Abstract: A centerbody for the exhaust system of a gas turbine engine having an upstream end mounted within an exhaust duct casing of the exhaust system. The centerbody includes a plurality of ventilation openings defined in a centerbody wall which provide fluid flow communication between an internal cavity and exhaust gas flow surrounding the centerbody, such that ventilating air from within the cavity can exit into the exhaust gas flow.

Abstract: Improvement of combustion stability in retard ignition at the time of starting in a cold state, high output in a full throttle condition, reduction of smoke, and prevention of wear of the cylinder liner caused by oil dilution, are to be attained. In connection with the flow of fuel into each hole and a fuel inflow angle which is determined by the axis of each hole formed in a plate, the fuel inflow angle of an hole directed to a spark plug is set large to reduce an effective flow path area, thereby making the amount of fuel in the hole smaller than in other holes. A shallow cavity is formed in a piston crown face and a small prominence confronting fuel sprays is formed within the cavity.

Abstract: A propulsion thrust control system and method for controlling thrust in a rocket motor includes configuring valves of an energized rocket motor to an initial total valve area according to a total thrust command. The total thrust command is converted into a commanded propellant mass flow discharge rate. A varying total valve area is computed from an error between the commanded propellant mass flow discharge rate and a calculated propellant mass flow discharge rate. The valves are reconfigured according to a distribution of the varying total valve area. The propulsion system includes a pressure vessel with valves and a controller for regulating the valve area according to a propellant mass flow discharge rate from the pressure vessel.

Abstract: A propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along an axis of the aircraft by a gas generator is disclosed. The propulsion gas exhaust assembly includes a transition element emerging in two duct elements each communicating with an ejection half-nozzle, wherein each of the two duct elements forms an elbow downstream of the transition element.

Abstract: An aircraft nacelle in which a power plant is arranged and delimits a duct for a flow which assists the thrust. The nacelle includes a device for reducing, canceling, or reversing the thrust that includes at least one flap that can an active position in which it deflects—in the direction of a radial opening—at least a portion of the flow and an at-rest position in which the flap does not interfere with the flow, whereby the wall of the nacelle delimiting the duct includes at least one moving part that can occupy a first position in which it is interposed between the flow to be deflected and the flap and another position in which it releases the flap so as to allow the flap to change position and to move from the at-rest position to the active position. Each flap includes articulation elements with a first pivoting axis and a second pivoting axis, whereby the pivoting axes are essentially parallel to the vertical median axis of the nacelle.

Abstract: Disclosed is an abrupt opening apparatus of a pressurized chamber in an intended procedure to accomplish thrust termination for a stage separation of the solid rocket motor. It can open trust termination ports with simple mechanical structure to thereby terminate the normal thrust of a nozzle reliably, if it is intended to terminate the normal thrust produced from the nozzle of the rocket motor to thereby impede the forward movement of the rocket motor by producing the reverse thrust. The thrust termination device for the rocket motor comprises a closure 210 for closing the thrust termination ports in an air-tight structure; a snap ring 220 for supporting the closure 210; a wedge 230 arranged between both free ends of the snap ring; a wedge fixing plate 240 for fixing the wedge; and, a pulling wire 250 linked to the wedge at one end thereof for extracting the wedge by being drawn when the thrust termination is performed.

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: The methods and the apparatuses of an aeration equipment are described. A floatable aeration equipment with mobility at least has a floatable apparatus, a plurality of aeration apparatuses, and a controller. The thrust causing the motion of the aeration equipment is generated from the aeration apparatuses while aerating. The moving directions and positions of aeration equipment are controlled by a controller, which switches on/off a power source of one or more selected aeration apparatus.

Abstract: Disclosed is a thrust termination device for a solid rocket motor, which terminates the net thrust by the reverse thrust of the rocket motor produced from the emission of the combustion gas in the reverse direction, when the stage separation signal is transferred at the normal thrust state of the rocket motor. An object of the present invention is to provide a thrust termination device for a rocket motor, which can contrive to accomplish the structural safety and mechanical sealing performance at the combustion chamber condition of the high temperature and high pressure, and easily remove the thrust termination device even at the low pressure state and open the trust termination ports successively with very small impacts when the thrust termination is commanded.

Abstract: An exhaust nozzle for use in a gas turbine engine comprises a flow body for receiving exhaust gas from the turbine engine and includes a leading edge and a trailing edge. The leading edge connects with the gas turbine engine such that the flow body surrounds a centerline of the engine. The trailing edge comprises a serrated portion and a non-serrated portion. The serrated portion is formed from a plurality of tabs for mixing exhaust gas exiting the flow body with gases passing by an exterior of the flow body. The non-serrated portion is positioned along a lower portion of the trailing edge with respect to the engine centerline.

