JP3040601B2 - Radial turbine blade - Google Patents
Radial turbine bladeInfo
- Publication number
- JP3040601B2 JP3040601B2 JP4177750A JP17775092A JP3040601B2 JP 3040601 B2 JP3040601 B2 JP 3040601B2 JP 4177750 A JP4177750 A JP 4177750A JP 17775092 A JP17775092 A JP 17775092A JP 3040601 B2 JP3040601 B2 JP 3040601B2
- Authority
- JP
- Japan
- Prior art keywords
- leading edge
- hub
- blade
- shroud
- radial turbine
- 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 - Fee Related
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
【0001】[0001]
【産業上の利用分野】本発明はラジアルタービン動翼に
関し、過給機、ガスタービン、ガスエキスパンダ等のラ
ジアルタービンに適用することができる。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a radial turbine blade, and can be applied to a radial turbine such as a supercharger, a gas turbine, a gas expander, and the like.
【0002】[0002]
【従来の技術】従来のラジアルタービンの一例を図4に
示す。図4はラジアルタービンの回転軸を含む断面での
断面図であり、図中、1は渦巻状流路であるスクロー
ル、2は動翼、3はスクロール出口、4はスクロール出
口壁、5は動翼2の前縁ハブ側6、前縁中央7及び前縁
シュラウド側8より成る動翼前縁を示している。2. Description of the Related Art FIG. 4 shows an example of a conventional radial turbine. FIG. 4 is a cross-sectional view including a cross section including the rotation axis of the radial turbine. In the drawing, 1 is a scroll which is a spiral flow path, 2 is a moving blade, 3 is a scroll outlet, 4 is a scroll outlet wall, and 5 is a dynamic The leading edge hub 6, the leading edge center 7, and the leading edge shroud side 8 of the blade 2 are shown.
【0003】ラジアルタービンに流入したガスは、スク
ロール1を周方向(図面直角方向)に流れる間に半径方
向流速が与えられ、動翼2に流入して、動翼2をその回
転軸まわりに回転させるよう作用する。The gas flowing into the radial turbine is given a radial velocity while flowing in the scroll 1 in the circumferential direction (perpendicular to the direction of the drawing), flows into the moving blade 2, and rotates the moving blade 2 around its rotation axis. Act to make it.
【0004】[0004]
【発明が解決しようとする課題】従来のラジアルタービ
ンにおいて、その動翼入口における速度三角形を図5に
示す。図5において、(a)は動翼入口中央での速度三
角形、(b)は動翼入口ハブ側又はシュラウド側での速
度三角形をそれぞれ示している。FIG. 5 shows a speed triangle at the blade entrance of a conventional radial turbine. 5A shows a speed triangle at the center of the blade entrance, and FIG. 5B shows a speed triangle at the blade inlet hub side or shroud side, respectively.
【0005】従来の動翼前縁5は、前縁ハブ側6の半径
rhub、前縁中央7の半径rmid及び前縁シュラウド側8
の半径rshroudが一定、すなわち、 rhub=rmid=rshroud であるため、各々の位置に対応する周速も Uhub=Umid=Ushroud となっている。The conventional blade leading edge 5 has a radius r hub of the leading edge hub 6, a radius r mid of the leading edge center 7 and a leading edge shroud side 8.
Is constant, that is, r hub = r mid = r shroud , so that the peripheral speed corresponding to each position is also U hub = U mid = U shroud .
【0006】一方、絶対流入速度は、スクロール出口3
内の二次流れやスクロール出口壁4上に発達する境界層
の影響により、動翼前縁5の前縁ハブ側6及び前縁シュ
ラウド側8では、図5に示す如く、前縁中央7の近傍よ
り周方向成分が小さく、半径方向成分が大きい、立った
流れとなる。その結果、動翼に相対的に流入する時の流
れの衝突角であるインシデンス角i3は i3,mid>i3,hub>i3,shroud となる。したがって、従来のラジアルタービン動翼で
は、図3に実線で示したように、前縁中央7におけるイ
ンシデンス角i3,midが最適インシデンス角i3,optであ
るとき、前縁ハブ側6及び前縁シュラウド側8のインシ
デンス角i3,hub、i3,shroudは最適値から外れ、その
結果、インシデンス損失が増加し、タービンの効率が低
下する、という問題点があった。On the other hand, the absolute inflow speed depends on the scroll outlet 3
As shown in FIG. 5, the leading edge hub side 6 and the leading edge shroud side 8 of the bucket leading edge 5 have the center 7 The standing flow has a smaller circumferential component and a larger radial component than the vicinity. As a result, the incident angle i 3, which is the collision angle of the flow when flowing relatively into the bucket, is i 3 , mid > i 3 , hub > i 3 , shroud . Therefore, in the conventional radial turbine rotor blade, as shown by a solid line in FIG. 3, when the incident angle i 3 , mid at the leading edge center 7 is the optimum incident angle i 3 , opt , the leading edge hub side 6 and the leading edge incidence angle i 3 edge shroud side 8, hub, i 3, shroud is deviated from the optimum value, as a result, increased incidence loss is, the efficiency of the turbine is disadvantageously decreases.
