RU2013101047A - GAS TURBINE (OPTIONS) - Google Patents
GAS TURBINE (OPTIONS) Download PDFInfo
- Publication number
- RU2013101047A RU2013101047A RU2013101047/06A RU2013101047A RU2013101047A RU 2013101047 A RU2013101047 A RU 2013101047A RU 2013101047/06 A RU2013101047/06 A RU 2013101047/06A RU 2013101047 A RU2013101047 A RU 2013101047A RU 2013101047 A RU2013101047 A RU 2013101047A
- Authority
- RU
- Russia
- Prior art keywords
- diffuser
- gas turbine
- wall
- external
- outlet
- Prior art date
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
-
- 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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/17—Purpose of the control system to control boundary layer
- F05D2270/172—Purpose of the control system to control boundary layer by a plasma generator, e.g. control of ignition
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Plasma Technology (AREA)
Abstract
1. Газовая турбина, содержащая:турбину, выпускающую выхлопной газ,выходной диффузор для приема выхлопного газа из турбины, имеющий впускное отверстие, выпускное отверстие и по меньшей мере одну стенку, расположенную между впускным и выпускным отверстиями, иплазменный актюатор, предназначенный для образования плазмы на указанной по меньшей мере одной стенке диффузора.2. Газовая турбина по п.1, в которой выходной диффузор содержит внутренний диффузор и внешний диффузор, причем внутренний диффузор в целом концентричен с внешним диффузором.3. Газовая турбина по п.2, в которой внутренний диффузор имеет внутреннюю стенку, на которой расположен плазменный актюатор.4. Газовая турбина по п.2, в которой внешний диффузор имеет внешнюю стенку, на которой расположен плазменный актюатор.5. Газовая турбина по п.2, в которой внутренний диффузор имеет в целом кольцевую конфигурацию.6. Газовая турбина по п.2, в которой внешний диффузор имеет в целом коническую конфигурацию.7. Газовая турбина по п.2, содержащая по меньшей мере один канал, расположенный между внутренним диффузором и внешним диффузором и имеющий внешнюю поверхность, на которой расположен другой плазменный актюатор.8. Газовая турбина по п.1, содержащая выходную стойку, расположенную между внутренней стенкой и внешней стенкой выходного диффузора и имеющую поперечное сечение в форме аэродинамического профиля.9. Газовая турбина по п.8, содержащая плазменный актюатор выходной стойки, расположенный на внешней поверхности выходной стойки.10. Газовая турбина по п.1, в которой плазменный актюатор содержит внутренний электрод, внешний электрод и диэлектрический материал.11. Газов1. A gas turbine comprising: a turbine that discharges exhaust gas, an outlet diffuser for receiving exhaust gas from the turbine, having an inlet, an outlet and at least one wall located between the inlet and outlet, and a plasma actuator for generating plasma on at least one wall of the diffuser. 2. The gas turbine of claim 1, wherein the outlet diffuser comprises an internal diffuser and an external diffuser, the internal diffuser being generally concentric with the external diffuser. The gas turbine of claim 2, wherein the inner diffuser has an inner wall on which the plasma actuator is located. The gas turbine of claim 2, wherein the outer diffuser has an outer wall on which the plasma actuator is located. The gas turbine of claim 2, wherein the internal diffuser has a generally annular configuration. The gas turbine of claim 2, wherein the outer diffuser has a generally conical configuration. A gas turbine according to claim 2, comprising at least one channel located between the inner diffuser and the outer diffuser and having an outer surface on which another plasma actuator is located. A gas turbine according to claim 1, comprising an outlet strut located between the inner wall and the outer wall of the outlet diffuser and having a cross-section in the form of an airfoil. A gas turbine according to claim 8, comprising an outlet strut plasma actuator located on an outer surface of the outlet strut. The gas turbine of claim 1, wherein the plasma actuator comprises an inner electrode, an outer electrode, and a dielectric material. Gases
Claims (16)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/349,299 | 2012-01-12 | ||
US13/349,299 US20130180245A1 (en) | 2012-01-12 | 2012-01-12 | Gas turbine exhaust diffuser having plasma actuator |
Publications (1)
Publication Number | Publication Date |
---|---|
RU2013101047A true RU2013101047A (en) | 2014-07-20 |
Family
ID=47678565
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2013101047/06A RU2013101047A (en) | 2012-01-12 | 2013-01-11 | GAS TURBINE (OPTIONS) |
Country Status (5)
Country | Link |
---|---|
US (1) | US20130180245A1 (en) |
EP (1) | EP2615252A1 (en) |
JP (1) | JP6291163B2 (en) |
CN (1) | CN103206272B (en) |
RU (1) | RU2013101047A (en) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140072401A1 (en) * | 2012-09-12 | 2014-03-13 | General Electric Company | Axial Diffuser Flow Control Device |
