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| Number | Title | Issue Date |
| 8356468 | Gas turbine engine nozzle configurations In one embodiment, a gas turbine engine exhaust nozzle comprises a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior surface, and a row of chevrons extending from an aft end of the housing, the... | 01/22/2013 |
| 8341934 | Infrared suppression system with spiral septum An InfraRed Suppression System (IRSS) includes a double-walled exhaust duct and double walled septum. The double walled structure provides a flow path for secondary (non-exhaust gas) cooling air flow to slots along the surfaces exposed to exhaust gases. Exhaust gas ... | 01/01/2013 |
| 8276364 | Bladder type variable area fan nozzle A variable fan nozzle for use in a gas turbine engine includes a nozzle section, such as an inflatable bladder, associated with a fan bypass passage for conveying a bypass airflow. The nozzle section has an internal fluid pressure that is selectively variable to inf... | 10/02/2012 |
| 8205434 | Joint for a shape memory material A joint including a first component and a second component. The second component including a shape memory material component. The first component has a half dovetail shaped slot and the shape memory material second component has a half dovetail shaped attachment fea... | 06/26/2012 |
| 8161728 | Gas turbines with multiple gas flow paths A representative gas turbine includes: a high pressure spool; a high pressure compressor; a high pressure turbine mechanically coupled to the high pressure spool; a lower pressure spool; a lower pressure turbine mechanically coupled to the lower pressure spool; a fa... | 04/24/2012 |
| 8156727 | Fan nozzle of adjustable section An adjustable section nozzle having a ring of deformable panels arranged close to its trailing edge is disclosed. Each panel has a dual-strip type structure made up of two materials presenting different coefficients of expansion, together with controlled heater devi... | 04/17/2012 |
| 8104265 | Gas turbines with multiple gas flow paths An representative gas turbine includes: a first annular gas flow path; a second annular gas flow path located radially outwardly from the first gas flow path; in series order, a multi-stage fan, radially inboard portions of a first set of high pressure compressor bl... | 01/31/2012 |
| 8069648 | Impingement cooling for turbofan exhaust assembly A cooling system for a turbine exhaust assembly comprises an annular case, a flowpath ring and a splash plate. The flowpath ring is coaxially disposed within the annular case. The splash plate extends axially between the annular case and the flowpath ring. A plurali... | 12/06/2011 |
| 8020368 | Aircraft jet engine provided with a device for reducing propulsion jet noise A nozzle allowing the reduction of noise generated by aircraft jet engines having at least one output ring which disturbs the propulsion jet, and having at least one pair of conduits from which the propulsion of jet air is ejected at the output of the nozzle. The co... | 09/20/2011 |
| 7963099 | Fluted chevron exhaust nozzle A gas turbine engine exhaust nozzle includes a fluted shell terminating in a row of chevrons. The nozzle is radially serpentine circumferentially around the shell and has a circumferentially serpentine trailing edge. ... | 06/21/2011 |
| 7882696 | Integrated support and mixer for turbo machinery A support and air mixer includes an inner annular member, an outer annular member shaped and positioned such that an annular air gap is formed between the inner annular member and the outer annular member, and a plurality of air mixing members, each air mixing membe... | 02/08/2011 |
| 7805924 | Thermally decoupled mixer The present invention provides a mixer assembly including a mixer and a plurality of scoops attached around a circumference of the mixer element via a combination of sliding brackets and fixed brackets. The sliding brackets provide attachment and allow relative move... | 10/05/2010 |
| 7784270 | Rotary motion mixer for a converging-stream nozzle of a turbomachine The invention relates to a mixer for a bypass turbomachine, the mixer comprising a member having a sinusoidal portion at its end defining inner lobes and outer lobes, each outer lobe comprising a pair of plane radial walls spaced apart from each other in the circumf... | 08/31/2010 |
