EP2615252A1 - Gas turbine - Google Patents
Gas turbine Download PDFInfo
- Publication number
- EP2615252A1 EP2615252A1 EP13150408.6A EP13150408A EP2615252A1 EP 2615252 A1 EP2615252 A1 EP 2615252A1 EP 13150408 A EP13150408 A EP 13150408A EP 2615252 A1 EP2615252 A1 EP 2615252A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- diffuser
- exhaust
- wall
- gas turbine
- turbine
- 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.)
- Withdrawn
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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
Definitions
- the subject matter disclosed herein relates to a gas turbine, and more specifically to a gas turbine exhaust diffuser having a plasma actuator for producing a plasma.
- Gas turbines generally include a compressor, a combustor, one or more fuel nozzles, a turbine and an exhaust diffuser. Air enters the gas turbine through an air intake and is compressed by the compressor. The compressed air is then mixed with fuel supplied by the fuel nozzles. The air-fuel mixture is supplied to the combustors at a specified ratio for combustion. The combustion generates pressurized exhaust gases, which drive blades of the turbine.
- An exhaust diffuser may be utilized to improve efficiency of the last stage turbine blade, which is also referred to as a last stage bucket, by decreasing the static pressure at the turbine exit.
- the exhaust diffuser generally consumes a large amount of space.
- the exhaust diffuser includes an inlet and an outlet that are located between diverging walls of the exhaust diffuser.
- An axial length of the exhaust diffuser is measured between the inlet and the outlet of the exhaust diffuser. If the axial length of the diffuser is not sufficient and is too short, flow separation may occur at the diverging walls of the exhaust diffuser, which results in pressure losses.
- a gas turbine including a turbine, an exhaust diffuser, and a plasma actuator.
- the turbine releases an exhaust gas.
- the exhaust diffuser receives the exhaust gas from the turbine.
- the exhaust diffuser has an inlet and an outlet, and at least one wall that is disposed between the inlet and the outlet.
- the plasma actuator produces a plasma along the at least one wall of the diffuser.
- FIG. 1 illustrates a schematic exemplary power generation system indicated by reference number 10.
- the power generation system 10 is a gas turbine system having a compressor 20, a combustor 22, a turbine 24, and an exhaust diffuser 26. Air enters the power generation system 10 though an air intake 30 connected to the compressor 20, and is compressed by the compressor 20. The compressed air is then mixed with fuel by a fuel nozzle 34 in a specific ratio for combustion. The combustion generates hot pressurized exhaust gas that drives blades (not shown) that are located within the turbine 24. The exhaust gas is sent from the turbine 24 to the exhaust diffuser 26.
- FIG. 2 is an exemplary illustration of a side view of the exhaust diffuser 26.
- the exhaust diffuser 26 includes an inlet 40, an outlet 42, an inner diffuser 44 and an outer diffuser 46.
- the inner diffuser 44 includes an inner wall 48 and the outer diffuser 50 includes an outer wall 52.
- the inner wall 48 and the outer wall 52 are both located between the inlet 40 and the outlet 42.
- the inner wall 48 of the inner diffuser 44 is generally concentric with the outer wall 52 of the outer diffuser 46.
- Both the inner diffuser 44 and the outer diffuser 46 are oriented about an axis A-A.
- the outer wall 52 of the outer diffuser 46 includes a generally diverging configuration.
- the inlet 40 of the exhaust diffuser 26 receives an exhaust gas 56 from the turbine 24 (shown in FIG.
- a plasma generator or actuator 60 is located on an outer surface 54 of the inner wall 48, and a plasma actuator 62 is located on an outer surface 58 of the outer wall 52. It should be noted that while FIG. 2 illustrates the plasma actuator 60 on the inner wall 48 as well as the plasma actuator 62 located on the outer wall 52, only one of the inner wall 48 or the outer wall 52 may include one of the plasma actuators 60 and 62 as well.
- FIG. 3 is a sectional view of the exhaust diffuser 26 taken along section line 3-3.
- both the inner wall 48 and the outer wall 52 include a 360° configuration.
- the inner wall 48 of the inner diffuser 44 includes a generally annular configuration
- the outer wall 52 of the outer diffuser 46 includes a generally conical configuration.
- a series of manways 68 are located between the inner wall 48 and the outer wall 52.
- the manways 68 provide personnel access to the inner diffuser 44.
- the manways 68 are each spaced at about a 120° configuration apart from one another, however it is to be understood that the manways 68 may be arranged in a variety of configurations as well.
- An outer surface 70 of each of the manways 68 may include a plasma actuator 72 as well.
- the outer surface 70 of each of the manways 68 are exposed to the exhaust gas 56 from the turbine 24 (shown in FIG. 1 ).
