US20090016871A1 - Systems and Methods Involving Variable Vanes - Google Patents
Systems and Methods Involving Variable Vanes Download PDFInfo
- Publication number
- US20090016871A1 US20090016871A1 US11/775,523 US77552307A US2009016871A1 US 20090016871 A1 US20090016871 A1 US 20090016871A1 US 77552307 A US77552307 A US 77552307A US 2009016871 A1 US2009016871 A1 US 2009016871A1
- Authority
- US
- United States
- Prior art keywords
- vane
- pressurized air
- operative
- throat area
- turbine engine
- 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.)
- Abandoned
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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
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- 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
- F01D5/148—Blades with variable camber, e.g. by ejection of fluid
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
Abstract
Description
- 1. Technical Field
- The invention relates to gas turbine engines.
- 2. Description of the Related Art
- Gas turbine engines use compressors to compress gas for combustion. In particular, a compressor typically uses alternating sets of rotating blades and stationary vanes to compress gas. Gas flowing through such a compressor is forced between the sets and between adjacent blades and vanes of a given set. Similarly, after combustion, hot expanding gas drives a turbine that has sets of rotating blades and stationary vanes.
- Systems and methods involving vanes are provided. In this regard, an exemplary embodiment of a gas turbine engine defining a gas flow path comprises: a first vane extending into the gas flow path and having: an interior operative to receive pressurized air; an outer surface; and outlet ports communicating between the outer surface and the interior of the first vane, the outlet ports being operative to receive the pressurized air from the interior and emit the pressurized air into the gas flow path such that a throat area defined, at least in part, by the first vane is modified.
- An exemplary embodiment of a vane assembly comprises: a first vane having: an outer surface; an interior defining a cavity operative to receive pressurized air; and outlet ports communicating between the outer surface and the cavity, the outlet ports being operative to receive the pressurized air from the cavity and emit the pressurized air through the outer surface a valve assembly operative to regulate the pressurized air emitted by the first vane.
- An exemplary embodiment of a method for modifying the throat area between vanes of a gas turbine engine comprises: directing a gas flow path of the gas turbine engine between a first vane and a second vane, wherein each of the first vane and the second vane has an outer surface and an interior; and emitting pressurized air from outlet ports communicating between the outer surface and the interior of the first vane, wherein the emitted pressurized air from the first vane modifies a throat area between the first vane and the second vane.
- Other systems, features, and/or advantages will be or may become apparent to one with skill in the art upon examination of the following drawings and detailed description. It is intended that all such additional systems, features, and/or advantages be included within this description and protected by the accompanying claims.
-
FIG. 1 is a schematic side cutaway view illustrating an exemplary embodiment of a turbine section of a gas turbine engine. -
FIG. 2 is a side cutaway view of an exemplary embodiment of a vane. -
FIG. 3 is a top cutaway view of an exemplary embodiment of vanes in a gas flow path. -
FIG. 4 is a top cutaway view of another exemplary embodiment of vanes in a gas flow path. -
FIG. 5 is a top cutaway view of another exemplary embodiment of vanes in a gas flow path. - Systems and methods involving vanes of gas turbine engines are provided. In this regard, several exemplary embodiments will be described. Notably, gas passing through a gas turbine engine enters a turbine that includes rotating blades and stationary vanes. The gas, following the gas flow path, is forced between adjacent vanes. The vanes are often shaped like airfoils and, therefore, have aerodynamic properties similar to airfoils. The flow of gas between adjacent vanes results in a throat area determined by, for example, the shape and relative position of the vanes. Often, the angle of the vanes relative to the gas flow path may be mechanically changed to vary the location and/or size of the throat area and alter the efficiency of the engine. However, it may be desirable, either additionally or alternatively, to alter the location and/or size of the throat area aerodynamically. In some embodiments, the gas turbine engine is configured as a turbofan.
