DE602006014269D1 - Dichtungsanordnung für eine gebläserotoranordnung einer spitzenturbine - Google Patents
Dichtungsanordnung für eine gebläserotoranordnung einer spitzenturbineInfo
- Publication number
- DE602006014269D1 DE602006014269D1 DE602006014269T DE602006014269T DE602006014269D1 DE 602006014269 D1 DE602006014269 D1 DE 602006014269D1 DE 602006014269 T DE602006014269 T DE 602006014269T DE 602006014269 T DE602006014269 T DE 602006014269T DE 602006014269 D1 DE602006014269 D1 DE 602006014269D1
- Authority
- DE
- Germany
- Prior art keywords
- assembly
- top turbine
- fan
- seal 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.)
- Active
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/068—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type being characterised by a short axial length relative to the diameter
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/122,368 US7201558B2 (en) | 2005-05-05 | 2005-05-05 | Seal arrangement for a fan-turbine rotor assembly |
PCT/US2006/009997 WO2006121506A1 (en) | 2005-05-05 | 2006-03-16 | Seal arrangement for a fan rotor assembly of a tip tubine |
Publications (1)
Publication Number | Publication Date |
---|---|
DE602006014269D1 true DE602006014269D1 (de) | 2010-06-24 |
Family
ID=36731097
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE602006014269T Active DE602006014269D1 (de) | 2005-05-05 | 2006-03-16 | Dichtungsanordnung für eine gebläserotoranordnung einer spitzenturbine |
Country Status (4)
Country | Link |
---|---|
US (1) | US7201558B2 (de) |
EP (1) | EP1888905B1 (de) |
DE (1) | DE602006014269D1 (de) |
WO (1) | WO2006121506A1 (de) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8757959B2 (en) * | 2004-12-01 | 2014-06-24 | United Technologies Corporation | Tip turbine engine comprising a nonrotable compartment |
US20070022738A1 (en) * | 2005-07-27 | 2007-02-01 | United Technologies Corporation | Reinforcement rings for a tip turbine engine fan-turbine rotor assembly |
US7931436B2 (en) * | 2007-09-12 | 2011-04-26 | United Technologies Corp. | Roller bearings, and struts and gas turbine engines having such bearings |
US7955046B2 (en) * | 2007-09-25 | 2011-06-07 | United Technologies Corporation | Gas turbine engine front architecture modularity |
US8205432B2 (en) | 2007-10-03 | 2012-06-26 | United Technologies Corporation | Epicyclic gear train for turbo fan engine |
US10151248B2 (en) | 2007-10-03 | 2018-12-11 | United Technologies Corporation | Dual fan gas turbine engine and gear train |
US8016297B2 (en) * | 2008-03-27 | 2011-09-13 | United Technologies Corporation | Gas turbine engine seals and engines incorporating such seals |
US8961141B2 (en) | 2011-08-29 | 2015-02-24 | United Technologies Corporation | Axial retention system for a bladed rotor with multiple blade types |
US9004849B2 (en) * | 2012-01-10 | 2015-04-14 | United Technologies Corporation | Gas turbine engine forward bearing compartment architecture |
US9416677B2 (en) * | 2012-01-10 | 2016-08-16 | United Technologies Corporation | Gas turbine engine forward bearing compartment architecture |
US9145772B2 (en) | 2012-01-31 | 2015-09-29 | United Technologies Corporation | Compressor disk bleed air scallops |
US8365514B1 (en) | 2012-02-27 | 2013-02-05 | United Technologies Corporation | Hybrid turbofan engine |
US10030530B2 (en) * | 2014-07-31 | 2018-07-24 | United Technologies Corporation | Reversible blade rotor seal |
RU182026U1 (ru) * | 2017-12-18 | 2018-07-31 | Публичное Акционерное Общество "Одк-Сатурн" | Двухъярусная лопатка рабочего колеса турбины |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3269120A (en) * | 1964-07-16 | 1966-08-30 | Curtiss Wright Corp | Gas turbine engine with compressor and turbine passages in a single rotor element |
US3363419A (en) * | 1965-04-27 | 1968-01-16 | Rolls Royce | Gas turbine ducted fan engine |
US3572960A (en) * | 1969-01-02 | 1971-03-30 | Gen Electric | Reduction of sound in gas turbine engines |
GB1291943A (en) * | 1970-02-11 | 1972-10-04 | Secr Defence | Improvements in or relating to ducted fans |
US3801222A (en) * | 1972-02-28 | 1974-04-02 | United Aircraft Corp | Platform for compressor or fan blade |
US3836279A (en) * | 1973-02-23 | 1974-09-17 | United Aircraft Corp | Seal means for blade and shroud |
US4265595A (en) * | 1979-01-02 | 1981-05-05 | General Electric Company | Turbomachinery blade retaining assembly |
US5501575A (en) * | 1995-03-01 | 1996-03-26 | United Technologies Corporation | Fan blade attachment for gas turbine engine |
DE19644543A1 (de) | 1996-10-26 | 1998-04-30 | Asea Brown Boveri | Vorrichtung zur Dichtung des Strömungsüberganges eines Kühlmediums zwischen Rotor und Laufschaufel |
CA2484580A1 (en) | 2002-04-15 | 2004-10-28 | Marius A. Paul | Integrated bypass turbojet engines for aircraft and other vehicles |
-
2005
- 2005-05-05 US US11/122,368 patent/US7201558B2/en active Active
-
2006
- 2006-03-16 DE DE602006014269T patent/DE602006014269D1/de active Active
- 2006-03-16 WO PCT/US2006/009997 patent/WO2006121506A1/en active Application Filing
- 2006-03-16 EP EP06748463A patent/EP1888905B1/de not_active Not-in-force
Also Published As
Publication number | Publication date |
---|---|
US20060251508A1 (en) | 2006-11-09 |
EP1888905B1 (de) | 2010-05-12 |
EP1888905A1 (de) | 2008-02-20 |
WO2006121506A1 (en) | 2006-11-16 |
US7201558B2 (en) | 2007-04-10 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
8364 | No opposition during term of opposition |