JP3040560B2 - Stator blade shroud integrated turbine - Google Patents
Stator blade shroud integrated turbineInfo
- Publication number
- JP3040560B2 JP3040560B2 JP3282959A JP28295991A JP3040560B2 JP 3040560 B2 JP3040560 B2 JP 3040560B2 JP 3282959 A JP3282959 A JP 3282959A JP 28295991 A JP28295991 A JP 28295991A JP 3040560 B2 JP3040560 B2 JP 3040560B2
- Authority
- JP
- Japan
- Prior art keywords
- shroud
- turbine
- hub
- bearing
- variable
- 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、航空用ガスタービンエ
ンジンのタービン、詳しくは可変静翼とシュラウドとが
同時に変位するタービンに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine for an aeronautical gas turbine engine, and more particularly to a turbine in which a variable vane and a shroud are simultaneously displaced.
【０００２】[0002]
【従来の技術】従来、航空用ガスタービンエンジンの静
翼可変構造としては、図２に示す片持ち式、あるいは図
３に示す両端支持式があり、ともにシュラウドはタービ
ンの半径方向に対して固定された構造であった。2. Description of the Related Art Conventionally, as a variable structure of a stationary blade of an aeronautical gas turbine engine, there is a cantilever type shown in FIG. 2 or a both-end supporting type shown in FIG. It was the structure that was done.
【０００３】即ち、片持ち式の図２では可変静翼１はチ
ップ側シュラウド２とハブ側シュラウド３との間に、チ
ップ側軸受４から軸まわりにアーム８により回動可能に
支持されている。In other words, in FIG. 2 of the cantilever type, the variable stator vane 1 is rotatably supported between the tip side shroud 2 and the hub side shroud 3 by the arm 8 around the axis from the tip side bearing 4. .
【０００４】また、両端支持式の図３では可変静翼１は
チップ側シュラウド２とハブ側シュラウド３との間に、
チップ側軸受４及びハブ側軸受５とによって両端をアー
ム８により回動可能に支持されている。In FIG. 3 of a double-end supporting type, the variable stator vane 1 has a tip shroud 2 and a hub shroud 3
Both ends are rotatably supported by the arm 8 by the chip-side bearing 4 and the hub-side bearing 5.
【０００５】なお、図２は特開昭６３−２５３２７号に
よって、図３は特開平１−１１６２５１号によって、そ
れぞれ開示されているものである。FIG. 2 is disclosed by JP-A-63-25327, and FIG. 3 is disclosed by JP-A-1-116251.
【０００６】[0006]
【発明が解決しようとする課題】上記従来のタービンに
は解決すべき次の課題があった。The above conventional turbine has the following problems to be solved.
【０００７】即ち、タービン可変静翼はエンジンサイク
ルに応じて確実に作動するように、静翼の両端とシュラ
ウド間には、熱伸びを考慮したクリアランスが必要であ
る。これに対し、従来のシュラウドは半径方向に対して
固定された構造であったため、相対的な熱伸びが最大と
なるエンジン作動点でクリアランスが最小となるように
設計すると、他の作動点ではクリアランスが大きくな
り、漏れ流れによる圧力損失を生じる可能性が大きいと
いう問題があった。That is, in order to reliably operate the variable turbine vane in accordance with the engine cycle, a clearance is required between both ends of the vane and the shroud in consideration of thermal expansion. On the other hand, the conventional shroud has a fixed structure in the radial direction, so if the clearance is designed to be minimum at the engine operating point where the relative thermal elongation is maximum, the clearance will be set at other operating points. Therefore, there is a problem that pressure loss due to leakage flow is likely to occur.
【０００８】本発明は上記課題を解決するため、少なく
とも一方のシュラウドが可変静翼を支持する軸受と共に
移動して熱伸びの影響を受けないようにした静翼シュラ
ウド一体型タービンを提供することを目的とする。In order to solve the above-mentioned problems, the present invention provides an integrated vane shroud turbine in which at least one shroud moves together with a bearing for supporting a variable vane so as not to be affected by thermal expansion. Aim.
【０００９】[0009]
【課題を解決するための手段】本発明は上記課題の解決
手段として、チップ側シュラウドとハブ側シュラウドと
の間に少なくとも一方の側に設けられた軸受によって回
動可能に支持され上記両側のシュラウドに両端が近接す
る可変静翼を備えたタービンにおいて、上記軸受の側の
シュラウドが複数に分割されて軸受に固定されると共に
他の構造部分とは独立してなることを特徴とする静翼シ
ュラウド一体型タービンを提供しようとするものであ
る。According to the present invention, as a means for solving the above-mentioned problems, the shrouds on both sides are rotatably supported by bearings provided on at least one side between a tip-side shroud and a hub-side shroud. A turbine blade having variable vanes whose both ends are close to each other, wherein the shroud on the bearing side is divided into a plurality of parts and fixed to the bearing, and is independent of other structural parts. It is intended to provide an integrated turbine.
【００１０】[0010]
【作用】本発明は上記のように構成されるので次の作用
を有する。The present invention is configured as described above and has the following effects.
【００１１】即ち、可変静翼を支持する軸受に対し、そ
の軸受側のシュラウドが固定され、かつ、他の構造部分
とは独立するため、可変静翼とシュラウドとが軸受を介
して一体となり、かつ他の部材から機械的拘束を受けな
い構造となるため、熱伸びを生じても、一体となって変
移する。That is, since the shroud on the bearing side is fixed to the bearing supporting the variable stationary blade and is independent of other structural parts, the variable stationary blade and the shroud are integrated via the bearing, In addition, since the structure is not mechanically restrained by other members, even if thermal elongation occurs, the structure is integrally changed.
【００１２】従って、初期に設定したクリアランスに変
化が生じない。これにより、クリアランスによる漏れ損
失が抑えられ、エンジン性能が向上する。Therefore, there is no change in the initially set clearance. Thereby, the leakage loss due to the clearance is suppressed, and the engine performance is improved.
【００１３】[0013]
【実施例】本発明の一実施例を図１により説明する。図
１は本実施例の静翼シュラウド一体型タービンの部分図
で、（ａ）はエンジンの軸方向に切断した縦断面図、
（ｂ）は（ａ）のｂ−ｂ矢視断面図である。なお、従来
例と同様の構成部材には同符号を付し、必要ある場合を
除き、説明を省略する。FIG. 1 shows an embodiment of the present invention. FIG. 1 is a partial view of a stationary blade shroud-integrated turbine according to the present embodiment, and FIG.
(B) is sectional drawing in the bb arrow line of (a). The same components as those in the conventional example are denoted by the same reference numerals, and description thereof will be omitted unless necessary.
【００１４】図において、可変静翼１にはチップ側軸受
４とハブ側軸受５が取付けられている。チップ側軸受４
は、タービンケース７に固定され、アーム８を介して、
可変静翼１の駆動用ユニゾンリング６と接続されてい
る。チップ側シュラウド２ａは、複数のセクタに分割さ
れており、タービンケース７および可変静翼１と組み合
わされ、タービンの半径方向に対して固定された構造と
なっている。ハブ側シュラウド３ａは、可変静翼１のハ
ブ側軸受５に組み合わせて固定され、他の部材から機械
的拘束を受けない構造となる。In FIG. 1, a tip side bearing 4 and a hub side bearing 5 are attached to a variable stationary blade 1. Tip bearing 4
Is fixed to the turbine case 7 and, through the arm 8,
It is connected to the driving unison ring 6 of the variable vane 1. The tip-side shroud 2a is divided into a plurality of sectors, is combined with the turbine case 7 and the variable stationary blade 1, and has a structure fixed in the radial direction of the turbine. The hub-side shroud 3a is fixed in combination with the hub-side bearing 5 of the variable stator vane 1, and has a structure that is not mechanically restricted by other members.
