Class / Patent application number | Description | Number of patent applications / Date published |
060226300 | Having means to effect a variable bypass ratio | 80 |
20090056307 | ACTUATING DEVICE, BYPASS AIR BLEED SYSTEM EQUIPPED THEREWITH, AND TURBOJET ENGINE COMPRISING THESE - The actuating device for opening and closing at least one shutter in a gas turbine engine such as a turbojet engine, comprises at least one actuator made of a two-way shape memory alloy having a first stable state at a first given temperature (θ | 03-05-2009 |
20090064659 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE HAVING A ROTATIONAL VALVE SYSTEM - A turbofan engine includes a fan variable area nozzle having a multiple of vents through a fan nacelle and rotatable elements rotatable within the vents by an actuator system. Rotation of the rotatable element within each vent changes the effective area of the fan nozzle exit area to permit efficient operation at a multiple of flight conditions. | 03-12-2009 |
20090090096 | Epicyclic gear train for variable cycle engine - A two-stage turbofan system for use in a gas turbine engine comprises a first-stage fan shaft, a second-stage fan shaft, a stationary torque tube and a gear system. The second-stage fan shaft connects with a drive shaft in the gas turbine engine such that the second-stage fan shaft is driven at the speed of the drive shaft. The stationary torque tube is connected with a fan case in the gas turbine engine. The gear system is connected to the second-stage fan shaft and the torque tube. The first-stage fan shaft extends from the gear system such that the first-stage fan shaft is driven at a speed reduced from that of the drive shaft. | 04-09-2009 |
20090094961 | THRUST REVERSING VARIABLE AREA NOZZLE - A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap between the first nozzle section and the second nozzle section. A movable door between the first nozzle section and the second nozzle section selectively opens or closes the gap. | 04-16-2009 |
20090107109 | Variable bypass turbine fan - An engine for powering a vehicle, such as a military aircraft or a commercial aircraft, is provided. The engine broadly comprises a main core with a plurality of spools with each spool having a plurality of compressor blades and a plurality of turbine blades attached thereto. One of the spools has a first set of fan blades attached thereto. The engine further has a variable bypass turbine fan formed by a second set of fan blades. The second set of fan blades is arranged outboard of the main core. The second set of fan blades may be decoupled from the first set of fan blades. | 04-30-2009 |
20090139202 | Convertible gas turbine propulsion system - A convertible gas turbine propulsion system operates in multiple output modes. The convertible gas turbine propulsion system comprises a gas generator, a first power turbine, a secondary propulsion system and an exhaust duct. The gas generator is configured to produce exhaust gas. The first power turbine is aligned with the gas generator to receive the exhaust gas. The secondary propulsion system is in series with the gas generator and the first power turbine. The exhaust duct coaxially extends from the first power turbine to the secondary propulsion system. The exhaust duct includes an exhaust port for opening the exhaust duct to ambient air pressure and permitting exhaust gas to bypass the secondary propulsion system. In various embodiments of the invention, the first power turbine is connected to a first rotary propulsion system, and the secondary propulsion system comprises a second power turbine or a nozzle. | 06-04-2009 |
20090260345 | FAN VARIABLE AREA NOZZLE WITH ADAPTIVE STRUCTURE - A fan variable area nozzle (FVAN) includes a flexible adaptive segment which defines the fan nozzle exit area. The flexible adaptive segment generally includes a multiple of flexible sections, a linkage and an actuator system to morph the flexible adaptive segment between a converged shape and a diverged shape. The flexible adaptive segments seal an interface between sectors to provide an asymmetrical fan nozzle exit area. | 10-22-2009 |
20090277155 | NACELLE FOR AIRCRAFT JET ENGINE AND AIRCRAFT INCLUDING SUCH NACELLE - The invention relates to a nacelle, for an aircraft jet engine ( | 11-12-2009 |
20090308050 | MULTIDIRECTIONAL TURBINE ENGINE - A gas turbine engine comprising a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating multidirectional thrust. | 12-17-2009 |
