DE602004031679D1 - Regenerative Kühlung einer Leit- und Laufschaufel für ein Tipturbinentriebwerk - Google Patents
Regenerative Kühlung einer Leit- und Laufschaufel für ein TipturbinentriebwerkInfo
- Publication number
- DE602004031679D1 DE602004031679D1 DE602004031679T DE602004031679T DE602004031679D1 DE 602004031679 D1 DE602004031679 D1 DE 602004031679D1 DE 602004031679 T DE602004031679 T DE 602004031679T DE 602004031679 T DE602004031679 T DE 602004031679T DE 602004031679 D1 DE602004031679 D1 DE 602004031679D1
- Authority
- DE
- Germany
- Prior art keywords
- tipturbine
- blade
- engine
- guide
- regenerative cooling
- 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
- 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
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
-
- 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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
-
- 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 (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/US2004/040096 WO2006059990A1 (en) | 2004-12-01 | 2004-12-01 | Regenerative turbine blade and vane cooling for a tip turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE602004031679D1 true DE602004031679D1 (de) | 2011-04-14 |
Family
ID=35502539
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DE602004031679T Active DE602004031679D1 (de) | 2004-12-01 | 2004-12-01 | Regenerative Kühlung einer Leit- und Laufschaufel für ein Tipturbinentriebwerk |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US7607286B2 (de) |
| EP (1) | EP1825128B1 (de) |
| DE (1) | DE602004031679D1 (de) |
| WO (1) | WO2006059990A1 (de) |
Families Citing this family (33)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1825116A2 (de) * | 2004-12-01 | 2007-08-29 | United Technologies Corporation | Ejektor-kühlung des aussengehäuses eines tip-turbinen-triebwerks |
| EP1828591B1 (de) | 2004-12-01 | 2010-07-21 | United Technologies Corporation | Umfangsbrennkammer für spitzenturbinenmotor |
| WO2006060004A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Combustor for turbine engine |
| US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
| WO2006060012A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine comprising turbine blade clusters and method of assembly |
| US8152469B2 (en) | 2004-12-01 | 2012-04-10 | United Technologies Corporation | Annular turbine ring rotor |
| EP1834076B1 (de) | 2004-12-01 | 2011-04-06 | United Technologies Corporation | Turbinenschaufelgruppe eines Fanrotors sowie Verfahren zur Montage einer solchen Gruppe |
| WO2006059970A2 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
| US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
| US7937927B2 (en) | 2004-12-01 | 2011-05-10 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| WO2006060001A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Fan rotor assembly for a tip turbine engine |
| WO2006059980A2 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Diffuser aspiration for a tip turbine engine |
| DE602004019710D1 (de) | 2004-12-01 | 2009-04-09 | United Technologies Corp | Fernbetätigung für eine verstellbare stufe eines verdichters für einen turbinenmotor |
| US7854112B2 (en) | 2004-12-01 | 2010-12-21 | United Technologies Corporation | Vectoring transition duct for turbine engine |
| US8096753B2 (en) | 2004-12-01 | 2012-01-17 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
| US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
| EP1819907A2 (de) | 2004-12-01 | 2007-08-22 | United Technologies Corporation | Fanschaufel mit integralem diffusorabschnitt und spitzenturbinenschaufelabschnitt für einen spitzenturbinenmotor |
| US8807936B2 (en) | 2004-12-01 | 2014-08-19 | United Technologies Corporation | Balanced turbine rotor fan blade for a tip turbine engine |
| US7721525B2 (en) * | 2006-07-19 | 2010-05-25 | Rohr, Inc. | Aircraft engine inlet having zone of deformation |
| JP4305518B2 (ja) * | 2007-02-06 | 2009-07-29 | トヨタ自動車株式会社 | チップタービン駆動ファン |
| US8162615B2 (en) * | 2009-03-17 | 2012-04-24 | United Technologies Corporation | Split disk assembly for a gas turbine engine |
| JP5834876B2 (ja) * | 2011-12-15 | 2015-12-24 | 株式会社Ihi | インピンジ冷却機構、タービン翼及び燃焼器 |
| JP5927893B2 (ja) * | 2011-12-15 | 2016-06-01 | 株式会社Ihi | インピンジ冷却機構、タービン翼及び燃焼器 |
| US8365514B1 (en) | 2012-02-27 | 2013-02-05 | United Technologies Corporation | Hybrid turbofan engine |
| WO2014134519A1 (en) * | 2013-02-28 | 2014-09-04 | United Technologies Corporation | Method and apparatus for collecting pre-diffuser airflow and routing it to combustor pre-swirlers |
| EP2949871B1 (de) * | 2014-05-07 | 2017-03-01 | United Technologies Corporation | Variables leitschaufelsegment |
| US10808612B2 (en) | 2015-05-29 | 2020-10-20 | Raytheon Technologies Corporation | Retaining tab for diffuser seal ring |
| US10590786B2 (en) * | 2016-05-03 | 2020-03-17 | General Electric Company | System and method for cooling components of a gas turbine engine |
| US10876407B2 (en) * | 2017-02-16 | 2020-12-29 | General Electric Company | Thermal structure for outer diameter mounted turbine blades |
| US11001389B2 (en) | 2018-11-29 | 2021-05-11 | General Electric Company | Propulsion engine thermal management system |
| US11359503B2 (en) | 2019-10-04 | 2022-06-14 | Aytheon Technologies Corporation | Engine with cooling passage circuit extending through blade, seal, and ceramic vane |
| US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
| US11549463B2 (en) * | 2021-02-22 | 2023-01-10 | General Electric Company | Compact low-pressure compressor |
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-
2004
- 2004-12-01 EP EP04822155A patent/EP1825128B1/de not_active Expired - Fee Related
- 2004-12-01 DE DE602004031679T patent/DE602004031679D1/de active Active
- 2004-12-01 US US11/719,956 patent/US7607286B2/en not_active Expired - Fee Related
- 2004-12-01 WO PCT/US2004/040096 patent/WO2006059990A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| EP1825128B1 (de) | 2011-03-02 |
| EP1825128A1 (de) | 2007-08-29 |
| WO2006059990A1 (en) | 2006-06-08 |
| US7607286B2 (en) | 2009-10-27 |
| US20070295011A1 (en) | 2007-12-27 |
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