| 7721526 | Turbofan engine A turbofan engine has a fan on a front side thereof and a turbine driving the fan. The turbofan engine includes a disk rotationally driven by the turbine, a spinner detachably mounted at a front side of the disk, a spiral blade integrally mounted on a surface of the... | 05/25/2010 |
| 7677026 | Mixer for separate-flow nozzle A mixer for a separate-stream turbojet nozzle, the mixer comprising along a longitudinal axis (X-X′) both a fastener shroud (10) for connecting said mixer to the exhaust casing of the nozzle, and a lobe structure (20) presenting a succession of inner... | 03/16/2010 |
| 7658063 | Gas turbine having a single shaft bypass configuration A gas turbine engine used in an aircraft includes a fan to provide a bypass flow through the engine. The fan delivers some airflow to the compressor for compression, and a fuel is mixed with the compressed air and delivered to a turbine to drive the engine and compr... | 02/09/2010 |
| 7581384 | Turbomachine nozzle cover provided with triangular patterns having a point of inflexion for reducing jet noise The invention relates to an annular cover for a turbomachine nozzle, the cover having a plurality of patterns extending a trailing edge of said cover and spaced apart circumferentially from one another, each pattern having an outline that is substantially triangular... | 09/01/2009 |
| 7520124 | Asymmetric serrated nozzle for exhaust noise reduction An exhaust nozzle for use in a gas turbine engine comprises a flow body for receiving exhaust gas from the turbine engine and includes a leading edge and a trailing edge. The leading edge connects with the gas turbine engine such that the flow body surrounds a cente... | 04/21/2009 |
| 7506501 | Compact mixer with trimmable open centerbody Compact exhaust mixer assemblies comprising a compact mixer and a trimmable open centerbody are provided. The trimmable center body allows for adjustments of the open centerbody after manufacturing and during production testing. The trimmable open centerbody may be ... | 03/24/2009 |
| 7434384 | Fluid mixer with an integral fluid capture ducts forming auxiliary secondary chutes at the discharge end of said ducts A fluid mixer for mixing two fluid streams 40, 42 includes a set of main lobes 26 defining alternating primary and secondary main chutes 30, 32, one or more auxiliary lobes 28 intermediate two of the main lobes, and an auxiliary fluid cap... | 10/14/2008 |
| 7424805 | Supersonic missile turbojet engine A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A controller is operatively joined to the core engine and afterburner and configured for scheduling fuel thereto for operating the after... | 09/16/2008 |
| 7399155 | Fluid flow guide element and fluid flow apparatus equipped therewith A fluid flow guide element (1) constructed, for example, as a diffuser having an inlet opening (2) and an outlet opening (3) whose respective cross-sectional areas differ from one another. Corresponding to the exterior view shown in FIG.... | 07/15/2008 |
| 7392651 | Turbomachine nozzle cover for reducing jet noise A cowl for a turbomachine nozzle, the cowl having a plurality of repeated patterns disposed circumferentially at a trailing edge, each pattern being asymmetrical about a midplane of the pattern containing a longitudinal axis of the cowl, and each pattern having a fi... | 07/01/2008 |
| 7389635 | Twisted mixer with open center body An exhaust mixer assembly having a twisted mixer and an open centerbody is provided. The open centerbody is centrally disposed within the twisted mixer and helps to provide efficient cooling of exhaust air from gas turbine engines. A method for cooling exhaust air f... | 06/24/2008 |
| 7353647 | Methods and apparatus for assembling gas turbine engines A method facilitates assembling a gas turbine engine including a compressor and a rotor assembly coupled in axial flow communication downstream from the compressor. The method comprises coupling a bypass system in flow communication with the compressor to channel a ... | 04/08/2008 |
| 7350619 | Auxiliary power unit exhaust duct with muffler incorporating an externally replaceable acoustic liner Methods and apparatus are provided for an exhaust duct having an externally replaceable acoustic liner. The exhaust duct includes a forward section that is configured to be axially coupled with a bulkhead collar on the aircraft, a body section that is coupled to the... | 04/01/2008 |