Abstract: Improvement of combustion stability in retard ignition at the time of starting in a cold state, high output in a full throttle condition, reduction of smoke, and prevention of wear of the cylinder liner caused by oil dilution, are to be attained. In connection with the flow of fuel into each hole and a fuel inflow angle which is determined by the axis of each hole formed in a plate, the fuel inflow angle of an hole directed to a spark plug is set large to reduce an effective flow path area, thereby making the amount of fuel in the hole smaller than in other holes. A shallow cavity is formed in a piston crown face and a small prominence confronting fuel sprays is formed within the cavity.

Abstract: The braking method for an aircraft propelled by at least one ducted fan jet engine, the latter comprising a fan, a jet engine core in which the primary flow circulates, a secondary flow exhaust nozzle, encased in a nacelle, comprises the step, in low-power operation, of unloading at least part of the secondary flow so as to reduce the residual thrust of the jet engine without producing any thrust. With the method of the invention, aircraft braking can be achieved without any thrust reverser device using the braking force generated by the drag of the jet engine or engines completed by reduction of residual thrust by unloading the secondary flow.

Abstract: A thrust reverser includes reverser doors pivotally mounted in a nacelle. Each door includes a latch pin mounted at a distal end thereof. A complementary latch hook is pivotally mounted in the nacelle for engagement with the pin to latch closed the reverser door. A rotary retainer adjoins the hook for blocking rotation of the hook to latch closed the door, and selectively unblock rotation of the hook to permit the pin to disengage the hook.

Abstract: A turbofan nacelle includes forward and aft cowls adjoining at a joint, and including an exhaust duct having a main outlet for discharging exhaust. A variable nozzle surrounds the exhaust duct and includes a secondary outlet around the main outlet. A thrust reverser bridges the forward and aft cowls upstream from the variable nozzle. The variable nozzle is inductively powered and controlled across the closed joint, and is uncoupled inductively from the forward cowl when the joint is open.

Abstract: An exhaust nozzle includes an outer duct surrounding an inner duct. The inner duct includes a main outlet, and a row of apertures spaced upstream therefrom. The outer duct includes a row of intakes at a forward end, an auxiliary outlet at an aft end, and surrounds the inner duct over the apertures to form a bypass channel terminating at the auxiliary outlet. A row of flaps are hinged at upstream ends to selectively cover and uncover the apertures for selectively bypassing a portion of exhaust flow from the inner duct through the outer duct in confluent streams from both main and auxiliary outlets. When the flaps cover the apertures, the intakes ventilate the bypass channel and discharge flow through the auxiliary outlet.

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

Abstract: An exhaust nozzle includes an exhaust duct with an outlet and a row of radial apertures upstream therefrom. A radial frame surrounds the duct upstream from the apertures. A row of flaps are hinged to the frame to selectively cover and uncover the apertures for controlling exhaust flow discharged therethrough. An arcuate unison bar surrounds the duct adjacent to the frame and includes circumferentially spaced apart cams engaging corresponding cam followers affixed to the flaps. An actuator is joined to the bar for selective rotation thereof between opposite first and second directions to pivot open and closed the flaps atop the apertures.

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: A thrust reverser system that includes one or more power drive units operable to supply a drive force. The power drive unit includes a motor and at least two output sections, each operably coupled to transmit the drive force to the thrust reverser movable components. Each of the output sections is operable to decouple the motor from associated thrust reverser movable components upon a torque magnitude being reached in the output section. A deadband coupler is provided to couple the first and second output sections together a time period after the torque magnitude is reached in one of the output sections.

Abstract: A gas turbine engine exhaust nozzle includes coaxial inner and outer conduits. The inner conduit has a main outlet at an aft end thereof, and a row of radial apertures spaced upstream from the outlet. The outer conduit has an auxiliary outlet at an aft end thereof, and surrounds the inner conduit over the apertures to form a bypass channel terminating at the auxiliary outlet. A plurality of flaps are hinged at upstream ends thereof to selectively cover and uncover corresponding ones of the apertures and selectively bypass a portion of exhaust flow from the inner conduit through the outer conduit in confluent streams from both the main and auxiliary outlets.

Abstract: An outlet device for a jet engine (2) includes an outlet channel (3), which has an upstream end (3′) for being connected to the jet engine and a downstream end (3″) and which defines a main flow direction (a) for a jet from the jet engine. The outlet channel has in the proximity of the downstream end an elongated shape, seen in a section across the flow direction, and includes at least two outlet portions (4, 5, 6), which are separated from each other, for a respective outlet flow of said jet. A first outlet portion (5, 6) includes means for controlling the outlet direction of the outlet flow in a first plane and a second outlet portion (4) includes means for controlling the outlet direction of the outlet flow in a second plane, which forms an angle to the first plane. An aircraft may include such an outlet device.

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:

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: 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 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: