RU2003101666A - DIFFUSER OF A GROUND OR AIRCRAFT GAS TURBINE ENGINE - Google Patents

DIFFUSER OF A GROUND OR AIRCRAFT GAS TURBINE ENGINE

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Publication number
RU2003101666A
RU2003101666A RU2003101666/06A RU2003101666A RU2003101666A RU 2003101666 A RU2003101666 A RU 2003101666A RU 2003101666/06 A RU2003101666/06 A RU 2003101666/06A RU 2003101666 A RU2003101666 A RU 2003101666A RU 2003101666 A RU2003101666 A RU 2003101666A
Authority
RU
Russia
Prior art keywords
fluid
diffuser according
annular
openings
diffuser
Prior art date
Application number
RU2003101666/06A
Other languages
Russian (ru)
Other versions
RU2318122C2 (en
Inventor
Клод НОТТЕН
Original Assignee
Снекма Моторс
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from FR0200764A external-priority patent/FR2835019B1/en
Application filed by Снекма Моторс filed Critical Снекма Моторс
Publication of RU2003101666A publication Critical patent/RU2003101666A/en
Application granted granted Critical
Publication of RU2318122C2 publication Critical patent/RU2318122C2/en

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Claims (10)

1. Диффузор (10) газотурбинного двигателя, расположенный между последней ступенью турбины и выходным устройством и содержащий наружную кольцевую стенку (16а) и внутреннюю кольцевую стенку (16b), образующие кольцевой проход (18) для текучей среды, расширяющийся в направлении (F) истечения этой текучей среды, отличающийся тем, что, по меньшей мере, одна из кольцевых стенок (16а, 16b) содержит несколько отверстий (20), открытых в указанный кольцевой проход и выходящих, по меньшей мере, в одну коллекторную камеру (22), сопряженную со средствами вывода части указанной текучей среды, для снижения скорости движения указанной текучей среды в указанном кольцевом проходе.1. The diffuser (10) of the gas turbine engine, located between the last stage of the turbine and the output device and containing the outer annular wall (16a) and the inner annular wall (16b), forming an annular passage (18) for the fluid, expanding in the direction (F) of the outflow this fluid, characterized in that at least one of the annular walls (16A, 16b) contains several holes (20) open in the specified annular passage and leaving at least one collector chamber (22), paired with means of output part uk azan fluid, to reduce the speed of movement of the specified fluid in the specified annular passage. 2. Диффузор по п.1, отличающийся тем, что указанные несколько отверстий (20) выходят в единственную кольцевую коллекторную камеру (22) для сбора подлежащей выводу части текучей среды.2. A diffuser according to claim 1, characterized in that said several openings (20) exit into a single annular collector chamber (22) to collect a portion of the fluid to be withdrawn. 3. Диффузор по п.1 или 2, отличающийся тем, что, по меньшей мере, одна коллекторная камера (22) связана, по меньшей мере, с одним каналом (24) вывода текучей среды.3. The diffuser according to claim 1 or 2, characterized in that at least one collector chamber (22) is connected to at least one channel (24) of the fluid outlet. 4. Диффузор по п.3, отличающийся тем, что указанный, по меньшей мере, один канал (24) вывода текучей среды проходит в обход секций (14, 30) выходного устройства, сообщающихся с указанным кольцевым проходом (18), формирующим горячий поток газотурбинного двигателя, и со вторым кольцевым проходом (28), формирующим холодный поток и коаксиальным указанному кольцевому проходу (18).4. A diffuser according to claim 3, characterized in that said at least one fluid output channel (24) passes around sections (14, 30) of the output device in communication with said annular passage (18) forming a hot stream a gas turbine engine, and with a second annular passage (28) forming a cold flow and coaxial to said annular passage (18). 5. Диффузор по любому из пп.1-4, отличающийся тем, что дополнительно содержит всасывающие средства (26) для отбора подлежащей выводу части текучей среды.5. A diffuser according to any one of claims 1 to 4, characterized in that it further comprises suction means (26) for selecting a portion of the fluid to be withdrawn. 6. Диффузор по любому из пп.1-5, отличающийся тем, что указанные отверстия (20) выполнены в виде каналов, по существу перпендикулярных указанной кольцевой стенке.6. A diffuser according to any one of claims 1 to 5, characterized in that said openings (20) are made in the form of channels essentially perpendicular to said annular wall. 7. Диффузор по любому из пп.1-5, отличающийся тем, что указанные отверстия (20) выполнены в виде каналов, по существу наклонных относительно указанной кольцевой стенки по направлению (F) истечения текучей среды.7. A diffuser according to any one of claims 1 to 5, characterized in that said openings (20) are made in the form of channels essentially inclined relative to said annular wall in the direction (F) of the fluid flow. 8. Диффузор по любому из пп.1-5, отличающийся тем, что указанные отверстия (20) выполнены в виде круговых или дуговых щелей, по существу перпендикулярных указанной кольцевой стенке.8. A diffuser according to any one of claims 1 to 5, characterized in that said openings (20) are made in the form of circular or arc slots substantially perpendicular to said annular wall. 9. Диффузор по любому из пп.1-5, отличающийся тем, что указанные отверстия (20) выполнены в виде круговых или дуговых щелей, по существу наклонных относительно указанной кольцевой стенки по направлению (F) истечения текучей среды.9. A diffuser according to any one of claims 1 to 5, characterized in that said openings (20) are made in the form of circular or arc slots substantially inclined relative to said annular wall in the direction (F) of the fluid flow. 10. Диффузор по п.8 или 9, отличающийся тем, что указанные отверстия (20) выполнены в виде щелей со скошенной кромкой для более эффективной подачи подлежащей выводу части текучей среды к указанным средствам вывода.10. A diffuser according to claim 8 or 9, characterized in that said openings (20) are made in the form of slots with a beveled edge to more efficiently supply a portion of the fluid to be withdrawn to said withdrawal means.
RU2003101666/06A 2002-01-22 2003-01-22 Diffuser for gas turbine engine RU2318122C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0200764 2002-01-22
FR0200764A FR2835019B1 (en) 2002-01-22 2002-01-22 DIFFUSER FOR A LAND OR AERONAUTICAL GAS TURBINE ENGINE

