JPH0726904A - Blade tip structure of rotating machine - Google Patents
Blade tip structure of rotating machineInfo
- Publication number
- JPH0726904A JPH0726904A JP17075993A JP17075993A JPH0726904A JP H0726904 A JPH0726904 A JP H0726904A JP 17075993 A JP17075993 A JP 17075993A JP 17075993 A JP17075993 A JP 17075993A JP H0726904 A JPH0726904 A JP H0726904A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- blade tip
- tip structure
- fluid
- rotating machine
- 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
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)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、翼列を有する回転機械
装置に係わり、更に詳しくは、回転機械装置の翼端部構
造に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rotary machine having a row of blades, and more particularly to a blade end structure of the rotary machine.
【０００２】[0002]
【従来の技術】圧縮機、ポンプ、ファン、及びタービン
等の回転機械装置は、回転体に取り付けられた翼列を一
般に備えている。この翼列の翼端面とこれに対向するケ
ーシングの内面との間には、通常わずかな隙間（以下、
クリアランス部という）が設けられ、翼列とケーシング
との接触を防ぐようになっている。しかし、このクリア
ランス部を通過する漏れ流れのため回転機械装置の効率
が低下する問題があった。2. Description of the Related Art Rotary machines, such as compressors, pumps, fans, and turbines, typically include a row of blades attached to a rotor. Normally, a small gap (hereinafter, referred to as
A clearance section is provided to prevent contact between the blade row and the casing. However, there is a problem that the efficiency of the rotary machine device is reduced due to the leakage flow passing through the clearance portion.
【０００３】この効率低下を低減するため、従来、図５
に示すように、翼端面１に対向したケーシング２の内面
３に溝（トレンチ）を設け、クリアランス部４を軸方向
に流れる流体を低減することが提案され、一部で実施さ
れていた。すなわち、図５（Ａ）は、翼端面１に対向し
たトレンチの内面３を拡径し、翼列のない部分の内面５
と翼端面１とを同一半径位置に並べたもの（以下、ライ
ンオンライントレンチという）であり、効率改善が報告
されている。また、図５（Ｂ）は、翼端面１を軸方向に
傾斜させ、この傾斜に沿ってトレンチの内面３を拡径さ
せたもの（以下、スロープトレンチという）であり、効
率改善が報告されている。In order to reduce this decrease in efficiency, the conventional method shown in FIG.
As shown in (1), it has been proposed to provide a groove (trench) in the inner surface 3 of the casing 2 facing the blade tip surface 1 to reduce the fluid flowing in the clearance portion 4 in the axial direction, and it has been partially implemented. That is, in FIG. 5 (A), the inner surface 3 of the trench facing the blade end surface 1 is expanded in diameter, and the inner surface 5 of the portion without blade rows is expanded.
And the blade tip surface 1 are arranged at the same radial position (hereinafter, referred to as line online trench), and efficiency improvement has been reported. Further, FIG. 5 (B) shows an example in which the blade tip surface 1 is inclined in the axial direction, and the inner surface 3 of the trench is expanded along this inclination (hereinafter referred to as a slope trench), and improvement in efficiency has been reported. There is.
【０００４】[0004]
【発明が解決しようとする課題】しかし、上述した従来
の回転機械装置の翼端部構造（ラインオンライントレン
チ及びスロープトレンチ）では、クリアランス部を軸方
向に流れる流体は低減されるが、クリアランス部で流体
の流れ方向が鋭角に曲げられるため、その部分で流れが
剥離し渦が発生して圧力損失が生じ、またクリアランス
部の流体が実質的に閉じ込められた状態となり、翼端に
よるこの部分の流体の攪拌のため攪拌損失が生ずる問題
点があった。However, in the blade tip structure (line online trench and slope trench) of the conventional rotary machine described above, the fluid flowing in the clearance portion in the axial direction is reduced, but the clearance portion does not. Since the flow direction of the fluid is bent at an acute angle, the flow is separated at that portion and vortices are generated, resulting in pressure loss, and the fluid in the clearance is substantially confined, and the fluid in this portion due to the blade tip However, there was a problem that stirring loss occurred due to stirring.
【０００５】本発明はかかる問題点を解決するために創
案されたものである。すなわち、本発明は、クリアラン
ス部で発生する圧力損失と攪拌損失を低減することがで
き、これにより高い効率を得ることができる回転機械装
置の翼端部構造を提供することにある。The present invention was devised to solve such problems. That is, the present invention is to provide a blade tip structure of a rotary machine device that can reduce pressure loss and agitation loss that occur in the clearance portion, and can thereby obtain high efficiency.
【０００６】[0006]
【課題を解決するための手段】本発明によれば、翼列を
有する回転機械装置の翼端部構造であって、翼端面の少
なくとも一部が軸方向に沿って緩い曲線で突出してお
り、かつ翼端面に対向するケーシング内面が翼端面から
ほぼ一定の間隔を隔てて対峙するように窪みが形成され
ている、ことを特徴とする回転機械装置の翼端部構造が
提供される。According to the present invention, there is provided a wing tip structure for a rotary machine having a blade row, wherein at least a part of the wing tip surface projects in a gentle curve along the axial direction, Further, there is provided a wing tip structure of a rotary machine device, wherein a recess is formed so that an inner surface of the casing facing the wing tip surface faces the wing tip surface at a substantially constant interval.
【０００７】[0007]
【作用】上記本発明の構成によれば、翼端面に対向する
ケーシング内面が翼端面からほぼ一定の間隔を隔てて対
峙するように窪みが形成されているので、翼列とケーシ
ングとの接触を防ぐことができる。また、翼端面の少な
くとも一部が軸方向に沿って緩い曲線で突出しているの
で、クリアランス部の流体の流れは円滑であり、流れが
剥離せず圧力損失が発生しない。更に、クリアランス部
の流体は翼端面に沿って流れるためクリアランス部に閉
じ込められず、翼端による流体の攪拌損失がほとんど生
じない。According to the above-mentioned structure of the present invention, since the inner surface of the casing facing the blade end surface is formed with the recess so as to face the blade end surface at a substantially constant interval, contact between the blade row and the casing is prevented. Can be prevented. Moreover, since at least a part of the blade tip surface projects along the axial direction with a gentle curve, the flow of the fluid in the clearance portion is smooth, the flow is not separated, and no pressure loss occurs. Further, since the fluid in the clearance portion flows along the blade tip surface, it is not confined in the clearance portion, and the stirring loss of the fluid by the blade tip hardly occurs.
【０００８】更に、突出部分の翼端部でも翼部で負荷を
有することができるため、翼端における背側と腹側の圧
力差が小さくなることが確認された。これにより、腹側
（正圧面）から背側（負圧面）への流体の漏れ流れが減
少し、漏れ損失を低減することができる。Further, it has been confirmed that the pressure difference between the dorsal side and the ventral side at the blade tip can be reduced because the blade tip can also have a load at the protruding blade tip. As a result, the leakage flow of the fluid from the ventral side (pressure surface) to the back side (negative pressure surface) is reduced, and the leakage loss can be reduced.
【０００９】[0009]
【実施例】以下、本発明の好ましい実施例を図面を参照
して説明する。図１は、本発明による回転機械装置の翼
端部構造を示す部分断面図である。この図において、回
転機械装置１０は、回転体１２に取り付けられた翼列１
４を有し、流体が軸方向に流れるようになっている。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT A preferred embodiment of the present invention will be described below with reference to the drawings. FIG. 1 is a partial cross-sectional view showing a wing tip structure of a rotary machine device according to the present invention. In this figure, a rotary machine device 10 includes a blade row 1 attached to a rotor 12.
4 to allow the fluid to flow in the axial direction.
【００１０】本発明によれば、翼列１４の翼端面１５の
少なくとも一部が軸方向に沿って緩い曲線で突出してい
る。この突出部は、翼端面１５の前縁から後縁まで緩い
曲線（例えば円弧）で突出するのが好ましいが、その一
部、例えば前縁付近のみが突出していてもよい。また、
翼端面１５に対向するケーシング１６の内面１７は翼端
面１５からほぼ一定の間隔で隔てられている。According to the present invention, at least a part of the blade end surface 15 of the blade row 14 projects along the axial direction with a gentle curve. It is preferable that the projecting portion projects from the leading edge of the blade tip surface 15 to the trailing edge with a gentle curve (for example, an arc), but a part thereof, for example, only near the leading edge may project. Also,
The inner surface 17 of the casing 16 facing the blade tip surface 15 is separated from the blade tip surface 15 by a substantially constant distance.
