Abstract: A fan thrust reverser includes a nacelle having radially outer and inner skins. An outer door is disposed in the outer skin, and mounted to the nacelle at a hinge joint. A toggle link is pivotally joined between the outer door and the nacelle for latching stowed the outer door in the nacelle. An actuator is provided for rotating the outer door about the hinge joint for deploying the door outwardly from the nacelle and toggling off the toggle link, and stowing inwardly the outer door upon reverse rotation thereof and toggling on the toggle link to latch the door stowed in the nacelle.

Abstract: 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.

Abstract: 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 basesheet side edges, respectively, extend longitudinally between the basesheet leading and trailing edges. Each basesheet segment has a panel body defined between a pair of segment side edges longitudinally extending between segment leading and trailing edges, respectively. Stiffeners having leading and trailing edge ribs at the segment leading and trailing edges of aft and forward ones of the basesheet segments, respectively, extend widthwise across the panel body between the segment side edges. The leading and trailing edge ribs are joined together only at intermediate sections of the stiffeners which are centered between left and right hand expansion sections, respectively, of the stiffener.

Abstract: 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.

Abstract: A convergent/divergent nozzle for a gas turbine engine has a throat portion of non-constant radius of curvature varying from an upstream high value to an intermediate low value and then to a downstream high value.

Abstract: The invention concerns a cooling system for a post combustion jet nozzle, The jet nozzle includes a primary gas duct allowing a primary flow of gas, and a secondary air duct allowing a secondary flow of air. The secondary air duct surrounds the primary gas duct and is separated from it by a protective thermal shroud. The secondary air duct has a downstream end, and dampers surrounding an output section of the primary gas duct. The system includes a protective thermal shell in the secondary air duct, at the downstream end of said duct. The protective thermal shell bears an annular diaphragm extending out in front of the dampers and being provided with support sectors and inter-sector zones equipped with slots. The inter-sector zones define spaces between the diaphragm and the protective thermal shroud.

Abstract: Control apparatus for a nozzle for a rocket or other vehicle having a combustion chamber with a propellant therein in communication with the nozzle, the nozzle having a throat and a pair of bores extending into the throat The bores may be in opposed or any other suitable relation. A pair of plungers are slidably mounted in the bores and are movable between an open position wherein they are disposed outside of the throat and a closed position wherein they extend into the throat to substantially close it. The plungers have a width or diameter substantially the same as the width or diameter of the throat. Actuator devices are provided for moving the plungers independently of each other to control thrust by controlling the flow of combustion gases through the throat and the pressure in the combustion chamber. The movement of the plungers can also be used for thrust vector control.

Abstract: 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.

Abstract: The radius of the hinged portion of the convergent/divergent axisymmetrical exhaust nozzle of a gas turbine engine is configured at the surface seeing the flow to be contoured at a critical radius so to enhance the flow characteristics of the nozzle and improve the low observable. The liner normally associated with the convergent flap is cut back at the juncture adjacent the hinged point connecting the divergent flap to be below the radar sight at the tail of the engine.

Abstract: An engine nozzle arrangement for an aircraft comprises a nozzle (18) for hot exhaust gases, and a shroud (20) for the stream of hot exhaust gases emerging from the exhaust nozzle. The shroud includes an intake for a boundary layer of air for cooling the stream of exhaust gases.

Abstract: An exhaust nozzle for an aircraft engine. The nozzle includes a mount for attaching the exhaust nozzle to a downstream end of the engine and first and second opposed upstream flaps moveably connected to the mount having inner surfaces defining an upstream exhaust gas flowpath. Each upstream flap extends between an upstream end and a downstream end and is moveable relative to the mount between an open position in which the downstream ends of the upstream flaps are spaced by a first distance, and a closed position in which the downstream ends touch to substantially block flow through the exhaust gas flowpath. First and second opposed downstream flaps are moveably connected to the first and second upstream flaps having inner surfaces defining a downstream exhaust gas flowpath.

Abstract: A nozzle for a gas turbine engine is provided which includes an outer casing, a convergent section, a divergent section, an external fairing, and a collapsible seal member. The divergent section has an aft end and a forward end, and the forward end of the divergent section is pivotally attached to the convergent section. The external fairing has an aft end and a forward end. The forward end of the external fairing is pivotally attached to the outer casing and the aft end of the external fairing is pivotally attached to the aft end of the divergent section. The external fairing is disposed radially outside of the divergent section. The collapsible seal member extends between the outer casing and the divergent section, circumferentially around and outside of the divergent section.

Abstract: The horsepower requirements for the actuation system for a convergent/divergent exhaust nozzle for a gas turbine engine is reduced by the judicious selection of the crank arms and their location on a torque shaft that rotates to move a connecting link attached to the convergent flap of the nozzle. A pressure balancing hood is attached to the top surface on the forward end of the convergent flap to augment the lowering of the horsepower requirements. In another embodiment a tie rod/end cup arrangement and two piece torque shaft are utilized for ease of removal of the actuation system from the exhaust nozzle assembly.

Abstract: A hinge arm for a thrust reverser door may be mounted to an exhaust nozzle using an aft mount. The mount includes a frame for attachment to the nozzle. A swing link has a first pin pivotally joined to the frame, and a second pin for pivotally joining the hinge arm to the link to permit both swinging and pivoting of the hinge arm from the frame. The aft mount thusly permits the reverser doors to be reliably stowed around the nozzle.

Abstract: The invention concerns a backblast gas structure for jet engine comprising a thrust reversal system with two downstream doors. The invention is characterized in that the two tilt-up doors articulated about axes (6, 7) are mounted on two side beams (2, 3) with free downstream edges (16, 17) comprising protuberances (18, 19). The door downstream edges (13, 14) having median zones (13b, 14b) forming an angle (A) with the lateral parts (13a, 14a), such that when the doors are in retracted position in direct jet, the beam (13b, 14b) edges (16, 17) of the doors are found in the same plane (P2), thereby constituting a gas exhaust outlet which is planar and substantially circular. The invention aims at improving the power package performance in direct jet.

Abstract: A hybrid-composite gas turbine exhaust nozzle compression link is formed as an elongated hollow tubular cylindrical shell having an axis of elongation. In cross section taken perpendicular to the axis of elongation, the shell has a structure of an inner rim of an inner-rim titanium-base alloy, a reinforcing layer having reinforcing fibers such as silicon carbide fibers extending parallel to the axis of elongation and embedded in a matrix titanium-base alloy, and an outer rim of an outer-rim titanium-base alloy. The titanium-base alloys are typically of the same nominal composition. Attachment fittings are present at each end of the shell.

Abstract: An exhaust assembly for a jet powerplant of a supersonic airplane comprising a rear structure fitted with a thrust reverser. The rear structure includes a primary multi-flap nozzle of variable cross-section situated downstream of a primary duct, a secondary multi-flap nozzle of variable cross-section situated downstream of a secondary duct enclosing the primary duct and a fairing enclosing the secondary duct and fitted with a throat downstream of an exhaust orifice of the secondary nozzle, the throat being followed by a diverging portion. The thrust reverser comprises two eyelids affixed in a pivotable manner to the fairing, one on each side to of an axial plane of symmetry. The eyelids are movable between an active, thrust-reversal position wherein the eyelids project transversely into a gas jet downstream of the fairing to deflect the gas jet in a forward direction for thrust-reversal and an inactive, forward-thrust position wherein the eyelids are situated in an extension of the fairing.