EP2740897A1 - Turbine diffuser - Google Patents
Turbine diffuser Download PDFInfo
- Publication number
- EP2740897A1 EP2740897A1 EP12198699.6A EP12198699A EP2740897A1 EP 2740897 A1 EP2740897 A1 EP 2740897A1 EP 12198699 A EP12198699 A EP 12198699A EP 2740897 A1 EP2740897 A1 EP 2740897A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- diffuser
- airfoil
- airfoils
- hub
- flow
- 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- Withdrawn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
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted 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
- 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
-
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/126—Baffles or ribs
Definitions
- the present invention relates generally to gas turbine engines and more particularly relate to a turbine diffuser with an airfoil arrangement to reduce swirl and flow separation during partial load operations and the like.
- Gas turbine engines and the like typically include a diffuser downstream of the last stage of a turbine.
- the diffuser converts the kinetic energy of the hot flow gases exiting the last stage into potential energy in the form of increased static pressure.
- the diffuser directs the hot flow gases through a casing of increasing area in the direction of the flow.
- the diffuser generally includes a number of struts mounted onto a hub and enclosed by the casing. Other configurations also may be known.
- a bucket exit tangential flow angle may increase and may lead to flow separation on the struts and the hub of the diffuser. Flow separation and an increase in swirl may reduce the diffuser static pressure recovery. Such a reduction may have an impact on overall gas turbine engine performance and efficiency.
- Such an improved design preferably may limit flow separations and swirl so as to improve overall performance and efficiency.
- the present invention thus provides a diffuser for use with a gas turbine.
- the diffuser may include hub, a number of struts extending from the hub, and a number of airfoils extending from the hub.
- the present invention further provides a diffuser for use with a gas turbine.
- the diffuser may include a hub, a number of struts extending from the hub, a number of airfoils extending from the hub such that one of the airfoils is positioned between a pair of the struts, and a casing.
- the present invention further provides a diffuser for use with a gas turbine.
- the diffuser may include a hub, a number of struts extending from the hub, and a number of airfoils extending from the hub.
- the airfoils may have a number of configurations.
- Fig. 1 shows a schematic view of gas turbine engine 10 as may be used herein.
- the gas turbine engine 10 may include a compressor 15.
- the compressor 15 compresses an incoming flow of air 20.
- the compressor 15 delivers the compressed flow of air 20 to a combustor 25.
- the combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35.
- the gas turbine engine 10 may include any number of combustors 25.
- the flow of combustion gases 35 is in turn delivered to a turbine 40.
- the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
- the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
- the gas turbine engine 10 also may include a diffuser 55.
- the diffuser 55 may be positioned downstream of the turbine 40.
- the diffuser 55 may include a number of struts 60 mounted on a hub 65 and enclosed within an outer casing 70.
- the diffuser 55 turns the flow of combustion gases 35 in an axial direction.
- Other configurations and other components may be used.
- the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
- the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company.
- the gas turbine engine 10 may have different configurations and may use other types of components.
- Other types of gas turbine engines also may be used herein.
- Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
- Fig. 2 and Fig. 3 show portions of an example of a diffuser 100 as may be described herein.
- the diffuser 100 may include a number of struts 110 positioned on a hub 120. Any number of struts 110 may be used.
- the struts 110 and the hub 120 may have any size or shape.
- the struts 110 may be enclosed within a casing that expands in diameter along the flow path therethrough. The casing may be similar to that described above.
- Other components and other configurations also may be used herein.
- the diffuser 100 also may have a number of airfoils 130 positioned on the hub 120.
- the airfoils 130 may be positioned adjacent to the struts 110.
- an airfoil 130 may be positioned between each pair of the struts 110. Any number of the airfoils 130 may be used herein.
- the angle, length, size, shape, and configuration of the airfoils 130 may vary. Airfoils 130 of different configurations may be used herein together.
- a slot 140 may be positioned through a portion of the airfoil 130. The slot 140 serves to direct the flow of combustion gases 35 therethrough.
- the slot 140 may have any desired size, shape, or configuration. Other components and other configurations may be used herein.
- the use of the airfoils 130 thus corrects the creation of swirl and reduces flow separation about the struts 110 and the hub 120 of the diffuser 100 through the entire partial load operations. Moreover, the airfoils 130 may be designed to not incur additional losses during full load ISO and cold day operations. An increase in airfoil count/solidity reduces airfoil-strut pitch so as to correct the swirl and the flow separation.
- the diffuser 100 thus may provide improved performance so as to improve overall gas turbine performance and efficiency.