- an exhaust strut 80 is located within the exhaust diffuser 26 between the inner wall 48 and the outer wall 52.
- the exhaust strut 80 includes a cross-section which is indicated by section line 4-4.
- the exhaust frame strut 80 includes a cross-section that is shaped as a cambered airfoil.
- the airfoil includes an upper camber portion 82 and a lower camber portion 84.
- the exhaust strut 80 has an outer surface 86, where a plasma actuator 88 may be located on the upper camber portion 82 or the lower camber portion 84 along the outer surface 86.
- FIG. 4 illustrates a cambered airfoil, it is to be understood that the airfoil may include a generally symmetrical configuration as well.
- FIG. 5 is an enlarged view of an exemplary plasma actuator 90, which may be used along the inner wall 48, the outer wall 52, along the outer surface 70 of the manways 68, or on the outer surface 86 of the exhaust strut 80 (shown in FIG. 2 ).
- the plasma actuator 90 includes an inner electrode 92, an outer electrode 94, and a dielectric material 96.
- the dielectric material 96 is configured for conforming to a conical or generally curved surface. That is, the dielectric material 96 is configured for conforming to a non-planer surface. Therefore, the plasma actuator 90 is configured for conforming to an outer surface of an object that is conical or includes a generally curved profile.
- the plasma actuator 60 is disposed along a generally annular outer surface 54
- the plasma actuator 62 is disposed along a generally conical outer surface 58.
- an AC power supply 100 is connected to both the inner electrode 92 and the outer electrode 94.
- the AC power supply 100 provides AC power to the inner electrode 92 and the outer electrode 94.
- the power consumption of the plasma actuator 90 is 15 Watts per linear foot of plasma.
- the plasma 102 produces a force on the exhaust gas 56, which in turn causes a change in the pressure distribution along a curved surface 110.
- the change in pressure distribution generally reduces or substantially prevents flow separation when the plasma actuator 90 is energized by the AC power supply 100.
- the plasma actuator 90 improves efficiency of the last stage turbine blade (not shown) or last stage bucket of the turbine 24 (shown in FIG. 1 ) by increasing the static pressure of the exhaust gas 56.
- the plasma actuators as illustrated in FIGS. 2-5 provide a robust design that is relatively simple, and also provides a relatively low amount of power consumption with real-time control.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Plasma Technology (AREA)
Abstract
Description
- The subject matter disclosed herein relates to a gas turbine, and more specifically to a gas turbine exhaust diffuser having a plasma actuator for producing a plasma.
- Gas turbines generally include a compressor, a combustor, one or more fuel nozzles, a turbine and an exhaust diffuser. Air enters the gas turbine through an air intake and is compressed by the compressor. The compressed air is then mixed with fuel supplied by the fuel nozzles. The air-fuel mixture is supplied to the combustors at a specified ratio for combustion. The combustion generates pressurized exhaust gases, which drive blades of the turbine. An exhaust diffuser may be utilized to improve efficiency of the last stage turbine blade, which is also referred to as a last stage bucket, by decreasing the static pressure at the turbine exit.
- The exhaust diffuser generally consumes a large amount of space. The exhaust diffuser includes an inlet and an outlet that are located between diverging walls of the exhaust diffuser. An axial length of the exhaust diffuser is measured between the inlet and the outlet of the exhaust diffuser. If the axial length of the diffuser is not sufficient and is too short, flow separation may occur at the diverging walls of the exhaust diffuser, which results in pressure losses.
- According to one aspect of the invention, a gas turbine is provided, including a turbine, an exhaust diffuser, and a plasma actuator. The turbine releases an exhaust gas. The exhaust diffuser receives the exhaust gas from the turbine. The exhaust diffuser has an inlet and an outlet, and at least one wall that is disposed between the inlet and the outlet. The plasma actuator produces a plasma along the at least one wall of the diffuser.