【0007】なお、図5においては、前縁ハブ側6及び
前縁シュラウド側8の速度三角形を同じとしているが、
前縁中央7からの両者の速度三角形のずれの度合は、ス
クロール1や動翼2の形状、作動条件等によって変るた
め、一般には、両者は一致しないが、ここでは、説明の
単純化のために、両者が同じ場合を例示した。In FIG. 5, the speed triangles of the leading edge hub side 6 and the leading edge shroud side 8 are the same.
The degree of deviation of the two speed triangles from the leading edge center 7 varies depending on the shapes of the scroll 1 and the moving blade 2, the operating conditions, and the like. In general, the two do not coincide with each other. An example in which both are the same is shown below.
【0008】したがって、本発明は上述のような問題点
に対し、インシデンス損失を低減させてタービン性能を
向上させることを可能にさせるラジアルタービン動翼を
提供することを目的とする。SUMMARY OF THE INVENTION Accordingly, it is an object of the present invention to provide a radial turbine rotor blade capable of reducing incident loss and improving turbine performance in order to solve the above problems.
【0009】[0009]
【課題を解決するための手段】上記目的に対し、本発明
によれば、流入ガス入口側の動翼前縁の形状を、前縁中
央では半径が大、前縁ハブ側及び前縁シュラウド側では
半径がそれより小の連続曲線で形成したことを特徴とす
るラジアルタービン動翼が提供される。According to the present invention, the shape of the leading edge of the moving blade on the inlet gas inlet side is large at the center of the leading edge, the leading edge hub side and the leading edge shroud side. Provides a radial turbine blade characterized by being formed by a continuous curve having a smaller radius.
【0010】[0010]
【作用】上記手段によれば、前縁ハブ側及び前縁シュラ
ウド側の半径が前縁中央の半径より小であるため、動翼
周速も前縁ハブ側の周速及び前縁シュラウド側の周速が
前縁中央の周速より小となり、前縁ハブ側及び前縁シュ
ラウド側のインシデンス角のずれが小さくなり、インシ
デンス損失が小さくなって、タービンの効率低下が小さ
くなる。According to the above means, since the radii on the leading edge hub side and the leading edge shroud side are smaller than the radius of the leading edge center, the moving blade peripheral speed is also the peripheral speed on the leading edge hub side and the leading edge shroud side. The peripheral speed is lower than the peripheral speed at the center of the leading edge, the deviation of the incident angle on the leading edge hub side and the leading edge shroud side is reduced, the incident loss is reduced, and the decrease in turbine efficiency is reduced.
【0011】[0011]
【実施例】図1は本発明によるラジアルタービン動翼を
例示したものであり、図中、図4に示したものと同一の
部分には同一の符号を付して、それらの詳細な説明は省
略する。FIG. 1 illustrates a radial turbine rotor blade according to the present invention. In FIG. 1, the same parts as those shown in FIG. 4 are denoted by the same reference numerals, and detailed description thereof will be omitted. Omitted.
【0012】図1によれば、動翼2の動翼前縁の形状
は、前縁中央7での半径rmidが大、前縁ハブ側6及び
前縁シュラウド側8での半径rhub、rshroudがそれよ
り小となるような連続曲線で形成してある。According to FIG. 1, the shape of the blade leading edge of the blade 2 is such that the radius r mid at the leading edge center 7 is large, the radius r hub at the leading edge hub side 6 and the leading edge shroud side 8, It is formed by a continuous curve such that r shroud is smaller.
【0013】より詳しくは、設計平均半径rdesign、前
縁ハブ側6の半径rhub、前縁中央7の半径rmid、前縁
シュラウド側8の半径rshroudの4者の関係を、それぞ
れ rdesign<rmid rdesign<rshroud<rmid rhub<rdesign (rhub+rmid+rshroud)/3=rdesign なる関係が満足するよう決め、半径rhub、rmid及びr
shroudを二次曲線で結んで、動翼前縁5を形成するよう
にしている。More specifically, the relationship among the design average radius r design , the radius r hub of the leading edge hub side 6, the radius r mid of the leading edge center 7, and the radius r shroud of the leading edge shroud side 8 is represented by r design <r decided to mid r design <r shroud <r mid r hub <r design (r hub + r mid + r shroud) / 3 = r design the relationship is satisfied, the radius r hub, r mid and r
The shroud is connected by a quadratic curve to form the bucket leading edge 5.
【0014】これら4者の関係は、スクロール、動翼2
の形状、タービン設計作動条件に応じて、たとえば図3
に破線で例示したように、動翼入口におけるインシデン
ス角分布ができるだけ最適に近づくように選定する。The relationship between these four members is that
According to the shape of the turbine and the operating conditions of the turbine design, for example, FIG.
As shown by the dashed line in FIG. 2, the incident angle distribution at the blade entrance is selected so as to be as optimal as possible.
