JP3402882B2 - Moving blades for radial and mixed flow turbines - Google Patents
Moving blades for radial and mixed flow turbinesInfo
- Publication number
- JP3402882B2 JP3402882B2 JP31588595A JP31588595A JP3402882B2 JP 3402882 B2 JP3402882 B2 JP 3402882B2 JP 31588595 A JP31588595 A JP 31588595A JP 31588595 A JP31588595 A JP 31588595A JP 3402882 B2 JP3402882 B2 JP 3402882B2
- Authority
- JP
- Japan
- Prior art keywords
- blade
- boss
- radial
- turbine
- mixed flow
- 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 - Lifetime
Links
Landscapes
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
【発明の詳細な説明】
【０００１】
【発明の属する技術分野】本発明は、ターボチャージャ
や、ガスタービン、エキスパンジョンタービン等に使用
されるラジアルタービン、斜流タービンにおける動翼の
構造に関する。
【０００２】
【従来の技術】図２に従来のラジアルタービン動翼を示
す。図２（ａ）はラジアルタービン動翼の側断面図、図
２（ｂ）は正面断面図、図２（ｃ）は流路面積の変化の
説明図である。
【０００３】これらの図において、２０１はラジアルタ
ービン動翼のボスで、該ボスには複数の翼２０２が取付
けられると共に、ボス２０１の形状はその半径ｒが動翼
出口２０７方向に向けて連続的に減少するよう構成され
ている。
【０００４】
【発明が解決しようとする課題】ところで前述のような
従来のラジアルタービン動翼は、図２（ａ）に示す動翼
の出口２０７にてＡ−Ａ断面での翼厚２０３が急速に０
になるため図２（ｂ）に示すように流路面積２０４が急
増し、逆に子午面流速は図示の２０５から２０６へ急減
速するため流れの損失が増加するという欠点がある。
【０００５】軸流タービンではこの問題が無いよう翼後
縁を極力薄くするが、ラジアルタービンや斜流タービン
では特に翼後縁にて翼の高さｈがボス半径ｒに対して大
きく、そのため翼根に作用する応力が高く翼厚２０３を
厚くせざるを得なかった。
【０００６】本発明は上記従来技術の不具合点を解消す
るため、翼面積の急減に対応してボス半径を増加させる
ことにより流路面積の急増を防止し、従来の動翼で生じ
ていた流速の急減を防ぎ、損失増加を低減できる新たな
動翼を得ることを目的としている。
【０００７】
【課題を解決するための手段】前記目的を達成するため
の構成として本発明のラジアルタービン、斜流タービン
の動翼は、ボスに複数の翼が放射状に取り付けられた、
ラジアルタービン、斜流タービンの動翼において、その
翼出口の翼根のボス径が翼出口にて翼断面積の減少に対
応して高くなりボス断面積が増加することを特徴として
いる。
【０００８】
【発明の実施の形態】以下本発明の好適と思われる実施
の形態の一例を図面に基づいて説明する。
【０００９】図１は本発明を説明するもので、図１
（ａ）はラジアルタービン動翼の側断面図、図１（ｂ）
は同装置における流路面積の変化の説明図である。
【００１０】これらの図において、１０１はラジアルタ
ービン動翼のボス、１０２は該ボスに放射状に取付けら
れた複数の翼、１０７は動翼出口を示す。
【００１１】また１０５は断面Ｂでの流速、１０６は断
面Ｃでの流速を示す。
【００１２】そして本発明動翼においては、ボス１０１
の図示Ｂ点からＣ点にかけてボスの半径を高くしてい
る。なおボスの半径は動翼の出口で最も高くするよう構
成する。
【００１３】このように図示Ｂ点からＣ点にかけてボス
の半径を高くすることにより流路面積（さきに従来技術
として説明した図２（ｂ）の符号２０４部分）の変化を
Ｂ点からＣ点にかけてスムーズにすることができ、流路
面積の急増が防止できるので、特に流路幅（図２（ｂ）
に示す符号２０８部分）が翼厚（同図２（ｂ）に示す符
号２０３部分）に比して小さいボス近傍では流れの急減
が防止でき、さきに説明した従来の動翼で生じていた流
速の急減を防止でき損失増加を低減できる。
【００１４】
【発明の効果】以上説明したように本発明によれば、次
に示す効果を奏する。
【００１５】（１）図１（ａ）に示す断面Ｂでの流速
（１０５）から断面Ｃでの流速（１０６）まで連続的に
スムーズに減速されるようになり損失の増加が低減でき
る。
【００１６】（２）さらに最も強度的にきびしい翼高さ
が低くなるので翼応力も低下するので翼を薄くすること
も同時に可能になる。その結果流路面積変化がさらにス
ムーズになる。Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a structure of a moving blade in a radial turbine or a mixed flow turbine used for a turbocharger, a gas turbine, an expansion turbine, or the like. 2. Description of the Related Art FIG. 2 shows a conventional radial turbine blade. 2A is a side sectional view of the radial turbine rotor blade, FIG. 2B is a front sectional view, and FIG. 2C is an explanatory diagram of a change in a flow path area. [0003] In these figures, reference numeral 201 denotes a boss of a radial turbine rotor blade, on which a plurality of blades 202 are attached, and the boss 201 has a shape in which the radius r is continuous toward the rotor blade outlet 207. Is configured to be reduced. [0004] Incidentally, in the conventional radial turbine blade as described above, the blade thickness 203 in the A-A cross section at the blade outlet 207 shown in FIG. To 0
