Abstract: A fuel spraybar assembly for spraying fuel within a gas turbine engine. The spraybar assembly includes radial and lateral members that distribute fuel within the flowpath. In one embodiment two lateral members are located at the radially inward end of a radial member and generally form a “T” shape. Circumferentially spaced adjacent spraybars subdivide the flowpath into a plurality of circumferential combustion zone segments. In one embodiment the junction of the radial and lateral members provides a flameholding feature that stabilizes the combustion flame. In another embodiment, fuel is introduced non-uniformly within the afterburner resulting in thermal vectoring of the engine thrust.

Abstract: An electromechanical thrust reverser actuation system that is designed with non-symmetric redundant channels is interfaced with an aircraft engine control system that is also redundantly designed. In one embodiment, the engine control system is also designed with non-symmetric redundant channels, and in another embodiment it is designed with symmetric redundant channels.

Abstract: A rocket nozzle assembly is provided for operatively coupling to a rocket motor. The assembly includes a nozzle insert structure having a converging-diverging passageway with a throat region. First and second thrust control cylinders are parallel to each other and rotatable about respective axes transverse to the passageway central axis. The first and second thrust control cylinders intersect the throat region and include respective grooves. A thrust control cylinder-rotating subassembly is operatively associated with the first and second thrust control cylinders to rotate the cylinders about their respective axes and move the grooves relative to the throat region. Movement of the grooves changes the effective cross-sectional throat area of the converging/diverging passageway at the throat region for controlling the thrust when the rocket nozzle assembly is operatively engaged with an operating rocket motor.

Abstract: A gas turbine engine of a fan bypass type includes an exhaust shroud having a perforated tubular wall extending between a forward end and an aft end. The exhaust shroud is adapted to be affixed to a gas turbine engine exhaust for discharging engine exhaust gases without substantial blockage thereto. The perforations formed in the shroud wall communicate the regions at both sides of the shroud wall to pass fluid flow across the perforated shroud wall so that the mixing of the engine exhaust gases with a surrounding fluid flow is enhanced. The mixing of the engine exhaust gases with the surrounding fluid flow is further enhanced by a trailing edge of the exhaust shroud. The trailing edge is deviated from a straight line in a circumferential direction of the tubular wall to effectively increase the peripheral length of the mixing boundary. Thus, the jet noise contribution volume of the engine exhaust gases is effectively reduced, thereby significantly reducing the aero-engine jet noise.

Abstract: In a turbojet thrust reverser comprising, in an annular section of an outer cowling of the turbojet, a number of movable doors which, in an inactive position during operation in a forward thrust configuration, close off passages separating rigid spars of a fixed structure, there is provided, between two adjacent doors, a locking system which allows substantially simultaneous opening of the two doors. The locking system comprises, for each door, at least one hook mounted on the fixed structure so that it can be pivoted by an olive secured to the door between a door locking position and an unlocked position during opening or closing movement of the door. The two hooks of the locking system are rotationally interlinked by a mechanical linkage device, for example link rods, so as to prevent the unlocking of one door if the other door is closed.

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: Disclosed is an exhaust mixer (50) including a passage (54) extending from an inlet (56) to an outlet (58) that is coincident with a centerline axis of mixer (50). Several ridges (68) are circumferentially disposed about the axis and each flare away from the centerline axis relative to a direction along the centerline axis from inlet (56) toward outlet (58). Ridges (68) each define a corresponding one of several inner channels (74) radially disposed about passage (54) that each intersect passage (54) between inlet (56) and outlet (58). Several outer channels (84) are also radially disposed about passage(54) and are each positioned between a corresponding pair of inner channels (74). Ridges are each shaped to turn inner channels (74and outer channels (84) about the axis as ridges (68) extend along the indicated direction. Inner channels (74) diverge away from the axis and one another in this direction while outer channels (84) converge toward the axis and one another in this direction.

