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| Number | Title | Issue Date |
| 8156745 | Exhaust nozzle seal with segmented basesheet An aircraft gas turbine engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments. Each of the basesheet segments includes a panel body between segment leading and trailing edges and slidable sealing joints with slidingly un-r... | 04/17/2012 |
| 8141366 | 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. ... | 03/27/2012 |
| 8122722 | Exhaust nozzle seal with segmented basesheet disposed between side rails An aircraft engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments having panel bodies between segment leading and trailing edges and slidable sealing joints with slidingly un-restrained center surfaces between adjacent seg... | 02/28/2012 |
| 8087250 | Duplex tab exhaust nozzle An exhaust nozzle includes a conical duct terminating in an annular outlet. A row of vortex generating duplex tabs are mounted in the outlet. The tabs have compound radial and circumferential aft inclination inside the outlet for generating streamwise vortices for a... | 01/03/2012 |
| 8061145 | Arrangement for propelling an aircraft, aircraft and outlet nozzle for a jet engine The invention relates to an arrangement for propelling an aircraft comprising a jet engine and an outlet nozzle arranged downstream of the jet engine. The jet engine is of a type which generates an internal core flow and an external fan flow. A part of the outlet no... | 11/22/2011 |
| 8047004 | Stave and ring CMC nozzle An engine exhaust nozzle comprises a plurality of CMC staves attached to one or more support rings arranged axially. The support rings provide a circumferential load path between the staves and for attaching the exhaust nozzle to the metallic engine components. The ... | 11/01/2011 |
| 8015820 | Gas turbine engine exhaust component and manufacturing method of same A gas turbine exhaust component, such as an exhaust nozzle, is provided that includes circumferential ribs arranged along a longitudinal axis. Longitudinal strakes are supported by the circumferential ribs and arranged about the longitudinal axis. Fastening elements... | 09/13/2011 |
| 8015819 | Wet active chevron nozzle for controllable jet noise reduction Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fash... | 09/13/2011 |
| 7975488 | Low profile attachment hanger system for a cooling liner within a gas turbine engine swivel exhaust duct An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachm... | 07/12/2011 |
| 7966824 | Jet engine nozzle exit configurations and associated systems and methods Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter tha... | 06/28/2011 |
| 7966826 | Systems and methods for reducing noise from jet engine exhaust Jet engine nozzles with projections (e.g., chevrons) and injected flow, and associated systems and methods are disclosed. A method in accordance with one embodiment includes generating a first flow of gas with a jet engine, delivering the first flow through a nozzle... | 06/28/2011 |
| 7966825 | Exhaust eductor system with a recirculation baffle An exhaust educator system includes a primary exhaust nozzle configured to transport an active flow stream; and a mixing duct at least partially surrounding the primary exhaust nozzle and configured to transport a passive flow stream that is entrained by mixing with... | 06/28/2011 |
| 7966827 | 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 n... | 06/28/2011 |
| 7958733 | Jet engine exhaust nozzle flow effector A jet engine exhaust nozzle flow effector is a chevron formed with a radius of curvature with surfaces of the flow effector being defined and opposing one another. At least one shape memory alloy (SMA) member is embedded in the chevron closer to one of the chevron's... | 06/14/2011 |
| 7950236 | Exhaust duct and tail cone attachment of aircraft engines An annular exhaust duct of a gas turbine engine includes inner and outer cases co-axially disposed, and radially spaced apart by a plurality of airfoils radially extending therebetween. The outer case includes a connection apparatus for supportably connecting the ex... | 05/31/2011 |
| 7926285 | Modular chevron exhaust nozzle An exhaust nozzle for a gas turbine engine includes a modular chevron. The chevron includes dual skins fixedly joined together at a base flange, and at a rim extending along the trailing edge of the chevron between the base and apex thereof. ... | 04/19/2011 |
| 7900460 | Outlet device for a jet engine and a jet engine comprising such an outlet device An outlet device for a jet engine includes an outlet nozzle and a plurality of guide vanes arranged movably in the outlet nozzle for guiding a gas from the jet engine for the purpose of steering a craft equipped with the jet engine. At least one of the guide vanes c... | 03/08/2011 |
| 7900459 | Inner plenum dual wall liner An exhaust nozzle assembly includes an inner liner exposed to hot combustion gases and an outer liner spaced a radial distance from the inner liner to form an annular chamber. The inner liner includes a hot side that is directly exposed to the hot combustion gas flo... | 03/08/2011 |
| 7891195 | Central body of a turbojet nozzle A device for attenuating acoustical noise from an exhaust nozzle of a turbojet is disclosed. The turbojet exhaust nozzle includes a central body defining the inner surface of the primary gas flow path. The central body includes an outer wall defining one, and only o... | 02/22/2011 |
| 7886543 | Central body for a turbojet exhaust channel, turbojet A device for attenuating acoustic noise from an exhaust nozzle of a turbojet is disclosed. The turbojet exhaust nozzle includes a central body spaced apart from an external casing, defining a gas exhaust channel therebetween. The central body includes a flexible sle... | 02/15/2011 |
| 7870741 | Turbine engine valve assembly and method of assembling the same A method of assembling a crank assembly for a turbine engine. The turbine engine includes a valve assembly including an outer fairing and an inner fairing coupled to the outer fairing with a strut. The valve assembly further includes an annular slide valve coupled b... | 01/18/2011 |