Therefore, as shown in FIG. 2B, the flow path area 204 rapidly increases, and conversely, the meridional flow velocity suddenly decelerates from 205 to 206 shown in FIG. In an axial turbine, the blade trailing edge is made as thin as possible to avoid this problem. In a radial turbine or a mixed flow turbine, the blade height h is larger than the boss radius r, especially at the blade trailing edge. The stress acting on the root was high and the blade thickness 203 had to be increased. The present invention solves the above-mentioned disadvantages of the prior art by increasing the radius of the boss in response to a sharp decrease in the blade area, thereby preventing a sudden increase in the flow path area, and preventing the flow velocity generated by the conventional moving blade. The purpose is to obtain a new rotor blade that can prevent a sharp decrease in the power consumption and reduce the increase in loss. In order to achieve the above object, a moving blade of a radial turbine or a mixed flow turbine according to the present invention has a plurality of blades radially attached to a boss.
In the moving blades of the radial turbine and the mixed flow turbine, the boss diameter of the blade root at the blade outlet increases at the blade outlet in accordance with the decrease in the blade cross-sectional area, and the boss cross-sectional area increases. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, an example of a preferred embodiment of the present invention will be described with reference to the drawings. FIG. 1 illustrates the present invention.
(A) is a side sectional view of a radial turbine rotor blade, FIG. 1 (b)
FIG. 4 is an explanatory diagram of a change in a flow channel area in the device. In these figures, reference numeral 101 denotes a boss of a radial turbine blade, 102 denotes a plurality of blades radially mounted on the boss, and 107 denotes a blade outlet. Reference numeral 105 denotes a flow velocity at the cross section B, and reference numeral 106 denotes a flow velocity at the cross section C. In the rotor blade of the present invention, the boss 101
The radius of the boss is increased from point B to point C in FIG. The radius of the boss is set to be the highest at the exit of the rotor blade. As described above, by increasing the radius of the boss from point B to point C in the drawing, the change in the flow path area (the portion indicated by reference numeral 204 in FIG. 2B described above as the prior art) can be changed from point B to point C. , And a sharp increase in the flow channel area can be prevented, and especially the flow channel width (FIG. 2B)
In the vicinity of the boss where the reference numeral 208 shown in FIG. 2 is smaller than the blade thickness (the reference numeral 203 shown in FIG. 2B), the flow can be prevented from sharply decreasing, and the flow velocity generated in the conventional rotor blade described above. Can be prevented from rapidly decreasing, and an increase in loss can be reduced. As described above, according to the present invention, the following effects can be obtained. (1) The flow velocity (105) at the cross section B shown in FIG. 1A is continuously and smoothly reduced from the flow velocity (106) at the cross section C, so that an increase in loss can be reduced. (2) Further, since the blade height, which is the most severe in strength, is reduced, the blade stress is also reduced, so that the blade can be made thinner at the same time. As a result, the change in the flow channel area becomes smoother.
