Abstract: A nozzle effective exit area control system is created with a convergent-divergent nozzle with a divergent portion of the nozzle having a wall at a predetermined angle of at least 12° from the freestream direction. Disturbance generators are located substantially symmetrically oppositely on the wall to induce flow separation from the wall with the predetermined wall angle inducing flow separation to extend upstream from each disturbance generator substantially to a throat of the nozzle pressurizing the wall and reducing the effective area of the jet flow at the nozzle exit.

Abstract: A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

Abstract: An embodiment of the invention is a technique to suppress noise in a jet engine. A substantially annular fan nozzle of a separate-flow turbofan engine includes a flow boundary surface and an outlet to discharge fan air into atmosphere. At least one vane extends substantially radially from the flow boundary surface to vector at least a portion of the fan air toward a direction where noise suppression is desired. The-vane is situated in proximity of the outlet and has a span substantially greater than a thickness of a local boundary layer of the fan air.

Abstract: A noise reducing device in a jet engine that has a cylindrical casing, a cylindrical partition wall that is inserted in the casing while protruding partially from a trailing edge of the casing, and a compressor that compresses air that is taken into the cylindrical partition wall, with the inside of the cylindrical partition wall serving as a duct in which a core stream of high-speed air flows, and the space between the cylindrical partition wall and the casing serving as a duct in which a bypass stream of low-speed air flows, and being connected with a wing of an airplane by a pylon that has a projection portion that extends beyond the casing to the downstream of the core stream and the bypass stream, the noise reducing device includes a nozzle, disposed at the pylon on the downstream of the core stream, that injects a fluid toward a noise generation source that is produced from the mutual approach of an ambient air stream that is produced outside of the bypass stream and the core stream.

Abstract: In one embodiment, a nozzle of a gas turbine engine may be provided having a coanda injector and a fluidic injector which operate together to provide for a change in exhaust flow direction. The fluidic injector may be coincident with or downstream of the coanda injector and both may be used in high pressure ratio operations of the nozzle. The fluidic injector may be positioned opposite the coanda injector and, when activated, may provide for a region of separated flow on the same side of the nozzle as the fluidic injector. The coanda injector may provide additional momentum to an exhaust flow flowing through the nozzle and may encourage the flow to stay attached on the coanda injector side of the nozzle.

Abstract: The invention relates to a thrust reverser (1) for the nacelle of a dual-flow turbine engine, in which the bypass means (4) and the actuation jacks (22) of the sliding cowling (2) and of the reverse flaps (20) are arranged in two substantially parallel planes arranged above one another in the radial direction of the nacelle. The invention also relates to a nacelle for a dual-flow turbine engine that comprises such a thrust reverser.

Abstract: 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 second wall structure. The first wall structure includes a first convergent flap pivotally connected to a first divergent flap. The second wall structure includes a second convergent flap pivotally connected to a second divergent flap. The first wall structure and the second wall structure define the throat along the passage and are reconfigurable to adjust dimensional area of the throat. One or more control valves modulate flow of the pressurized fluid into the passage through a first opening in the first wall structure and a second opening in the second wall structure approximate to the throat to change effective area of the throat by fluidic control.

Abstract: A thrust reverser for a double-flow nacelle that has a cowling, with the thrust reverser having an internal door and an external door designed to be made within the thickness of the cowling. The reverser also has means for simultaneously displacing the doors between a first position called the rest position, in which the doors are integrated into the cowling so as to form an aerodynamic continuity with the external wall and the internal wall of the cowling, and a second active position, in which the doors are open so that the internal and external doors extend toward the inside and toward the outside of the nacelle, respectively, thus at least partially blocking the annular channel of the secondary flow, to deflect the secondary flow and to generate a thrust reversal, with the means being designed to be received in a compartment arranged inside the cowling formed by the doors in the rest position.

Abstract: Systems and methods for influencing thrust of a gas turbine engine are disclosed. A system includes a plurality of pipes positioned at an exhaust nozzle of the gas turbine engine. Each one of the plurality of pipes includes: an inlet inside the exhaust nozzle; an outlet inside the exhaust nozzle; and an intermediate portion outside the exhaust nozzle.

Abstract: This actuator for an aircraft engine nacelle mobile structure (9) comprises a motor (1) intended to be mounted on a fixed part of the said nacelle, an endless screw (21) able to be turned by this motor (1), a slideway (5) intended to be connected to the said mobile structure (9) and comprising a nut (29) in mesh with the said endless screw, and a first ball end (15) allowing an angular offset between the axis of the said endless screw (21) and the said slideway (5). This actuator is notable in that it comprises a sleeve (19) able to accommodate the said screw (21) and extending with clearance inside the said slideway (5), the said nut (29) being mounted on that end of the said sleeve (19) that is closest to the said motor (1), and the said first ball end being interposed between the other end of the said sleeve (19) and the said slideway (5).

