JP5604148B2 - ガスタービン内側流路カバー部材 - Google Patents
ガスタービン内側流路カバー部材 Download PDFInfo
- Publication number
- JP5604148B2 JP5604148B2 JP2010076540A JP2010076540A JP5604148B2 JP 5604148 B2 JP5604148 B2 JP 5604148B2 JP 2010076540 A JP2010076540 A JP 2010076540A JP 2010076540 A JP2010076540 A JP 2010076540A JP 5604148 B2 JP5604148 B2 JP 5604148B2
- Authority
- JP
- Japan
- Prior art keywords
- turbine
- gas turbine
- cover member
- impellers
- inner channel
- 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
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Dental Tools And Instruments Or Auxiliary Dental Instruments (AREA)
Description
101 翼形スロット
105 タービン翼車
110 タービン翼車
115 キャビティ
200 ガスタービン構成
205 タービン翼車
206 雌型の鳩尾形嵌合対
210 タービン翼車
211 雌型の鳩尾形嵌合対
215 キャビティ
220 高温部タービンノズル
225 縮小した上側キャビティ
300 ガスタービン内側流路カバー部材
301 雄型の鳩尾形嵌合対
305 本体
306 第1の(上側)表面
307 第2の(下側)表面
310 側方部材
315 構造支持部
320 アイソグリッドパターン
Claims (5)
- 第1のタービン翼車(205)と第2のタービン翼車(210)とを有するガスタービン(200)であって、前記第1及び第2のタービン翼車(205、210)は翼形スロットを有するガスタービン(200)の前記第1及び第2のタービン翼車(205、210)間に設けられる装置において、
第1の表面(306)と第2の表面(307)とを有する本体(305)と、
前記本体(305)の前記第1の表面(306)上に設けられる側方部材(310)と、
前記本体(305)の前記第2の表面(307)上に設けられる構造支持部(315)と、
前記構造支持部(315)に隣接する前記本体(305)の前記第2の表面(307)上に設けられた第1の鳩尾形嵌合部(301)と
を含み、
前記第1の鳩尾形嵌合部(301)は、前記第1及び第2のタービン翼車(205、210)の少なくとも一方に隣接して設けられた第2の鳩尾形嵌合部(206又は211)に嵌合するよう構成され、
前記側方部材(310)は、前記第1の表面と連続し且つ前記第1及び第2の表面と垂直をなすと共に、前記第1及び第2の鳩尾形嵌合部と同一平面上に位置する
ことを特徴とする、装置。 - 前記第1の表面(306)は、前記ガスタービン(200)内の高温空気の流路に合致する所定の形状を含む、請求項1に記載の装置。
- 前記側方部材(310)が、前記第1及び第2のタービン翼車(205、210)に接触し且つ前記第1及び第2のタービン翼車(205、210)の少なくとも一方の回転引張力下において変形するように構成されることにより、前記第1及び第2のタービン翼車(205、210)の少なくとも一方の表面に当接するシールが形成される、請求項1又は2に記載の装置。
- 前記第1及び第2の表面(306、307)の少なくとも一方にアイソグリッドパターン(320)を更に含む、請求項1乃至3のいずれか1項に記載の装置。
- 翼形スロットを有する第1のタービン翼車(205)と、
翼形スロットを有する第2のタービン翼車(210)と、
前記第1及び第2のタービン翼車(205、210)間に設けられた請求項1乃至4のいずれか1項に記載の装置と
を含む、ガスタービン(200)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/417,129 | 2009-04-02 | ||
US12/417,129 US8348603B2 (en) | 2009-04-02 | 2009-04-02 | Gas turbine inner flowpath coverpiece |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2010242757A JP2010242757A (ja) | 2010-10-28 |
JP5604148B2 true JP5604148B2 (ja) | 2014-10-08 |
Family
ID=42102269
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2010076540A Expired - Fee Related JP5604148B2 (ja) | 2009-04-02 | 2010-03-30 | ガスタービン内側流路カバー部材 |
Country Status (4)
Country | Link |
---|---|
US (1) | US8348603B2 (ja) |
EP (1) | EP2236767B1 (ja) |
JP (1) | JP5604148B2 (ja) |
CN (1) | CN101858257B (ja) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8845284B2 (en) | 2010-07-02 | 2014-09-30 | General Electric Company | Apparatus and system for sealing a turbine rotor |
US8511976B2 (en) * | 2010-08-02 | 2013-08-20 | General Electric Company | Turbine seal system |
US9217334B2 (en) | 2011-10-26 | 2015-12-22 | General Electric Company | Turbine cover plate assembly |
US8864453B2 (en) | 2012-01-20 | 2014-10-21 | General Electric Company | Near flow path seal for a turbomachine |
US9080456B2 (en) | 2012-01-20 | 2015-07-14 | General Electric Company | Near flow path seal with axially flexible arms |
US20130186103A1 (en) * | 2012-01-20 | 2013-07-25 | General Electric Company | Near flow path seal for a turbomachine |
US20130189097A1 (en) * | 2012-01-20 | 2013-07-25 | General Electric Company | Turbomachine including a blade tuning system |
US9540940B2 (en) * | 2012-03-12 | 2017-01-10 | General Electric Company | Turbine interstage seal system |
US9151169B2 (en) | 2012-03-29 | 2015-10-06 | General Electric Company | Near-flow-path seal isolation dovetail |
US20150071771A1 (en) * | 2013-09-12 | 2015-03-12 | General Electric Company | Inter-stage seal for a turbomachine |
US9404376B2 (en) | 2013-10-28 | 2016-08-02 | General Electric Company | Sealing component for reducing secondary airflow in a turbine system |
FR3015592B1 (fr) * | 2013-12-19 | 2018-12-07 | Safran Aircraft Engines | Rotor comportant une virole amelioree et procede de realisation |
