Abstract: Dielectric barrier discharge plasma actuators are used to manipulate exhaust flow within and behind a jet engine nozzle. The dielectric barrier discharge plasma actuators may be used to direct cooling airflow near the surface of the nozzle to reduce heating of the nozzle, create thrust vectoring, and reduce noise associated with the exhaust flow exiting the nozzle.

Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The 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, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.

Abstract: Within a turbine engine a heat exchanger may be provided to cool compressor air flows to be utilized for cabin ventilation or other functions. A fluid flow acting as a coolant for the heat exchanger is generally drawn from the by-pass duct of the engine and a dedicated outlet duct is provided such that the exhausted fluid flow from the heat exchanger is delivered along the conduit duct to a low pressure region. In such circumstances, an appropriate pressure differential across the heat exchanger is maintained for operational efficiency when required, whilst the exhausted fluid flow is isolated and does not compromise the usual engine ventilation vent exit area sizing. Over-sized ventilation vents would create an aerodynamic step and therefore drag upon the thrust of the engine.

Abstract: 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 the aft portion of the gas turbine engine, a divergent flap pivotally connected to the convergent flap and configured to be kinematically connected to the aft portion of the gas turbine engine, at least one actuator configured to be connected to the aft portion of the gas turbine engine and to mechanically prescribe the position of the convergent flap and the divergent flap by moving through one or more positions, and at least one biasing apparatus. The biasing apparatus is configured to position at least one of the convergent flap and the divergent flap independent of the positions of the actuator by substantially balancing a force on the at least one of the convergent flap and the divergent flap produced by a gas pressure on the nozzle.

Abstract: 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 respective curved outlines and they are interconnected by a curved portion presenting a radius of curvature greater than the radii of curvature of the outlines of said vertices, each side being connected to the trailing edge of the cover via a curved outline presenting a radius of curvature greater than the radii of curvature of the outlines of the vertices and greater than the radius of curvature of the outline of the curved portion, and the vertices and the curved portion are inclined radially towards the inside of the cover, with the curved portion being radially offset outwards relative to the vertices.

Abstract: A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked. A ring rotates with another ring to control both this air flow, and a supply of cooling air to an interior of the nozzle.

Abstract: 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 chevrons having a root region and a tip, wherein at least a portion of at least one of the interior surface or the exterior surface is scalloped proximate the root region of a chevron. Other embodiments may be described.

Abstract: An improved thermal spray apparatus and method of promotes mixing of axially fed particles in a carrier stream with a heated effluent stream without introducing significant turbulence into either the effluent or carrier streams. An axial injection port includes a plurality of chevrons at the distal end of the port. The chevrons are located radially around the circumference of the distal end of the axial injection port to increase the shared area between the two flow streams at the outlet of the port.

Abstract: A protocol for assembling a fuel shut off pin valve assembly for a turbo fan engine. The protocol outlines a specific sequence of events in order to ensure failsafe incorporation of a fuel shut off valve assembly within the low pressure turbine area and specifically within the engine casing of the turbo fan.

Abstract: 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 position defining a reduced nozzle (9) section and a downstream position defining an enlarged nozzle (9) section. The nacelle includes an intermediate member (25) arranged edge-to-edge with said front cowling (13), said member defining a housing (27) for receiving the upstream edge (11) of said rear cowling (1a) when the latter is in the upstream position.

Abstract: An embodiment of the invention is a technique to suppress noise in a jet engine. A substantially annular fan nozzle is attached to a pylon and discharges a fan stream into atmosphere from an aft end thereof. A core nozzle discharges core stream into the atmosphere. The core nozzle has an exterior surface. A stream director is mounted on the pylon to direct the fan stream away from the pylon. At least a portion of the stream director is situated outside the aft end to maintain substantially constant flow area of the fan nozzle.

Abstract: Integrated engine exhaust systems and techniques for operating integrated engine exhaust systems are disclosed. In one embodiment, a propulsion system includes an engine installation configured to be mounted on a wing assembly of an aircraft. The engine installation includes an engine, and an exhaust system operatively coupled to the engine. The exhaust system includes at least one nozzle to exhaust an exhaust flow from the engine. The nozzle includes a variable portion configured to vary an exit aperture of the nozzle from a first shape to a second shape to change a flowfield shape of at least a portion of the nozzle flowfield proximate the wing assembly, thereby reducing at least one of drag and thermal loading on the wing assembly. In a further embodiment, the exhaust system includes an inner nozzle that exhausts a core exhaust flow, and an outer nozzle that exhausts a secondary exhaust flow, the outer nozzle having the variable portion configured to vary the exit aperture of the outer nozzle.