Publications (2)

Publication Number Publication Date
RU2003101666A true RU2003101666A (en) 2004-08-10
RU2318122C2 RU2318122C2 (en) 2008-02-27

Family

ID=8871375

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2003101666/06A RU2318122C2 (en) 2002-01-22 2003-01-22 Diffuser for gas turbine engine

Country Status (6)

Country Link
US (1) US6973771B2 (en)
EP (1) EP1329595A1 (en)
JP (1) JP4035059B2 (en)
CA (1) CA2416150C (en)
FR (1) FR2835019B1 (en)
RU (1) RU2318122C2 (en)

Families Citing this family (32)

* Cited by examiner, † Cited by third party
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
US20100290906A1 (en) * 2007-12-28 2010-11-18 Moeckel Curtis W Plasma sensor stall control system and turbomachinery diagnostics
US8317457B2 (en) 2007-12-28 2012-11-27 General Electric Company Method of operating a compressor
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
US8282336B2 (en) 2007-12-28 2012-10-09 General Electric Company Instability mitigation system
US20100047055A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Rotor
US20090169363A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Stator
US8282337B2 (en) 2007-12-28 2012-10-09 General Electric Company Instability mitigation system using stator plasma actuators
US20100205928A1 (en) * 2007-12-28 2010-08-19 Moeckel Curtis W Rotor stall sensor system
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
US20100172747A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced compressor duct
US20100170224A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced booster and method of operation
US8337153B2 (en) * 2009-06-02 2012-12-25 Siemens Energy, Inc. Turbine exhaust diffuser flow path with region of reduced total flow area
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
JP5901131B2 (en) * 2011-03-30 2016-04-06 三菱重工業株式会社 Diffuser
RU2484264C2 (en) * 2011-05-05 2013-06-10 Юрий Игоревич Гладков Continuous transient channel between high-pressure turbine and low-pressure turbine of double-flow aircraft engine
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 (en) * 2013-03-19 2017-04-26 三菱重工業株式会社 Rotating machine diffuser and rotating machine
US9322553B2 (en) 2013-05-08 2016-04-26 General Electric Company Wake manipulating structure for a turbine system
US9739201B2 (en) 2013-05-08 2017-08-22 General Electric Company Wake reducing structure for a turbine system and method of reducing wake
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)

* Cited by examiner, † Cited by third party
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 (en) * 1950-07-01 1952-04-15 Maschf Augsburg Nuernberg Ag Axially loaded impeller flow machine, in particular gas or air turbine with outlet diffuser
DE1054791B (en) * 1954-11-11 1959-04-09 Licentia Gmbh Boundary layer suction device for walls flowed by condensable steam
GB1573926A (en) * 1976-03-24 1980-08-28 Rolls Royce Fluid flow diffuser
RO82608A (en) * 1981-01-08 1983-09-26 Societe Anonyme Dite Alsthom-Atlantique,Fr PARIETAL WASHER DIFFUSER
DE76668T1 (en) * 1981-10-06 1983-12-22 Aktieselskabet Kongsberg Vaapenfabrikk, Kongsberg METHOD FOR DERIVING A LIQUID IN A TURBO MACHINE AND TURBO MACHINES WITH SUCH A DEVICE.
US4515524A (en) * 1982-09-27 1985-05-07 Allis-Chalmers Corporation Draft tube for hydraulic turbine
JPS62174507A (en) * 1986-01-27 1987-07-31 Toshiba Corp Exhaust diffuser for axial flow turbo machine
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

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