FR2835019B1 - Diffuseur pour moteur a turbine a gaz terrestre ou aeronautique - Google Patents
Diffuseur pour moteur a turbine a gaz terrestre ou aeronautiqueInfo
- Publication number
- FR2835019B1 FR2835019B1 FR0200764A FR0200764A FR2835019B1 FR 2835019 B1 FR2835019 B1 FR 2835019B1 FR 0200764 A FR0200764 A FR 0200764A FR 0200764 A FR0200764 A FR 0200764A FR 2835019 B1 FR2835019 B1 FR 2835019B1
- Authority
- FR
- France
- Prior art keywords
- diffuser
- land
- gas turbine
- turbine engine
- aeronautical gas
- 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 - Lifetime
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0200764A FR2835019B1 (fr) | 2002-01-22 | 2002-01-22 | Diffuseur pour moteur a turbine a gaz terrestre ou aeronautique |
EP03290045A EP1329595A1 (fr) | 2002-01-22 | 2003-01-09 | Diffuseur pour moteur à turbine à gaz terrestre ou aèronautique |
CA2416150A CA2416150C (fr) | 2002-01-22 | 2003-01-15 | Diffuseur pour moteur a turbine a gaz terrestre ou aeronautique |
US10/347,446 US6973771B2 (en) | 2002-01-22 | 2003-01-21 | Diffuser for terrestrial or aviation gas turbine |
JP2003011886A JP4035059B2 (ja) | 2002-01-22 | 2003-01-21 | 地上又は航空ガスタービン用ディフューザ |
RU2003101666/06A RU2318122C2 (ru) | 2002-01-22 | 2003-01-22 | Диффузор наземного или авиационного газотурбинного двигателя |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0200764A FR2835019B1 (fr) | 2002-01-22 | 2002-01-22 | Diffuseur pour moteur a turbine a gaz terrestre ou aeronautique |
Publications (2)
Publication Number | Publication Date |
---|---|
FR2835019A1 FR2835019A1 (fr) | 2003-07-25 |
FR2835019B1 true FR2835019B1 (fr) | 2004-12-31 |
Family
ID=8871375
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR0200764A Expired - Lifetime FR2835019B1 (fr) | 2002-01-22 | 2002-01-22 | Diffuseur pour moteur a turbine a gaz terrestre ou aeronautique |
Country Status (6)
Country | Link |
---|---|
US (1) | US6973771B2 (fr) |
EP (1) | EP1329595A1 (fr) |
JP (1) | JP4035059B2 (fr) |
CA (1) | CA2416150C (fr) |
FR (1) | FR2835019B1 (fr) |
RU (1) | RU2318122C2 (fr) |
Families Citing this family (32)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7353647B2 (en) * | 2004-05-13 | 2008-04-08 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
US7137245B2 (en) * | 2004-06-18 | 2006-11-21 | General Electric Company | High area-ratio inter-turbine duct with inlet blowing |
US7980055B2 (en) * | 2005-08-04 | 2011-07-19 | Rolls-Royce Corporation | Gas turbine exhaust diffuser |
US7870719B2 (en) * | 2006-10-13 | 2011-01-18 | General Electric Company | Plasma enhanced rapidly expanded gas turbine engine transition duct |
US20090169356A1 (en) * | 2007-12-28 | 2009-07-02 | Aspi Rustom Wadia | Plasma Enhanced Compression System |
US20090169363A1 (en) * | 2007-12-28 | 2009-07-02 | Aspi Rustom Wadia | Plasma Enhanced Stator |
US20100205928A1 (en) * | 2007-12-28 | 2010-08-19 | Moeckel Curtis W | Rotor stall sensor system |
US20100290906A1 (en) * | 2007-12-28 | 2010-11-18 | Moeckel Curtis W | Plasma sensor stall control system and turbomachinery diagnostics |
US8282336B2 (en) | 2007-12-28 | 2012-10-09 | General Electric Company | Instability mitigation system |
US8282337B2 (en) | 2007-12-28 | 2012-10-09 | General Electric Company | Instability mitigation system using stator plasma actuators |
US8317457B2 (en) | 2007-12-28 | 2012-11-27 | General Electric Company | Method of operating a compressor |
US20100047055A1 (en) * | 2007-12-28 | 2010-02-25 | Aspi Rustom Wadia | Plasma Enhanced Rotor |
US20100284785A1 (en) * | 2007-12-28 | 2010-11-11 | Aspi Rustom Wadia | Fan Stall Detection System |
US8348592B2 (en) | 2007-12-28 | 2013-01-08 | General Electric Company | Instability mitigation system using rotor plasma actuators |
US8313286B2 (en) | 2008-07-28 | 2012-11-20 | Siemens Energy, Inc. | Diffuser apparatus in a turbomachine |
US8061980B2 (en) * | 2008-08-18 | 2011-11-22 | United Technologies Corporation | Separation-resistant inlet duct for mid-turbine frames |
US20100170224A1 (en) * | 2009-01-08 | 2010-07-08 | General Electric Company | Plasma enhanced booster and method of operation |
US20100172747A1 (en) * | 2009-01-08 | 2010-07-08 | General Electric Company | Plasma enhanced compressor duct |
US8647057B2 (en) * | 2009-06-02 | 2014-02-11 | Siemens Energy, Inc. | Turbine exhaust diffuser with a gas jet producing a coanda effect flow control |
