Abstract: In a jet engine having a plug nozzle and a plug extending rearwardly from the nozzle exit, the improvement comprising a plug having successive cross sections spaced apart rearwardly of the nozzle exit, the cross sections transitioning from circular or near circular at the exit plane defined at the nozzle exit, to progressively non-circular, rearwardly.

Abstract: A vectoring nozzle with external actuation generates thrust vectoring by applying mechanical or fluidic actuation, or both, on the nozzle deck, external sidewalls, and/or air vehicle aft body to produce changes in the aft body flowfield and/or exhaust plume. An external mechanical sidewall may be integrated into a nozzle deck or side walls without the need for engine bleed to supply fluid injectors. An external fluidic vectoring system uses injectors or plasma devices located aft of the nozzle exit to vector the exhaust plume with no external moving parts. Elements of both mechanical and fluidic systems may be combined for a given application.

Abstract: The invention relates to a nacelle for a variable area nozzle propulsion unit comprising a nacelle, hosting a turbofan jet engine, of dual-flow type. The propulsion unit includes: a fixed part, carried by the inboard half-nacelle defined by a vertical plane of symmetry of the nacelle; and a movable part carried by the outboard half-nacelle. The moving part containing or releasing part of the secondary flow, depending on its open or closed position. The moving part being able to move to a discrete number of positions including a closed position, an open position, and one or more intermediate positions so as to provide variable area nozzle configurations for the turbofan engine.

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: A nozzle assembly for a gas turbine engine includes a door axially slidable relative to a passage in communication with a secondary flow path to regulate the secondary flow though the passage.

Abstract: A thrust reverser for a gas turbine engine includes a hinge, a propulsion system duct, and a kicker blocker. Bypass air and gas path air travel through the propulsion system duct and the propulsion system duct has an intake inlet and an exhaust outlet. The kicker blocker has a kicker portion and a blocker portion. The kicker blocker is rotatably attached to the hinge and is movable between a stowed position and a deployed position. The blocker portion extends into the propulsion system duct when the kicker blocker is in the deployed position to block bypass air and gas path air traveling through the propulsion system duct in a first direction prior to the exhaust outlet, thereby redirecting the bypass air and the gas path air in a second direction.

Abstract: The present invention relates to an aircraft gas turbine with a core engine 10 which is surrounded by a bypass duct 29 enclosed radially outwards by a bypass wall 30, with a radially inner wall 31 of the bypass duct 29 forming with the radially outer bypass wall 30 a bypass nozzle 32, and with the radially inner wall 31 including an adjusting element 33 extending along the circumference of the inner wall 31 and being deformable radially outwards.

Abstract: A nozzle includes first guiding elements (10) circumferentially arranged at a nozzle rim (9). To reduce sound emission while keeping flow losses low, second guiding elements (20) are also circumferentially arranged at the nozzle rim (9), with one of the first and second guiding elements (10, 20) being diffuser-type and the other of the first and second guiding elements (10, 20) being nozzle-type and with both types of guiding elements circumferentially alternating with each other.

Abstract: A composite article includes a composite member, a flexible member and at least one shape memory material member. The composite member has longitudinally extending fibers in a matrix material. The at least one shape memory material member extends substantially parallel to the composite member and the flexible member is positioned between the composite member and the at least one shape memory material member to bond the at least one shape memory material member to the composite member. The composite article is particularly suitable for use as a tab for an exhaust nozzle of a turbofan gas turbine engine.

Abstract: A gas turbine engine system includes a fan bypass passage (27), a core nacelle (28) having an inner fixed structure (40) within the fan bypass passage, a passage (42) extending through the inner fixed structure, and a duct nozzle (48). The passage includes an inlet (44) for receiving a fan airflow (F2) from the fan bypass passage and an outlet (46) for discharging the fan airflow. The duct nozzle includes a variable cross-sectional exit area (50) for controlling the fan airflow within the passage and is selectively moveable to influence the variable cross-sectional exit area.