Abstract: A cascade type thrust reverser for an air duct of a turbofan engine includes a lock mechanism mounted on a track beam that supports the translating sleeve. A locking portion of a lock member of the lock mechanism is engageable with a slider by which the translating sleeve is supported by the track beam to lock the translating sleeve in the forward, closed position.

Abstract: The invention relates to lobe-type mixer tube for a bypass jet engine in which a bypass flow delivered by a fan is mixed with a hot gas stream issuing from the core engine, said lobe-type mixer tube having essentially circumferentially equally spaced gutter-shaped, radially moderately alternately inward and outward directed ducts to guide both the bypass flow and the hot gas stream, said ducts each having an end formed by an essentially plane extreme section and the respective extreme sections of some ducts when viewed in a longitudinal section extending in the direction of flow being inclined vis-a-vis the extreme sections of the other ducts. In this arrangement the radially outward directed ducts, when viewed circumferentially, alternately issue at points offset one from the other.

Abstract: A diffuser comprises a conduit having a cross-sectional area that increases in a direction fluid flow. In one embodiment, the diffuser is used to reduce the incidence and severity of flow fluctuations that occur in an electrostatic deposition apparatus. In some embodiments, the diffuser includes one or more flow control features. A first flow-control feature comprises one or more appropriately-shaped annular slits through which fluid having a greater momentum than a primary fluid moving through the diffuser is injected into the “boundary layer” near the wall of the diffuser. A second flow control feature comprises one or more annular slits or, alternatively, slots or holes that are disposed at appropriate locations around the circumference of the diffuser through which a portion of fluid flowing in the boundary layer is removed. Boundary-layer flow removal is effected, in one embodiment, by creating a pressure differential across such annular slit or slots.

Abstract: A jet noise suppressor is disclosed. The jet noise suppressor includes first and second high frequency pulse injection units located exteriorly of the turbine engine exhaust nozzle. The pulse injection units are located oppositely, diametrically across the exhaust nozzle. The pulse injection units include a resonance tube in outlet fluid communication with an injector nozzle. High pressure gas is supplied to the resonance tubes. A second source of high pressure gas includes a switch for supplying an alternating flow of high pressure gas to the injector nozzles. The combination of the high frequency pulses emitted from the injection units with the alternating low frequency, high amplitude mode of injection across the exhaust nozzle, provides a dramatic reduction of noise as well as exhaust temperature.

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: An exhaust nozzle includes an annular exhaust duct for discharging exhaust from an aft end thereof. Circumferentially adjoining chevrons extend from the duct aft end around only an arcuate portion thereof leaving a plain arcuate shelf between terminal ones of the chevrons. Each of the chevrons has a triangular configuration and a compound arcuate contour both circumferentially and axially.

Abstract: The present invention relates to a gas turbine engine jet noise suppressor which does not appreciably adversely impact engine thrust and performance. The jet noise suppressor includes a nozzle, having an arrangement thereon of tabs disposed on the downstream end of the nozzle, the tabs having a length and the angular offset with respect to the engine flow such that mixing occurs primarily at the interface of the engine flow and the ambient air. In addition, various construction details are developed for the tabs including tabs that are trapezoidal with tapered sides such that the tabs minimize adverse impact to engine performance.

Abstract: A variable area exhaust nozzle with a variable thrust vector angle for a turbo-fan engine and mounted on the aft portion of the nacelle which wraps said engine. The nozzle may include a fixed structure having at least two lateral arms separating two radial cutouts. The cutouts are positioned one above the other, one being located above the engine axis, the other one below the engine axis. At least two shells close the fixed structure cutouts and are pivotally mounted on the fixed structure to form a portion of the exhaust nozzle of the engine. A sealing means ensures fluid tightness between the shells and the fixed structure for any angular position of said shells. Actuator means are provided for pivoting the shells either to a symmetrical configuration for changing of the value of the exhaust area of the nozzle or to an unsymmetrical configuration for changing the angle of the thrust vector of the exhaust nozzle.

