ITTO20020699A0 - Paletta per lo statore di una turbina a geometria variabile, particolarmente per motori aeronautici - Google Patents
Paletta per lo statore di una turbina a geometria variabile, particolarmente per motori aeronauticiInfo
- Publication number
- ITTO20020699A0 ITTO20020699A0 IT2002TO000699A ITTO20020699A ITTO20020699A0 IT TO20020699 A0 ITTO20020699 A0 IT TO20020699A0 IT 2002TO000699 A IT2002TO000699 A IT 2002TO000699A IT TO20020699 A ITTO20020699 A IT TO20020699A IT TO20020699 A0 ITTO20020699 A0 IT TO20020699A0
- Authority
- IT
- Italy
- Prior art keywords
- stator
- turbine
- blade
- variable geometry
- aircraft engines
- Prior art date
Links
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 title 1
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
- 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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
-
- 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
-
- 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
- F01D5/186—Film cooling
-
- 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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- 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)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IT000699A ITTO20020699A1 (it) | 2002-08-06 | 2002-08-06 | Paletta per lo statore di una turbina a geometria variabile, |
DE60308963T DE60308963T2 (de) | 2002-08-06 | 2003-08-05 | Statorschaufel einer Turbine mit variabler Geometrie, insbesondere für Flugzeugtriebwerke |
US10/604,620 US6913440B2 (en) | 2002-08-06 | 2003-08-05 | Variable-geometry turbine stator blade, particularly for aircraft engines |
EP03017855A EP1388642B1 (en) | 2002-08-06 | 2003-08-05 | Variable-geometry turbine stator blade, particularly for aircraft engines |
AT03017855T ATE342429T1 (de) | 2002-08-06 | 2003-08-05 | Statorschaufel einer turbine mit variabler geometrie, insbesondere für flugzeugtriebwerke |
CA2436638A CA2436638C (en) | 2002-08-06 | 2003-08-05 | Variable-geometry turbine stator blade, particularly for aircraft engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IT000699A ITTO20020699A1 (it) | 2002-08-06 | 2002-08-06 | Paletta per lo statore di una turbina a geometria variabile, |
Publications (2)
Publication Number | Publication Date |
---|---|
ITTO20020699A0 true ITTO20020699A0 (it) | 2002-08-06 |
ITTO20020699A1 ITTO20020699A1 (it) | 2004-02-07 |
Family
ID=11459561
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
IT000699A ITTO20020699A1 (it) | 2002-08-06 | 2002-08-06 | Paletta per lo statore di una turbina a geometria variabile, |
Country Status (6)
Country | Link |
---|---|
US (1) | US6913440B2 (it) |
EP (1) | EP1388642B1 (it) |
AT (1) | ATE342429T1 (it) |
CA (1) | CA2436638C (it) |
DE (1) | DE60308963T2 (it) |
IT (1) | ITTO20020699A1 (it) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101514711A (zh) * | 2008-02-22 | 2009-08-26 | 赵明慧 | 涡轮叶片和涡轮机 |
US8778487B2 (en) * | 2008-10-16 | 2014-07-15 | Rolls-Royce Corporation | Tape |
US20100098896A1 (en) * | 2008-10-16 | 2010-04-22 | Edward Claude Rice | Patch |
US8202056B2 (en) * | 2008-10-16 | 2012-06-19 | Rolls-Royce Corporation | Morphable composite structure |
US8382436B2 (en) | 2009-01-06 | 2013-02-26 | General Electric Company | Non-integral turbine blade platforms and systems |
US20100180599A1 (en) * | 2009-01-21 | 2010-07-22 | Thomas Stephen R | Insertable Pre-Drilled Swirl Vane for Premixing Fuel Nozzle |
US8262345B2 (en) * | 2009-02-06 | 2012-09-11 | General Electric Company | Ceramic matrix composite turbine engine |
US20120070302A1 (en) * | 2010-09-20 | 2012-03-22 | Ching-Pang Lee | Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles |
US9347324B2 (en) * | 2010-09-20 | 2016-05-24 | Siemens Aktiengesellschaft | Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles |
US20120067054A1 (en) | 2010-09-21 | 2012-03-22 | Palmer Labs, Llc | High efficiency power production methods, assemblies, and systems |
US8668445B2 (en) | 2010-10-15 | 2014-03-11 | General Electric Company | Variable turbine nozzle system |
WO2014200831A1 (en) | 2013-06-14 | 2014-12-18 | United Technologies Corporation | Variable area gas turbine engine component having movable spar and shell |
WO2015108606A2 (en) | 2013-11-25 | 2015-07-23 | United Technologies Corporation | A method for providing coolant to a movable airfoil |
US10907497B2 (en) | 2018-12-13 | 2021-02-02 | Transportation Ip Holdings, Llc | Method and systems for a variable geometry turbocharger for an engine |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3066910A (en) * | 1958-07-09 | 1962-12-04 | Thompson Ramo Wooldridge Inc | Cooled turbine blade |
US3164367A (en) * | 1962-11-21 | 1965-01-05 | Gen Electric | Gas turbine blade |
US4169692A (en) * | 1974-12-13 | 1979-10-02 | General Electric Company | Variable area turbine nozzle and means for sealing same |
US4193738A (en) * | 1977-09-19 | 1980-03-18 | General Electric Company | Floating seal for a variable area turbine nozzle |
DE2810240C2 (de) * | 1978-03-09 | 1985-09-26 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Verstelleitgitter für axial durchströmte Turbinen, insbesondere Hochdruckturbinen von Gasturbinentriebwerken |
US4214852A (en) * | 1978-04-20 | 1980-07-29 | General Electric Company | Variable turbine vane assembly |
DE2834822C2 (de) * | 1978-08-09 | 1981-09-17 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Einrichtung zur Verdichterluftentnahme bei Gasturbinentriebwerken |
JPS55117009A (en) * | 1979-02-28 | 1980-09-09 | Toshiba Corp | Gas-turbine blade |
GB2051964B (en) * | 1979-06-30 | 1983-01-12 | Rolls Royce | Turbine blade |
US4798515A (en) * | 1986-05-19 | 1989-01-17 | The United States Of America As Represented By The Secretary Of The Air Force | Variable nozzle area turbine vane cooling |
US6478535B1 (en) * | 2001-05-04 | 2002-11-12 | Honeywell International, Inc. | Thin wall cooling system |
ITTO20010445A1 (it) * | 2001-05-11 | 2002-11-11 | Fiatavio Spa | Statore di una turbina assiale a geometria variabile per applicazioniaeronautiche. |
ITTO20010446A1 (it) * | 2001-05-11 | 2002-11-11 | Fiatavio Spa | Paletta per uno statore di una turbina a geometria variabile, in particolare per motori aeronautici. |
ITTO20010704A1 (it) * | 2001-07-18 | 2003-01-18 | Fiatavio Spa | Paletta a doppia parete per una turbina, particolarmente per applicazioni aeronautiche. |
ITTO20020607A1 (it) * | 2002-07-12 | 2004-01-12 | Fiatavio Spa | Metodo per la realizzazione ed il montaggio di un dispositivo di raffreddamento in una paletta di una turbina assiale a gas e paletta per un |
ITTO20020624A1 (it) * | 2002-07-16 | 2004-01-16 | Fiatavio Spa | Dispositivo di incernieramento di un organo rotante in un motore aeronautico |
-
2002
- 2002-08-06 IT IT000699A patent/ITTO20020699A1/it unknown
-
2003
- 2003-08-05 CA CA2436638A patent/CA2436638C/en not_active Expired - Fee Related
- 2003-08-05 EP EP03017855A patent/EP1388642B1/en not_active Expired - Lifetime
- 2003-08-05 AT AT03017855T patent/ATE342429T1/de not_active IP Right Cessation
- 2003-08-05 US US10/604,620 patent/US6913440B2/en not_active Expired - Lifetime
- 2003-08-05 DE DE60308963T patent/DE60308963T2/de not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
DE60308963D1 (de) | 2006-11-23 |
EP1388642A2 (en) | 2004-02-11 |
CA2436638C (en) | 2011-08-02 |
EP1388642A3 (en) | 2004-10-06 |
ITTO20020699A1 (it) | 2004-02-07 |
ATE342429T1 (de) | 2006-11-15 |
EP1388642B1 (en) | 2006-10-11 |
CA2436638A1 (en) | 2004-02-06 |
DE60308963T2 (de) | 2007-04-05 |
US20040096321A1 (en) | 2004-05-20 |
US6913440B2 (en) | 2005-07-05 |
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