【００１５】本実施例は上記のように構成されるので、
可変静翼１が熱伸びによりタービンの半径方向に変移し
ても、ハブ側シュラウド３ａが、可変静翼１と一体とな
って変移するため、クリアランスの変化が少なく、初期
設定した最小値のクリアランスを保持する。This embodiment is configured as described above.
Even if the variable stationary blade 1 is displaced in the radial direction of the turbine due to thermal expansion, the hub-side shroud 3a is displaced integrally with the variable stationary blade 1, so that the change in clearance is small, and the initially set minimum clearance Hold.
【００１６】この結果、ガスの漏洩が最小に抑えられ、
圧損が殆どなく、高効率のタービンを得ることができ
る。As a result, gas leakage is minimized,
A highly efficient turbine with almost no pressure loss can be obtained.
【００１７】以上、本実施例は好適例としてハブ側シュ
ラウド３ａがハブ側軸受５に組合わされる例について説
明したが、本発明はこれに限定されるものではなく、構
造が許す限り、チップ側シュラウド２ａとチップ側軸受
４とが結合されてもよく、或はその両方であってもよ
い。As described above, the present embodiment has been described as a preferred example in which the hub-side shroud 3a is combined with the hub-side bearing 5, but the present invention is not limited to this. The shroud 2a and the tip-side bearing 4 may be combined, or both.
【００１８】以上の通り、本実施例によればハブ側軸受
５にハブ側シュラウド３ａを固定するので、熱伸びによ
って、ハブ側軸受５と共に可変静翼１が移動してもハブ
側軸受５と共にハブ側シュラウド３ａも追随して移動す
るので、可変静翼１の端部とハブ側シュラウド３ａとの
間には相対差は生ぜず、従って最小値に設定されたクリ
アランスも熱伸びの影響を殆ど受けないため、クリアラ
ンスが設定値のまま保持され、ガス洩れによる圧損が最
小に抑えられるという利点がある。As described above, according to this embodiment, since the hub-side shroud 3a is fixed to the hub-side bearing 5, even if the variable stationary blade 1 moves with the hub-side bearing 5 due to thermal expansion, the hub-side shroud 3a is moved together with the hub-side bearing 5. Since the hub-side shroud 3a also follows, there is no relative difference between the end of the variable stator vane 1 and the hub-side shroud 3a. Since there is no pressure loss, there is an advantage that the clearance is maintained at the set value and pressure loss due to gas leakage is minimized.
【００１９】[0019]
【発明の効果】本発明は上記のように構成されるので次
の効果を有する。The present invention has the following effects because it is configured as described above.
【００２０】即ち、本発明によれば、エンジンの作動状
態にかかわらず、可変静翼とシュラウドとの間のクリア
ランスを最小かつ一定に近い値で保持することが可能と
なり、クリアランスが原因で生じるタービンの漏れ流れ
による圧力損失を少なく抑えられる。That is, according to the present invention, it is possible to maintain the clearance between the variable vane and the shroud at a minimum and nearly constant value irrespective of the operating state of the engine, and the turbine generated due to the clearance can be maintained. The pressure loss due to the leakage flow can be reduced.
【００２１】これにより、タービン効率の向上、燃料消
費率の改善が達成される。As a result, an improvement in turbine efficiency and an improvement in fuel consumption rate are achieved.
【図１】本発明の一実施例に係る静翼シュラウド一体型
タービンの部分図で、（ａ）は縦断面図、（ｂ）は
（ａ）のｂ−ｂ矢視断面図、BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a partial view of a stationary blade shroud integrated turbine according to one embodiment of the present invention, where (a) is a longitudinal sectional view, (b) is a sectional view taken along the line bb of (a),
【図２】従来例（片持ち式）の部分断面図、FIG. 2 is a partial cross-sectional view of a conventional example (cantilever type);
【図３】従来例（両端支持式）の部分断面図である。FIG. 3 is a partial cross-sectional view of a conventional example (both ends supported type).