【図面の簡単な説明】
【図１】本発明タービン動翼の説明図で、（ａ）はラジ
アルタービン動翼の側断面図、（ｂ）は流路面積の変化
の説明図である。
【図２】従来のタービン動翼の説明図で、（ａ）は側断
面図、（ｂ）は正面断面図、（ｃ）は流路面積の変化の
説明図である。
【符号の説明】
１０１ ボス
１０２ 翼
１０５ 断面Ｂでの流速
１０６ 断面Ｃでの流速
１０７ 動翼出口BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is an explanatory view of a turbine rotor blade of the present invention, in which (a) is a side sectional view of a radial turbine rotor blade, and (b) is an explanatory view of a change in a flow path area. 2A and 2B are explanatory views of a conventional turbine blade, wherein FIG. 2A is a side sectional view, FIG. 2B is a front sectional view, and FIG. [Description of Signs] 101 Boss 102 Blade 105 Flow velocity at cross section B 106 Flow velocity at cross section C 107 Rotor blade outlet
───────────────────────────────────────────────────── フロントページの続き (58)調査した分野(Int.Cl.7，ＤＢ名) F04D 29/28 F01D 5/00 F01D 5/12 F02B 39/00 ──────────────────────────────────────────────────続 き Continuation of front page (58) Field surveyed (Int. Cl. 7 , DB name) F04D 29/28 F01D 5/00 F01D 5/12 F02B 39/00
Claims (1)
た、ラジアルタービン、斜流タービンの動翼において、
その翼出口の翼根のボス径が翼出口にて翼断面積の減少
に対応して高くなりボス断面積が増加することを特徴と
するラジアルタービン、斜流タービンの動翼。(57) [Claim 1] In a moving blade of a radial turbine or a mixed flow turbine in which a plurality of blades are radially attached to a boss,
A moving blade of a radial turbine or a mixed flow turbine, wherein a boss diameter of a blade root at an outlet of the blade increases at the blade outlet in accordance with a decrease in the sectional area of the blade, and the sectional area of the boss increases.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP31588595A JP3402882B2 (en) | 1995-11-10 | 1995-11-10 | Moving blades for radial and mixed flow turbines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP31588595A JP3402882B2 (en) | 1995-11-10 | 1995-11-10 | Moving blades for radial and mixed flow turbines |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH09133095A JPH09133095A (en) | 1997-05-20 |
| JP3402882B2 true JP3402882B2 (en) | 2003-05-06 |
Family
ID=18070781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP31588595A Expired - Lifetime JP3402882B2 (en) | 1995-11-10 | 1995-11-10 | Moving blades for radial and mixed flow turbines |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3402882B2 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4918455B2 (en) * | 2007-10-31 | 2012-04-18 | 三菱重工業株式会社 | Turbocharger |
| JP5230784B2 (en) * | 2011-10-03 | 2013-07-10 | 三菱重工業株式会社 | Turbocharger |
| JP6019701B2 (en) * | 2012-04-20 | 2016-11-02 | 株式会社Ihi | Turbocharger |
| RU2014145610A (en) | 2012-04-23 | 2016-06-10 | Боргварнер Инк. | TURBINE HUB WITH SURFACE SURFACE AND TURBOCHARGER CONTAINING SUCH HUB |
| RU2014145575A (en) | 2012-04-23 | 2016-06-10 | Боргварнер Инк. | TURBOCHARGER CASING WITH CROSS grooves AND TURBOCHARGER WITH SUCH CASING |
-
1995
- 1995-11-10 JP JP31588595A patent/JP3402882B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH09133095A (en) | 1997-05-20 |
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