- Referring now in detail to the drawings,
FIG. 1 is a schematic side view illustrating an exemplary embodiment of aturbine section 100 of a gas turbine engine. Inturbine section 100, rotatingblades 104 are attached to a disk that is rotated by ashaft 106.Stationary vanes 108 are attached to the casing of the engine between theblades 104. In operation, gas enters the turbine section alonggas flow path 102 and drives theblades 104. The gas exits theturbine section 100 alonggas flow path 102. -
FIG. 2 is a simplified, side cutaway view ofvane assembly 200 that includes avane airfoil 202 and avalve assembly 208. Note thatvane airfoil 202 typically is mounted to and spans between an outer diameter vane platform and an inner diameter vane platform, neither of which is depicted inFIG. 2 . - In the embodiment of
FIG. 2 ,valve assembly 208 includes apiston 204 andsolenoid 220, which is used to actuate the piston.Inlet ports 218 provide gas to the valve assembly so that actuation of the piston pressurizes the received gas. - Vane
airfoil 202 includes aninterior cavity 214 that receives pressurized air from the inlet ports via the piston, andoutlet ports 216 that are used to emit the pressurized air into the gas flow path. In particular, the gas emitted by theoutlet ports 216 affects the throat area formed betweenvane airfoil 202 and an adjacent vane airfoil. This is in contrast to emission of pressurized gas from ports of a vane airfoil for performing film cooling. Notably, the pressure of the pressurized gas emitted from theoutlet ports 216 is greater than that used for performing film cooling. As such, the pressurized gas from theoutlet ports 216 urges the gas flow path, which flows about the vane airfoil during operation of the gas turbine engine, away from the exterior surface of the vane airfoil to a greater extent than that caused by pressurized gas involved in film cooling. In fact, in those embodiments that additionally include film cooling, the boundary layer formed by the film-cooling air also is urged away from the exterior of the vane airfoil. Typically, the pressure of the gas required to alter the throat is not available from the compressor alone. Thus,piston 204 is used in the embodiment ofFIG. 2 to increase the pressure of the gas provided to the outlet ports. In other embodiments, various other mechanisms could be used to increase the gas pressure. - The shape of the
vane assembly 200 illustrated inFIG. 2 is merely an illustration of but one possible embodiment. The shape of thevane assembly 200 may vary depending on a variety of factors including, but not limited to, the component to which thevane assembly 200 is attached, the location of thevane assembly 200 in the gas turbine engine, the gas flow path around thevane assembly 200 at particular gas flow velocities, desired design characteristics of the gas turbine engine, and materials used in the fabrication of the gas turbine engine. - In
FIG. 2 , acontroller 212 also is provided. Thecontroller 212 is used to open and close thevalve assembly 208. In one mode of operation, thevalve assembly 208 is left open such that theoutlet ports 216 emit a constant flow of pressurized air. Additionally, or alternatively, thevalve assembly 208 may be opened and closed intermittently. In this mode of operation, the pressurized air may be emitted from theoutlet ports 216 in pulses. Notably, operation in a pulsed mode allows the pressure of the pressurized air to increase prior to being emitted into a gas flow path. In some of these embodiments, thecontroller 212 may be set to control the frequency of the pulses of emitted pressurized air. Controlling the frequency of the pulses may be desirable because a change in the throat area based on a frequency of pulses may allow the aerodynamic characteristics of the engine to be adjusted. - Specifically, the frequencies of the pulses may be controlled to modify one or more throat areas in a specific region of an engine to control local pressure ratios and/or local temperatures. The pulse frequencies may also be timed to adjust for resonance in the engine that may result in vane and blade vibrations. These pulses may be used to add a canceling frequency that may effectively cancel engine resonance, for example.
-
FIG. 3 is a top cutaway view of a pair of vanes in an embodiment of a gas turbine engine. As shown inFIG. 3 , gas is forced between thevanes 300 alonggas flow path 302, forming athroat area 304. The shape of theadjacent vanes 300, their proximity to each other, and the angle of incidence to thegas flow path 302 are possible factors that can influence the location and size of thethroat area 304. -
FIG. 4 depicts a top cutaway view of another embodiment of a vane assembly. In this embodiment,vanes Vane 406 has aninterior cavity 404 that is connected to a pressurized air source (not shown).Outlet ports 410 are located on the surface ofvane 406 and are in communication withinterior cavity 404. - Pressurized air emitted from the
outlet ports 410 invane 406 defines aboundary layer 408 that has an aerodynamic effect on thegas flow path 402. Notably, theboundary layer 408 associated with the pressurized air from the outlet ports modifies the location and/or size of thethroat area 416. Also note that the outlet ports of this embodiment are oriented such that the flow from the outlet ports is generally in a direction of the gas flow path. In other embodiments, however, the orientation can be different, such as by providing a perpendicular (seeFIG. 5 ) or counter flow (not shown). - Modifying the throat area of an engine may affect the flow of gasses through the engine. For instance, such modifying can affect the pressure ratio of the compressor and change the relationship between the flow and the pressure ratio. For example, a lower flow rate can increase the pressure ratio.