- These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
- The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
-
FIG. 1 is a partially cross-sectioned schematic view of an exemplary gas turbine system having a compressor; -
FIG. 2 is a cross-sectioned view of an exhaust diffuser shown inFIG. 1 ; -
FIG. 3 is a cross-sectioned view of the exhaust diffuser shown inFIG. 2 along section lines 3-3; -
FIG. 4 is a cross-sectioned view of an exhaust strut shown inFIG. 2 along section lines 4-4; and -
FIG. 5 is an enlarged view of a plasma actuator as shown inFIGS. 2-4 . - The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
-
FIG. 1 illustrates a schematic exemplary power generation system indicated byreference number 10. Thepower generation system 10 is a gas turbine system having acompressor 20, acombustor 22, aturbine 24, and anexhaust diffuser 26. Air enters thepower generation system 10 though anair intake 30 connected to thecompressor 20, and is compressed by thecompressor 20. The compressed air is then mixed with fuel by afuel nozzle 34 in a specific ratio for combustion. The combustion generates hot pressurized exhaust gas that drives blades (not shown) that are located within theturbine 24. The exhaust gas is sent from theturbine 24 to theexhaust diffuser 26. -
FIG. 2 is an exemplary illustration of a side view of theexhaust diffuser 26. Theexhaust diffuser 26 includes aninlet 40, anoutlet 42, aninner diffuser 44 and anouter diffuser 46. Theinner diffuser 44 includes aninner wall 48 and the outer diffuser 50 includes anouter wall 52. Theinner wall 48 and theouter wall 52 are both located between theinlet 40 and theoutlet 42. Theinner wall 48 of theinner diffuser 44 is generally concentric with theouter wall 52 of theouter diffuser 46. Both theinner diffuser 44 and theouter diffuser 46 are oriented about an axis A-A. In the embodiment as shown, theouter wall 52 of theouter diffuser 46 includes a generally diverging configuration. Theinlet 40 of theexhaust diffuser 26 receives anexhaust gas 56 from the turbine 24 (shown inFIG. 1 ). A plasma generator oractuator 60 is located on anouter surface 54 of theinner wall 48, and aplasma actuator 62 is located on anouter surface 58 of theouter wall 52. It should be noted that whileFIG. 2 illustrates theplasma actuator 60 on theinner wall 48 as well as theplasma actuator 62 located on theouter wall 52, only one of theinner wall 48 or theouter wall 52 may include one of theplasma actuators -
FIG. 3 is a sectional view of theexhaust diffuser 26 taken along section line 3-3. As seen inFIG. 3 , both theinner wall 48 and theouter wall 52 include a 360° configuration. Specifically, referring now toFIG. 2-3 , theinner wall 48 of theinner diffuser 44 includes a generally annular configuration, and theouter wall 52 of theouter diffuser 46 includes a generally conical configuration. A series ofmanways 68 are located between theinner wall 48 and theouter wall 52. Themanways 68 provide personnel access to theinner diffuser 44. In the embodiment as shown inFIG. 3 , themanways 68 are each spaced at about a 120° configuration apart from one another, however it is to be understood that themanways 68 may be arranged in a variety of configurations as well. Anouter surface 70 of each of themanways 68 may include aplasma actuator 72 as well. Theouter surface 70 of each of themanways 68 are exposed to theexhaust gas 56 from the turbine 24 (shown inFIG. 1 ). - Referring back to
FIG. 2 , anexhaust strut 80 is located within theexhaust diffuser 26 between theinner wall 48 and theouter wall 52. Theexhaust strut 80 includes a cross-section which is indicated by section line 4-4. Referring now toFIG. 4 , which is an illustration of theexhaust strut 80 at section 4-4, theexhaust frame strut 80 includes a cross-section that is shaped as a cambered airfoil. The airfoil includes anupper camber portion 82 and alower camber portion 84. Theexhaust strut 80 has anouter surface 86, where aplasma actuator 88 may be located on theupper camber portion 82 or thelower camber portion 84 along theouter surface 86. It should be noted that whileFIG. 4 illustrates a cambered airfoil, it is to be understood that the airfoil may include a generally symmetrical configuration as well. -
FIG. 5 is an enlarged view of anexemplary plasma actuator 90, which may be used along theinner wall 48, theouter wall 52, along theouter surface 70 of themanways 68, or on theouter surface 86 of the exhaust strut 80 (shown inFIG. 2 ). Theplasma actuator 90 includes aninner electrode 92, anouter electrode 94, and adielectric material 96. Thedielectric material 96 is configured for conforming to a conical or generally curved surface. That is, thedielectric material 96 is configured for conforming to a non-planer surface. Therefore, theplasma actuator 90 is configured for conforming to an outer surface of an object that is conical or includes a generally curved profile. For example, referring now toFIG. 2 , theplasma actuator 60 is disposed along a generally annularouter surface 54, and theplasma actuator 62 is disposed along a generally conicalouter surface 58. - Referring back to
FIG. 5 , anAC power supply 100 is connected to both theinner electrode 92 and theouter electrode 94. TheAC power supply 100 provides AC power to theinner electrode 92 and theouter electrode 94. In one exemplary embodiment, the power consumption of theplasma actuator 90 is 15 Watts per linear foot of plasma. When the amplitude of the AC voltage reaches a threshold value, theexhaust gas 56 from the turbine 24 (shown inFIG. 1 ) ionizes in a region of the largest electric potential to form aplasma 102. Theplasma 102 begins at anedge 104 of theouter electrode 94 and spreads over anarea 106 projected by theouter electrode 94 that is adjacent thedielectric material 96. Theplasma 102 produces a force on theexhaust gas 56, which in turn causes a change in the pressure distribution along acurved surface 110. The change in pressure distribution generally reduces or substantially prevents flow separation when theplasma actuator 90 is energized by theAC power supply 100. Thus, in the embodiments as shown inFIGS. 2-5 , theplasma actuator 90 improves efficiency of the last stage turbine blade (not shown) or last stage bucket of the turbine 24 (shown inFIG. 1 ) by increasing the static pressure of the exhaust gas 56.The plasma actuators as illustrated inFIGS. 2-5 provide a robust design that is relatively simple, and also provides a relatively low amount of power consumption with real-time control. - While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
Claims (10)
- A gas turbine, comprising:a turbine (24) releasing an exhaust gas;an exhaust diffuser (26) for receiving the exhaust gas from the turbine (24), the exhaust diffuser (26) having an inlet (40), an outlet (42) and at least one wall (48,52) that is disposed between the inlet (40) and the outlet (42); anda plasma actuator (60) producing a plasma along the at least one wall (48,52) of the diffuser (26).