Abstract: The invention relates to a device for damping the lateral forces due to jet separation that act on a rocket engine nozzle during a stage of starting or stopping the engine, the engine including at least two identical drive assemblies mounted on the nozzle to take up the lateral forces acting thereon, each drive assembly comprising a first member forming a strut, a second member forming an anchor structure, and an actuator. Each strut comprises means enabling it to act as a rigid strut so long as the lateral forces acting on the corresponding actuator remain below a determined force threshold, and as an element for peak limiting force and for dissipating residual kinetic energy once the forces acting on the actuator exceed the determined force threshold.

Abstract: A turbofan engine (10) includes a fan variable area nozzle (FVAN) (50) which effectively changes the physical area and geometry within a fan bypass flow path (40) to manipulate the pressure ratio of the bypass flow. The FVAN generally includes a multitude of aerodynamically shaped inserts (52) circumferentially located about the core nacelle (12). The FVAN at a fully stowed position (takeoff/landing) takes up a minimum of area within the fan bypass flow path to effectively maximize the fan nozzle exit area (44) while in the fully deployed position (cruise) takes up a maximum of area within the bypass flow path to effectively minimize the fan nozzle exit area. By separately adjusting each of the multiple of inserts relative the other inserts the FVAN provides an asymmetrical fan nozzle exit area to selectively vector the fan bypass flow.

Abstract: A turbofan engine includes a fan variable area nozzle having a multiple of vents through a fan nacelle and a sleeve system movable relative to the vents by an actuator system. The fan variable area nozzle changes the effective area of the fan nozzle exit area to permit efficient operation at predefined pressure ratios. The vents include a grid structure which directs and smoothes the airflow therethrough as well as to reduce noise generation.

Abstract: The present invention relates to a thrust inverter for a turbojet engine nacelle (1) including at least one outer cowl (11) that is movable between a closed position and a thrust inversion position, said movable cowl also being able to be opened into a supporting position towards which said movable cowl is hinged and guided through the use of a guiding means that is suitable to said movable cowl and located substantially on a pylon, to which the nacelle is intended to be attached and at least one front frame (15) capable of being mounted downstream from an air blower housing for said turbojet engine and directly or indirectly holds at least one flow diversion means (12). Said thrust inverter is characterized in that the front frame is detachably connected to the housing in a translatable manner along at least one related guiding member (17) once said front frame is detached from the housing.

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 method and system for thrust vectoring a primary fluid flow from an exhaust nozzle of a jet engine that significantly increases the non-axial force able to be generated by a flight control surface associated with the nozzle. In one implementation the method involves placing a flight control element having a movable portion adjacent a downstream edge of the nozzle. A secondary fluid flow is created adjacent a surface of the flight control element that influences a boundary layer of the primary fluid flow over the flight control element. This causes the primary fluid flow to generate a force that is directed non-parallel (i.e., non-axial) to a longitudinal axis of the nozzle. In one specific implementation a plurality of slots are formed in the flight control surface, and the flight control surface is formed by an airfoil. In another implementation the flight control surface is formed on an interior wall of the nozzle at a downstream edge of the nozzle.

Abstract: An afterburner nozzle actuation system includes a case, an actuation structure, a plurality of cam plates, a plurality of nozzle flaps and seals, and a plurality of rollers. The actuation structure surrounds at least a portion of the case and includes an aft end that has a polygonal cross section shape. The cam plates are removably coupled to an inner surface of the actuation structure, and each includes a cam surface. The nozzle flaps are rotationally coupled to the case and extend at least partially from the actuation structure aft end. Each nozzle flap is movably coupled to a different one of the cam plates. The rollers are each rotationally mounted on a different one of the nozzle flaps and engage the cam surface of one of the cam plates.

Abstract: A gas turbine engine includes a fan, a bypass duct having a nozzle, through which fluid from the fan flows, and a variable area nozzle device located in the nozzle. The variable area nozzle device has an arcuate fairing having one end in slidable cooperation with the bypass duct. In a deployed position the area of the nozzle is reduced from that when stowed, thereby improving engine operability and efficiency.