-
FIG. 5 depicts a top cutaway view of another embodiment of a vane assembly. In the illustrated embodiment,vane assembly 500 incorporates two adjacent vanes, afirst vane 501 and asecond vane 503. Thefirst vane 501 and thesecond vane 503 are spaced from each other to define agas flow path 502. Thefirst vane 501 includes three chambers—a film-cooling chamber 504, asuction side chamber 505 and apressure side chamber 507. The film-cooling chamber 504,suction side chamber 505 and thepressure side chamber 507 include ports, such asports - In operation, the film-cooling chamber 504 receives cooling pressurized air that is emitted from the associated ports, e.g.,
port 506. This air creates a relativelythin boundary layer 530 that is located adjacent to the exterior of thevane 501 to serve as a barrier against thehot gas flowpath 502. Thesuction side chamber 505 and thepressure side chamber 507 also receive pressurized air, which is at a higher pressure than that provided to chamber 504, that is emitted from associated ports, e.g.,ports chamber 507 creates aboundary layer 513 along thepressure surface 515 of thefirst vane 501 that affects thethroat area 550. Notably, theboundary layer 513 tends to urge theboundary layer 530 away from thepressure surface 515, thereby causing theboundary layer 530 to dissipate and mix with the gas of thegas flow path 502. - The
second vane 503 also includes three chambers—a film-coolingchamber 532, asuction side chamber 510 and apressure side chamber 512. The film-coolingchamber 532,suction side chamber 510 and thepressure side chamber 512 include ports, such asports - In operation, the film-cooling
chamber 532 receives cooling pressurized air that is emitted from the associated ports, e.g.,port 534. This air creates a relatively thin boundary layer 536 that is located adjacent to the exterior of thevane 503. Thesuction side chamber 510 and thepressure side chamber 512 also receive pressurized air, which is at a higher pressure than that provided tochamber 534, that is emitted from associated ports, e.g.,ports chamber 510 creates aboundary layer 525 along thesuction surface 506 of thevane 503 that affects thethroat area 550. Notably, theboundary layer 525 tends to urge the boundary layer 536 away from thesuction surface 506, thereby causing the boundary layer 536 to dissipate and mix with the gas of thegas flow path 502. - The
suction side chambers pressure side chambers suction side chambers pressure side chambers - It should be emphasized that the above-described embodiments are merely possible examples of implementations. Many variations and modifications may be made to the above-described embodiments. By way of example, although a solenoid is described with respect to the embodiment of
FIG. 2 , other types of actuation could be used. As another example, a pressurized line could be used to provide gas to a valve assembly. All such modifications and variations are intended to be included herein within the scope of this disclosure and protected by the accompanying claims.
Claims (20)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/775,523 US20090016871A1 (en) | 2007-07-10 | 2007-07-10 | Systems and Methods Involving Variable Vanes |
EP08252364A EP2014871B1 (en) | 2007-07-10 | 2008-07-10 | Systems and methods involving variable vanes |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/775,523 US20090016871A1 (en) | 2007-07-10 | 2007-07-10 | Systems and Methods Involving Variable Vanes |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090016871A1 true US20090016871A1 (en) | 2009-01-15 |
Family
ID=39830181
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/775,523 Abandoned US20090016871A1 (en) | 2007-07-10 | 2007-07-10 | Systems and Methods Involving Variable Vanes |
Country Status (2)
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US (1) | US20090016871A1 (en) |
EP (1) | EP2014871B1 (en) |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090162189A1 (en) * | 2007-12-19 | 2009-06-25 | United Technologies Corp. | Systems and Methods Involving Variable Throat Area Vanes |
EP2532857A1 (en) | 2011-06-06 | 2012-12-12 | United Technologies Corporation | Turbomachine assembly with combustors having different flow directions and corresponding operating method |