20100005778 | FAN VARIABLE AREA NOZZLE WITH CABLE ACTUATOR SYSTEM - A fan variable area nozzle (FVAN) includes a flap driven through a cable which circumscribes the fan nacelle. The cable is strung through a multiple of flaps to define a flap set of each circumferential sector of the EVAN. An actuator system includes a compact high power density electromechanical actuator which rotates a spool to deploy and retract the cable and effectively increase or decrease the length thereof between the spool and a fixed attachment to increase and decrease the fan nozzle exit area. | 01-14-2010 |
20100037588 | VARIABLE FAN NOZZLE USING SHAPE MEMORY MATERIAL - A gas turbine engine ( | 02-18-2010 |
20100043393 | GAS TURBINE ENGINE WITH VARIABLE AREA FAN NOZZLE - A nozzle section of a gas turbine engine includes a regulator system in fluid communication with a secondary flow duct and a tertiary flow duct to selectively regulate communication of secondary airflow into the tertiary flow duct. | 02-25-2010 |
20100043394 | GAS TURBINE ENGINE FAN VARIABLE AREA NOZZLE WITH SWIVALABLE INSERT SYSTEM - A turbofan engine ( | 02-25-2010 |
20100050595 | GAS TURBINE ENGINE WITH AXIAL MOVABLE FAN VARIABLE AREA NOZZLE - A turbofan engine includes a fan variable area nozzle having an axial overlapped nozzle assembly with a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides forward along the engine axis relative the fixed first fan nacelle section to change the effective area of the fan nozzle exit area. | 03-04-2010 |
20100050596 | THRUST VECTORABLE FAN VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE FAN NACELLE - A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates synchronizing ring segments relative the static ring to adjust segments of the flap assembly to vary the annular fan exit area and vector the thrust through asymmetrical movement of the thrust vectorable FVAN segments. In operation, adjustment of the entire periphery of the thrust vectorable FVAN in which all segments are moved simultaneously to maximize engine thrust and fuel economy during each flight regime. By separately adjusting the segments of the thrust vectorable FVAN, engine trust is selectively vectored to provide, for example only, trim balance or thrust controlled maneuvering. | 03-04-2010 |
20100077724 | CORE COWL AIRFOIL FOR A GAS TURBINE ENGINE - An example core nacelle for a gas turbine engine includes a core cowl positioned adjacent an inner duct boundary of a fan bypass passage and having a pocket and an airfoil received within the pocket. The airfoil is moveable between a first position and a second position to adjust a discharge airflow cross-sectional area of the gas turbine engine. | 04-01-2010 |
20100089030 | CONTROLLING THE AERODYNAMIC DRAG OF A GAS TURBINE ENGINE DURING A SHUTDOWN STATE - A gas turbine engine system includes a gas turbine engine ( | 04-15-2010 |
20100095650 | TRANSLATING CORE COWL FOR A GAS TURBINE ENGINE - An example core nacelle includes a core cowl positioned adjacent to an inner duct boundary of a fan bypass passage having an associated discharge airflow cross-sectional area. The core cowl includes a translating section located aft of an exit guide vane positioned within the fan bypass passage. The translating section is moveable to vary the discharge airflow cross-sectional area. | 04-22-2010 |
20100139243 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE, NACELLE ASSEMBLY AND METHOD OF VARYING AREA OF A FAN NOZZLE - A turbofan engine includes a fan variable area nozzle, which includes a louver system having a multiple of slats generally transverse to the engine axis. Each of the louver slats are pivotally mounted to the fan nacelle to vary the effective area of the fan nozzle exit area and permit efficient engine operation at predefined pressure ratios. | 06-10-2010 |
20100154383 | GAS TURBINE ENGINE - An adaptive cycle gas turbine engine is disclosed having a number of features. A fan arrangement is provided having counter-rotating fan stages, one fan stage is operable to be clutched and decoupled from the other stage. A high pressure compressor bypass is also provided. A clutch is provided to at least partially drive an intermediate pressure compressor with a high pressure turbine when the high pressure compressor is bypassed. A partial bypass of the high pressure turbine may be provided. | 06-24-2010 |
20100162683 | TURBOFAN ENGINE - A turbofan engine is provided that includes a fan nacelle surrounding a core nacelle. The core nacelle houses a spool. The fan and core nacelles provide a bypass flow path having a nozzle exit area. A turbofan is arranged within the fan nacelle upstream from the core nacelle. A flow control device is adapted to effectively change the nozzle exit area to obtain a desired operating condition for the turbofan engine. A gear train couples the spool and turbofan for reducing a turbofan rotational speed relative to a spool rotational speed. A controller is programmed to respond to at least one sensor. The controller is programmed to effectively control the nozzle area. | 07-01-2010 |