US8668449B2 (en) * | 2009-06-02 | 2014-03-11 | Siemens Energy, Inc. | Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow |
US8337153B2 (en) * | 2009-06-02 | 2012-12-25 | Siemens Energy, Inc. | Turbine exhaust diffuser flow path with region of reduced total flow area |
JP5901131B2 (ja) * | 2011-03-30 | 2016-04-06 | 三菱重工業株式会社 | ディフューザ |
RU2484264C2 (ru) * | 2011-05-05 | 2013-06-10 | Юрий Игоревич Гладков | Безотрывный переходный канал между турбиной высокого давления и турбиной низкого давления двухконтурного авиационного двигателя |
US20130091865A1 (en) * | 2011-10-17 | 2013-04-18 | General Electric Company | Exhaust gas diffuser |
US9267687B2 (en) | 2011-11-04 | 2016-02-23 | General Electric Company | Combustion system having a venturi for reducing wakes in an airflow |
US20130149107A1 (en) * | 2011-12-08 | 2013-06-13 | Mrinal Munshi | Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow |
GB201217944D0 (en) | 2012-10-08 | 2012-11-21 | Rolls Royce Plc | An exhaust arrangement |
JP6122671B2 (ja) * | 2013-03-19 | 2017-04-26 | 三菱重工業株式会社 | 回転機械のディフューザ、及び、回転機械 |
US9739201B2 (en) | 2013-05-08 | 2017-08-22 | General Electric Company | Wake reducing structure for a turbine system and method of reducing wake |
US9322553B2 (en) | 2013-05-08 | 2016-04-26 | General Electric Company | Wake manipulating structure for a turbine system |
US9435221B2 (en) | 2013-08-09 | 2016-09-06 | General Electric Company | Turbomachine airfoil positioning |
US9598981B2 (en) * | 2013-11-22 | 2017-03-21 | Siemens Energy, Inc. | Industrial gas turbine exhaust system diffuser inlet lip |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2594042A (en) | 1947-05-21 | 1952-04-22 | United Aircraft Corp | Boundary layer energizing means for annular diffusers |
DE834474C (de) * | 1950-07-01 | 1952-04-15 | Maschf Augsburg Nuernberg Ag | Axial beaufschlagte Kreiselrad-Stroemungsmaschine, insbesondere Gas- oder Luftturbine mit Austrittsdiffusor |
DE1054791B (de) * | 1954-11-11 | 1959-04-09 | Licentia Gmbh | Grenzschichtabsaugungseinrichtung fuer von einem kondensierbaren Dampf bestroemte Waende |
GB1573926A (en) * | 1976-03-24 | 1980-08-28 | Rolls Royce | Fluid flow diffuser |
RO82608A (fr) * | 1981-01-08 | 1983-09-26 | Societe Anonyme Dite Alsthom-Atlantique,Fr | Diffuseur avec aspiration parietale |
DE3272914D1 (en) * | 1981-10-06 | 1986-10-02 | Kongsberg Vapenfab As | Turbo-machines with bleed-off means |
US4515524A (en) * | 1982-09-27 | 1985-05-07 | Allis-Chalmers Corporation | Draft tube for hydraulic turbine |
JPS62174507A (ja) * | 1986-01-27 | 1987-07-31 | Toshiba Corp | 軸流タ−ボ機械の排気デイフユ−ザ |
US5467591A (en) * | 1993-12-30 | 1995-11-21 | Combustion Engineering, Inc. | Gas turbine combined cycle system |
US5590520A (en) * | 1995-05-05 | 1997-01-07 | The Regents Of The University Of California | Method of eliminating mach waves from supersonic jets |
US6574965B1 (en) * | 1998-12-23 | 2003-06-10 | United Technologies Corporation | Rotor tip bleed in gas turbine engines |
-
2002
- 2002-01-22 FR FR0200764A patent/FR2835019B1/fr not_active Expired - Lifetime
-
2003
- 2003-01-09 EP EP03290045A patent/EP1329595A1/fr not_active Withdrawn
- 2003-01-15 CA CA2416150A patent/CA2416150C/fr not_active Expired - Fee Related
- 2003-01-21 JP JP2003011886A patent/JP4035059B2/ja not_active Expired - Fee Related
- 2003-01-21 US US10/347,446 patent/US6973771B2/en not_active Expired - Fee Related
- 2003-01-22 RU RU2003101666/06A patent/RU2318122C2/ru not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
EP1329595A1 (fr) | 2003-07-23 |
CA2416150C (fr) | 2011-01-11 |
JP2003214117A (ja) | 2003-07-30 |
FR2835019A1 (fr) | 2003-07-25 |
RU2318122C2 (ru) | 2008-02-27 |
JP4035059B2 (ja) | 2008-01-16 |
US20030136102A1 (en) | 2003-07-24 |
CA2416150A1 (fr) | 2003-07-22 |
US6973771B2 (en) | 2005-12-13 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
CD | Change of name or company name | ||
PLFP | Fee payment |
Year of fee payment: 15 |
|
PLFP | Fee payment |
Year of fee payment: 16 |
|
PLFP | Fee payment |
Year of fee payment: 17 |
|
CD | Change of name or company name |
Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
|
PLFP | Fee payment |
Year of fee payment: 19 |
|
PLFP | Fee payment |
Year of fee payment: 20 |