Abstract: 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 circumferential direction and interconnected by an outer dome, each inner lobe comprising a pair of plane radial walls spaced apart from each other in the circumferential direction and connected together by an inner dome, the walls of the outer lobes being disposed to extend the walls of the inner lobes radially, the radial walls of a given outer lobe extending radially in mutually parallel directions, with these walls, when extended geometrically, defining a zone from which the axis of symmetry of the cylindrical member is excluded.

Abstract: 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 curvature in response to temperature changes that occur during the flow of combustion products through the nozzle. The temperature change may be the gradual heating of the nozzle wall from hot combustion gases, and the shape change may result in a decrease in the throat diameter or an expansion of the throat diameter. A decrease in throat diameter will be useful when the depletion of propellant as burning proceeds causes a drop in the pressure or flow rate of the combustion gas and there is a need to compensate for this drop to maintain the pressure drop across the throat. An increase in throat diameter will be useful when an initial high thrust is no longer needed and depletion of the fuel by itself is insufficient to lower the thrust to its desired reduced level.

Abstract: A nozzle system includes a multitude of circumferentially distributed convergent flaps and seals that circumscribe an engine centerline. A cooling liner body cooperates with a cooling liner panel attached to respective convergent flaps and convergent seals to define an annular cooling airflow passageway which is movable therewith. Each cooling liner panels includes an arcuate cooling liner leading edge with a multiple of openings to distribute cooling airflow over both the inner “cold-side” and outer “hot-side” surfaces thereof. Through this backside cooling, thermal gradients are controlled at the attachment interface between the arcuate cooling liner leading edge and the main cooling liner body.

Abstract: 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.

Abstract: A system and method for actively manipulating fluid flow over a surface using synthetic pulsators. Synthetic pulsators produce pulsed jet operable to manipulate the primary fluid flow proximate to the synthetic pulsator. The synthetic pulsator includes a dual diaphragm synthetic jet coupled to high performance dual actuator solenoids, wherein the synthetic jet is operable to produce an oscillatory flow. The oscillatory flow of the synthetic jet(s) produces the pulsed jet operable to manipulate the primary fluid flow. These synthetic pulsators may then be actively manipulated to control the flow behavior of the ducted fluid flow, influence the inception point and trajectory of flow field vortices within the fluid flow, and reduce flow separation within the primary fluid flow.

Abstract: Pulsed detonation engines (PDEs), or various components thereof, such as the detonation chamber and/or nozzle, can be economically constructed from materials having low thermal stability, such as plastics, composites, and light metals. During operation, the intermittent injection and detonation of reactants produces a motive force (e.g., thrust) over relatively short intervals useful in orbit control and the like. The relatively short intervals of operation prevent temperatures of the PDE components from reaching temperatures that would result in their dimensional failure.

Abstract: The thrust reverser is used with a gas turbine engine and includes first and second doors pivotable between a stowed position and a deployed position. When deployed, pivoting fairings on the first door are moved so as to give room to the second door as its trailing edge moves within the first door. When stowed, the second door preferably provides the locking mechanism to the pivoting fairings of the first door.

Abstract: 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 cam drive ring relative an engine centerline axis which results in a follower of the flap linkage following a cam surface to pivot each flap such that the flap assembly dilates about the circumferential hinge line. Rotation of the cam drive ring adjusts dilation of the entire fan nozzle exit area in a symmetrical manner. Another cam drive ring includes a multiple of movable cams which engages the follower of the flap linkage of each flap such that pivotable movement of a particular number of the multiple of movable cams about a respective cam pivot results in vectoring of the FVAN.

Abstract: 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 range of possible movement of the flap portion. A link includes a guide member portion that is received in the curved slot for guiding the movement of the flap portion. The link is connected to a static engine structure and the bracket is movable with the flap portion. The curved slot establishes a range of possible movement of the flap portion along a direction of the curved slot.