20100162684 | AIRCRAFT NOZZLE - A nozzle is provided that can be used as part of an aircraft engine. In one form the nozzle includes an inner cowl and an outer cowl. The inner cowl can be actuated to a variety of positions. The outer cowl is piggybacked on the inner cowl and is initially retained in first position relative to the inner cowl with an outer cowl actuator. The outer cowl actuator can be commanded to release the outer cowl so that the outer cowl can be moved to a second position relative to the inner cowl. In one form the outer cowl actuator is an explosive bolt and a spring is provided to urge the outer cowl to the second position. | 07-01-2010 |
20100170220 | TURBOFAN ENGINE HAVING INNER FIXED STRUCTURE INCLUDING DUCTED PASSAGES - A gas turbine engine system includes a fan bypass passage ( | 07-08-2010 |
20100170221 | TURBO FAN ENGINE - A turbo fan engine is equipped with a main body portion that has a high-pressure turbine and a low-pressure turbine, an output portion that is provided separately from the main body portion, a gas flow channel that communicates with a space between the high-pressure turbine and the low-pressure turbine and is connected to the output portion, and a flow rate adjustment portion that is provided in the gas flow channel to adjust a flow rate of a gas flowing through the gas flow channel. | 07-08-2010 |
20100180573 | A GAS TURBINE ENGINE - A gas turbine engine is proposed which comprises a bypass duct, a core engine, and a fluid mixing arrangement. The fluid mixing arrangement is configured to mix a bypass flow of fluid and a secondary flow of fluid, the secondary flow of fluid being drawn from the core engine. The arrangement comprises a flow duct terminating with an outlet and being arranged to direct said secondary flow through the outlet and into the bypass flow. The arrangement is characterised by the provision of a wing in the region of the outlet, said wing extending at least partially across the duct and being configured to generate lift from said secondary flow effective to produce at least one trailing vortex extending into said bypass flow. The fluid mixing arrangement can be used as a ventilation arrangement or as part of a bleed valve arrangement in the gas turbine engine. | 07-22-2010 |
20100180574 | GAS TURBINE ENGINE - A gas turbine engine is disclosed which comprises a bypass duct, a core engine, and a fluid mixing arrangement. The fluid mixing arrangement is configured to mix a bypass flow of fluid and a secondary flow of fluid, the secondary flow of fluid being drawn from the core engine. The arrangement comprises a flow-duct terminating with an outlet and being arranged to direct said secondary flow through the outlet and into the bypass flow. The arrangement is characterised by the provision of a delta-shaped wing in the region of the outlet, said wing extending at least partially across the duct and being configured to generate lift from said secondary flow effective to produce at least one trailing vortex extending into said bypass flow. The fluid mixing arrangement can be used as a ventilation arrangement or as part of a bleed valve arrangement in the gas turbine engine. | 07-22-2010 |
20100199633 | BLEED STRUCTURE FOR A BLEED PASSAGE IN A GAS TURBINE ENGINE - A bleed structure for a bleed passage in a gas turbine engine includes a first wall portion defining a first side of an opening for the passage, and a second wall portion defining a second side, opposite the first side of the opening. The first and second wall portions end at different positions in an extension direction of the opening. | 08-12-2010 |
20110072781 | SYSTEMS AND METHODS FOR PASSIVELY DIRECTING AIRCRAFT ENGINE NOZZLE FLOWS - Systems and methods for passively directing aircraft engine nozzle flow are disclosed. One system includes an aircraft nozzle attachable to an aircraft turbofan engine, with the nozzle including a first flow path wall bounding a first flow path and being positioned to receive engine exhaust products, and a second flow path wall bounding a second flow path and being positioned to receive engine bypass air. The first flow path wall is positioned between the first and second flow paths, and the second flow path wall is positioned between the second flow path and an ambient air flow path. Multiple flow passages can be positioned in at least one of the first and second flow path walls to passively direct gas from a corresponding flow path within the flow path wall through the flow path wall to a corresponding flow path external to the flow path wall. Neighboring flow passages can have neighboring circumferentially-extending and circumferentially-spaced exit openings positioned at an interface with the corresponding flow path external to the flow path wall. | 03-31-2011 |
