbine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS51116304A (en) * | 1975-04-04 | 1976-10-13 | Hitachi Ltd | Moving root fin |
| JPS57116102A (en) * | 1980-08-06 | 1982-07-20 | Rolls Royce | Stationary blade assembly for turbo apparatus |
-
1983
- 1983-11-10 JP JP17306683U patent/JPS6081202U/en active Granted
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS51116304A (en) * | 1975-04-04 | 1976-10-13 | Hitachi Ltd | Moving root fin |
| JPS57116102A (en) * | 1980-08-06 | 1982-07-20 | Rolls Royce | Stationary blade assembly for turbo apparatus |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6081202U (en) | 1985-06-05 |
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