- the airfoil also may include additional features or mechanisms as shown in, for example, Figs. 4-9 . These additional features also avoid flow separation on the airfoil and improve performance.
- Fig. 4 shows a diffuser 150.
- the diffuser 150 may include the strut 110 and a "hunch back"-like airfoil 160 positioned adjacent thereto.
- the hunch back airfoil 160 may have a spoiler like configuration 165 to direct the flow of combustion gases 35.
- Fig. 5 shows a further example of a diffuser 170.
- the diffuser 170 may include the strut 110 and a vortex generator airfoil 180 positioned adjacent thereto.
- the vortex generator airfoil 180 may have a largely sinusoidal configuration 185 to direct the flow of combustion gases 35.
- Fig. 6 shows a further example of a diffuser 190.
- the diffuser 190 may include the strut 110 and a fluidic airfoil 200 positioned adjacent thereto.
- the fluidic airfoil 200 may have a number of fluidic ports 210 to provide suction and/or blowing so as to direct the flow of combustion gases 35.
- Fig. 7 shows a further example of a diffuser 220.
- the diffuser 220 may include the strut 110 and a high lift airfoil 230 positioned adjacent thereto.
- the high lift airfoil 230 may include a number of airfoil elements 240 so as to direct the flow of combustion gases 35.
- Fig. 8 shows a further example of a diffuser 250.
- the diffuser 250 may include the strut 110 and a cambered airfoil 260 positioned adjacent thereto.
- the cambered airfoil 260 may take a thickened configuration 270 so as to direct the flow of combustion gases 35.
- Fig. 9 shows a further example of a diffuser 250.
- the diffuser 250 may include the strut 110 and an extended airfoil 280 positioned adjacent thereto.
- the extended airfoil 280 may take a forward bend 290 so as to direct the flow of combustion gases 35.
- the diffusers described herein thus may include airfoils 130 of various sizes, shapes, and configurations.
- the use of the airfoils 130 with the struts 110 thus controls the flow separation and swirl during partial load operations so as to improve overall efficiency.
- Many other sizes, shapes, and configurations of diffusers and airfoils may be used herein.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- The present invention relates generally to gas turbine engines and more particularly relate to a turbine diffuser with an airfoil arrangement to reduce swirl and flow separation during partial load operations and the like.
- Gas turbine engines and the like typically include a diffuser downstream of the last stage of a turbine. Generally described, the diffuser converts the kinetic energy of the hot flow gases exiting the last stage into potential energy in the form of increased static pressure. The diffuser directs the hot flow gases through a casing of increasing area in the direction of the flow. The diffuser generally includes a number of struts mounted onto a hub and enclosed by the casing. Other configurations also may be known.
- During partial load operations, a bucket exit tangential flow angle (swirl) may increase and may lead to flow separation on the struts and the hub of the diffuser. Flow separation and an increase in swirl may reduce the diffuser static pressure recovery. Such a reduction may have an impact on overall gas turbine engine performance and efficiency.
- There is thus a desire for an improved gas turbine engine diffuser design. Such an improved design preferably may limit flow separations and swirl so as to improve overall performance and efficiency.
- The present invention thus provides a diffuser for use with a gas turbine. The diffuser may include hub, a number of struts extending from the hub, and a number of airfoils extending from the hub.
- The present invention further provides a diffuser for use with a gas turbine. The diffuser may include a hub, a number of struts extending from the hub, a number of airfoils extending from the hub such that one of the airfoils is positioned between a pair of the struts, and a casing.
- The present invention further provides a diffuser for use with a gas turbine. The diffuser may include a hub, a number of struts extending from the hub, and a number of airfoils extending from the hub. The airfoils may have a number of configurations.
- These and other features and improvements of the present application and the resultant patent will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.
- Embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings in which:
-
Fig. 1 is a schematic diagram of a gas turbine engine showing a compressor, a combustor, a turbine, and a diffuser. -
Fig. 2 is a partial perspective view of a portion of a diffuser as may be described herein. -
Fig. 3 is a plan view of portions of the diffuser ofFig. 2 -
Fig. 4 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein. -
Fig. 5 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein. -
Fig. 6 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein. -
Fig. 7 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein. -
Fig. 8 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein. -
Fig. 9 is a plan view of portions of an alternative embodiment of a diffuser as may be described herein. - Referring now to the drawings, in which like numerals refer to like elements throughout the several views,
Fig. 1 shows a schematic view ofgas turbine engine 10 as may be used herein. Thegas turbine engine 10 may include acompressor 15. Thecompressor 15 compresses an incoming flow ofair 20. Thecompressor 15 delivers the compressed flow ofair 20 to acombustor 25. Thecombustor 25 mixes the compressed flow ofair 20 with a pressurized flow offuel 30 and ignites the mixture to create a flow ofcombustion gases 35. Although only asingle combustor 25 is shown, thegas turbine engine 10 may include any number ofcombustors 25. The flow ofcombustion gases 35 is in turn delivered to aturbine 40. The flow ofcombustion gases 35 drives theturbine 40 so as to produce mechanical work. The mechanical work produced in theturbine 40 drives thecompressor 15 via ashaft 45 and anexternal load 50 such as an electrical generator and the like. - The
gas turbine engine 10 also may include adiffuser 55. Thediffuser 55 may be positioned downstream of theturbine 40. As described above, thediffuser 55 may include a number ofstruts 60 mounted on ahub 65 and enclosed within anouter casing 70. Thediffuser 55 turns the flow ofcombustion gases 35 in an axial direction. Other configurations and other components may be used. - The
gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels. Thegas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company. Thegas turbine engine 10 may have different configurations and may use other types of components. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together. -
Fig. 2 andFig. 3 show portions of an example of adiffuser 100 as may be described herein. Generally described, thediffuser 100 may include a number ofstruts 110 positioned on ahub 120. Any number ofstruts 110 may be used. Thestruts 110 and thehub 120 may have any size or shape. Thestruts 110 may be enclosed within a casing that expands in diameter along the flow path therethrough. The casing may be similar to that described above. Other components and other configurations also may be used herein. - The
diffuser 100 also may have a number ofairfoils 130 positioned on thehub 120. In this example, theairfoils 130 may be positioned adjacent to thestruts 110. Specifically, anairfoil 130 may be positioned between each pair of thestruts 110. Any number of theairfoils 130 may be used herein. The angle, length, size, shape, and configuration of theairfoils 130 may vary.Airfoils 130 of different configurations may be used herein together. Aslot 140 may be positioned through a portion of theairfoil 130. Theslot 140 serves to direct the flow ofcombustion gases 35 therethrough. Theslot 140 may have any desired size, shape, or configuration. Other components and other configurations may be used herein. - The use of the
airfoils 130 thus corrects the creation of swirl and reduces flow separation about thestruts 110 and thehub 120 of thediffuser 100 through the entire partial load operations. Moreover, theairfoils 130 may be designed to not incur additional losses during full load ISO and cold day operations. An increase in airfoil count/solidity reduces airfoil-strut pitch so as to correct the swirl and the flow separation. Thediffuser 100 thus may provide improved performance so as to improve overall gas turbine performance and efficiency. - The airfoil also may include additional features or mechanisms as shown in, for example,
Figs. 4-9 . These additional features also avoid flow separation on the airfoil and improve performance.Fig. 4 shows adiffuser 150. Thediffuser 150 may include thestrut 110 and a "hunch back"-likeairfoil 160 positioned adjacent thereto. The hunch backairfoil 160 may have a spoiler likeconfiguration 165 to direct the flow ofcombustion gases 35. -
Fig. 5 shows a further example of adiffuser 170. Thediffuser 170 may include thestrut 110 and avortex generator airfoil 180 positioned adjacent thereto. Thevortex generator airfoil 180 may have a largelysinusoidal configuration 185 to direct the flow ofcombustion gases 35. -
Fig. 6 shows a further example of adiffuser 190. Thediffuser 190 may include thestrut 110 and afluidic airfoil 200 positioned adjacent thereto. Thefluidic airfoil 200 may have a number offluidic ports 210 to provide suction and/or blowing so as to direct the flow ofcombustion gases 35. -
Fig. 7 shows a further example of adiffuser 220. Thediffuser 220 may include thestrut 110 and ahigh lift airfoil 230 positioned adjacent thereto. Thehigh lift airfoil 230 may include a number ofairfoil elements 240 so as to direct the flow ofcombustion gases 35. -
Fig. 8 shows a further example of adiffuser 250. Thediffuser 250 may include thestrut 110 and acambered airfoil 260 positioned adjacent thereto. Thecambered airfoil 260 may take a thickenedconfiguration 270 so as to direct the flow ofcombustion gases 35. -
Fig. 9 shows a further example of adiffuser 250. Thediffuser 250 may include thestrut 110 and anextended airfoil 280 positioned adjacent thereto. Theextended airfoil 280 may take aforward bend 290 so as to direct the flow ofcombustion gases 35. - The diffusers described herein thus may include
airfoils 130 of various sizes, shapes, and configurations. The use of theairfoils 130 with thestruts 110 thus controls the flow separation and swirl during partial load operations so as to improve overall efficiency. Many other sizes, shapes, and configurations of diffusers and airfoils may be used herein. - It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.