20110120080 | VARIABLE AREA FAN NOZZLE COWL AIRFOIL - A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The second fan nacelle section being axially movable relative the first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, the second fan nacelle section includes at least one cowl with an inner portion, an outer portion and a multiple of stiffeners therebetween to increase a flutter margin. | 05-26-2011 |
20110120081 | VARIABLE AREA FAN NOZZLE BEARING TRACK - A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that includes a bearing assembly. A VAFN cowl is mounted to the second track slider. | 05-26-2011 |
20110120082 | MULTISTAGE TIP FAN - A fan assembly having an outer fan system is disclosed, the fan assembly comprising an outer fan first stage and an outer fan second stage both extending radially outward from an arcuate platform. | 05-26-2011 |
20110120083 | GAS TURBINE ENGINE WITH OUTER FANS - A gas turbine engine comprising an outer fan system is disclosed, having an outer fan first stage having a circumferential row of outer fan first blades, an outer fan second stage having a circumferential row of outer fan second blades located axially aft from the outer fan first stage wherein the outer fan first stage and the outer fan second stage are adapted to rotate with the fan rotor. | 05-26-2011 |
20110167791 | CONVERTIBLE FAN ENGINE - A gas turbine engine is disclosed having a fan system with a front stage fan rotor and an aft fan rotor coupled to a low-pressure turbine, a core having a compressor coupled to a high-pressure turbine, an annular inner bypass passage and an annular outer bypass passage. The aft fan rotor has a row of aft fan blades having an arcuate splitter that forms a portion of an inner flow passage and an outer flow passage wherein the aft fan blade pressurizes an inner flow and an outer flow and wherein the fan tip pressure ratio can be changed while the air flow into the front stage fan rotor is held substantially constant. | 07-14-2011 |
20110167792 | ADAPTIVE ENGINE - An adaptive gas turbine engine is disclosed having a convertible fan system adapted to have a variable fan pressure ratio while the air flow into the convertible fan system remains substantially constant and an adaptive core having a compressor capable of maintaining a substantially constant core pressure ratio while a core airflow flow rate is varied. | 07-14-2011 |
20110302907 | VARIABLE AREA FAN NOZZLE - A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle in communication with a fan bypass flow path. An actuator assembly is operable to move a second fan nacelle section relative to a first fan nacelle section to vary a fan nozzle exit area and adjust fan bypass airflow, the actuator assembly extends at least partially into the fan bypass flow path. | 12-15-2011 |
20120011827 | BLEED AIR OUTLET IN THE BYPASS DUCT OF A TURBOFAN ENGINE - A bleed air outlet provided in the bypass duct of a turbofan engine includes a bleed air tube protruding into the bypass duct and a cover having a plurality of air outlet openings provided in the top of the cover, with the cover being conceived as an elongate, essentially oval, shell-like aerodynamic fairing element ( | 01-19-2012 |
20120023901 | Variable area fan nozzle for gas turbine engine - A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance. | 02-02-2012 |
20120055137 | FAN BLADES WITH CYCLIC SETTING - A fan portion of a dual flow turbojet engine including a plurality of fan blades, a disk supporting the blades and configured to be rotated relative to a stator portion of the fan, along a longitudinal axis of the fan, and a system for setting the angle of attack associated with each fan blade, the systems configured such that the angle of attack of each blade varies according to a same setting law according to the angular position of the blade relative to the stator portion, along the longitudinal axis, the same setting law being periodic with a period of P=360°/n, where n is an integer at least equal to 1. | 03-08-2012 |