US20160061054A1 (en) * | 2014-09-03 | 2016-03-03 | Honeywell International Inc. | Structural frame integrated with variable-vectoring flow control for use in turbine systems |
US20160298470A1 (en) * | 2015-04-08 | 2016-10-13 | United Technologies Corporation | Airfoils |
JP2016211569A (en) * | 2015-05-11 | 2016-12-15 | ゼネラル・エレクトリック・カンパニイ | System and method for flow control in turbine |
EP3133246A1 (en) * | 2015-08-18 | 2017-02-22 | General Electric Company | Airflow injection nozzle for a gas turbine engine |
US20170070973A1 (en) * | 2011-08-12 | 2017-03-09 | Qualcomm Incorporated | Devices for reduced overhead paging |
US9617868B2 (en) | 2013-02-26 | 2017-04-11 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine variable geometry flow component |
US20180355738A1 (en) * | 2017-06-13 | 2018-12-13 | General Electric Company | Turbine engine with variable effective throat |
US10578028B2 (en) | 2015-08-18 | 2020-03-03 | General Electric Company | Compressor bleed auxiliary turbine |
US10711702B2 (en) | 2015-08-18 | 2020-07-14 | General Electric Company | Mixed flow turbocore |
US20210301684A1 (en) * | 2020-03-30 | 2021-09-30 | General Electric Company | Fluidic flow control device |
US11692448B1 (en) | 2022-03-04 | 2023-07-04 | General Electric Company | Passive valve assembly for a nozzle of a gas turbine engine |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB0910647D0 (en) | 2009-06-22 | 2009-08-05 | Rolls Royce Plc | A compressor blade |
CN109477417B (en) * | 2016-12-21 | 2021-12-24 | 三菱重工发动机和增压器株式会社 | Turbocharger, nozzle vane of turbocharger, and turbine |
US20200362704A1 (en) * | 2019-05-17 | 2020-11-19 | Solar Turbines Incorporated | Nozzle segment |
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US2746672A (en) * | 1950-07-27 | 1956-05-22 | United Aircraft Corp | Compressor blading |
US2801790A (en) * | 1950-06-21 | 1957-08-06 | United Aircraft Corp | Compressor blading |
US2825532A (en) * | 1951-01-04 | 1958-03-04 | Snecma | Device for controlling the flow of fluid between cambered blades |
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US4624104A (en) * | 1984-05-15 | 1986-11-25 | A/S Kongsberg Vapenfabrikk | Variable flow gas turbine engine |
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US4740138A (en) * | 1985-12-04 | 1988-04-26 | MTU Motoren-und Turbinen-Munchen GmbH | Device for controlling the throat areas between the diffusor guide vanes of a centrifugal compressor of a gas turbine engine |
US4741667A (en) * | 1986-05-28 | 1988-05-03 | United Technologies Corporation | Stator vane |
US5207556A (en) * | 1992-04-27 | 1993-05-04 | General Electric Company | Airfoil having multi-passage baffle |
US5645397A (en) * | 1995-10-10 | 1997-07-08 | United Technologies Corporation | Turbine vane assembly with multiple passage cooled vanes |
US5833433A (en) * | 1997-01-07 | 1998-11-10 | Mcdonnell Douglas Corporation | Rotating machinery noise control device |
US6026791A (en) * | 1997-03-03 | 2000-02-22 | Alliedsignal Inc. | Exhaust gas recirculation valve with integral feedback proportional to volumetric flow |
US6164903A (en) * | 1998-12-22 | 2000-12-26 | United Technologies Corporation | Turbine vane mounting arrangement |
US6565313B2 (en) * | 2001-10-04 | 2003-05-20 | United Technologies Corporation | Bleed deflector for a gas turbine engine |
US6929446B2 (en) * | 2003-10-22 | 2005-08-16 | General Electric Company | Counterbalanced flow turbine nozzle |
US20090162189A1 (en) * | 2007-12-19 | 2009-06-25 | United Technologies Corp. | Systems and Methods Involving Variable Throat Area Vanes |
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FR1499216A (en) * | 1966-07-12 | 1967-10-27 | Snecma | Cooling vane device |
-
2007
- 2007-07-10 US US11/775,523 patent/US20090016871A1/en not_active Abandoned
-
2008
- 2008-07-10 EP EP08252364A patent/EP2014871B1/en not_active Expired - Fee Related
Patent Citations (17)
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US2801790A (en) * | 1950-06-21 | 1957-08-06 | United Aircraft Corp | Compressor blading |
US2746672A (en) * | 1950-07-27 | 1956-05-22 | United Aircraft Corp | Compressor blading |
US2825532A (en) * | 1951-01-04 | 1958-03-04 | Snecma | Device for controlling the flow of fluid between cambered blades |
US4072008A (en) * | 1976-05-04 | 1978-02-07 | General Electric Company | Variable area bypass injector system |