１ 可変静翼 ２ａ チップ側シュラウド ３ａ ハブ側シュラウド ４ チップ側軸受 ５ ハブ側軸受 ６ 駆動用ユニゾンリング ７ タービンケース ８ アーム DESCRIPTION OF SYMBOLS 1 Variable stationary blade 2a Tip side shroud 3a Hub side shroud 4 Tip side bearing 5 Hub side bearing 6 Driving unison ring 7 Turbine case 8 Arm
───────────────────────────────────────────────────── フロントページの続き (56)参考文献 米国特許3584458（ＵＳ，Ａ) 仏国特許出願公開2584458（ＦＲ，Ａ １) (58)調査した分野(Int.Cl.7，ＤＢ名) F02C 9/22 F02C 7/00 F02C 7/20 ＷＰＩ／Ｌ（ＱＵＥＳＴＥＬ)────────────────────────────────────────────────── (5) References US Patent 3584458 (US, A) French Patent Application Publication 2584458 (FR, A1) (58) Fields investigated (Int. Cl. 7 , DB name) F02C 9 / 22 F02C 7/00 F02C 7/20 WPI / L (QUESTEL)
Claims (1)
との間に少なくとも一方の側に設けられた軸受によって
回動可能に支持され上記両側のシュラウドに両端が近接
する可変静翼を備えたタービンにおいて、上記軸受の側
のシュラウドが複数に分割されて軸受に固定されると共
に他の構造部分とは独立してなることを特徴とする静翼
シュラウド一体型タービン。1. A turbine having variable stator vanes rotatably supported by bearings provided on at least one side between a tip-side shroud and a hub-side shroud, and having both ends close to the shrouds on both sides. A shroud integrated with a stationary vane, wherein the shroud on the bearing side is divided into a plurality of parts and fixed to the bearing, and is independent of other structural parts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3282959A JP3040560B2 (en) | 1991-10-29 | 1991-10-29 | Stator blade shroud integrated turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3282959A JP3040560B2 (en) | 1991-10-29 | 1991-10-29 | Stator blade shroud integrated turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH05125960A JPH05125960A (en) | 1993-05-21 |
| JP3040560B2 true JP3040560B2 (en) | 2000-05-15 |
Family
ID=17659345
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3282959A Expired - Fee Related JP3040560B2 (en) | 1991-10-29 | 1991-10-29 | Stator blade shroud integrated turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3040560B2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101947415B1 (en) * | 2018-07-05 | 2019-02-13 | 강성길 | Water device for self water of plant |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ITMI20021231A1 (en) * | 2002-06-06 | 2003-12-09 | Nuovo Pignone Spa | FLAME TEMPERATURE CONTROL AND REGULATION SYSTEM FOR SINGLE SHAFT GAS TURBINES |
| US6742324B2 (en) * | 2002-09-13 | 2004-06-01 | General Electric Company | Methods and apparatus for supporting variable bypass valve systems |
| US20090067993A1 (en) * | 2007-03-22 | 2009-03-12 | Roberge Gary D | Coated variable area fan nozzle |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3584458A (en) | 1969-11-25 | 1971-06-15 | Gen Motors Corp | Turbine cooling |
| FR2584458A1 (en) | 1985-07-06 | 1987-01-09 | Bosch Gmbh Robert | FUEL INJECTION PUMP FOR INTERNAL COMBUSTION ENGINES |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2583820B1 (en) * | 1985-06-20 | 1989-04-28 | Snecma | DEVICE FOR VARIATION OF THE PASSAGE SECTION OF A TURBINE DISTRIBUTOR |
-
1991
- 1991-10-29 JP JP3282959A patent/JP3040560B2/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3584458A (en) | 1969-11-25 | 1971-06-15 | Gen Motors Corp | Turbine cooling |
| FR2584458A1 (en) | 1985-07-06 | 1987-01-09 | Bosch Gmbh Robert | FUEL INJECTION PUMP FOR INTERNAL COMBUSTION ENGINES |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101947415B1 (en) * | 2018-07-05 | 2019-02-13 | 강성길 | Water device for self water of plant |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH05125960A (en) | 1993-05-21 |
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