Abstract: The exhaust ejector nozzle has a tubular wall defining an exhaust flow passage leading to an outlet plane, and a de-swirl cascade including a plurality of circumferentially interspaced fins each having a first end connected to the wall adjacent the outlet plane and a second end extending into the exhaust flow passage. The de-swirl cascade can maintain the pumping action of the ejector in high swirl exhaust conditions.

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: 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: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.

Abstract: An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The secondary duct has a portion selectively rotatable relative to the remainder of the secondary duct for directing the exhaust gas vector. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.

Abstract: An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.

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: In one embodiment, a nozzle of a gas turbine engine may be provided having a coanda injector and a fluidic injector which operate together to provide for a change in exhaust flow direction. The fluidic injector may be coincident with or downstream of the coanda injector and both may be used in high pressure ratio operations of the nozzle. The fluidic injector may be positioned opposite the coanda injector and, when activated, may provide for a region of separated flow on the same side of the nozzle as the fluidic injector. The coanda injector may provide additional momentum to an exhaust flow flowing through the nozzle and may encourage the flow to stay attached on the coanda injector side of the nozzle.

Abstract: The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles. The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.

Abstract: Exhaust nozzle 14 for an engine of a flying craft, comprising a tubular body with two outlet ducts 16, 18 and boxes 26, 28 for injecting gas into the outlet ducts for the purpose of thrust vectoring, these boxes having windows 38 aligned with slots 39 formed in the outlet ducts, and controlled means for adjusting the outflow of gas injected into the outlet ducts.

Abstract: A manual release mechanism for a thrust reverser actuation system electromechanical brake includes a first release plate, a second release plate, at least two balls, and a handle. The first and second release plates each have grooves formed therein that have a cam surface located at a predetermined angle. The release plates face one another such that the grooves in each plate are substantially aligned, and the balls are each positioned in the aligned grooves. The first release plate is configured to rotate, and the second release plate is configured to translate. The handle is coupled to the first release plate to allow manual rotation thereof. In response to rotation of the first release plate, the second release plate will translate and disengage the electromechanical brake.

Abstract: The present invention reveals a method and apparatus for controlling the effective area and thrust vector angle of a fluid flow. In one embodiment, the fluid flow is controlled in an advanced, high aspect ratio, complex aperture geometry nozzle using asymmetric injection into the subsonic portion of the fluid flow. The present invention vectors the primary flow by partially blocking the flow with an opposed flow across the flow field. A fluidic flow field is defined in a flow container that directs a pressurized, primary fluidic flow from the container towards an exit of the container. A nozzle may cooperate with the exit of the flow container to control the fluidic flow as it exits the flow container. One or more injectors associated with the container are proximate to the effect throat of the primary flow while other are located downstream of to introduce an opposing fluidic flow that interacts with the primary fluidic flow.

Abstract: The process for the continuous preparation of homopolymers or copolymers by free-impinging-jet micromixing of fluids formed (1) of monomer(s) and (2) of an initiator system consists in micromixing the said fluids (1) and (2) and in recovering the mixture of these fluids in the form of a resultant jet Jr, originating from the point of impingement (I), the micromixture being obtained by: a) forming at least one group of at least two jets Ja of the said identical or different fluids, these jets coinciding at a point of impingement (I), the jets Ja of the same group all being of identical geometry, their axes being arranged such that their projections on a plane perpendicular to the axis (A) of the resultant jet Jr are distributed angularly in a uniform manner and these axes being inclined relative to the said axis (A) by the same non-zero angle ? of not more than 90°; b) simultaneously directing at the point of impingement (I) at least one jet Jb of a fluid which is different from at least one of the fluids o

Abstract: According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion, at least one port located in a wall of the nozzle and angled with respect to the fluid flow, and at least one pulse detonation device operable to inject a plurality of detonation waves in a pulsed manner through the port and into the fluid flow. The pulsed detonation waves operate to alter the fluid flow.

Abstract: A pneumatic inhaler that is able to deliver a controlled burst or dose of aerosol from a reservoir of liquid medication. The inhaler is suitable for the aerosolization of liquid medication that is in solution or suspension form. The inhaler is also ideal for the delivery of unique and specialty liquid medications in short aerosol bursts because no additional formulation development is needed and has the further advantage of being able to deliver multiple medications, as mixed by the patient, doctor, or pharmacist, with a single burst at a repeatable output. Because medication and propellant are not mixed until aerosolization occurs, the inhaler is appropriate for more pharmaceutical agents than the current inhalers available and at a substantial cost savings.

Abstract: A device for controlling the direction of flow of a primary fluid includes one or more injectors oriented to inject a secondary fluid against the direction of flow of the primary fluid. The injector is formed by drilling or otherwise forming a hole at an angle to the surface of one or more sidewalls of an engine nozzle or other device. A feedback controller regulates the amount and duration of the secondary fluid injection to achieve the commanded attitude or attitude rate. The controller is coupled to one or more plenums attached to the sidewall(s). The plenums can be arranged to deliver secondary fluid to one or more of the injectors. Secondary fluid delivery to each plenum can be controlled independently to control the flow of the primary fluid in one or more directions. The device can be used to provide thrust vectoring in an aircraft or other type of vehicle, as well as other applications where it is desired to control the direction of a primary fluid.

Abstract: A jet engine nozzle having a pair of pivoting extension arms and a pair of pivoting shells connected to a jet pipe is provided. The first extension arm is pivotally connected to the jet pipe at a first location, while the second extension arm is pivotally connected to the jet pipe at a second location. Each shell is pivotally connected at both the first and second locations. An axis of rotation associated with the first location is coaxial to an axis of rotation associated with the second location. Independent actuation means are provided to rotate the extension arms and the shells, thereby enabling adjustment of the thrust-vector angle or the exhaust area of the nozzle.

Abstract: The process for the continuous preparation of homopolymers or copolymers by free-impinging-jet micromixing of fluids formed (1) of monomer(s) and (2) of an initiator system consists in micromixing the said fluids (1) and (2) and in recovering the mixture of these fluids in the form of a resultant jet Jr, originating from the point of impingement (I).

Abstract: Augmentation of the thrust achieved by a supersonic nozzle of continuous curvature is achieved by causing secondary combustion to occur in an annular region of the interior of the divergent section of the nozzle. The secondary combustion forms a secondary combustion gas that complements the primary combustion gas passing through the nozzle and maintains a wall pressure that is equal to or greater than ambient pressure at low altitudes, eliminating the negative component of the thrust in an overexpanded nozzle at takeoff.

Abstract: In an airless dispensing system, liquids may be dispensed at variable angles from substantially 0° to as much as 50°-60°, by a simple adjustment made by a dispenser operator without ceasing operation or disassembling the dispenser apparatus. A variable angle liquid dispenser comprises a nozzle having a forward face with a dispensing orifice, a first passageway in the nozzle having a central axis intersecting the dispensing orifice, a plurality of angled second passageways in the nozzle, each angled second passageway having a central axis intersecting the dispensing orifice and the central axis of the first passageway, and a variable flow control adjustable to vary the flows of liquid entering the first passageway and the plurality of angled second passageways and to thereby vary the included angle of the liquid dispensed from the dispensing orifice and the width of liquid that may be applied to a substrate.

Abstract: The invention relates to a rocket engine nozzle comprising a system for controlling jet separation of the flow in the nozzle, wherein said control system exhibits a plurality of separation triggering elements (5, 10) arranged in such a way as to generate, from mutually spaced initiation points (9), distinct zones (6) of jet separation, so as to form a three-dimensional separation of the flow.

Abstract: A control system for selectively adjusting effective flow areas of an aircraft engine exhaust nozzle to change operational characteristics of the nozzle. The control system includes a chamber having a hollow interior, a plurality of outlet passages extending from the hollow interior of the chamber to sites within the exhaust nozzle, and an adjustable inlet extending from a pressurized air source to the hollow interior of the chamber for delivering a jet of pressurized air to the chamber. The inlet is adjustable to direct pressurized air to selected one or more outlet passages for the delivery of air via the one or more outlets to corresponding one or more sites within the exhaust nozzle, thereby to change the operational characteristics of the nozzle.

Abstract: A stream of primary gas flowing through a bi-stable thrust vectoring nozzle becomes attached to a first or second surface extending downstream of the nozzle, each surface incorporating one or more control ports for controlling to which surface the stream is attached, wherein relative to the longitudinal axis of the nozzle, the angle of discharge from the first surface is substantially different from the angle of discharge from the second surface, preferably with the first surface substantially aligned with the longitudinal axis of the nozzle. In one embodiment, a plurality of nozzles are arranged with the respective first surfaces substantially aligned with the longitudinal axis of the nozzle combination and each of the respective second surfaces arranged to laterally deflect a respective portion of the stream of primary gas in a respective direction along each of two orthogonal lateral axes.

Abstract: An improved pivoting door thrust reverser system for a turbofan aircraft jet engine having a non-translatable housing and at least one thrust reverser door being pivotable between a stowed forward thrust position and a deployed reverse thrust position. The thrust reverser door is pivotable about a first axis and a kicker plate is hinged to the door at a second axis. As the door is deployed by an actuator a spring loaded roller clamp means keeps the kicker plate clamped to the actuator body until a portion of the kicker plate positively engages the thrust reverser door and the roller clamp means is then disengaged from the actuator body.