- The gas turbine of claim 1, wherein the exhaust diffuser (26) includes an inner diffuser (44) and an outer diffuser (46), wherein the inner diffuser (44) is generally concentric with the outer diffuser (46).
- The gas turbine of claim 2, wherein the inner diffuser (44) includes an inner wall (48), and wherein the plasma actuator (60) is disposed along the inner wall (48) of the inner diffuser (44).
- The gas turbine of claim 2 or 3, wherein the outer diffuser (46) includes an outer wall (52), and wherein the plasma actuator (60) is disposed along the outer wall (52) of the outer diffuser (46).
- The gas turbine of any of claims 2 to 4, wherein the inner diffuser (44) includes a generally annular configuration.
- The gas turbine of any of claims 2 to 5, wherein the outer diffuser (46) includes a generally conical configuration.
- The gas turbine of any of claims 2 to 6, comprising at least one manway (68) located between the inner diffuser (44) and the outer diffuser (46), wherein the at least one manway (68) includes an outer manway surface (70), and wherein another plasma actuator (60) is located along the outer manway surface (70).
- The gas turbine of any preceding claim, comprising an exhaust strut (80) that is located between an inner wall (48) and an outer wall (52) of the exhaust diffuser (26), the exhaust strut (80) having a cross-section, wherein the cross-section of the exhaust strut (80) includes an airfoil shape.
- The gas turbine of claim 8, comprising an exhaust strut plasma actuator (88) that is disposed along an outer surface of the exhaust strut (80).
- The gas turbine of claim 1, wherein the plasma actuator (90) includes an inner electrode (92), an outer electrode (94), and a dielectric material (96).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/349,299 US20130180245A1 (en) | 2012-01-12 | 2012-01-12 | Gas turbine exhaust diffuser having plasma actuator |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2615252A1 true EP2615252A1 (en) | 2013-07-17 |
Family
ID=47678565
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13150408.6A Withdrawn EP2615252A1 (en) | 2012-01-12 | 2013-01-07 | Gas turbine |
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) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2016167769A1 (en) * | 2015-04-16 | 2016-10-20 | Siemens Aktiengesellschaft | Exhaust diffuser strut apparatus |
Families Citing this family (8)
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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 |
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 |
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EP1914385A2 (en) * | 2006-10-13 | 2008-04-23 | General Electric Company | Plasma enhanced rapidly expanded gas turbine engine transition duct |
EP1918520A2 (en) * | 2006-10-31 | 2008-05-07 | General Electric Company | Plasma lifted boundary layer on a gas turbine engine vane |
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US3371491A (en) * | 1966-03-09 | 1968-03-05 | Aerojet General Co | Thrust direction modification means |
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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 |
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 |
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-
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
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EP1914385A2 (en) * | 2006-10-13 | 2008-04-23 | General Electric Company | Plasma enhanced rapidly expanded gas turbine engine transition duct |
EP1918520A2 (en) * | 2006-10-31 | 2008-05-07 | General Electric Company | Plasma lifted boundary layer on a gas turbine engine vane |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2016167769A1 (en) * | 2015-04-16 | 2016-10-20 | Siemens Aktiengesellschaft | Exhaust diffuser strut apparatus |
Also Published As
Publication number | Publication date |
---|---|
CN103206272B (en) | 2017-03-01 |
RU2013101047A (en) | 2014-07-20 |
CN103206272A (en) | 2013-07-17 |
JP2013142403A (en) | 2013-07-22 |
US20130180245A1 (en) | 2013-07-18 |
JP6291163B2 (en) | 2018-03-14 |
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