【００１１】かかる構成により、翼端面１５とケーシン
グ内面１７とがほぼ一定の間隔を隔てて対峙するように
窪みが形成されているので、翼列１４とケーシング１６
との接触を防ぐことができる。また、翼端面１５の少な
くとも一部が軸方向に沿って緩い曲線で突出しているの
で、クリアランス部１８の流体は翼端面１５に沿って円
滑に流れ、流れが剥離せず圧力損失が発生しない。更
に、クリアランス部１８の流体は翼端面１５に沿って流
れるためクリアランス部１８に閉じ込められず、翼端に
よる流体の攪拌損失がほとんど生じない。With this structure, the blade rows 14 and the casing 16 are formed so that the blade end surfaces 15 and the casing inner surface 17 face each other with a substantially constant distance therebetween.
It is possible to prevent contact with. Further, since at least a part of the blade tip surface 15 projects along the axial direction with a gentle curve, the fluid in the clearance portion 18 smoothly flows along the blade tip surface 15, and the flow does not separate and a pressure loss does not occur. Further, since the fluid in the clearance portion 18 flows along the blade tip surface 15, it is not confined in the clearance portion 18, and the stirring loss of the fluid due to the blade tip hardly occurs.
【００１２】図２は、図１のＡ−Ａ線における断面図で
ある。翼列１４を構成する翼２０は、前縁２１と後縁２
２、及び背側２３と腹側２４からなる。翼２０の前縁２
１に流速Ｕ1 で流入した流れは、翼２０の後縁２２から
流速Ｕ2 で流出し、そのベクトル変化に対応した揚力Ｌ
が翼２０に作用する。この揚力Ｌは、腹側２４に発生す
る正圧と、背側２３に発生する負圧の差に対応する。FIG. 2 is a sectional view taken along line AA of FIG. The blades 20 constituting the blade row 14 include a leading edge 21 and a trailing edge 2
2 and a dorsal side 23 and a ventral side 24. Leading edge 2 of wing 20
The flow that has flowed into unit 1 at the flow velocity U1 flows out from the trailing edge 22 of the blade 20 at the flow velocity U2, and the lift force L corresponding to the vector change
Acts on the wing 20. The lift force L corresponds to the difference between the positive pressure generated on the ventral side 24 and the negative pressure generated on the back side 23.
【００１３】本発明によれば、翼端面１５の少なくとも
一部が軸方向に沿って緩い曲線で突出しているので、翼
端面１５付近に流入した流体は突出部分にも広がって翼
面を流れ、次いで緩やかに狭まって後縁２２から流出す
る。従って、翼端面１５付近のケーシング内面から一定
幅を考えると、流速Ｕ1 及び流速Ｕ2 が同じであり揚力
Ｌが同一であるにもかかわらず、揚力発生に寄与する翼
面積が突出部分の分だけ広くなっている。これにより、
翼面積の単位面積当たりの揚力は小さくなり、腹側２４
に発生する正圧と、背側２３に発生する負圧の差が小さ
くなる。According to the present invention, since at least a part of the blade end surface 15 projects along the axial direction with a gentle curve, the fluid flowing in the vicinity of the blade end surface 15 spreads also to the projecting portion and flows on the blade surface. Then, it gradually narrows and flows out from the trailing edge 22. Therefore, considering a certain width from the inner surface of the casing near the blade end surface 15, even though the flow velocity U1 and the flow velocity U2 are the same and the lift L is the same, the blade area contributing to the lift generation is wider by the protruding portion. Has become. This allows
Lifting force per unit area of wing area becomes smaller,
The difference between the positive pressure generated on the rear side and the negative pressure generated on the back side 23 becomes small.
