90results about "Jet flaps" patented technology

A fan thrust reverser includes an outer louver door joined to an inner blocker door by a drive link in a bifold configuration. The louver door is stowed closed in the outer skin of a fan nacelle outside the blocker door stowed closed in the inner skin of the nacelle. An actuator deploys open the louver and blocker doors, with the louver door extending radially outwardly and the blocker door extending radially inwardly for reversing fan exhaust flow during thrust reverse operation.

A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat of the nozzle. An outer shroud surrounds the inner shroud and cooperates with the centerbody to define the exit area of the nozzle. Both shrouds are independently translatable to provide independent control of the nozzle throat area and the nozzle expansion ratio.

A nozzle structure of a dish washer is provided. In the nozzle structure, a nozzle holder is provided, a gasket unit is mounted on an end of the nozzle holder and it includes at least one inlet port, a flap support unit is protruded from a front of the gasket unit, and a check valve flap is rotatably coupled to the flap support unit.

An apparatus comprises a platform configured to move in a streamwise direction, an actuation unit associated with a control surface of the platform, a fluid source configured to supply an airflow to the actuation unit, and a control unit for moving an air jet across the control surface. The actuation unit is configured to form a traversing air jet pointing in the streamwise direction.

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 sections with intermeshing tiles. The tiles include drive tiles that are pivotal between nominal and dilated positions and driven tiles that intermesh with the drive tiles and shift with the drive tiles between the positions. The intermeshing tiles cooperatively adjust an orifice size of the nozzle by shifting between the positions and thereby affect the thrust and noise developed by the ducted fan assembly.

A method of controlling movement of a vehicle including generating a fluid jet adjacent an aerodynamic surface of the vehicle, and changing at least one of a strength and a position of a shock wave traveling over the aerodynamic surface of the vehicle by directing the jet into a boundary layer flow of air attached to the aerodynamic surface.

Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling extends outwardly from the surface of the airfoil that has an exit plane configured for directing exhaust gases toward a rear of the aircraft. Fences extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft.

An aircraft control structure can be utilized for purposes of drag management, noise control, or aircraft flight maneuvering. The control structure includes a high pressure engine nozzle, such as a bypass nozzle or a core nozzle of a turbofan engine. The nozzle exhausts a high pressure fluid stream, which can be swirled using a deployable swirl vane architecture. The control structure also includes a variable geometry pylon configured to be coupled between the nozzle and the aircraft. The variable geometry pylon has a moveable pylon section that can be deployed into a deflected state to maintain or alter a swirling fluid stream (when the swirl vane architecture is deployed) for drag management purposes, or to assist in the performance of aircraft flight maneuvers.

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 thrust and fuel efficiency in varying conditions. Vanes also move independently to impart directional force to roll, pitch and yaw traditional aircraft and hover VTOL aircraft. A bleed air pressure actuator for moving the vanes is disclosed.

A horizontal augmented thrust system includes at least one wing. The wing includes a wing outer envelope, a trailing edge and a flap. At least one pulse jet engine is positioned entirely within the wing outer envelope. The pulse jet engine produces a pulsating thrust dischargeable adjacent the trailing edge of the wing and onto the flap.

A method for adjusting a throat area of a jet aircraft exhaust nozzle assembly includes positioning a lower structure within a substantially rectangular nozzle assembly, coupling a ramp flap to the lower structure, and coupling an outer flap to the nozzle assembly such that movement of at least one of the ramp flap and the outer flap adjusts the throat area of the nozzle assembly.