【0015】したがって、半径rhub及びrshroudが半
径rmidより小となるため、図2に示したように動翼周
速も前縁ハブ側6の周速Uhub及び前縁シュラウド側8
の周速Ushroudが前縁中央7の周速Umidより小とな
り、図3の破線のように、前縁ハブ側6及び前縁シュラ
ウド側8のインシデンス角のずれが小さくなる。これに
より、インシデンス損失が低減されることになる。Accordingly, since the radius r hub and r shroud are smaller than the radius r mid , as shown in FIG. 2, the rotor blade peripheral speed is also the peripheral speed U hub of the leading edge hub side 6 and the leading edge shroud side 8.
Is smaller than the peripheral speed U mid at the center 7 of the leading edge, and the deviation of the incident angle between the leading edge hub side 6 and the leading edge shroud side 8 is reduced as shown by the broken line in FIG. Thereby, the incident loss is reduced.
【0016】[0016]
【発明の効果】上述のように、本発明によれば、動翼入
口流れの非一様性によって生じる不適切なインシデンス
角分布が是正され、インシデンス損失が低減されること
により、タービン性能を向上させることができる。As described above, according to the present invention, an inappropriate incident angle distribution caused by non-uniformity of the blade inlet flow is corrected, and the incident loss is reduced, thereby improving the turbine performance. Can be done.
【図1】本発明によるラジアルタービン動翼を例示した
断面図である。FIG. 1 is a cross-sectional view illustrating a radial turbine blade according to the present invention.
【図2】本発明によるラジアルタービン動翼の作用を説
明するための動翼入口速度三角形を示す図である。FIG. 2 is a view showing a moving blade entrance speed triangle for explaining the operation of the radial turbine moving blade according to the present invention.
【図3】本発明によるラジアルタービン動翼の作用を従
来のものと比較するためのインシデンス角分布比較図で
ある。FIG. 3 is an incident angle distribution comparison diagram for comparing the action of the radial turbine rotor blade according to the present invention with that of a conventional one.
【図4】従来のラジアルタービンを例示した断面図であ
る。FIG. 4 is a cross-sectional view illustrating a conventional radial turbine.
【図5】従来のラジアルタービンの動翼入口速度三角形
を示す図である。FIG. 5 is a diagram showing a moving blade inlet speed triangle of a conventional radial turbine.
1 スクロール 2 動翼 3 スクロール出口 4 スクロール出口壁 5 動翼前縁 6 前縁ハブ側 7 前縁中央 8 前縁シュラウド側 REFERENCE SIGNS LIST 1 scroll 2 rotor blade 3 scroll outlet 4 scroll outlet wall 5 rotor blade leading edge 6 leading edge hub side 7 leading edge center 8 leading edge shroud side
フロントページの続き (58)調査した分野(Int.Cl.7,DB名) F01D 1/08 F02C 3/05 F02B 33/00 - 39/16 Continuation of the front page (58) Field surveyed (Int. Cl. 7 , DB name) F01D 1/08 F02C 3/05 F02B 33/00-39/16
Claims (1)
中央では半径が大、前縁ハブ側及び前縁シュラウド側で
は半径がそれより小の連続曲線で形成したことを特徴と
するラジアルタービン動翼。The shape of the leading edge of the blade on the inlet gas inlet side is formed as a continuous curve having a large radius at the center of the leading edge, and a smaller radius at the leading edge hub side and the leading edge shroud side. Radial turbine blade.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP4177750A JP3040601B2 (en) | 1992-06-12 | 1992-06-12 | Radial turbine blade |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP4177750A JP3040601B2 (en) | 1992-06-12 | 1992-06-12 | Radial turbine blade |
Publications (2)
Publication Number | Publication Date |
---|---|
JPH05340265A JPH05340265A (en) | 1993-12-21 |
JP3040601B2 true JP3040601B2 (en) | 2000-05-15 |
Family
ID=16036472
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP4177750A Expired - Fee Related JP3040601B2 (en) | 1992-06-12 | 1992-06-12 | Radial turbine blade |
Country Status (1)
Country | Link |
---|---|
JP (1) | JP3040601B2 (en) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6742989B2 (en) * | 2001-10-19 | 2004-06-01 | Mitsubishi Heavy Industries, Ltd. | Structures of turbine scroll and blades |
JP4288051B2 (en) | 2002-08-30 | 2009-07-01 | 三菱重工業株式会社 | Mixed flow turbine and mixed flow turbine blade |
US7147433B2 (en) * | 2003-11-19 | 2006-12-12 | Honeywell International, Inc. | Profiled blades for turbocharger turbines, compressors, and the like |
JP5398515B2 (en) * | 2009-12-22 | 2014-01-29 | 三菱重工業株式会社 | Radial turbine blades |
US9702299B2 (en) | 2012-12-26 | 2017-07-11 | Honeywell International Inc. | Turbine assembly |
CN106489019B (en) * | 2014-09-30 | 2018-04-27 | 三菱重工业株式会社 | Turbine |
-
1992
- 1992-06-12 JP JP4177750A patent/JP3040601B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
JPH05340265A (en) | 1993-12-21 |
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