Claims (15)
- A diffuser (100,150,170,190,220,250) for use with a gas turbine (10), comprising:a hub (120);a plurality of struts (110) extending from the hub (120); anda plurality of airfoils (130) extending from the hub (120).
- The diffuser of claim 1, wherein one of the plurality of airfoils (130) is positioned between a pair of the plurality of struts (110).
- The diffuser of claim 1 or 2, wherein one or more of the plurality of airfoils (130) comprises a slot (140) therein.
- The diffuser of any of claims 1 to 3, wherein one or more of the plurality of airfoils (130) comprises a hunch back airfoil (160).
- The diffuser of claim 4, wherein the hunch back airfoil (160) comprises a spoiler (165) thereon.
- The diffuser of any of claims 1 to 3, wherein one or more of the plurality of airfoils (130) comprises a vortex generator airfoil (180).
- The diffuser of claim 6, wherein the vortex generator airfoil (180) comprises a sinusoidal configuration (185).
- The diffuser of any of claims 1 to 3, wherein one or more of the plurality of airfoils (130) comprises a fluidic airfoil (200).
- The diffuser of claim 8, wherein the fluidic airfoil (200) comprises one or more ports (210) thereon.
- The diffuser of any of claims 1 to 3, wherein one or more of the plurality of airfoils (130) comprises a high lift airfoil (230).
- The diffuser of claim 10, wherein the high lift airfoil (230) comprises one or more airfoil elements (240).
- The diffuser of any of claims 1 to 3, wherein one or more of the plurality of airfoils (130) comprises a cambered airfoil (260).
- The diffuser of claim 12, wherein the cambered airfoil (260) comprises a thickened configuration (270).
- The diffuser of any of claims 1 to 3, wherein one or more of the plurality of airfoils (130) comprises an extended airfoil (280).
- The diffuser of claim 14, wherein the extended airfoil (280) comprises a forward bend (290).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/343,021 US20130170969A1 (en) | 2012-01-04 | 2012-01-04 | Turbine Diffuser |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2740897A1 true EP2740897A1 (en) | 2014-06-11 |
Family
ID=47664077
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12198699.6A Withdrawn EP2740897A1 (en) | 2012-01-04 | 2012-12-20 | Turbine diffuser |
Country Status (5)
Country | Link |
---|---|
US (1) | US20130170969A1 (en) |
EP (1) | EP2740897A1 (en) |
JP (1) | JP2013139785A (en) |
CN (1) | CN103195572A (en) |
RU (1) | RU2012158350A (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP6409072B2 (en) * | 2014-03-18 | 2018-10-17 | ゼネラル・エレクトリック・カンパニイ | Exhaust gas diffuser with main and small struts |
US9836066B2 (en) * | 2014-07-16 | 2017-12-05 | Caterpillar Inc. | Vortex diffuser for rotating/stationary interfaces |
JP2016217355A (en) | 2015-05-22 | 2016-12-22 | ゼネラル・エレクトリック・カンパニイ | Turbomachine diffuser including flow mixing lobes and method therefor |
US10047636B2 (en) * | 2015-05-29 | 2018-08-14 | Siemens Energy, Inc. | Gas turbine diffuser outer diameter and inner diameter wall strips for turbine exhaust manifold pressure oscillation reduction |
US10563543B2 (en) | 2016-05-31 | 2020-02-18 | General Electric Company | Exhaust diffuser |
DE102017212311A1 (en) | 2017-07-19 | 2019-01-24 | MTU Aero Engines AG | Umströmungsanordung for arranging in the hot gas duct of a turbomachine |
GB2568109B (en) * | 2017-11-07 | 2021-06-09 | Gkn Aerospace Sweden Ab | Splitter vane |
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US2314572A (en) * | 1938-12-07 | 1943-03-23 | Herman E Chitz | Turboengine |
US4023350A (en) * | 1975-11-10 | 1977-05-17 | United Technologies Corporation | Exhaust case for a turbine machine |
EP0978632A1 (en) * | 1998-08-07 | 2000-02-09 | Asea Brown Boveri AG | Turbomachine with intermediate blades as flow dividers |
WO2005100752A1 (en) * | 2004-04-09 | 2005-10-27 | Norris Thomas R | Externally mounted vortex generators for flow duct passage |
US20110052373A1 (en) * | 2009-09-03 | 2011-03-03 | General Electric Company | High-turning diffuser strut with flow cross-over slots |