20120067025 | BLOOM MIXER FOR A TURBOFAN ENGINE - An adjustable bloom mixer for a turbofan engine for setting a mixing ratio, adapted to the respective flight condition, between cold airflow in the bypass duct and hot airflow in the core flow duct includes an air-guiding element ( | 03-22-2012 |
20120073263 | GAS TURBINE ENGINE WITH AXIAL MOVABLE FAN VARIABLE AREA NOZZLE - A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle axially movable relative the fan nacelle to define an auxiliary port to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 03-29-2012 |
20120096832 | FLUTTER SENSING AND CONTROL SYSTEM FOR A GAS TURBINE ENGINE - An exemplary gas turbine engine assembly includes a nacelle, a core engine casing within the nacelle, a low pressure turbine having a pressure ratio that is greater than five, and a bypass passage established between the nacelle and the core engine casing. About 80% or more of airflow entering the engine is moved through the bypass passage. | 04-26-2012 |
20120102915 | GAS TURBINE ENGINE BIFURCATION LOCATED FAN VARIABLE AREA NOZZLE - A gas turbine engine includes a core engine defined about an axis, a gear system driven by the core engine, a fan, and a variable area flow system. The gear system defines a gear reduction ratio of greater than or equal to about 2.3. The fan is driven by the gear system about the axis to generate a bypass flow. The variable area flow system operates to effect the bypass flow. | 05-03-2012 |
20120117940 | GAS TURBINE ENGINE WITH PYLON MOUNTED ACCESSORY DRIVE - A gas turbine engine includes an accessory gearbox within an engine pylon. The accessory components may be mounted within the engine pylon to save weight and space within the core nacelle as well as provide a relatively lower temperature operating environment. | 05-17-2012 |
20120124965 | VARIABLE AREA FAN NOZZLE FAN FLUTTER MANAGEMENT SYSTEM - A gas turbine engine includes a controller that controls a fan blade flutter characteristic through control of a variable area fan nozzle. | 05-24-2012 |
20120131902 | AFT FAN ADAPTIVE CYCLE ENGINE - A gas turbine engine includes: a front fan having at least one rotor carrying fan blades disposed within a fan duct, and drivingly connected to a low pressure turbine, the front fan including at least one row of outer fan blades disposed outwardly of and connected to the fan blades, the outer fan blades extending across an outer bypass duct which circumscribes the fan duct; a core engine located between the front fan and the low pressure turbine; an aft fan disposed downstream of the low pressure turbine, having at least one rotor carrying aft turbine blades disposed within an aft turbine duct, the aft turbine further including at least one row of aft fan blades disposed outwardly of and connected to the aft turbine blades, and extending across an aft fan duct that surrounds the core engine; and apparatus operable to selectively throttle flow through the outer bypass duct. | 05-31-2012 |
20120198815 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine. | 08-09-2012 |
20120198816 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages. | 08-09-2012 |
20120198817 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train. | 08-09-2012 |
20120222397 | GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO - A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 09-06-2012 |
20120222398 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A turbofan engine includes a geared architecture and a fan variable area nozzle axially movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 09-06-2012 |
20120233981 | GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO - A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. | 09-20-2012 |
20120233982 | GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages. | 09-20-2012 |
20120255276 | LOAD LIMITED ACTUATOR - An actuator includes a first piston and a second piston. The first piston has a piston ring that separates a first chamber from a second chamber of the actuator. The first piston has an interior chamber that communicates with the first chamber. The second piston is disposed within the interior chamber of the first piston so as to be movable with respect thereto. The second piston has a surface that interfaces with the second chamber. | 10-11-2012 |
20120279198 | GAS TURBINE ENGINE WITH BYPASS MIXER - One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 11-08-2012 |
20130008146 | EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES - A gas turbine engine includes a spool, a turbine coupled to drive the spool, and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 20 of the propulsor blades. | 01-10-2013 |
