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| Number | Title | Issue Date |
| 8104263 | Actuator arrangement for vectorable nozzles of gas turbine An actuator arrangement for moving a first component relative to a second component, the arrangement comprising: an actuator chamber for receiving a fluid under pressure, a side wall of the chamber being fixed relative to the first component; an actuating element fi... | 01/31/2012 |
| 8061119 | Actuation mechanism for a convertible gas turbine propulsion system An actuation mechanism for use in a convertible gas turbine propulsion system comprises a plenum, a pneumatically powered drive body and a spring system. The plenum receives pressurized air from the convertible gas turbine propulsion system. The pneumatically powere... | 11/22/2011 |
| 7975467 | Apparatus for driving body with three-degree of freedom angular motion An apparatus for driving a body with 3-degree of freedom angular motion, comprises: a body connected to a fixing part so as to be rotatable centering around a pitch axis, a yaw axis, and a roll axis; a pitch axis driving unit for rotating the body centering around t... | 07/12/2011 |
| 7770379 | Apparatus for moving rotatable components The present invention provides an actuating apparatus for moving relatively rotatable components. In one embodiment the apparatus comprises: a bearing (30) including first (34) and second (36) relatively rotatable bearing elements for mounting r... | 08/10/2010 |
| 7581382 | Gas turbine engine air valve assembly A gas turbine engine air valve assembly has first and second valving elements. The second element is rotatable about a first axis relative to the first element. The rotation controls a flow of air through the first and second elements. An actuator is coupled by a li... | 09/01/2009 |
| 7555894 | Swivelling exhaust nozzle for an aircraft engine Swivelling nozzle for an aircraft engine, the nozzle 10 being pivotally mounted about a transverse yaw axis by means of two elastically deformable one-piece articulations 24 mounted on two external pivots 22 of the nozzle and housed in engine ca... | 07/07/2009 |
| 7406821 | Adapter device for a rocket engine nozzle having a movable diverging portion An adapter device for controlling a rocket engine nozzle under conditions of external pressure that can lead to the jet separating inside the nozzle, the nozzle being fitted with a diverging portion that is movably mounted relative to a stationary portion of the noz... | 08/05/2008 |
| 7313910 | Jet vane thrust vector control system Disclosed is a jet vane thrust vector control (JV-TVC) system. A general system has many problems in design techniques considering actual operation environments, and does not have reliability in component assembly design. The JV-TVC system improves thrust vector con... | 01/01/2008 |
| 7302793 | Methods and apparatus to reduce turbine engine nozzle basesheet stresses A method facilitates assembling a flap system for a gas turbine engine exhaust nozzle including at least one backbone assembly. The method comprises providing a basesheet including a pair of circumferentially-spaced sides coupled together by an upstream side and a d... | 12/04/2007 |
| 7296397 | Ventilation system for a convergent divergent exhaust nozzle The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle... | 11/20/2007 |
| 7287504 | Over-center actuator The disclosure allows a short runner valve or manifold tuning valve type manifold tuning device to retain sufficient force on the valve assembly in its closed state to eliminate any vibration or chatter from the system under normal engine operation. The disclosure a... | 10/30/2007 |
| 7269951 | Throat retention apparatus for hot gas applications A nozzle for use in a hot gas valve is provided that includes a housing, an insert, and a throat retainer. The housing is constructed of an insulating material and has a flow path formed therein. The flow path has a throat section. The insert is made of material cap... | 09/18/2007 |
| 7225622 | Turbine engine nozzle A turbine engine nozzle assembly has an upstream flap and a downstream flap pivotally coupled thereto for relative rotation about a hinge axis. An actuator linkage is coupled to the downstream flap along a forward portion thereof for actuating the upstream flaps and... | 06/05/2007 |
| 7219490 | Nested core gas turbine engine A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section. ... | 05/22/2007 |