| 7340883 | Morphing structure An apparatus is provided that includes a body having a first wall and a second wall, at least one appending structure extending from an end of the body and at least one actuator positioned between the first and second walls. The actuator includes first end coupled t... | 03/11/2008 |
| 7334409 | Retractable afterburner for jet engine The present invention is a retractable afterburner shroud for use upon a jet engine. The retractable shroud conforms to an outer surface of a jet engine. The afterburner shroud is affixed by a plurality of moveable support arms. The afterburner shroud is retractable... | 02/26/2008 |
| 7316109 | Lobed exhaust diffuser apparatus, system, and method A lobed exhaust diffuser apparatus, system, and method configured to cool exhaust gases from an internal combustion engine comprises a diffuser having a proximal end, configured to receive exhaust gases from the engine, and a distal end, configured to expel the exha... | 01/08/2008 |
| 7313920 | Aircraft engine mounting An aircraft engine mounting assembly comprising a bracket arrangement with two plates located either side of an opening in the structural bypass duct. The bracket arrangement mounts two inclined links which connect to the engine. In normal usage, tension/compression... | 01/01/2008 |
| 7313909 | High-emissivity infrared coating applications for use in HIRSS applications A high emissivity (Hi-E) coating for use on the exhaust baffles of HIRSS systems. HIRSS systems were developed to reduce the infrared (IR) signature of helicopter engines. Increasing operating temperatures of helicopter engines have made the HIRSS systems less effec... | 01/01/2008 |
| 7314035 | Rotary vane engine and thermodynamic cycle A heat engine having a rotary vane compressor and a rotary vane turbine operates in a highly efficient thermodynamic cycle which includes a power expansion phase up to ambient pressure and a limited temperature constant volume combustion followed by a constant press... | 01/01/2008 |
| 7310939 | Device for reducing the jet noise of a turbomachine A device for reducing the jet noise of a turbomachine, the turbomachine having a longitudinal axis and a substantially cylindrical nozzle extending along the longitudinal axis of the turbomachine, having a downstream end for mixing the flows of gas inside and outsid... | 12/25/2007 |
| 7308966 | Device for reducing jet engine exhaust noise using oscillating jets A device for reducing engine exhaust noise in an aircraft engine includes a number of oscillating jets which direct an oscillating flow into the engine exhaust. The oscillating jets are connected via channels to a turbomachinery source of high pressure gas, where th... | 12/18/2007 |
| 7305817 | Sinuous chevron exhaust nozzle A gas turbine engine exhaust nozzle includes a row of laterally sinuous chevrons extending from an aft end of an exhaust duct. The chevrons have radially outer and inner surfaces bound by a laterally sinuous trailing edge extending between a base of the chevrons adj... | 12/11/2007 |
| 7299635 | Device for mixing two flows of fluid which are initially guided separate from one another in a bypass jet engine The invention relates to a device for mixing two fluid flows, initially guided separately from one another, in a two-circuit reaction engine, a mixing tube which encloses a hot core stream being provided, along the outer shaped lateral surface of which a cold bypass... | 11/27/2007 |
| 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 |
| 7293401 | Jet engine noise suppressor An embodiment of the invention is a technique to suppress noise in a jet engine. A noise suppressor includes an exhaust duct to exhaust a first stream from an air stream taken from an inlet. The exhaust duct has an exit end. The air stream is divided into the first ... | 11/13/2007 |
| 7257894 | Process for making a panel with a protected acoustic damping layer A process for the production of a panel with a protective acoustic damping layer. The protective layer includes at least one porous core covered, on the one side, with a porous acoustic damping layer and on the other side with a total acoustic reflector. The porous ... | 08/21/2007 |
| 7255307 | Closure panel arrangement A closure panel arrangement is provided in which a closure panel 6 can only be retained when appropriately aligned with engagement between clasp hooks 8 and pins 9 is achieved along with association between latch hooks 10 and pins 11 | 08/14/2007 |