20130008147 | Aircraft gas turbine with variable bypass nozzle - The present invention relates to an aircraft gas turbine with a core engine | 01-10-2013 |
20130014489 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train. | 01-17-2013 |
20130014490 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine. | 01-17-2013 |
20130019585 | VARIABLE FAN INLET GUIDE VANE FOR TURBINE ENGINE - A turbine engine includes a compressor section, a combustor arranged in fluid-receiving communication with the compressor section, a turbine section arranged in fluid-receiving communication with the combustor and a gearbox assembly coupled to be driven by the turbine section. The gearbox assembly is located at an axial position that is aft of the compressor section. | 01-24-2013 |
20130145744 | SYSTEM FOR DIRECTING AIR FLOW TO A PLURALITY OF PLENA - A system for directing air flow to separate plena of a compartment that is defined at least by a compartment wall includes a NACA scoop, and a Pitot scoop. The NACA scoop is formed in the compartment wall, and includes two side walls, a bottom wall, and an entrance lip that is defined by the compartment wall and is spaced apart from the bottom wall to form a NACA scoop air inlet. The Pitot scoop is longitudinally aligned with the NACA scoop, includes a Pitot scoop air inlet, a Pitot scoop air outlet, and a Pitot scoop flow passage. | 06-13-2013 |
20130145745 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO - A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45. | 06-13-2013 |
20130160425 | VARIABLE AREA FAN NOZZLE WITH DRIVE SYSTEM HEALTH MONITORING - A nacelle for a turbofan engine includes a variable area fan nozzle (VAFN) and a proximity sensor that is attached to a nacelle forward portion to sense the presence of the VAFN when stowed. The proximity sensor is not attached to the VAFN, thereby enabling the use of a proximity sensor such as linear variable displacement transformer having a relatively compact operational stroke. | 06-27-2013 |
20130174534 | SYSTEM AND DEVICE FOR CONTROLLING FLUID FLOW THROUGH A GAS TURBINE EXHAUST - A system and device for controlling fluid flow through a gas turbine exhaust. One gas turbine exhaust may include a strut of the gas turbine exhaust having a first opening configured to permit a fluid to flow between an interior portion of the strut and an exterior portion of the strut. The gas turbine exhaust also may include a moveable plate coupled to the strut and configured to control an amount of the fluid flowing through the first opening. | 07-11-2013 |
20130192200 | GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE - A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine. | 08-01-2013 |
20130192201 | GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE - A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine. | 08-01-2013 |
20140041360 | FLOW CONDUCTING ASSEMBLY FOR COOLING THE LOW-PRESSURE TURBINE HOUSING OF A GAS TURBINE JET ENGINE - A gas turbine jet engine having a main flow channel ( | 02-13-2014 |
20140060005 | MAGNETIC ADVANCED GENERATION JET ELECTRIC TURBINE - Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exoskeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture. Engine performance may be controlled across the entire desired flight envelope, whether subsonic, transonic or supersonic flight conditions. | 03-06-2014 |
20140096509 | Geared Turbofan Engine With Increased Bypass Ratio and Compressor Ratio ... - A gas turbine engine is typically comprised of a fan stage, multiple compressor stages, and multiple turbine stages. These stages are made up of alternating rotating blade rows and static vane rows. The total number of blades and vanes is the airfoil count. An overall pressure ratio is greater than 30. A bypass ratio is greater than 8. A stage ratio is the product of the bypass ratio and the overall pressure ratio divided by the number of stages. An airfoil ratio is that product divided by the airfoil count. The stage ratio is greater than or equal to 22 and/or the airfoil ratio is greater than or equal to 0.12. | 04-10-2014 |
20140102076 | Turbine Section of High Bypass Turbofan - A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170. | 04-17-2014 |
20140130479 | Gas Turbine Engine With Mount for Low Pressure Turbine Section - A gas turbine engine includes a very high speed low-pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for a higher pressure turbine is at a ratio between about 0.5 and about 1.5. In addition, the lower pressure turbine is mounted with a first bearing mounted in a mid-turbine frame, and a second bearing mounted within a turbine exhaust case. | 05-15-2014 |
