JP2005180428A - ガスタービンエンジン用静翼アセンブリ - Google Patents
ガスタービンエンジン用静翼アセンブリ Download PDFInfo
- Publication number
- JP2005180428A JP2005180428A JP2004356041A JP2004356041A JP2005180428A JP 2005180428 A JP2005180428 A JP 2005180428A JP 2004356041 A JP2004356041 A JP 2004356041A JP 2004356041 A JP2004356041 A JP 2004356041A JP 2005180428 A JP2005180428 A JP 2005180428A
- Authority
- JP
- Japan
- Prior art keywords
- shroud
- outer shroud
- gas turbine
- stator assembly
- seal
- 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
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】 ガスタービン用の低圧コンプレッサー出口ステータアセンブリは、完全フープ外部シュラウドと内部シュラウドとの間に配設された複数の翼を具備する。外部シュラウドおよび内部シュラウドは中間ケース構造体に配設される。外部シュラウドとブリードダクト構造体との間には、熱膨張不整合に適応するためシールが配置される。
【選択図】 図4
Description
12 ファン部分
14 低圧コンプレッサー部分(LPC)
16 高圧コンプレッサー部分(HPC)
18 燃焼器部分
20 高圧タービン部分
22 低圧タービン部分
24 ブレード
26,26s 翼
26a 低圧コンプレッサー出口ステータアセンブリ
28 中間ケース構造体
30 ブリードダクト構造体
32 コア仕切り
33 ブリードダクト
34,34’ 完全フープ外部シュラウド
36 内部シュラウド
38 シール
40 差込みファスナー
42 ファスナー
44 保持体
46 ネジ付きファスナー
48 リップ
50 リベット止め保持リング
52 棚部
Claims (15)
- 外部シュラウドと、
内部シュラウドと、
前記外部シュラウドと前記内部シュラウドとの間に配設された複数の翼と、
前記外部シュラウドに配設されたシールと、を具備してなることを特徴とするステータアセンブリ。 - 前記外部シュラウドは完全フープ構造を具備することを特徴とする請求項1に記載のステータアセンブリ。
- 前記外部シュラウドは連続していることを特徴とする請求項1に記載のステータアセンブリ。
- 前記外部シュラウドはアルミニウムから製造されることを特徴とする請求項1に記載のステータアセンブリ。
- 前記内部シュラウドはチタニウムから製造されることを特徴とする請求項1に記載のステータアセンブリ。
- 前記外部シュラウドはガスタービンエンジンの中間ケース構造体に配設されていることを特徴とする請求項1に記載のステータアセンブリ。
- 前記複数の翼は、ガスタービンエンジンの低圧コンプレッサー部分と高圧コンプレッサー部分との間の過渡ダクトの上流に配置されていることを特徴とする請求項1に記載のステータアセンブリ。
- 前記シールは前記外部シュラウドの外径の周囲に配置されていることを特徴とする請求項1に記載のステータアセンブリ。
- 保持体と前記外部シュラウドとの間に前記シールを捕らえる前記保持体をさらに具備することを特徴とする請求項8に記載のステータアセンブリ。
- 前記外部シュラウドから延在するリップ上で前記シールを捕らえるリベットをさらに具備することを特徴とする請求項1に記載のステータアセンブリ。
- 中間ケース構造体と、
ブリードダクト構造体と、
前記中間ケース構造体に配設された外部シュラウドと、
前記中間ケースに配設された内部シュラウドと、
前記外部シュラウドと前記内部シュラウドとの間に配設された複数の翼と、
前記外部シュラウドに配設されたシールと、を具備し、前記シールは前記ブリードダクト構造体と係合していることを特徴とするガスタービンエンジン。 - 前記外部シュラウドは完全フープ構造を具備することを特徴とする請求項11に記載のガスタービンエンジン。
- 前記外部シュラウドは連続していることを特徴とする請求項11に記載のガスタービンエンジン。
- 前記シールは前記ブリードダクト構造体内の仕切りを密封することを特徴とする請求項11に記載のガスタービンエンジン。
- 前記複数の翼は、ガスタービンエンジンの低圧コンプレッサー部分と高圧コンプレッサー部分との間の過渡ダクトの上流に配置されていることを特徴とする請求項11に記載のガスタービンエンジン。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/742,725 US7025563B2 (en) | 2003-12-19 | 2003-12-19 | Stator vane assembly for a gas turbine engine |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005180428A true JP2005180428A (ja) | 2005-07-07 |
JP4095060B2 JP4095060B2 (ja) | 2008-06-04 |
Family
ID=34523259
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2004356041A Expired - Fee Related JP4095060B2 (ja) | 2003-12-19 | 2004-12-08 | ガスタービンエンジン用静翼アセンブリ |
Country Status (6)
Country | Link |
---|---|
US (1) | US7025563B2 (ja) |
EP (1) | EP1544415B1 (ja) |
JP (1) | JP4095060B2 (ja) |
KR (1) | KR100706723B1 (ja) |
CN (1) | CN1648417A (ja) |
IL (1) | IL165844A0 (ja) |
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CA2813263A1 (en) * | 2010-09-30 | 2012-04-05 | General Electric Company | Aircraft engine systems and methods for operating same |
US9429029B2 (en) | 2010-09-30 | 2016-08-30 | Pratt & Whitney Canada Corp. | Gas turbine blade and method of protecting same |