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US2941781A (en) * | 1955-10-13 | 1960-06-21 | Westinghouse Electric Corp | Guide vane array for turbines |
US2938336A (en) * | 1956-12-06 | 1960-05-31 | United Aircraft Corp | Gas flow straightening vanes |
GB1048968A (en) * | 1964-05-08 | 1966-11-23 | Rolls Royce | Combustion chamber for a gas turbine engine |
US3704075A (en) * | 1970-12-14 | 1972-11-28 | Caterpillar Tractor Co | Combined turbine nozzle and bearing frame |
US4624104A (en) * | 1984-05-15 | 1986-11-25 | A/S Kongsberg Vapenfabrikk | Variable flow gas turbine engine |
US4793770A (en) * | 1987-08-06 | 1988-12-27 | General Electric Company | Gas turbine engine frame assembly |
US4989406A (en) * | 1988-12-29 | 1991-02-05 | General Electric Company | Turbine engine assembly with aft mounted outlet guide vanes |
US6139259A (en) * | 1998-10-29 | 2000-10-31 | General Electric Company | Low noise permeable airfoil |
GB0001399D0 (en) * | 2000-01-22 | 2000-03-08 | Rolls Royce Plc | An aerofoil for an axial flow turbomachine |
US6715983B2 (en) * | 2001-09-27 | 2004-04-06 | General Electric Company | Method and apparatus for reducing distortion losses induced to gas turbine engine airflow |
US6866479B2 (en) * | 2003-05-16 | 2005-03-15 | Mitsubishi Heavy Industries, Ltd. | Exhaust diffuser for axial-flow turbine |
ITBA20030052A1 (en) * | 2003-10-17 | 2005-04-18 | Paolo Pietricola | ROTORIC AND STATHIC POLES WITH MULTIPLE PROFILES |
US6997676B2 (en) * | 2004-03-10 | 2006-02-14 | General Electric Company | Bifurcated outlet guide vanes |
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EP2092163A4 (en) * | 2006-11-14 | 2013-04-17 | Volvo Aero Corp | Vane assembly configured for turning a flow ina a gas turbine engine, a stator component comprising the vane assembly, a gas turbine and an aircraft jet engine |
US7824152B2 (en) * | 2007-05-09 | 2010-11-02 | Siemens Energy, Inc. | Multivane segment mounting arrangement for a gas turbine |
JP2009215897A (en) * | 2008-03-07 | 2009-09-24 | Mitsubishi Heavy Ind Ltd | Gas turbine engine |
DE102008033861A1 (en) * | 2008-07-19 | 2010-01-21 | Mtu Aero Engines Gmbh | Shovel of a turbomachine with vortex generator |
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US9359900B2 (en) * | 2012-10-05 | 2016-06-07 | General Electric Company | Exhaust diffuser |
US20140137533A1 (en) * | 2012-11-19 | 2014-05-22 | General Electric Company | Exhaust gas diffuser for a gas turbine |
US20140161603A1 (en) * | 2012-12-07 | 2014-06-12 | General Electric Company | Exhaust diffuser |
US9422864B2 (en) * | 2012-12-20 | 2016-08-23 | General Electric Company | Staggered double row, slotted airfoil design for gas turbine exhaust frame |
-
2012
- 2012-01-04 US US13/343,021 patent/US20130170969A1/en not_active Abandoned
- 2012-12-20 EP EP12198699.6A patent/EP2740897A1/en not_active Withdrawn
- 2012-12-21 JP JP2012278796A patent/JP2013139785A/en active Pending
- 2012-12-27 RU RU2012158350/06A patent/RU2012158350A/en not_active Application Discontinuation
-
2013
- 2013-01-04 CN CN2013100012466A patent/CN103195572A/en active Pending
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2314572A (en) * | 1938-12-07 | 1943-03-23 | Herman E Chitz | Turboengine |
US4023350A (en) * | 1975-11-10 | 1977-05-17 | United Technologies Corporation | Exhaust case for a turbine machine |
EP0978632A1 (en) * | 1998-08-07 | 2000-02-09 | Asea Brown Boveri AG | Turbomachine with intermediate blades as flow dividers |
WO2005100752A1 (en) * | 2004-04-09 | 2005-10-27 | Norris Thomas R | Externally mounted vortex generators for flow duct passage |
US20110052373A1 (en) * | 2009-09-03 | 2011-03-03 | General Electric Company | High-turning diffuser strut with flow cross-over slots |
Also Published As
Publication number | Publication date |
---|---|
CN103195572A (en) | 2013-07-10 |
JP2013139785A (en) | 2013-07-18 |
US20130170969A1 (en) | 2013-07-04 |
RU2012158350A (en) | 2014-07-10 |
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