20140237990 | VARIABLE AREA FAN NOZZLE WITH WALL THICKNESS DISTRIBUTION - A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nacelle is arranged around the fan, and a bypass passage extends between the fan nacelle and the core engine. A variable area fan nozzle (VAFN) extends at least partially around the central axis and defines an exit area of the bypass passage. The VAFN is selectively movable to vary the exit area. The VAFN includes a body that defines an airfoil cross-section shape. The VAFN includes a wall that has a mechanical property distribution in accordance with a computer-simulated vibration profile of a flutter characteristic of the VAFN. | 08-28-2014 |
20140290213 | DUCT BLOCKER SEAL ASSEMBLY FOR A GAS TURBINE ENGINE - A seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section. | 10-02-2014 |
20140298772 | MISCHVORRICHTUNG UND TURBOFANTRIEBWERK MIT EINER DERARTIGEN MISCHVORRICHTUNG - The invention relates to a mixing device and a turbofan engine having such a mixing device | 10-09-2014 |
20140345253 | MULTI-NOZZLE FLOW DIVERTER FOR JET ENGINE - An exhaust system for a variable cycle aircraft engine. The exhaust system comprises a core exhaust for bypass air and hot gases of combustion. The core exhaust includes a convergent-divergent nozzle. The convergent-divergent nozzle is formed from a plurality of flaps and seals. The exhaust system comprises a third air duct for a third stream of air. The third stream of air is selectively exhausted from the third duct through a secondary nozzle or divergent slots in the convergent-divergent nozzle, or both depending upon the flight mode. A diverter valve is positioned in the third stream duct to selectively control the flow of third stream air through the secondary nozzle, the divergent slots and combinations thereof. | 11-27-2014 |
20140345254 | SECONDARY NOZZLE FOR JET ENGINE - A third stream duct producing a third air stream at reduced pressure that is exhausted through a separate nozzle that is concentric with the main or primary engine nozzle. The third stream exhaust air from the separate concentric nozzle is exhausted to a location at which pressure is ambient or sub-ambient. The location at which the third stream air is exhausted contributes to the thrust of the aircraft. The airstream from the third air duct is exhausted through an exhaust nozzle of the third duct that is positioned at the interface between the aft of the airframe and the leading edge of the engine outer flaps. This location is a low pressure region that has a recirculation zone. The exhaust of third stream air to this low pressure region substantially reduces or eliminates this recirculation zone and associated boat tail drag, thereby improving the efficiency of the engine. | 11-27-2014 |
20150059315 | APPARATUS AND METHOD FOR BLEEDING OFF COMPRESSOR AIR IN A JET ENGINE - A device and a method for bleeding compressor air in an engine includes at least one actuator and at least one closing element linked to the actuator for closing or partially closing a bypass duct via which compressor air can be bled off. It is provided here that the closing element is designed to be successively moved into the bypass duct, with the airflow passing through the bypass duct being settable by the position of the closing element. Furthermore, an air guiding device linked to the closing element is provided and has air guiding surfaces which adjoin the closing element downstream, the spatial alignment of the air guiding surfaces being dependent on the position of the closing element. | 03-05-2015 |
20150107223 | HIGH DURABILITY TURBINE EXHAUST CASE - A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material. | 04-23-2015 |
20150308374 | SINGLE ACTUATOR VARIABLE AREA FAN NOZZLE SYSTEM AND METHOD - A single actuator variable area fan nozzle (“VAFN”) system is provided. In contrast to typical system, the single actuator VAFN may comprise a single actuator, a linkage and a VAFN panel. The single actuator may be configured to actuate the VAFN panel between a stowed position and a deployed position. In various embodiments, the linkage may travel a path during deployment and/or retraction that is between the loft lines of the nacelle. | 10-29-2015 |
20160053717 | GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE TO REDUCE FAN INSTABILITY - A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle movable relative a fan nacelle to vary a fan nozzle exit area to reduce a fan instability. | 02-25-2016 |
20160053721 | GAS TURBINE ENGINE AND METHOD OF OPERATION - A gas turbine engine ( | 02-25-2016 |