| 7216476 | Two-axis thrust vectoring nozzle A nozzle for a jet engine generally includes a nozzle rim and a bendable duct for communicating an exhaust flow generated by the engine to the nozzle rim. A gimbal joint pivotably couples the nozzle rim to supporting structure. The gimbal joint allows the nozzle rim... | 05/15/2007 |
| 7178325 | Divergent flap for a gas turbine engine A divergent flap assembly of a gas turbine engine includes a hotsheet, a backbone structure for supporting the hotsheet, and a plow portion secured to the backbone structure to bridge a gap between the hotsheet and an external flap. The plow portion is fabricated fr... | 02/20/2007 |
| 7134271 | Thrust vectoring aft FLADE engine An aft FLADE gas turbine engine including a fan section drivenly connected to a low pressure turbine section followed by an aft FLADE turbine having at least one row of aft FLADE fan blades radially extending across a FLADE duct circumscribing the aft FLADE turbine,... | 11/14/2006 |
| 7096662 | Variable area throat exhaust nozzle with vectorable sideways shifting of exhaust flow A nozzle includes a sideways split and aftwardly swept nozzle ramp extends between a fixed lower nozzle wall and a pivotal upper nozzle wall pivotally connected to an aft end of the nozzle and operable to vary a throat area of a throat of the nozzle. The upper and l... | 08/29/2006 |
| 7096661 | Axial divergent section slot nozzle An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross sectional area of the nozzle in a throat region, and a bridge member po... | 08/29/2006 |
| 7062901 | Variable geometry nozzle with flexible side wall The disclosed device is directed toward a periodic combustion propulsion system. The periodic combustion propulsion system comprises at least one periodic combustion chamber configured to contain periodic combustion and at least one supersonic exhaust nozzle coupled... | 06/20/2006 |
| 7055307 | Vectorable nozzle with sideways pivotable ramp A vectorable nozzle includes a longitudinally extending upper fixed wall spaced upwardly and aftwardly of a longitudinally extending lower fixed wall and an aftwardly swept fixed ramp extending between the upper and lower fixed walls. The upper and lower fixed walls... | 06/06/2006 |
| 7028462 | Method and apparatus for arresting a crack within a body An inseparable assembly includes a body having a plurality of plies stacked in face to face relation and bonded together, wherein each of the plurality of plies includes a ceramic matrix composite material having a first predetermined ductility. The assembly further... | 04/18/2006 |
| 7013650 | Flexible flap for a variable-section turbomachine nozzle In a variable-section turbomachine nozzle, a plurality of flexible follower flaps are provided that are interposed between adjacent controlled flaps against which the follower flaps are held by fastener means, each follower flap comprising a plurality of independent... | 03/21/2006 |
| 6969028 | Scarf nozzle for a jet engine and method of using the same A scarf nozzle for a jet engine supported within a nacelle. The scarf nozzle is at an aft end of the nacelle. The scarf nozzle includes a first trailing edge portion and a second trailing edge portion. The second trailing edge portion is disposed aft of the first tr... | 11/29/2005 |
| 6948307 | Rocket engine nozzle that is steerable by means of a moving diverging portion on a cardan mount The nozzle comprises a moving diverging portion (20) and a static portion (16) secured to the rear end wall of the combustion chamber (12) of the engine. A cardan mount jointed link device connects the moving diverging portion of the nozzle to t... | 09/27/2005 |
| 6938408 | Thrust vectoring and variable exhaust area for jet engine nozzle A jet engine nozzle having a pair of pivoting extension arms and a pair of pivoting shells connected to a jet pipe is provided. The first extension arm is pivotally connected to the jet pipe at a first location, while the second extension arm is pivotally connected ... | 09/06/2005 |
| 6935118 | Exhaust nozzle segmented basesheet and production method thereof A basesheet for use in an aircraft gas turbine engine exhaust nozzle includes a plurality of basesheet segments extending between longitudinally extending spaced apart basesheet leading and trailing edges, respectively, of the basesheet. Right and left hand baseshee... | 08/30/2005 |