Abstract: An electric thrust reverser actuation system includes an electric motors that is controlled to operate in both a motoring mode and a generating mode. During normal actuation system operations, the electric motor is controlled to operate in the motoring mode to move one or more moveable thrust reverser components. During a power interrupt event, in which the motor's primary power source is lost, the motor is controlled to operate in the generating mode. The electrical power generated by the motor during its operation in the generating mode maintains the thrust reverser system locking mechanisms in an energized, unlocked condition, thereby preventing damage to system components.

Abstract: A middle layer (22) having partitioned cavities (28) is sandwiched between an imperforate sheet (24) and an optional perforate sheet (26) to form a low resistance acoustic liner (22). A preferred method of manufacture of the low resistance acoustic liner (20) uses aspects of the buried septum technique including placing an uncured imperforate septum (36) between a support layer (32) and a partitioned cavity middle layer (22), pressing the middle layer into the imperforate sheet (24) and through the support layer (32), curing the imperforate septum 36 to form the imperforate sheet (24), removing the support layer (32), and attaching a perforate sheet (26) of roughly at least 15% open area to the top side of the middle layer. A preferred embodiment of inner and outer linings (47), (49) is provided. Each lining includes a combination of annuluses of absorptive and/or low resistance liners (51), (53).

Abstract: A gas turbine engine exhaust nozzle includes an exhaust duct for channeling a gas jet. A plurality of adjoining chevrons are disposed at an aft end of the duct to define an exhaust outlet. Each of the chevrons is triangular in configuration, with a base, apex, side trailing edges converging therebetween, and radially opposite first and second surfaces bounded thereby. The trailing edges of adjacent chevrons are spaced laterally apart to define respective diverging slots disposed in flow communication with the duct. The chevrons have a concave contour axially between the bases and apexes which promotes jet mixing through the slots.

Abstract: Brush seals formed in hemispherical rings are supported to the end of the convergent nozzle of the each of the clam shells of a multi-axis vector thrust nozzle of a gas turbine engine powering aircraft. The brush seal may be arced or straight and bear against the spherical surface of the collar formed on the end of the tail pipe and is mounted so that high pressure forces the bristles against the backing plate of the seals.

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 thrust directing mechanism to vector thrust and control discharge throat area with a number of vanes mounted across the passage. The mechanism includes a control link pivotally coupled to each of the vanes. The control link is selectively movable to correspondingly pivot the vanes and has at least two degrees of freedom corresponding to a two coordinate position. A desired orientation of the vanes may be determined as a function of the two coordinate position. The discharge exit area is contracted by adjusting convergence of the vanes. During convergence, the vanes are pivoted to various pivot angles selected to optimize thrust efficiency when contracting the throat area.

Abstract: A gas turbine engine includes a variable area nozzle having a plurality of flaps. The flaps are actuated by a plurality of actuating mechanisms driven by shape memory alloy (SMA) actuators to vary fan exist nozzle area. The SMA actuator has a deformed shape in its martensitic state and a parent shape in its austenitic state. The SMA actuator is heated to transform from martensitic state to austenitic state generating a force output to actuate the flaps. The variable area nozzle also includes a plurality of return mechanisms deforming the SMA actuator when the SMA actuator is in its martensitic state.

Abstract: The present invention relates to a gas turbine engine exhaust nozzle for suppressing jet noise. The nozzle has an arrangement of tabs that extend in radially inward and outward directions. The tabs cause the formation of vortices which pull into mixing engagement the exhaust gas streams from the core and fan ducts and the ambient air. In addition, various construction details are developed for the tab arrangement including tabs that are directed radially inwardly and outwardly, and tabs that are continuous with the nozzle duct therebetween.