Abstract: The proposed adaptive exhaust nozzle features an innovative use of the shape memory alloy (SMA) actuators for actively control of the opening area of the exhaust nozzle for jet engines. The SMA actuators remotely control the opening area of the exhaust nozzle through a set of mechanism. An important advantage of using SMA actuators is the reduction of weight of the actuator system for variable area exhaust nozzle. Another advantage is that the SMA actuator can be activated using the heat from the exhaust and eliminate the need of other energy source. A prototype has been designed and fabricated. The functionality of the proposed SMA actuated adaptive exhaust nozzle is verified in the open-loop tests.

Abstract: 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 cowl and the nacelle, and an inner core cowl baffle assembly positioned within the fan nozzle duct. The inner core cowl baffle assembly includes a first core cowl baffle coupled to a portion of the core cowl within the fan nozzle duct, a second core cowl baffle coupled to a portion of the core cowl and positioned a distance radially inward from the first core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the second core cowl baffle with respect to the first core cowl baffle. A method for operating the turbofan engine assembly is also provided.

Abstract: 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 selectively positioning a first arcuate portion and a second arcuate portion of a split cowl assembly to vary a throat area of a fan nozzle duct defined downstream from the core gas turbine engine to facilitate improving engine efficiency at the second operating speed. The split cowl assembly is downstream from the core gas turbine engine and inside the fan nozzle duct. A turbofan engine assembly and nozzle assembly are also provided.

Abstract: A device for controlling fluid flow. The device includes an arc generator coupled to electrodes. The electrodes are placed adjacent a fluid flowpath such that upon being energized by the arc generator, an arc filament plasma adjacent the electrodes is formed. In turn, this plasma forms a localized high temperature, high pressure perturbation in the adjacent fluid flowpath. The perturbations can be arranged to produce vortices, such as streamwise vortices, in the flowing fluid to control mixing and noise in such flows. The electrodes can further be arranged within a conduit configured to contain the flowing fluid such that when energized in a particular frequency and sequence, can excite flow instabilities in the flowing fluid. The placement of the electrodes is such that they are unobtrusive relative to the fluid flowpath being controlled.

Abstract: Integrated engine exhaust systems and methods for reducing drag and thermal loads are disclosed. In one embodiment, a propulsion system includes an engine installation configured to be mounted on a wing assembly of an aircraft. The engine installation includes an engine, and an exhaust system operatively coupled to the engine. The exhaust system includes at least one nozzle configured to exhaust an exhaust flow from the engine. The nozzle includes a variable portion configured to vary an exit aperture of the nozzle from a first shape to a second shape to change a flowfield shape of at least a portion of the nozzle flowfield proximate the wing assembly, thereby reducing at least one of drag and thermal loading on the wing assembly. In a further embodiment, the exhaust system includes an inner nozzle that exhausts a core exhaust flow, and an outer nozzle that exhausts a secondary exhaust flow, the outer nozzle having the variable portion configured to vary the exit aperture of the outer nozzle.

Abstract: 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.

Abstract: A fuel nozzle centerbody is provided that includes a cylindrical cross-sectional area, and a baffle co-axially aligned within the centerbody. The baffle includes a plurality of circumferentially-spaced apertures configured to channel an airflow radially outward such that the channeled airflow impinges a centerbody inner surface.

Abstract: The invention relates to a yaw control device for an aircraft fitted with a supersonic nozzle having a rectangular or flat section comprising a supersonic throat extended by a diverging portion in which supersonic flow occurs. In order to enable the aircraft to be controlled in yaw in the absence of a vertical fin, the device of the invention makes use of jet control surfaces in the form of airfoils disposed in the diverging portion of the nozzle. The control surfaces are movable about respective pivot axes in order to generate a lateral force when in a deflected position, so as to enable the aircraft to turn about its yaw axis.

Abstract: A nozzle system includes a multitude of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of an exhaust gas path. Each divergent flap includes longitudinal sides having a set of extension which are located at different longitudinal stations such that the extensions on adjacent divergent flaps interfit when the nozzle is in a minimum dilated position yet provide support for the intermediate flap seal when the nozzle is in a maximum dilated position to thereby provide a relative increase in the nozzle area ratio range.