【００１４】図３は、図２で説明した翼端部の圧力分布
を示す解析結果である。この図において、横軸は翼の前
縁からの位置であり、左端は前縁を右端は後縁を示して
おり、縦軸は翼表面の静圧の大きさを示している。また
図中破線はトレンチのない従来の翼端部構造の場合であ
り、実線は本発明による翼端部構造の場合を示してい
る。更に、上の２本（実線、破線）は、翼の腹側（正圧
面）の圧力を示し、下の２本は、翼の背側（負圧面）の
圧力を示している。この図から明らかなように、従来の
翼端部構造と比較して本発明の翼端部構造では、翼端に
おける背側２３と腹側２４の圧力差が小さくなることが
解析により確認された。これにより、図２における腹側
２４（正圧面）から背側２３（負圧面）への流体の漏れ
流れが減少し、漏れ損失を低減することができる。FIG. 3 is an analysis result showing the pressure distribution at the blade tip portion explained in FIG. In this figure, the horizontal axis represents the position from the leading edge of the blade, the left edge represents the leading edge, the right edge represents the trailing edge, and the vertical axis represents the magnitude of the static pressure on the blade surface. Further, the broken line in the drawing shows the case of the conventional blade tip structure without a trench, and the solid line shows the case of the blade tip structure according to the present invention. Furthermore, the upper two (solid line, broken line) show the pressure on the ventral side (pressure side) of the blade, and the lower two show the pressure on the back side (suction side) of the blade. As is clear from this figure, it was confirmed by analysis that the pressure difference between the dorsal side 23 and the ventral side 24 at the blade tip becomes smaller in the blade tip structure of the present invention than in the conventional blade tip structure. As a result, the leakage flow of fluid from the ventral side 24 (pressure side) to the back side 23 (negative pressure side) in FIG. 2 is reduced, and the leakage loss can be reduced.
【００１５】図４は、翼による損失係数を模式的に示す
図である。この図において、縦軸は翼末端からの位置
（スパン）であり、下端０％が末端を上端１００％が先
端（翼端面）を示しており、横軸は各スパンにおける翼
の損失係数を示している。また、図中破線はトレンチの
ない従来の翼端部構造の場合であり、実線は本発明によ
る翼端部構造の場合を示している。この図から明らかな
ように、本発明による翼端部構造では、翼端部（スパン
１００％）付近における損失係数が大幅に改善される。
これは前述のように、クリアランス部１８の流体が翼端
面１５に沿って円滑に流れ、流れが剥離せず圧力損失が
発生せず、かつ、クリアランス部１８の流体がクリアラ
ンス部１８に閉じ込められず、翼端による流体の攪拌損
失がほとんど生じないことによるものである。FIG. 4 is a diagram schematically showing the loss coefficient of the blade. In this figure, the vertical axis is the position (span) from the blade end, the lower end 0% indicates the end, the upper end 100% indicates the tip (blade end face), and the horizontal axis indicates the blade loss coefficient in each span. ing. The broken line in the figure shows the case of the conventional blade tip structure without a trench, and the solid line shows the case of the blade tip structure according to the present invention. As is clear from this figure, in the blade tip structure according to the present invention, the loss coefficient in the vicinity of the blade tip (span 100%) is significantly improved.
As described above, the fluid in the clearance portion 18 smoothly flows along the blade end surface 15, the flow does not separate, the pressure loss does not occur, and the fluid in the clearance portion 18 is not trapped in the clearance portion 18. This is because the stirring loss of the fluid due to the blade tip hardly occurs.
【００１６】[0016]
【発明の効果】上述したように、本発明の回転機械装置
の翼端部構造によれば、翼端面に対向するケーシング内
面が翼端面からほぼ一定の間隔を隔てて対峙するように
窪みが形成されているので、翼列とケーシングとの接触
を防ぐことができる。また、翼端面の少なくとも一部が
軸方向に沿って緩い曲線で突出しているので、クリアラ
ンス部の流体の流れは円滑であり、流れが剥離せず圧力
損失が発生しない。更に、クリアランス部の流体は翼端
面に沿って流れるためクリアランス部に閉じ込められ
ず、翼端による流体の攪拌損失がほとんど生じない。As described above, according to the blade tip structure of the rotary machine device of the present invention, the recess is formed such that the inner surface of the casing facing the blade tip surface faces the blade tip surface at a substantially constant interval. Therefore, it is possible to prevent contact between the blade row and the casing. Moreover, since at least a part of the blade tip surface projects along the axial direction with a gentle curve, the flow of the fluid in the clearance portion is smooth, the flow is not separated, and no pressure loss occurs. Further, since the fluid in the clearance portion flows along the blade tip surface, it is not confined in the clearance portion, and the stirring loss of the fluid by the blade tip hardly occurs.