| 7866158 | Exhaust liner attachment arrangement A turbine engine exhaust nozzle is disclosed that includes an exhaust liner having a first attachment structure. A liner support member includes a second attachment structure. A pin cooperates with the first and second attachment structures and is configured to secu... | 01/11/2011 |
| 7854123 | Turbomachine nozzle cover provided with triangular patterns having pairs of vertices for reducing jet noise The pattern relates to a cover for a turbomachine nozzle, the cover having a plurality of patterns each with an outline of triangular shape having a base and two vertices that are spaced downstream and interconnected by a side. For each pattern, the vertices present... | 12/21/2010 |
| 7845176 | Mode strut and divergent flap interface In one example, a gas turbine engine includes an exhaust nozzle. The exhaust nozzle includes a flap supported relative to a static structure by a strut. The flap includes a backbone providing a slot. A slider interconnects a strut end to the backbone. In one example... | 12/07/2010 |
| 7845175 | Heat shield for mounting on a heat-radiating object, particularly on a rocket engine A heat shield for mounting on a heat-radiating object, particularly on a rocket engine comprises a first planar element having a front side and a back side. In its mounted state, the first planar element extending from the heat-radiating object toward the outside, w... | 12/07/2010 |
| 7836700 | Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flaws An exhaust flow system for use with a turbofan jet engine that provides separate fan flow and core flow streams that are not mixed. The system includes a fan nozzle and a primary flow nozzle. The primary flow nozzle includes a downstream edge portion that is either ... | 11/23/2010 |
| 7827802 | Variable-section flow mixer for a double-flow turbojet for a supersonic airplane The invention relates to a variable-section flow mixer for a double-flow turbojet for a supersonic airplane, the mixer comprising a central body, a primary cover, a secondary cover, and a nozzle extending the secondary cover. The nozzle has a plurality of external-a... | 11/09/2010 |
| 7810335 | Core exhaust mixer, having a variable area, for turbo-fan jet engines of supersonic aircraft The invention relates to a core exhaust mixer, having a variable area, for turbo-fan jet engines of supersonic aircraft, comprising a nozzle (24) intended to be arranged about a gas generator of the jet engine, the nozzle comprising a plurality of external ai... | 10/12/2010 |
| 7793504 | Nozzle with an adjustable throat One embodiment of the present invention includes a nozzle defining a passage to receive and discharge working fluid to produce thrust. The nozzle includes the first wall structure opposite a second wall structure. The first wall structure includes a first convergent... | 09/14/2010 |
| 7784283 | Sound-absorbing exhaust nozzle center plug A sound-absorbing exhaust nozzle center plug for an aircraft gas turbine engine can include an outer skin and at least one forward cavity within the outer skin. At least one aft cavity can be located within the outer skin and substantially aft of the forward cavity.... | 08/31/2010 |
| 7784284 | Exhaust assembly forming a horizontal propulsion gas elbow in an aircraft A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator is disclosed. The exhaust assembly includes a duct which forms a vertical elbow and a nozzle. ... | 08/31/2010 |
| 7784285 | Apparatus and method for reduction of jet noise from single jets An exhaust flow nozzle for use with a jet engine. The exhaust flow nozzle includes a beveled downstream edge portion that helps to direct noise generated by the jet engine upwardly away from a ground surface during takeoff and landing operations. One specific embodi... | 08/31/2010 |
| 7775048 | Seal assembly A sprung seal assembly includes a flexible sprung seal having a center section disposed between opposing curved and cantilevered first and second end sections. First and second free edges of the first and second end sections respectively are trapped within a retaine... | 08/17/2010 |
| 7770399 | Gas turbine engine nozzle liner with thermally compliant attachment brackets A gas turbine engine has the convergent flaps and seals of an adjustable cross-sectional area nozzle connected to associated liners with a thermally compliant bracket. The bracket includes spaced feet with an intermediate notch spaced away from the liner. In this ma... | 08/10/2010 |
| 7739872 | Cooled dual wall liner closeout An example exhaust duct assembly includes a front liner, an intermediate liner and a rear liner. Each of the front, intermediate and rear liners include an inner liner exposed to combustion gases and an outer liner spaced radially apart from the inner liner. An air ... | 06/22/2010 |
| 7721549 | Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area through a cam drive ring. The flap assembly generally includes a multiple of flaps, flap linkages and an actuator system. The actuator system rotationally translates the c... | 05/25/2010 |
| 7698896 | Compact, light weight eductor oil cooler plenum and surge flow plenum design An eductor assembly is provided that includes a primary nozzle, a cooler plenum, and a surge plenum. In one embodiment, and by way of example only, the primary nozzle is configured to accelerate and discharge turbine exhaust gas therefrom and the cooler plenum surro... | 04/20/2010 |
| 7681399 | Turbofan engine cowl assembly and method of operating the same A turbofan engine assembly is provided. The turbofan engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core... | 03/23/2010 |
| 7681400 | Exhaust assembly forming a horizontal propulsion gas elbow in an aircraft A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along an axis of the aircraft by a gas generator is disclosed. The propulsion gas exhaust assembly includes a transition element emerging in two duct elements each communicating with an... | 03/23/2010 |
| 7673458 | Turbofan engine nozzle assembly and method for operating the same A method for operating a turbofan engine assembly including a core gas turbine engine is provided. The method includes varying an operating speed of the turbofan engine assembly from a first operating speed to a second operating speed. The method also includes selec... | 03/09/2010 |