Abstract: An apparatus and method comprising a fan nozzle sleeve, a plurality of slider mechanisms, and a fan nozzle actuator system. A flow of gases generated by an engine moves through and exits the engine at an aft end of the fan nozzle sleeve. The plurality of slider mechanisms is configured to connect the fan nozzle sleeve to a translating sleeve for a thrust reverser for the engine. The fan nozzle actuator system is configured to activate the plurality of slider mechanisms to move the fan nozzle sleeve in an aft direction to change a direction of the flow of gases exiting the engine at the aft end of the fan nozzle sleeve.

Abstract: A blocker door system to be used with an aircraft engine thrust reverser comprises a push ring, a plurality of connecting rods, a plurality of crankshafts, a plurality of blocker doors, and a plurality of linking elements. The push ring may encircle the aircraft engine. The connecting rods may connect along the circumference of the push ring. The crankshafts may rotatably couple to the connecting rods. The blocker doors may be positioned adjacent one another around the circumference of the aircraft engine wherein at least a portion of one blocker door covers at least a portion of the adjacent blocker door. The linking elements may connect one blocker door to the adjacent blocker door and may be operable to guide the motion of the blocker doors relative to one another.

Abstract: 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 feature disposed in the half dovetail shaped slot in the first component.

Abstract: The invention relates to a twelve-hour structure for a thrust reverser, that comprises a half beam (1) capable of holding a reverser half cowling and including a plurality of hinge yokes (9c) for rotatingly mounting said half beam (1) on a nacelle-holding mast. The half beam (1) is at least partially made of a composite material.

Abstract: Varying the fan nozzle flow area in a gas turbine engine allows adjustment of the bypass flow for varying operational conditions such as cruise and take off. However, care must be taken with regard to variation in order not to introduce drag or operational susceptibility to failure. By provision of a deformable member having a contiguous surface, which is deformed laterally from a splitter such as a pylon variation in flow area is achieved. A deformable member will be secured through seals to ensure a smooth surface. Actuation may be through a shape memory alloy material or provision of mechanical actuators to cause deformation of the contiguous surface.

Abstract: 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 leading and trailing edges and slidable sealing joints with slidingly un-restrained center surfaces between adjacent segment leading and trailing edges. Segmented first and second basesheet side edges first and second segment side edges of the basesheet segments respectively. Slidably sealingly engaged overlapping flanges at the segment leading and trailing edges include tacked together transversely spaced apart first and second distal ends of the overlapping flanges. Leading and trailing edge ribs supporting the overlapping flanges are clipped together with longitudinally spaced apart and transversely extending forward and aft slits in retainers.

Abstract: An aircraft engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments having panel bodies between segment leading and trailing edges and slidable sealing joints with slidingly un-restrained center surfaces between adjacent segment leading and trailing edges. Segmented first and second basesheet side edges include first and second segment side edges of the basesheet segments respectively. Slidably sealingly engaged overlapping flanges at the segment leading and trailing edges include tacked together transversely spaced apart first and second distal ends of the overlapping flanges. A basesheet assembly includes a frame includes first and second side rails supporting the first and second basesheet side edges. An aircraft gas turbine engine exhaust nozzle includes divergent seals with the basesheet assemblies in sealing engagement against divergent flaps along the first and second side rails.

Abstract: A missile in which a nose portion is rotatably mounted on a main body portion of the missile and is subjected to thrust to bring it to a demanded roll attitude and to apply to it a demanded lateral steering force. The thrust is produced by a propellant gas and supplied to discharge ducts in the nose portion which provide for the discharge of the propellant gas tangentially with respect to the nose portion. The discharge ducts are selectively opened and closed by relative axial displacement of the nose portion and a valve spool which controls the flow of propellant gas. An actuator responsive to guidance control signals causes a predetermined roll torque to bring the nose portion to a demanded roll attitude and a predetermined lateral steering force on the missile.

Abstract: The invention relates to a torque limiter for an actuator including a screw (101), a nut mounted on said screw, an actuation tube (105) rigidly connected to the nut and means (109, 133) for rotating said screw, said limiter being characterized in that it includes an abutment (115, 110) capable of: preventing the rotation of said tube (105) by friction simply by an axial force exerted by said screw (101) onto said nut during the movement thereof; and enabling the rotation of said tube (105) when said nut arrives at an axial abutment of said screw beyond a predetermined torque threshold defined by the axial force.

