JP2005036806A - ターボジェットエンジンのステータ用の、可変静翼の外側ピボットのための案内システム - Google Patents
ターボジェットエンジンのステータ用の、可変静翼の外側ピボットのための案内システム Download PDFInfo
- Publication number
- JP2005036806A JP2005036806A JP2004202721A JP2004202721A JP2005036806A JP 2005036806 A JP2005036806 A JP 2005036806A JP 2004202721 A JP2004202721 A JP 2004202721A JP 2004202721 A JP2004202721 A JP 2004202721A JP 2005036806 A JP2005036806 A JP 2005036806A
- Authority
- JP
- Japan
- Prior art keywords
- bushing
- stator
- boss
- pivot
- turbojet engine
- 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.)
- Granted
Links
- 239000002184 metal Substances 0.000 claims description 18
- 239000000463 material Substances 0.000 claims description 3
- 210000000078 claw Anatomy 0.000 abstract description 2
- 239000002131 composite material Substances 0.000 description 6
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Images
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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】ボスから外側へ突出し、ボス21の長さよりも長く、ステータのボス21内に配置されるブッシング50を含み、外側ピボット11の接触長さが延長される。ブッシングは、爪によりブッシングの引き出しを可能にするための把持フック41で、終端している。ブッシングに位置決めエッジ42が備えられると有利である。ターボジェットエンジンに適用される。システムは、翼10の外側ピボット11の案内長さにおける増加を可能にし、静翼ケーシングを開く必要なしにブッシング50を引き出せる。
【選択図】 図2
Description
3 制御レバー
4 ナット
5、6、50 ブッシング
10 翼
11 外側ピボット
12 スペース
13 ねじ
21 ボス
22 リーマ部
40、44 金属ライナー
41 フック
42 位置決めエッジ
44 外方端部
51 外側フック
60 爪
Claims (3)
- ターボジェットエンジンのステータケーシングにおける所定長さのリーマ部(22)内を回転するために翼の外側ピボット(11)を有するターボジェットエンジンのステータ用である、可変静翼(10)の外側ピボット(11)のための案内システムであって、
低い摩擦係数を持つ材料から作られ、長さがリーマ部(22)の長さよりも長く、リーマ部から外側に突き出し、内径が外側ピボット(11)の外径よりもわずかに大きい、単一のブッシング(30、50)を備えており、更に、外径がリーマ部の内径よりもわずかに大きく、内径が、ブッシングの周りに配置されるようにブッシング(50)の外径に対応しており、外方端部(44)に外側フック(41)が設けられた、金属ライナー(40)を備えていることを特徴とする、案内システム。 - ブッシング(50)が金属であり、金属ライナーの外方端部(44)の所に周方向外側フック(51)を備えていることを特徴とする、請求項1に記載の案内システム。
- 金属ライナー(40)が、ステータケーシングのボス(21)に支承される位置決めエッジ(42)を有することを特徴とする、請求項1に記載の案内システム。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0350343A FR2857692B1 (fr) | 2003-07-17 | 2003-07-17 | Systeme de guidage du pivot exterieur d'une aube a angle de calage variable, de stator de turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005036806A true JP2005036806A (ja) | 2005-02-10 |
JP4056995B2 JP4056995B2 (ja) | 2008-03-05 |
Family
ID=33484736
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2004202721A Active JP4056995B2 (ja) | 2003-07-17 | 2004-07-09 | ターボジェットエンジンのステータ用の、可変静翼の外側ピボットのための案内システム |
Country Status (9)
Country | Link |
---|---|
US (1) | US7214030B2 (ja) |
EP (1) | EP1500791B1 (ja) |
JP (1) | JP4056995B2 (ja) |
CA (1) | CA2473819C (ja) |
DE (1) | DE602004006197T2 (ja) |
ES (1) | ES2285356T3 (ja) |
FR (1) | FR2857692B1 (ja) |
RU (1) | RU2340778C2 (ja) |
UA (1) | UA83794C2 (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008175209A (ja) * | 2007-01-22 | 2008-07-31 | General Electric Co <Ge> | 増分回転可能ブッシュを有するガスタービンエンジン用の可変ベーン組立体 |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2868490B1 (fr) * | 2004-04-05 | 2006-07-28 | Snecma Moteurs Sa | Douille a base de ceramique pour un systeme de calage variable d'aubes de turbomachines |
FR2881146B1 (fr) | 2005-01-27 | 2007-10-19 | Snecma Moteurs Sa | Procede de reparation d'une surface de frottement d'une aube a calage variable de turbomachine |