JP6632190B2 (en) * | 2014-03-25 | 2020-01-22 | キヤノン株式会社 | Liquid ejection device and liquid ejection method |
EP2963241B1 (en) * | 2014-06-30 | 2019-03-06 | Safran Aero Boosters SA | Guiding element for a turbomachine gas flow |
EP3072695B1 (en) | 2015-03-19 | 2020-01-15 | Canon Kabushiki Kaisha | Liquid ejecting apparatus |
WO2016167769A1 (en) * | 2015-04-16 | 2016-10-20 | Siemens Aktiengesellschaft | Exhaust diffuser strut apparatus |
DE102017117783A1 (en) * | 2017-08-04 | 2019-02-07 | Man Diesel & Turbo Se | Turbine inlet housing of an axial turbine of a turbocharger |
US10807703B2 (en) * | 2018-07-19 | 2020-10-20 | General Electric Company | Control system for an aircraft |
CN110805495B (en) * | 2019-12-05 | 2021-10-01 | 江西洪都航空工业集团有限责任公司 | Fixed-geometry wide-speed-range supersonic air inlet, working method thereof and aircraft |
WO2023056046A1 (en) * | 2021-10-01 | 2023-04-06 | Georgia Tech Research Corporation | Air-breathing plasma jet engine |
Family Cites Families (22)
Publication number | Priority date | Publication date | Assignee | Title |
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US3371491A (en) * | 1966-03-09 | 1968-03-05 | Aerojet General Co | Thrust direction modification means |
CH672004A5 (en) * | 1986-09-26 | 1989-10-13 | Bbc Brown Boveri & Cie | |
US5320309A (en) * | 1992-06-26 | 1994-06-14 | British Technology Group Usa, Inc. | Electromagnetic device and method for boundary layer control |
JP3070401B2 (en) * | 1994-08-23 | 2000-07-31 | 株式会社日立製作所 | Gas turbine exhaust structure |
US7669404B2 (en) * | 2004-09-01 | 2010-03-02 | The Ohio State University | Localized arc filament plasma actuators for noise mitigation and mixing enhancement |
US20080067283A1 (en) * | 2006-03-14 | 2008-03-20 | University Of Notre Dame Du Lac | Methods and apparatus for reducing noise via a plasma fairing |
US7870719B2 (en) * | 2006-10-13 | 2011-01-18 | General Electric Company | Plasma enhanced rapidly expanded gas turbine engine transition duct |
US7766599B2 (en) * | 2006-10-31 | 2010-08-03 | General Electric Company | Plasma lifted boundary layer gas turbine engine vane |
US7628585B2 (en) * | 2006-12-15 | 2009-12-08 | General Electric Company | Airfoil leading edge end wall vortex reducing plasma |
US20090169363A1 (en) * | 2007-12-28 | 2009-07-02 | Aspi Rustom Wadia | Plasma Enhanced Stator |
WO2009107438A1 (en) * | 2008-02-27 | 2009-09-03 | 三菱重工業株式会社 | Connection structure of exhaust chamber, support structure of turbine, and gas turbine |
US7717229B2 (en) * | 2008-05-09 | 2010-05-18 | Siemens Energy, Inc. | Gas turbine exhaust sound suppressor and associated methods |
US8006497B2 (en) * | 2008-05-30 | 2011-08-30 | Honeywell International Inc. | Diffusers, diffusion systems, and methods for controlling airflow through diffusion systems |
DE09803664T1 (en) * | 2008-07-31 | 2011-12-22 | Bell Helicopter Textron, Inc. | SYSTEM AND METHOD FOR AERODYNAMIC RIVER CONTROL |
US8146341B2 (en) * | 2008-09-22 | 2012-04-03 | General Electric Company | Integrated gas turbine exhaust diffuser and heat recovery steam generation system |
US7984614B2 (en) * | 2008-11-17 | 2011-07-26 | Honeywell International Inc. | Plasma flow controlled diffuser system |
JP5398405B2 (en) * | 2009-07-30 | 2014-01-29 | 三菱重工業株式会社 | Channel structure and gas turbine exhaust diffuser |
US8453457B2 (en) * | 2009-08-26 | 2013-06-04 | Lockheed Martin Corporation | Nozzle plasma flow control utilizing dielectric barrier discharge plasma actuators |
US8435001B2 (en) * | 2009-12-17 | 2013-05-07 | Siemens Energy, Inc. | Plasma induced flow control of boundary layer at airfoil endwall |
FR2959342B1 (en) * | 2010-04-27 | 2012-06-15 | Snecma | METHOD OF PROCESSING ACOUSTIC WAVES EMITTED AT A TURBOMOTOR OF AN AIRCRAFT WITH A DIELECTRIC BARRIER DISCHARGE DEVICE AND AN AIRCRAFT COMPRISING SUCH A DEVICE |
US8500404B2 (en) * | 2010-04-30 | 2013-08-06 | Siemens Energy, Inc. | Plasma actuator controlled film cooling |
JP2011231928A (en) * | 2011-04-27 | 2011-11-17 | Toshiba Corp | Diffuser |
-
2012
- 2012-01-12 US US13/349,299 patent/US20130180245A1/en not_active Abandoned
-
2013
- 2013-01-07 EP EP13150408.6A patent/EP2615252A1/en not_active Withdrawn
- 2013-01-09 JP JP2013001448A patent/JP6291163B2/en not_active Expired - Fee Related
- 2013-01-11 CN CN201310010097.XA patent/CN103206272B/en not_active Expired - Fee Related
- 2013-01-11 RU RU2013101047/06A patent/RU2013101047A/en not_active Application Discontinuation
Also Published As
Publication number | Publication date |
---|---|
CN103206272A (en) | 2013-07-17 |
JP6291163B2 (en) | 2018-03-14 |
US20130180245A1 (en) | 2013-07-18 |
CN103206272B (en) | 2017-03-01 |
JP2013142403A (en) | 2013-07-22 |
EP2615252A1 (en) | 2013-07-17 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
FA92 | Acknowledgement of application withdrawn (lack of supplementary materials submitted) |
Effective date: 20170621 |