Abstract: A method for reducing the nonsteady side loads acting on a nozzle of a rocket engine during a startup phase of said engine. The nozzle comprises a combustion chamber (1) where exhaust gases are generated, a divergent portion (3) in which a supersonic flow of said exhaust gases occurs, and a throat (2) connecting the combustion chamber to the divergent portion, which method comprises the positioning of a body of rounded shape (5) inside the divergent portion (3) along its axis corresponding to an axial position such that, during at least part of the startup phase, a shock wave (8), induced by the distrubance of the flow of the exhaust gases by the body of rounded shape (5) is incident to the wall of the divergent portion (3) at an axial incidence position where it produces a jet separation or a separation in the form of a toroidal separation bulb.

Abstract: Gas turbine engine systems involving variable nozzles with sliding doors are provided.

Abstract: A propulsion system with a divergent-convergent nozzle is provided with variable thrust by a pintle whose position relative to the nozzle throat is controlled by an actuator that includes a rotor that external to, and encircling, the nozzle, and that is coupled to either the pintle or to the nozzle shell by a linkage that translates the rotary movement of the rotor into linear movement of either the pintle or the shell.

Abstract: The proposed adaptive exhaust nozzle features an innovative use of the shape memory alloy (SMA) actuators for actively control of the opening area of the exhaust nozzle for jet engines. The SMA actuators remotely control the opening area of the exhaust nozzle through a set of mechanism. An important advantage of using SMA actuators is the reduction of weight of the actuator system for variable area exhaust nozzle. Another advantage is that the SMA actuator can be activated using the heat from the exhaust and eliminate the need of other energy source. A prototype has been designed and fabricated. The functionality of the proposed SMA actuated adaptive exhaust nozzle is verified in the open-loop tests.

Abstract: 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 in shape, with a base formed by a portion of the trailing edge of the cover and a vertex spaced downstream from the base and connected thereto by two sides. For each pattern, the vertex presents an outline that is substantially curved; each side is connected to the trailing edge of the cover following an outline that is substantially curved having a radius of curvature that is greater than the radius of curvature of the outline of the vertex; and the outline of each of the sides includes at least one point of inflexion having a tangent that is substantially parallel to the base.

Abstract: Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance.

Abstract: An exhaust nozzle assembly includes a plurality of interfitting flap assemblies that are moveable between a maximum area ratio and a minimum area ratio. Each of the pluralities of flap assemblies includes a slot and a wing. The wing fits within an adjacent slot of an adjacent flap assembly. Each of the flap assemblies includes a divergent element that provides a specific geometric shape forming the trailing edge surfaces. The flap element is attached to the divergent element and extends to a static structure. The flap element and the divergent element combine to form a continuous faceted outer surface of the exhaust nozzle assembly substantially void of gaps throughout the range of motion between the maximum and minimum area ratios.

Abstract: Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing in their side walls 22,28 gas injection slits 23,30 oriented in oblique directions 24,26 relative to the gas stream 11, and controlled means for the adjustable closure of these slits 23,30.

Abstract: A system for controlling a position of jet engine exhaust mixing tabs includes a plurality of exhaust mixing tabs spaced apart from one another and extending from a lip of an exhaust nozzle of a jet engine nacelle adjacent a flow path of an exhaust flow emitted from the exhaust nozzle. Each of the exhaust mixing tabs are constructed to be controllably deformable from a first position adjacent the flow path to a second position extending into the flow path of the exhaust flow in response to a control signal applied to each of the exhaust mixing tabs. In the first position, the exhaust mixing tabs either have no affect on the thrust produced, or increase the momentum (thrust) of the exhaust flow exiting from the exhaust nozzle. In the second position, that is, the “deployed” position, the exhaust mixing tabs are deformed to extend into the flow path. In this position the exhaust mixing tabs promote mixing of the exhaust flow with an adjacent air flow.

Abstract: A shroud for an aircraft engine exhaust plume, the shroud being formed of a flexible material secured at one end to the exhaust nozzle and selectively extendable downstream with the exhaust plume so as to surround and shroud it, thereby to reduce infrared/radar/noise emissions from the aircraft engine.

Abstract: A nozzle assembly for a turbine engine has a convergent portion for converging fluid flow from a turbine engine core. A divergent portion for diverging fluid flow from the turbine engine core is in fluid communication with the convergent portion. A conduit is in communication with a bypass fluid flow. The conduit has a thrust vectoring port located near the divergent portion.