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: 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: An actuation activation system for an aircraft engine thrust reverser system is provided including an improved locking actuator (29), a sleeve sensor mechanism, and auto-restow control logic. The locking actuator (29) includes a lever (57) corresponding to whether the actuator is locked or unlocked. A slide-by first proximity sensor (45) is positioned near the lever and set to normally far and triggering near. The first proximity sensor produces a first trigger signal for use in the auto-restow control logic. The sensor mechanism includes a second slide-by proximity sensor and a target in communication with a thrust reverser translating sleeve. The second sensor is connected to the forward side of an engine torque box. A preferred embodiment sensor mechanism (78) is provided and includes a pivotable target arm (96) having a proximal end (98), a distal end (100), and a middle portion pivotably connected to fixed engine structure, preferably torque box (30).

Abstract: An axially symmetric turbojet-engine exhaust nozzle which is directable as a unit. The exhaust nozzle is situated downstream of an exhaust duct (1) fitted with a spherical wall (5). A single control ring (12) driven by linear actuators (30) allows regulation of the nozzle cross section and direction. Converging flaps (7) are guided on an upstream side by the spherical wall (5) and are supported at a downstream side by a control lever (13) which hinges on the control ring (12) and rests upstream on an external surface (16) of the spherical wall (5). Diverging flaps (10) hinge on the converging flaps (7) to form an inner ring of hot flaps. The diverging flaps (10) are situated downstream in an extension of the converging flaps (7) and further hinge on an outer ring of cold flaps (11), which in turn hinge on the control ring (12).

Abstract: A thruster valve has a continuously positionable piston between a closed position and a maximum open position. The piston moves in response to the difference in pressure between the pressure of the valve's inlet and thruster nozzle and the pressure behind the piston. A pivotable flapper valve regulates this pressure difference. When a change in thrust is required a force is applied to the flapper causing a change in this pressure difference which causes the piston to move until the desired thrust level is obtained.

Abstract: A method and apparatus for adjusting the flame exit velocity of a high velocity burner. The burner includes burner combustor chamber having a fluid accelerating nozzle and a burner combustor exhaust port. Fuel is delivered to the burner combustor through a fuel inlet. An ignitor is provided to initiate combustion of the fuel which is mixed with air from an air inlet. An adjusting device is provided to vary the flame exit area of the burner. The adjusting device includes an adjusting rod connected to an extension rod which preferably extends through the burner ignition chamber to the burner combustion exit port. For example, a tapered plug is attached to the end of the extension rod. The tapered plug is tapered in a direction decreasing toward the burner combustion exit port and can include fins attached around a periphery of the plug.

Abstract: Three vectoring ring support and actuation apparatuses are disposed in an equi-angular manner circumferentially about the engine casing. Each of the vectoring ring support and actuation apparatuses includes a vectoring ring means to transfer side loads from the vectoring ring to the engine casing, a vectoring ring translation means for allowing the ring to be translated, and a support pivoting means and ring gimballing means to allow the vectoring ring attitude adjustments by a set of linear actuators. The vectoring ring support apparatus transfers side loads acting on a vectoring ring and generated by a gas turbine engine thrust vectoring nozzle to a relatively stationary portion of the engine and allows tilting of the vectoring ring to vector the thrust of the nozzle.

Abstract: A turbo fan engine nacelle houses an engine which forces engine exhaust through a primary nozzle and a fan nozzle positioned along a common central axis. The primary nozzle is bordered interiorly by a primary nozzle plug and bordered exteriorly by a primary nozzle sleeve. The fan nozzle is bordered interiorly by a core cowl and bordered exteriorly by a fan nozzle sleeve. The primary nozzle plug includes a generally cone shaped outer surface which is concave when viewed in side elevation. The concave outer surface has a radius of curvature (Rc). The core cowl has a distal end which is radially spaced from the outer surface of the primary plug by a distance (&Dgr;H) in a direction perpendicular to the central axis. The primary nozzle plug and core cowl define a ratio Rc/&Dgr;H between approximately 14 and 18. The distal end of the core cowl has a core cowl radius Rp with respect to the central axis.