US9719363B2 (en) | 2014-06-06 | 2017-08-01 | United Technologies Corporation | Segmented rim seal spacer for a gas turbine engine |
US10648481B2 (en) * | 2014-11-17 | 2020-05-12 | United Technologies Corporation | Fiber reinforced spacer for a gas turbine engine |
US10337345B2 (en) | 2015-02-20 | 2019-07-02 | General Electric Company | Bucket mounted multi-stage turbine interstage seal and method of assembly |
CN106906839A (zh) * | 2017-02-23 | 2017-06-30 | 天津大学 | 一种带裙板的组合式筒型基础及其施工方法 |
Family Cites Families (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3056579A (en) * | 1959-04-13 | 1962-10-02 | Gen Electric | Rotor construction |
GB1236920A (en) * | 1967-07-13 | 1971-06-23 | Rolls Royce | Bladed fluid flow machine |
US3551068A (en) * | 1968-10-25 | 1970-12-29 | Westinghouse Electric Corp | Rotor structure for an axial flow machine |
US4086378A (en) * | 1975-02-20 | 1978-04-25 | Mcdonnell Douglas Corporation | Stiffened composite structural member and method of fabrication |
DE2555911A1 (de) * | 1975-12-12 | 1977-06-23 | Motoren Turbinen Union | Rotor fuer stroemungsmaschinen, insbesondere gasturbinenstrahltriebwerke |
FR2404134A1 (fr) * | 1977-09-23 | 1979-04-20 | Snecma | Rotor pour turbomachines |
US4379812A (en) * | 1978-12-27 | 1983-04-12 | Union Carbide Corporation | Stress relieved metal/ceramic abradable seals and deformable metal substrate therefor |
US4521496A (en) * | 1980-07-24 | 1985-06-04 | Sara Raymond V | Stress relieved metal/ceramic abradable seals |
GB2159895B (en) * | 1984-06-04 | 1987-09-16 | Gen Electric | Stepped-tooth rotating labyrinth seal |
US4884950A (en) * | 1988-09-06 | 1989-12-05 | United Technologies Corporation | Segmented interstage seal assembly |
US5236302A (en) * | 1991-10-30 | 1993-08-17 | General Electric Company | Turbine disk interstage seal system |
US5217348A (en) * | 1992-09-24 | 1993-06-08 | United Technologies Corporation | Turbine vane assembly with integrally cast cooling fluid nozzle |
GB2280478A (en) * | 1993-07-31 | 1995-02-01 | Rolls Royce Plc | Gas turbine sealing assemblies. |
US5630703A (en) * | 1995-12-15 | 1997-05-20 | General Electric Company | Rotor disk post cooling system |
DE19940525A1 (de) * | 1999-08-26 | 2001-03-01 | Asea Brown Boveri | Wärmestaueinheit für eine Rotoranordnung |
EP1111195B2 (de) * | 1999-12-20 | 2013-05-01 | Sulzer Metco AG | Profilierte, als Anstreifschicht verwendete Oberfläche in Strömungsmaschinen |
US6464453B2 (en) * | 2000-12-04 | 2002-10-15 | General Electric Company | Turbine interstage sealing ring |
FR2825748B1 (fr) * | 2001-06-07 | 2003-11-07 | Snecma Moteurs | Agencement de rotor de turbomachine a deux disques aubages separes par une entretoise |
US6899520B2 (en) * | 2003-09-02 | 2005-05-31 | General Electric Company | Methods and apparatus to reduce seal rubbing within gas turbine engines |
FR2867223B1 (fr) * | 2004-03-03 | 2006-07-28 | Snecma Moteurs | Turbomachine comme par exemple un turboreacteur pour avion |
US7955694B2 (en) * | 2006-06-21 | 2011-06-07 | General Electric Company | Strain tolerant coating for environmental protection |
CN201116500Y (zh) * | 2007-11-19 | 2008-09-17 | 浙江吉利汽车有限公司 | 进气歧管 |
-
2009
- 2009-04-02 US US12/417,129 patent/US8348603B2/en active Active
-
2010
- 2010-03-30 JP JP2010076540A patent/JP5604148B2/ja not_active Expired - Fee Related
- 2010-03-31 EP EP10158796.2A patent/EP2236767B1/en not_active Not-in-force
- 2010-03-31 CN CN201010159771.7A patent/CN101858257B/zh not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
EP2236767A3 (en) | 2014-04-23 |
US20100254805A1 (en) | 2010-10-07 |
EP2236767A2 (en) | 2010-10-06 |
EP2236767B1 (en) | 2018-10-17 |
JP2010242757A (ja) | 2010-10-28 |
CN101858257B (zh) | 2015-09-09 |
CN101858257A (zh) | 2010-10-13 |
US8348603B2 (en) | 2013-01-08 |
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