US4504189A (en) * | 1982-11-10 | 1985-03-12 | Rolls-Royce Limited | Stator vane for a gas turbine engine |
US4624104A (en) * | 1984-05-15 | 1986-11-25 | A/S Kongsberg Vapenfabrikk | Variable flow gas turbine engine |
US4740138A (en) * | 1985-12-04 | 1988-04-26 | MTU Motoren-und Turbinen-Munchen GmbH | Device for controlling the throat areas between the diffusor guide vanes of a centrifugal compressor of a gas turbine engine |
US4707981A (en) * | 1986-01-27 | 1987-11-24 | Rockwell International Corporation | Variable expansion ratio reaction engine |
US4741667A (en) * | 1986-05-28 | 1988-05-03 | United Technologies Corporation | Stator vane |
US5207556A (en) * | 1992-04-27 | 1993-05-04 | General Electric Company | Airfoil having multi-passage baffle |
US5645397A (en) * | 1995-10-10 | 1997-07-08 | United Technologies Corporation | Turbine vane assembly with multiple passage cooled vanes |
US5833433A (en) * | 1997-01-07 | 1998-11-10 | Mcdonnell Douglas Corporation | Rotating machinery noise control device |
US6026791A (en) * | 1997-03-03 | 2000-02-22 | Alliedsignal Inc. | Exhaust gas recirculation valve with integral feedback proportional to volumetric flow |
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US6565313B2 (en) * | 2001-10-04 | 2003-05-20 | United Technologies Corporation | Bleed deflector for a gas turbine engine |
US6929446B2 (en) * | 2003-10-22 | 2005-08-16 | General Electric Company | Counterbalanced flow turbine nozzle |
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Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8197209B2 (en) * | 2007-12-19 | 2012-06-12 | United Technologies Corp. | Systems and methods involving variable throat area vanes |
US20090162189A1 (en) * | 2007-12-19 | 2009-06-25 | United Technologies Corp. | Systems and Methods Involving Variable Throat Area Vanes |
EP2532857A1 (en) | 2011-06-06 | 2012-12-12 | United Technologies Corporation | Turbomachine assembly with combustors having different flow directions and corresponding operating method |
US20170070973A1 (en) * | 2011-08-12 | 2017-03-09 | Qualcomm Incorporated | Devices for reduced overhead paging |
US9617868B2 (en) | 2013-02-26 | 2017-04-11 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine variable geometry flow component |
US10221720B2 (en) * | 2014-09-03 | 2019-03-05 | Honeywell International Inc. | Structural frame integrated with variable-vectoring flow control for use in turbine systems |
US20160061054A1 (en) * | 2014-09-03 | 2016-03-03 | Honeywell International Inc. | Structural frame integrated with variable-vectoring flow control for use in turbine systems |
US20190078466A1 (en) * | 2014-09-03 | 2019-03-14 | Honeywell International Inc. | Structural frame integrated with variable-vectoring flow control for use in turbine systems |
US20160298470A1 (en) * | 2015-04-08 | 2016-10-13 | United Technologies Corporation | Airfoils |
US10641113B2 (en) * | 2015-04-08 | 2020-05-05 | United Technologies Corporation | Airfoils |
JP2016211569A (en) * | 2015-05-11 | 2016-12-15 | ゼネラル・エレクトリック・カンパニイ | System and method for flow control in turbine |
US20170051680A1 (en) * | 2015-08-18 | 2017-02-23 | General Electric Company | Airflow injection nozzle for a gas turbine engine |
US10578028B2 (en) | 2015-08-18 | 2020-03-03 | General Electric Company | Compressor bleed auxiliary turbine |
EP3133246A1 (en) * | 2015-08-18 | 2017-02-22 | General Electric Company | Airflow injection nozzle for a gas turbine engine |
US10711702B2 (en) | 2015-08-18 | 2020-07-14 | General Electric Company | Mixed flow turbocore |
CN109083690A (en) * | 2017-06-13 | 2018-12-25 | 通用电气公司 | With the turbogenerator that can be changed effective venturi |
US20180355738A1 (en) * | 2017-06-13 | 2018-12-13 | General Electric Company | Turbine engine with variable effective throat |
US10760426B2 (en) * | 2017-06-13 | 2020-09-01 | General Electric Company | Turbine engine with variable effective throat |
US20210301684A1 (en) * | 2020-03-30 | 2021-09-30 | General Electric Company | Fluidic flow control device |
US11692448B1 (en) | 2022-03-04 | 2023-07-04 | General Electric Company | Passive valve assembly for a nozzle of a gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
EP2014871B1 (en) | 2012-11-14 |
EP2014871A3 (en) | 2011-08-31 |
EP2014871A2 (en) | 2009-01-14 |
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