Abstract: There is provided a hydrogen chrolide gas ejecting nozzle I used in a reaction apparatus for producing trichlorosilane in which metal silicon powder is reacted with hydrogen chloride gas to generate trichlorosilane. The member is provided with a shaft portion extending in the longitudinal direction and a head portion that is provided on an end of the shaft portion and extends in a direction intersecting the longitudinal direction of the shaft portion. A supply hole extending in the longitudinal direction is formed in the shaft portion, a plurality of ejection holes are formed in the head portion, and each of the ejection holes is communicatively connected to the supply hole and opened on the outer surface of the head portion toward a direction intersecting the direction to which the supply hole extends.

Abstract: A propulsion system with a pintle for variable thrust is constructed such that the pintle contains a shaft at its fore end which passes through an opening in the thrust chamber wall and extends into a boss on the outside surface of the thrust chamber. A dynamic seal that maintains the pressurization of the thrust chamber while allowing movement of the pintle is positioned inside the boss, between the pintle shaft and the boss, and actuation of the pintle is achieved by a rack affixed to the fore end of the pintle and a gear that engages the rack. The dynamic seal, rack and gear are thus external to the thrust chamber, providing the thrust chamber with a compact external envelope, a greater thermal standoff, or both.

Abstract: An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located at an unvectored nozzle throat. Transversely spaced apart upper and lower tips of the exhaust vane may be incorporated to sealingly engage a nozzle outer wall along upper and lower surfaces of the outer wall of the nozzle. The exhaust vane has flat or contoured vane sidewalls and contoured vane sidewalls may be concave. The exhaust vane may have transversely biased apart upper and lower vane sections extending transversely inwardly from the upper and lower tips of the exhaust vane respectively. The exhaust vane may be articulated having upstream and downstream sections separately sideways pivotable about the vane pivot axis and a second pivot axis downstream of and parallel to the vane pivot axis respectively.

Abstract: A fuel-injection system for direct injection of fuel into a combustion chamber through a combustion-chamber top arranged opposite a piston has a fuel injector which includes an actuable valve-closure member. The valve-closure member cooperates with a valve-seat surface to form a sealing seat. A multitude of spray-discharge orifices generates a spray cloud, each spray-discharge orifice generating a fuel jet, and the multitude of fuel jets generating the spray cloud in the combustion chamber. A first opening angle of the spray cloud in a first plane is greater than a second opening angle in a second plane extending perpendicular to the first plane.

Abstract: An exhaust nozzle assembly provides fluidic thrust vectoring of the primary stream to enhance aircraft maneuverability. The exhaust nozzle assembly includes a cooling air passage that supplies cooling air to a plurality of cooling holes that generate an insulating layer of air. A vector slot injects cooling airflow into the exhaust passage normal to the primary stream. A cover plate partially blocks the vector slot to direct cooling airflow into the exhaust passage that in turn directs portions of the primary stream.

Abstract: An actuator arrangement comprises an actuator having a rotatable drive input, a motor, and a drive transmission arrangement for transmitting rotary drive from the motor to the rotatable drive input of the actuator, wherein the transmission arrangement includes a telescopic drive coupling.

Abstract: A fuel injector for an internal combustion engine, particularly of inwards or outwards opening needle injector type, includes an injector body, e.g., forming a nozzle ending in an injection office, a mechanism for closing off the injection orifice of the injector body, the closing-off mechanism including a vibrating pintle ending in a head for closing off the injection orifice, a return mechanism returning the closing-off to the position in which they close off the injection orifice, and a mechanism for setting the pintle and/or the nozzle into cyclic longitudinal vibration so as to open and close the injection orifice alternately. The fuel injector includes a selectively activatable mechanism immobilizing the pintle with respect to the body.

Abstract: A convergent turbojet exhaust nozzle comprising a ring of hinged flaps made up of controlled flaps and of follower flaps disposed in alternation and co-operating at their upstream ends with a peripheral sealing gasket arranged at the outlet from an afterburner channel, each flap being made out of a ceramic-matrix composite material, and at its upstream end, each flap being made integrally with bearing means for bearing against the above-mentioned peripheral gasket, and with spherical-joint means between their upstream ends.

Abstract: A primary exhaust nozzle for a turbofan engine of the double, separated air-flow type for aircraft comprises: an inner coat, within which there circulates a primary air flow (FP), comprising chevrons at an external end and an outer coat at least partially surrounding the inner coat and along which there flows a secondary air flow (FS), the outer coat being mobile along the inner coat. Also disclosed is an aircraft comprising such an exhaust nozzle.