| 6910328 | Vectorable variable area nozzle A vectorable variable area nozzle is formed by a pair of parallel sidewalls, a pair of opposed clamshell elements arranged between the sidewalls and each able to rotate about an axis perpendicular to the sidewalls and a pair of flaps each pivotally lined to the down... | 06/28/2005 |
| 6779336 | Cooled variable geometry exhaust nozzle A variable geometry exhaust nozzle 10 for a turbine engine includes convergent and divergent flaps 12, 18 that circumscribe a gaspath 26 and define convergent and divergent nozzle sections 30, 32 with a throat 34 therebetween. A pr... | 08/24/2004 |
| 6758437 | Rocket engine nacelle A nacelle comprised of a rigid shroud and a support truss. The shroud encloses the truss and a rocket engine. The shroud is comprised of three sections, including a top section and two side sections. The top section has openings to permit the communication of lines ... | 07/06/2004 |
| 6735936 | Variable area nozzle for gas turbine engines driven by shape memory alloy actuators A gas turbine engine includes a variable area nozzle having a plurality of flaps. The flaps are actuated by a plurality of actuating mechanisms driven by shape memory alloy (SMA) actuators to vary fan exist nozzle area. The SMA actuator has a deformed shape in its m... | 05/18/2004 |
| 6694723 | Valve assembly for gas turbine engine A valve assembly for supplying cooling air to a nozzle of a gas turbine engine. The nozzle can move between a first configuration and a second configuration. The valve assembly includes a first member having openings that receive cooling air. The valve as... | 02/24/2004 |
| 6622472 | Apparatus and method for thrust vector control A multi-lobed, low friction vane, thrust vector controller is disclosed. Low friction vanes are independently movable into and out of the thrust of the exhaust of a jet engine. All vanes may be used together to adjust exhaust surface area to maximize thru... | 09/23/2003 |
| 6546716 | Jet engine nozzle with variable thrust vectoring and exhaust area A variable area exhaust nozzle with a variable thrust vector angle for a turbo-fan engine and mounted on the aft portion of the nacelle which wraps said engine. The nozzle may include a fixed structure having at least two lateral arms separating two radia... | 04/15/2003 |
| 6508055 | Variable mode jet engine--suitable for STOVL This jet engine comprises a complete low bypass turbofan unit 1 including secondary fan unit 2 and engine core, ahead of which sits a larger diameter main fan unit 3 driven from the front of the secondary fan via a long drive shaft 4. A center portion of ... | 01/21/2003 |
| 6385965 | System for activating a steerable thrust-vectoring nozzle for a jet propulsion system using several circumferentially distributed elastic assemblies A steerable nozzle for a reaction engine comprises a fixed portion (1) for fixing to the engine, a moving portion (2) hinged to the fixed portion, control means (3) for controlling the moving portion, and one or more resilient assemblies (4) disposed betw... | 05/14/2002 |
| 6378294 | System for activating an adjustable tube by means of an elastic ring for a thrust nozzle A steerable nozzle for a reaction engine comprises a fixed portion (1) for connection to the engine, a plurality of steerable flaps (21) mounted on one end (11) of the fixed portion, and flap steering means (3, 4, 22, 31). The nozzle is characterized in t... | 04/30/2002 |
| 6360527 | Axisymmetric, converging-diverging exhaust nozzle swiveled by a guided ring An axisymmetric, converging-diverging exhaust nozzle swiveled by a guided vectoring ring (20). The guides comprise three axial apertures (44) which are each located in a base firmly joined to relatively fixed structure and of which the center planes inter... | 03/26/2002 |
| 6349539 | Axisymmetric, converging-diverging, jet-deflecting turbojet-engine exhaust-nozzle An axisymmetric, converging-diverging turbojet-engine exhaust nozzle for jet deflection. The diverging flaps are connected by linkrods to a vectoring ring (13). The vectoring ring (13) is driven by linear actuators (20) anchored in the stationary structur... | 02/26/2002 |
| 6327846 | Universal-joint vectoring system for a turbojet-engine exhaust nozzle The invention relates to a wide-vectoring, axisymmetric turbojet-engine exhaust nozzle including vectoring structure (12) supporting a plurality of converging flaps (21). The vectoring structure is mounted on the downstream end of an exhaust housing (2) b... | 12/11/2001 |