FR2913052B1 (fr) | 2007-02-22 | 2011-04-01 | Snecma | Commande des aubes a angle de calage variable |
US8215902B2 (en) * | 2008-10-15 | 2012-07-10 | United Technologies Corporation | Scalable high pressure compressor variable vane actuation arm |
US8858165B2 (en) * | 2010-09-30 | 2014-10-14 | Rolls-Royce Corporation | Seal arrangement for variable vane |
US10030533B2 (en) | 2012-09-21 | 2018-07-24 | United Technologies Corporation | Flanged bushing for variable vane |
FR3039226B1 (fr) * | 2015-07-20 | 2017-07-14 | Snecma | Etage d'aubes a calage variable pour une turbomachine |
CN111288020B (zh) * | 2020-02-24 | 2021-05-28 | 中国航发沈阳发动机研究所 | 一种压气机静子叶片联动结构 |
CN114251134B (zh) * | 2021-12-07 | 2024-01-26 | 萍乡德博科技股份有限公司 | 一种汽油机涡轮增压可变截面喷嘴环 |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3325087A (en) * | 1965-04-28 | 1967-06-13 | David R Davis | Stator casing construction for gas turbine engines |
GB1083156A (en) * | 1965-05-17 | 1967-09-13 | Gen Electric | Improvements in control mechanism |
US3367628A (en) * | 1966-10-31 | 1968-02-06 | United Aircraft Corp | Movable vane unit |
CA2082709A1 (en) * | 1991-12-02 | 1993-06-03 | Srinivasan Venkatasubbu | Variable stator vane assembly for an axial flow compressor of a gas turbine engine |
US6481960B2 (en) * | 2001-03-30 | 2002-11-19 | General Electric Co. | Variable gas turbine compressor vane structure with sintered-and-infiltrated bushing and washer bearings |
US6767183B2 (en) * | 2002-09-18 | 2004-07-27 | General Electric Company | Methods and apparatus for sealing gas turbine engine variable vane assemblies |
-
2003
- 2003-07-17 FR FR0350343A patent/FR2857692B1/fr not_active Expired - Fee Related
-
2004
- 2004-07-09 JP JP2004202721A patent/JP4056995B2/ja active Active
- 2004-07-12 US US10/887,832 patent/US7214030B2/en active Active
- 2004-07-13 EP EP04103336A patent/EP1500791B1/fr active Active
- 2004-07-13 DE DE602004006197T patent/DE602004006197T2/de active Active
- 2004-07-13 ES ES04103336T patent/ES2285356T3/es active Active
- 2004-07-13 CA CA2473819A patent/CA2473819C/en active Active
- 2004-07-16 RU RU2004121995/06A patent/RU2340778C2/ru active
- 2004-07-16 UA UA20040705840A patent/UA83794C2/uk unknown
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2008175209A (ja) * | 2007-01-22 | 2008-07-31 | General Electric Co <Ge> | 増分回転可能ブッシュを有するガスタービンエンジン用の可変ベーン組立体 |
US8517661B2 (en) | 2007-01-22 | 2013-08-27 | General Electric Company | Variable vane assembly for a gas turbine engine having an incrementally rotatable bushing |
Also Published As
Publication number | Publication date |
---|---|
UA83794C2 (uk) | 2008-08-26 |
EP1500791B1 (fr) | 2007-05-02 |
FR2857692A1 (fr) | 2005-01-21 |
DE602004006197D1 (de) | 2007-06-14 |
ES2285356T3 (es) | 2007-11-16 |
DE602004006197T2 (de) | 2007-12-20 |
JP4056995B2 (ja) | 2008-03-05 |
FR2857692B1 (fr) | 2007-05-11 |
RU2004121995A (ru) | 2006-01-20 |
CA2473819C (en) | 2012-08-28 |
US20050036885A1 (en) | 2005-02-17 |
EP1500791A1 (fr) | 2005-01-26 |
RU2340778C2 (ru) | 2008-12-10 |
US7214030B2 (en) | 2007-05-08 |
CA2473819A1 (en) | 2005-01-17 |
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