Abstract: The invention relates to a system for actuating a plurality of actuators (15) that can move a mobile panel of an aircraft nacelle. Said system comprises at least two motors (16) that can drive the actuators (15), the two motors (16) being controlled and supplied by at least two separate control units (33, 35), and the actuators (15) being mechanically interconnected by a mechanical transmission (37). The invention also relates to a nacelle comprising such an actuating system.

Abstract: An exhaust mixer for a gas turbine engine including a plurality of circumferentially distributed alternating inner and outer lobes, where each of the inner lobes is configured with a circumferential offset between the base and the tip thereof, and a direction of the circumferential offset defined from the base to the tip of each of the inner lobes is the same for all of the inner lobes and opposite to that of a swirl component of a main gas path flow entering the exhaust mixer.

Abstract: A gas turbine engine system includes a fan (14), a housing (28) arranged about the fan, a gas turbine engine core having a compressor (16) at least partially within the housing, and a fan bypass passage (30) downstream of the fan for conveying a bypass airflow (D) between the housing and the gas turbine engine core. A nozzle (40) associated with the fan bypass passage includes a first nozzle section (54a) that is operative to move in a generally axial direction to influence the bypass airflow, and a second nozzle section that is operative to also move in a generally axial direction between a stowed position and a thrust reverse position that diverts the bypass airflow in a thrust reversing direction. An actuator (42) selectively moves the first nozzle section and the second nozzle section to influence the bypass airflow and provide thrust reversal.

Abstract: A gas turbine engine system includes a nozzle having a plurality of positions for altering a discharge flow received through the nozzle from a gas turbine engine fan bypass passage. The nozzle is integrated with a thrust reverser having a stowed position and a deployed position to divert the discharge flow and generate a reverse thrust force. At least one actuator is coupled with the nozzle and the thrust reverser to selectively move the nozzle between the plurality of positions and to move the thrust reverser between the stowed position and the deployed position.

Abstract: An exhaust nozzle includes a conical duct terminating in an annular outlet. A row of vortex generating duplex tabs are mounted in the outlet. The tabs have compound radial and circumferential aft inclination inside the outlet for generating streamwise vortices for attenuating exhaust noise while reducing performance loss.

Abstract: An external flap connection assembly for a turbine engine nozzle has a track frame, a slider track, and an external flap. The external flap is removably connected to the slider track via a retaining member which has a slider block.

Abstract: A non-invasive system, method, and apparatus for control input prediction and state verification of an aircraft's fluidic vectoring exhaust is disclosed. The control system derives a desired vector state, then predicts and sets the fluidic injection input required to produce the desired vector state. A vectored state verification routine is used to determine the resulting vector state for feedback to the control system.

Abstract: This leaf spring (17) for a thrust reverser shutter (13) is noteworthy in that it has two branches (19, 21) defining a U shape, the ends (19a, 19b, 21a, 21b) of these branches being able to cooperate respectively with a shutter (13) of said reverser and with a link (15) for actuating this shutter.

Abstract: In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diffusion pipes each secured to a respective maintenance cover, each air diffusion pipe opening out into an air injection pipe secured to a thrust reverser cover and itself opening out to the outside of the nacelle via the trailing edge thereof, each air injection pipe being suitable for uncoupling from the corresponding air diffusion pipe when the corresponding thrust reverser cover slides downstream.

Abstract: The invention relates to a structure for a thrust inverter, that comprises: a boom (3, 5) for a thrust inverter structure, that comprises an integrated portion defining a bowl to be inserted into and attached to a front half-frame (1) of said thrust inverter; a front half-frame (1) for the thrust inverter structure, shaped at least one of its two ends so as to be fitted on and attached to a bowl of a boom according to the above; and a thrust inverter half-structure, characterised in that it comprises upper (3) and lower (5) booms and a front half-frame (1) according to the above.

Abstract: A gas turbine engine comprising a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating multidirectional thrust.