US9291064B2 (en) | 2012-01-31 | 2016-03-22 | United Technologies Corporation | Anti-icing core inlet stator assembly for a gas turbine engine |
US9427835B2 (en) | 2012-02-29 | 2016-08-30 | Pratt & Whitney Canada Corp. | Nano-metal coated vane component for gas turbine engines and method of manufacturing same |
FR2989722B1 (fr) * | 2012-04-23 | 2016-02-12 | Snecma | Etage de turbine dans une turbomachine |
US9045985B2 (en) | 2012-05-31 | 2015-06-02 | United Technologies Corporation | Stator vane bumper ring |
US9394915B2 (en) * | 2012-06-04 | 2016-07-19 | United Technologies Corporation | Seal land for static structure of a gas turbine engine |
US9322337B2 (en) | 2012-06-20 | 2016-04-26 | United Technologies Corporation | Aerodynamic intercompressor bleed ports |
US20130343883A1 (en) * | 2012-06-20 | 2013-12-26 | Ryan Edward LeBlanc | Two-piece duct assembly |
US9062603B2 (en) | 2012-06-20 | 2015-06-23 | United Technologies Corporation | Four bar drive mechanism for bleed system |
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US9188062B2 (en) * | 2012-08-30 | 2015-11-17 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine |
US10982551B1 (en) | 2012-09-14 | 2021-04-20 | Raytheon Technologies Corporation | Turbomachine blade |
US9366149B2 (en) | 2012-09-21 | 2016-06-14 | United Technologies Corporation | Multi-stage high pressure compressor case |
WO2014051668A1 (en) | 2012-09-26 | 2014-04-03 | United Technologies Corporation | Gas turbine engine including vane structure and seal to control fluid leakage |
US9297312B2 (en) | 2012-12-29 | 2016-03-29 | United Technologies Corporation | Circumferentially retained fairing |
US9631517B2 (en) | 2012-12-29 | 2017-04-25 | United Technologies Corporation | Multi-piece fairing for monolithic turbine exhaust case |
US9777584B2 (en) | 2013-03-07 | 2017-10-03 | Rolls-Royce Plc | Outboard insertion system of variable guide vanes or stationary vanes |
US20150013301A1 (en) * | 2013-03-13 | 2015-01-15 | United Technologies Corporation | Turbine engine including balanced low pressure stage count |
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2003
- 2003-12-19 US US10/742,725 patent/US7025563B2/en not_active Expired - Lifetime
-
2004
- 2004-12-03 KR KR1020040100790A patent/KR100706723B1/ko not_active IP Right Cessation
- 2004-12-08 JP JP2004356041A patent/JP4095060B2/ja not_active Expired - Fee Related
- 2004-12-16 EP EP04257870A patent/EP1544415B1/en not_active Expired - Fee Related
- 2004-12-16 IL IL16584404A patent/IL165844A0/xx unknown
- 2004-12-17 CN CNA2004101049878A patent/CN1648417A/zh active Pending
Also Published As
Publication number | Publication date |
---|---|
IL165844A0 (en) | 2006-01-15 |
JP4095060B2 (ja) | 2008-06-04 |
KR20050062375A (ko) | 2005-06-23 |
KR100706723B1 (ko) | 2007-04-13 |
EP1544415B1 (en) | 2012-12-12 |
EP1544415A3 (en) | 2008-11-12 |
EP1544415A2 (en) | 2005-06-22 |
US7025563B2 (en) | 2006-04-11 |
US20050135928A1 (en) | 2005-06-23 |
CN1648417A (zh) | 2005-08-03 |
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