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Match Document Document Title
US20100044504 REAR PROPULSION SYSTEM WITH LATERAL AIR INLETS FOR AN AIRCRAFT WITH SUCH SYSTEM  
A propulsive system for an aircraft including an auxiliary jet engine is integrated within a tail cone of a fuselage. Lateral air intakes include each one a scoop movable between a closed position...
US20140026582 ANTI-FIRE SEAL ASSEMBLY AND NACELLE COMPRISING SUCH A SEAL  
A seal assembly for a turbojet nacelle includes a first end fastened to a first structure, and a second end contacting against a bearing zone of a second structure. The seal assembly further...
US20150252751 GEARED GAS TURBINE ENGINE INTEGRATED WITH A VARIABLE AREA FAN NOZZLE WITH REDUCED NOISE  
A gas turbine engine includes a spool and a turbine coupled to drive the spool. A fan is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the fan and the...
US20110271685 VARIABLE FAN DUCT NOZZLE  
An aircraft nacelle comprising an outer cowl and an inner cowl located inward of the outer cowl with an air flow path formed therebetween. The inner cowl may comprise a forward portion and an aft...
US20060086093 Variable-section turbomachine nozzle with a one-piece control lever support  
A variable-section nozzle for a turbomachine, the nozzle comprising a plurality of moving flaps mounted on the downstream end of an annular casing of the turbomachine, a moving flap control system...
US20150135678 GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE  
A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis. A fan nacelle is mounted at least partially around the core nacelle to...
US20120167575 ROCKET ENGINE WITH EXTENDABLE DIVERGENT  
A rocket engine with an extendible exit cone including an exhaust nozzle for gas from a combustion chamber, the nozzle presenting a longitudinal axis having a first portion defining a nozzle...
US20080092548 Gas turbine engine having slim-line nacelle  
A nacelle assembly for a gas turbine engine includes a nacelle, a variable area fan nozzle, a sensor that detects a windmilling condition and a controller that communicates with the sensor. The...
US20110232291 SYSTEM AND METHOD FOR AN EXHAUST DIFFUSER  
An exhaust diffuser includes a shroud and a wall radially separated from the shroud to define a fluid passage between the shroud and the wall. A strut extends between the shroud and the wall, and...
US20080163606 Variable area nozzle with woven sleeve extension  
A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is attachable to a gas turbine engine for influencing flow through the fan bypass passage of the...
US20090133406 FAN NOZZLE OF ADJUSTABLE SECTION  
Varying the flowsection for air leaving the fan as a function of flying conditions. According to the invention, the nozzle has a ring of deformable panels arranged close to its trailing edge, each...
US20070256419 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...
US20090178416 BIFURCATION AND AFT VENT USED TO VARY FAN NOZZLE EXIT AREA  
A turbofan engine includes a core nacelle housing a spool having a turbine. A turbofan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the turbofan...
US20090067993 COATED VARIABLE AREA FAN NOZZLE  
A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is movable between a plurality of positions to change an effective area associated with a bypass...
US20090235638 VARIABLE AREA NOZZLE ASSISTED GAS TURBINE ENGINE RESTARTING  
A turbofan engine starting system includes a core nacelle housing (12), a compressor (16) and a turbine (18). The core nacelle is disposed within a fan nacelle (34). The fan nacelle includes a...
US20110088403 NOZZLE-AREA RATIO FLOAT BIAS  
A mechanism included in a convergent-divergent nozzle connected to an aft portion of a gas turbine engine, which mechanism includes a convergent flap configured to be kinematically connected to...
US20100050595 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...
US20100018212 DILATING FAN DUCT NOZZLE  
A turbofan engine includes an engine core and a ducted fan assembly, with the ducted fan assembly including an annular cowling and a dilating fan duct nozzle. The nozzle includes continuous nozzle...
US20090100823 Gas turbine engine reheat fuel system  
A gas turbine propulsion engine reheat system having a variable area exhaust nozzle comprising a nozzle area control system including means for accelerating increases of nozzle area
US20090173077 Nozzle with Temperature-Responsive Throat Diameter  
Nozzles that offer shape variability to maintain or purposely change the pressure drop across the throat are obtained by constructing the nozzles with components that change their shape, angle, or...
US20100018213 GAS TURBINE ENGINE WITH ROTATIONALLY OVERLAPPED FAN VARIABLE AREA NOZZLE  
A turbofan engine includes a fan variable area nozzle having a rotationally overlapped nozzle assembly having a first tab section and a second tab section rotationally mounted relative to the...
US20080028763 Thermal management system with thrust recovery for a gas turbine engine fan nacelle assembly  
A thermal management system locates a separate engine heat exchanger and generator heat exchanger into an engine nacelle pylon that is split to provide independent control of both a generator...
US20080236167 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...
US20100139285 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...
US20100000220 FAN VARIABLE AREA NOZZLE WITH ELECTROMECHANICAL ACTUATOR  
A fan variable area nozzle (FVAN) (42) includes a multiple of compact high power density electromechanical actuators (EMA) (56) located within a fan nacelle (34). Each EMA directly pitches an...
US20090090817 Aircraft configuration, gas turbine engine, controller and trim system for neutralizing pitching moments with power changes  
An aircraft, gas turbine engine, controller and trim system for neutralizing pitching moments caused by power changes and consequent changes in engine thrust. Several expedients are disclosed,...
US20100175383 DILATING FAN DUCT NOZZLE  
A turbofan engine includes an engine core and a ducted fan assembly, with the ducted fan assembly including an annular cowling and a dilating fan duct nozzle. The nozzle includes continuous nozzle...
US20090255269 Gas Turbine Engine Systems Involving Variable Nozzles with Sliding Doors  
Gas turbine engine systems involving variable nozzles with sliding doors are provided. In this regard, a representative door assembly for a gas turbine engine includes: a door configured for...
US20120067052 DEPLOYABLE DIVERGENT NOZZLE FOR A PROPULSIVE UNIT  
The present invention relates to a deployable diverging bell (2) for a thruster, the bell comprising: a stationary first diverging bell portion (3) suitable for being connected to a stationary...
US20070033921 Aircraft engine exhaust flap curved strut slot  
An aircraft engine nozzle assembly includes an adjustable flap portion that is movable about a pivot for changing the size of an exhaust exit area. A bracket having a curved slot establishes a...
US20070266712 EXHAUST ASSEMBLY FORMING A HORIZONTAL PROPULSION GAS ELBOW IN AN AIRCRAFT  
The present invention relates to a propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a duct (21) and a...
US20130092756 VARIABLE AREA NOZZLE FOR GAS TURBINE ENGINE  
A variable area nozzle for a gas turbine engine is provided that has a circumferential outer boundary (which may be formed at least in part by the nacelle of a turbofan engine) that has a fixed...
US20110203288 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...
US20130145768 CASE ASSEMBLY WITH FUEL OR HYDRAULIC DRIVEN VAFN ACTUATION SYSTEMS  
A variable area fan nozzle (VAFN) system for an aircraft is provided. The VAFN system includes a fluid-driven motor configured to receive a fluid; one or more actuators coupled to the fluid-driven...
US20090217671 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...
US20100115958 RADIALLY TRANSLATING FAN NOZZLE NACELLE  
A variable area nozzle system for a turbofan gas turbine engine comprises a fan duct inner wall, a fan duct outer wall and a fan nozzle. The fan duct outer wall is disposed in radially-spaced...
US20100170261 ENGINE NOISE  
In order to provide noise suppression, bumps or undulations are provided on a nozzle surface in order to vary the convergent-divergent ratio between that surface and an opposed nozzle surface. By...
US20090320488 GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE  
A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.
US20100011777 MORPHING STRUCTURE AND METHOD  
A method of controlling mixing of a flow exiting a nozzle associated with a jet engine. The method may involve pivotally supporting a mixing structure forming a hinge device at a downstream edge...
US20110030380 HIGH STIFFNESS SHAPE MEMORY ALLOY ACTUATED AEROSTRUCTURE  
A shape memory alloy (SMA) actuated aerostructure operable to dynamically change shape according to flight conditions is disclosed. Deformable structures are actuated by SMA actuators that are...
US20100058769 FAN VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE FAN NACELLE WITH DRIVE RING ACTUATION SYSTEM  
A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area. The flap assembly generally includes a multiple of flaps, flap linkages and an actuator system. The...
US20080223956 Mounting structure for variable nozzle mechanism in variable-throat exhaust turbocharger  
Provided is a variable-throat exhaust turbocharger in which a nozzle assembly including a nozzle mount and nozzle vanes has a firm support structure without affection by a thermal deformation of a...
US20120317956 Constant Volume Combustion Chamber  
A constant volume combustion chamber, combustor, and method for constant volume combustion involve combusting a fuel in a chamber sealed by a pintle having a conical portion fitted into a conical...
US20110000217 MANAGING SPOOL BEARING LOAD USING VARIABLE AREA FLOW NOZZLE  
A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to...
US20140245743 DOUBLE-ACTING LINEAR ACTUATOR  
The present disclosure relates to a double-acting linear actuator for moving an inner part and an outer part of a cowl relative to a fixed frame. The linear actuator includes a first tubular body...
US20100269511 NACELLE FOR AIRCRAFT ENGINE HAVING A NOZZLE WITH A VARIABLE SECTION  
The invention relates to a nacelle for an aircraft engine that comprises a front cowling (13) and a rear cowling (1a), the rear cowling (1a) being mounted so as to slide between an upstream...
US20060021351 Method for resistance welding two sheet metal elements together  
A method for resistance welding first and second sheet metal elements together by placing a copper shunt between and in contact with a first sheet metal element and a third sheet metal element,...
US20120255806 NOISE REDUCTION OF SUPERSONIC JET ENGINES  
A jet engine adapted for reducing far-field noise levels is disclosed. The jet engine has a plurality of flap assemblies that are disposed around a perimeter of an exhaust port of the jet engine....
US20100139240 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...
US20060277914 Combi-Supersonic-Adjusting-Nozzle  
The filed application is a supplement to my U.S. application Ser. No. 10/757,596 and to my German application No.: 103 02 041.1-13, which represent a basic conception for a novel internal...

Matches 1 - 50 out of 65 1 2 >