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: This invention relates town ejector nozzle tube 1, having along its length an essentially constant, essentially oval hollow cross-section, with an inflow lip 2, having a pitch-circle type cross-section, being arranged at a flow leading-edge area of the ejector nozzle tube 1. The inflow lip 2 is provided with a plurality of grooves 3 issuing (4) to the top and bottom sides of the ejector nozzle tube 1 and connecting to an interior 5 of the ejector nozzle tube 1 formed by the hollow profile. It also relates to an aircraft engine with optimized oil heat exchanger with at least one oil cooler 6 disposed in a trailing-edge area 7 of an aerofoil-type structure 8, with at least one flow entrance area 9 being provided to supply ambient air to the oil cooler 6 disposed in a flow duct 10, and with an ejector nozzle tube 1 in accordance with one of the claims 1 to 3 being arranged downstream of the oil cooler 6 in the flow duct 10.

Abstract: A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body.

Abstract: A system that allows for quick and easy adjustment of the position of a thrust reverser pivot door comprises an actuator rod end bolt and a pair of pivot door hinge pins, all of which have an eccentric element. The actuator rod end bolt includes a cylindrical portion along the center of the length of the bolt that has an eccentric element which protrudes beyond the outer surface of the cylinder. Each pivot door hinge pin includes a cylindrical portion along the center of the length of the pin that has an eccentric element which protrudes beyond the outer surface of the cylinder. Rotation of either the actuator rod end bolt or the pivot door hinge pins or both the actuator rod end bolt and the pivot door hinge pins adjusts the position of the pivot door.

Abstract: An apparatus for driving a body with 3-degree of freedom angular motion, comprises: a body connected to a fixing part so as to be rotatable centering around a pitch axis, a yaw axis, and a roll axis; a pitch axis driving unit for rotating the body centering around the pitch axis; and a yaw axis driving unit for rotating the body centering around the yaw axis. Since one of the pitch axis driving unit and the yaw axis driving unit restricts the body from rotating centering around the roll axis fixed to the body, the conventional roll-rotation restricting link is not needed between the body and the fixing part. Accordingly, a size of the apparatus is reduced.

Abstract: Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter.

Abstract: Elbow nozzles in VTOL aircraft engines, are highly stressed when operating, in that they act as high pressure vessels. The invention provides a means for varying the outlet area of such a nozzle without weakening its structure. A single flap is inserted inside the nozzle and connected to the nozzle extremity for pivoting about an axis which lies across the outlet between a position wherein its edges seal against the nozzle side and so restrict the nozzle outlet area and, a position wherein it lies parallel with a wall of the nozzle so that exhaust gas can pass both sides and out of a bigger outlet.

Abstract: 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 gas turbine engine. The nozzle section is movable between a first length and a second length that is larger than the first length to influence the flow. For example, the nozzle section includes members that are woven together to form collapsible openings that are open when the nozzle section is moved to the first length and that are closed when the nozzle section is moved to the second length.

Abstract: An annular exhaust duct of a gas turbine engine includes inner and outer cases co-axially disposed, and radially spaced apart by a plurality of airfoils radially extending therebetween. The outer case includes a connection apparatus for supportably connecting the exhaust duct to the gas turbine engine and the inner case includes an axial end portion at a rear end thereof for connection with a tail cone. The axial end portion bends radially and inwardly at a rear extremity thereof to stiffen the rear end of the inner ease.

Abstract: An actuator arrangement comprises a plurality of linearly extendable actuators arranged to be driven by a common electrically driven motor, each actuator, being provided with limit stops to limit extension and/or retraction thereof, wherein the limit stops of the actuators are positioned such that a first one of the actuators has a smaller range of permitted extension than at least a second one of the actuators.

Abstract: The cross sectional flow area of a fan discharge nozzle on one side of a central plane of an associated gas turbine engine power plant is greater than the corresponding flow area of the fan discharge nozzle on an opposite side of the central plane to compensate for the blockage of fan airflow by a pylon.

Abstract: An outlet device for a jet engine includes an outlet nozzle and a plurality of guide vanes arranged movably in the outlet nozzle for guiding a gas from the jet engine for the purpose of steering a craft equipped with the jet engine. At least one of the guide vanes can be adjusted into such a position that hot parts of the engine located inside the outlet nozzle are at least substantially concealed seen from the outlet side of the outlet nozzle.