【００１７】更に、突出部分の翼端部でも翼部で負荷を
有することができるため、翼端における背側と腹側の圧
力差が小さくなり、腹側（正圧面）から背側（負圧面）
への流体の漏れ流れが減少し、漏れ損失を低減すること
ができる。従って、本発明の回転機械装置の翼端部構造
は、クリアランス部で発生する圧力損失と攪拌損失を低
減することができ、これにより高い効率を得ることがで
きる、優れた効果を有する。Furthermore, since the blade portion of the protruding portion can have a load on the blade portion, the pressure difference between the back side and the ventral side at the blade tip becomes small, and the ventral side (positive pressure surface) to the back side (negative pressure surface).
The leakage flow of the fluid to and from is reduced, and the leakage loss can be reduced. Therefore, the blade tip structure of the rotary machine device of the present invention has an excellent effect that the pressure loss and the stirring loss generated in the clearance portion can be reduced, and thereby high efficiency can be obtained.
【図１】本発明による回転機械装置の翼端部構造を示す
部分断面図である。FIG. 1 is a partial cross-sectional view showing a wing tip structure of a rotary machine device according to the present invention.
【図２】図１のＡ−Ａ線における断面図である。FIG. 2 is a sectional view taken along line AA of FIG.
【図３】翼端部の圧力分布を示す解析結果である。FIG. 3 is an analysis result showing a pressure distribution at a blade tip.
【図４】翼による損失係数を示す試験結果である。FIG. 4 is a test result showing a loss coefficient due to a blade.
【図５】従来の回転機械装置の翼端部構造を示す部分断
面図である。FIG. 5 is a partial cross-sectional view showing a wing tip structure of a conventional rotary machine device.
１ 翼端面 ２ ケーシング ３ 内面 ４ クリアランス部 １０ 回転機械装置 １２ 回転体 １４ 翼列 １５ 翼端面 １６ ケーシング １７ 内面 １８ クリアランス部 ２０ 翼 ２１ 前縁 ２２ 後縁 ２３ 背側 ２４ 腹側 1 Blade End Surface 2 Casing 3 Inner Surface 4 Clearance Section 10 Rotating Machinery 12 Rotating Machine 14 Blade Row 15 Blade End Surface 16 Casing 17 Inner Surface 18 Clearance Section 20 Blade 21 Front Edge 22 Trailing Edge 23 Dorsal Side 24 Ventral Side
Claims (1)
転機械装置の翼端部構造であって、 翼端面の少なくとも一部が軸方向に沿って緩い曲線で突
出しており、かつ翼端面に対向するケーシング内面が翼
端面からほぼ一定の間隔を隔てて対峙するように窪みが
形成されている、ことを特徴とする回転機械装置の翼端
部構造。1. A wing tip structure for a rotary machine having a blade row attached to a rotating body, wherein at least a part of the wing tip surface projects along the axial direction with a gentle curve, and A wing tip structure of a rotary machine device, wherein recesses are formed so that inner surfaces of the casings facing each other face each other at a substantially constant distance from the wing tip surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17075993A JPH0726904A (en) | 1993-07-12 | 1993-07-12 | Blade tip structure of rotating machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17075993A JPH0726904A (en) | 1993-07-12 | 1993-07-12 | Blade tip structure of rotating machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0726904A true JPH0726904A (en) | 1995-01-27 |
Family
ID=15910860
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17075993A Pending JPH0726904A (en) | 1993-07-12 | 1993-07-12 | Blade tip structure of rotating machine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0726904A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102004059904A1 (en) * | 2004-12-13 | 2006-06-14 | Alstom Technology Ltd | Moving blade e.g. for turbo machine, has blade point which faces stator in turbo machine and contacts into channel of stator with blade point provided in such way that blade contacts channel at its edges and into rotor |
| WO2006137696A1 (en) * | 2005-06-23 | 2006-12-28 | Korea Ocean Research And Development Institute | Impulse turbine with rotor blade for prevention clearance flow loss |
| WO2010006976A1 (en) * | 2008-07-17 | 2010-01-21 | Siemens Aktiengesellschaft | Axial turbine for a gas turbine with limited play between blades and housing |
| JP2014181655A (en) * | 2013-03-21 | 2014-09-29 | Mitsubishi Heavy Ind Ltd | Turbine and rotary machine including the same |
| JP2016044568A (en) * | 2014-08-20 | 2016-04-04 | 三菱重工業株式会社 | Rotary machine |
| US9353632B2 (en) | 2010-10-21 | 2016-05-31 | Rolls-Royce Plc | Aerofoil structure |
| WO2017072843A1 (en) * | 2015-10-27 | 2017-05-04 | 三菱重工業株式会社 | Rotary machine |
| WO2017072844A1 (en) * | 2015-10-27 | 2017-05-04 | 三菱重工業株式会社 | Rotary machine |
| CN108487942A (en) * | 2018-03-15 | 2018-09-04 | 哈尔滨工业大学 | Control the casing and blade combined shaping method of turbine blade-tip gap flowing |
-
1993
- 1993-07-12 JP JP17075993A patent/JPH0726904A/en active Pending
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102004059904A1 (en) * | 2004-12-13 | 2006-06-14 | Alstom Technology Ltd | Moving blade e.g. for turbo machine, has blade point which faces stator in turbo machine and contacts into channel of stator with blade point provided in such way that blade contacts channel at its edges and into rotor |
| WO2006137696A1 (en) * | 2005-06-23 | 2006-12-28 | Korea Ocean Research And Development Institute | Impulse turbine with rotor blade for prevention clearance flow loss |
| KR100720909B1 (en) * | 2005-06-23 | 2007-05-22 | 한국해양연구원 | Impulse turbine with rotor blade for prevention against clearance flow loss |
| GB2441270A (en) * | 2005-06-23 | 2008-02-27 | Korea Ocean Res & Dev I | Impulse turbine with rotor blade for prevention clearance flow loss |
| GB2441270B (en) * | 2005-06-23 | 2011-06-15 | Korea Ocean Res & Dev Inst | Impulse turbine with rotor blade for prevention clearance flow loss |
| WO2010006976A1 (en) * | 2008-07-17 | 2010-01-21 | Siemens Aktiengesellschaft | Axial turbine for a gas turbine with limited play between blades and housing |
| JP2011528082A (en) * | 2008-07-17 | 2011-11-10 | シーメンス アクティエンゲゼルシャフト | Axial turbine for gas turbine with play defined between blade and housing |
| US9353632B2 (en) | 2010-10-21 | 2016-05-31 | Rolls-Royce Plc | Aerofoil structure |
| JP2014181655A (en) * | 2013-03-21 | 2014-09-29 | Mitsubishi Heavy Ind Ltd | Turbine and rotary machine including the same |
| JP2016044568A (en) * | 2014-08-20 | 2016-04-04 | 三菱重工業株式会社 | Rotary machine |
| WO2017072843A1 (en) * | 2015-10-27 | 2017-05-04 | 三菱重工業株式会社 | Rotary machine |
| WO2017072844A1 (en) * | 2015-10-27 | 2017-05-04 | 三菱重工業株式会社 | Rotary machine |
| US20180073375A1 (en) * | 2015-10-27 | 2018-03-15 | Mitsubishi Heavy Industries, Ltd. | Rotary machine |
| CN107850082A (en) * | 2015-10-27 | 2018-03-27 | 三菱重工业株式会社 | Rotating machinery |
| US10626739B2 (en) | 2015-10-27 | 2020-04-21 | Mitsubishi Heavy Industries, Ltd. | Rotary machine |
| US10968759B2 (en) | 2015-10-27 | 2021-04-06 | Mitsubishi Heavy Industries, Ltd. | Rotary machine |
| CN108487942A (en) * | 2018-03-15 | 2018-09-04 | 哈尔滨工业大学 | Control the casing and blade combined shaping method of turbine blade-tip gap flowing |
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