Abstract: A manufacturing method is provided during which a plurality of first apertures are formed in a first plate to provide an apertured first plate. The apertured first plate is configured from or otherwise includes first plate metal. A first sheet is bonded to the apertured first plate to form a first grid structure. The first apertures extend through the apertured first plate to the first sheet. The first sheet is configured from or otherwise includes first sheet metal.

Abstract: A variable area nozzle assembly for a gas turbine engine includes a fixed structure including a first fixed ring and a second fixed ring. The second fixed ring is spaced axially aft from the first fixed ring to define a first portion of an ejector passage therebetween. A nozzle defines an inner radial exhaust flow path surface. The nozzle includes a forward ejector door and an aft ejector door. The forward ejector door and the aft ejector door define a first surface portion of the inner radial exhaust flow path surface. Each of the forward ejector door and the aft ejector door are pivotable between respective closed positions and respective open positions. A translating ejector sleeve is mounted within the fixed structure and configured to axially translate within the fixed structure between a first axial position and a second axial position.

Abstract: There is provided an exhaust mixer arrangement for a turbofan engine having a bypass passage for channelling a bypass flow and a core passage for channelling a core flow around a central axis. The exhaust mixer arrangement comprises a mixer body mounted for rotation about the central axis. The mixer body has an annular wall extending around the central axis. The annular wall defines a plurality of circumferentially distributed alternating inner and outer lobes, with each inner lobe protruding into the core passage, and each outer lobe protruding into the annular bypass passage. A driving unit is operatively connected to the mixer body for selectively driving the mixer body in rotation about the central axis. A controller is operatively connected to the driving unit for controlling a rotational speed of the mixer body as a function of a flight operating condition.

Abstract: Internal structure for a turbomachine nacelle, the internal structure being intended to surround at least one part of a compartment capable of receiving a gas generator of the turbomachine, the internal structure comprising a ventilation cavity of said compartment, the ventilation cavity being provided with a main ventilation outlet and an auxiliary ventilation outlet separate to the main ventilation outlet, the internal structure comprising a shut-off member movable relative to the ventilation cavity between a flow position and a shut-off position in which the shut-off member shuts off the auxiliary ventilation outlet to a greater extent than in the flow position.

Abstract: An apparatus is provided for an aircraft propulsion system. This apparatus includes an exhaust nozzle. The exhaust nozzle includes a flowpath, a passage, an outer door, an inner door and an actuator configured to move the outer door and the inner door between an open arrangement and a closed arrangement. The flowpath extends axially along a centerline through the exhaust nozzle. The passage extends laterally into the exhaust nozzle to the flowpath when the outer door and the inner door are in the open arrangement. The outer door is configured to pivot inwards towards the centerline when the outer door moves from the closed arrangement to the open arrangement. The inner door is configured to pivot outwards away from the centerline when the inner door moves from the closed arrangement to the open arrangement.

Abstract: A line of sight blocker including a cover defining a duct bounded by the cover and a heated surface when the cover is fastened over the heated surface. The cover blocks transmission of infrared radiation emitted from the heated surface; the cover comprises a material having a lower thermal conductivity than the heated surface; and the duct comprises a vent and a path for latent heat from the heated surface to escape through the vent.

Abstract: A fuel nozzle device for a gas turbine engine includes a nozzle body extending in an axial direction and projecting into the combustion chamber, and swirler including a tubular portion concentrically surrounding the nozzle body, a deflector formed as a hollow shell concentrically surrounding the tubular portion, and a plurality of swirl vanes extending between the tubular portion and the deflector. Each swirl vane extends along a logarithmic spiral around an axial center of the nozzle body between the tubular portion and the deflector with a certain meridian crossing angle ? and a certain twist angle ? such that the outer peripheral inclination angle ? is smaller than the stacking angle ? of the swirl vane when the swirl vane is manufactured by an additive manufacturing process with a front end up orientation.

Abstract: Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.

Abstract: A ducted fan assembly includes a duct having an inlet, an inner surface, an expanding diffuser and an outlet. A fan disposed within the duct between the inlet and the expanding diffuser is configured to rotate about a fan axis to generate airflow. An active flow control system includes a plurality of injection zones circumferentially distributed about the inner surface. The expanding diffuser has a diffuser angle configured to create flow separation when the airflow is uninfluenced by the active flow control system such that the airflow has a thrust vector with a first direction that is substantially parallel to the fan axis. Injection of pressurized air from one of the injection zones asymmetrically reduces the flow separation between the airflow and the expanding diffuser downstream of that injection zone such that the thrust vector of the airflow has a second direction that is not parallel to the first direction.

Abstract: A ducted fan propulsion comprises a duct with a cutout and a movable duct section that is moved between a retracted position within the cutout and am extended position relative to the duct. An actuator is disposed within the duct wall and is connected to the movable duct section with actuating linkage. A control linkage connects the movable duct section to the cutout edges. The movable duct section is extended when the ducted fan propulsion transitions from vertical takeoff to a level flight or transitions from level flight to a vertical landing. The movable duct section is retracted into cutout an becomes integrated with the duct during level flight.

Abstract: A nacelle for an aircraft turbofan includes a rear section including a thrust reversal device having an upper door and a lower door, the upper and lower doors being mobile in rotation between a stowed position in which they are aerodynamically continuous with the rest of the nacelle and a deployed position in which the upper and lower doors are able to redirect forward the core and bypass flows produced by the jet engine, each door being moved from one position to the other by at least one dedicated actuator. The opening angle (X) of the upper door in the deployed position is smaller than the opening angle (Y) of the lower door.

Abstract: A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

Abstract: An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.

Abstract: An ejector system for propelling a vehicle. The system includes a diffusing structure and a duct coupled to the diffusing structure. The duct includes a wall having openings formed therethrough and configured to introduce to the diffusing structure a primary fluid produced by the vehicle. An airfoil is positioned within the flow of the primary fluid through the openings to the diffusing structure.

Abstract: A liquid propellant rocket engine includes a combustion chamber that has a throat and a nozzle aft of the throat. The nozzle has a first nozzle section adjacent the throat and a second nozzle section aft of the first nozzle section. The first nozzle section includes active cooling features and the second nozzle section excludes any active cooling features. The first nozzle section is operative via at least the active cooling features to form a condensate that passively cools the second nozzle section.

Abstract: It is provided a mixer for an engine, that for the mixing of fluid flows from a primary flow channel and a secondary flow channel of the engine, respectively has multiple first and second guide elements that alternate along a circumferential direction and extend along a central axis, wherein the first guide elements are formed in a diffusor-like manner with at least one radially outwardly extending section, and the second guide elements are formed in a nozzle-like manner with at least one radially inwardly extending section, and the mixer is made of a composite material with at least two separate material layers. The at least two material layers are arranged with their edges along the central axis in an overlapping manner and/or edge to edge, and namely in an area of the mixer in which the first and second guide elements are provided.

Abstract: A jet noise suppressor and an airplane are provided. The jet noise suppressor includes a nozzle with a front end, a back end, an interior surface, and an exterior surface, a plurality of struts, and a plurality of vents. Each strut includes a base and a distal end with the base of each strut coupled to the interior surface of the nozzle, and each vent corresponds to a respective strut and is formed within the interior surface of the nozzle between the front end of the nozzle and the base of the respective strut.

Abstract: A turbofan engine that comprises a primary flow channel inside of which a primary flow flows through a gas generator during operation, a secondary flow channel inside of which a secondary flow is guided past the gas generator during operation, and an oil separator of a lube oil system that has a pipeline for exhausting breather air, wherein the pipeline forms a pipeline end. It is provided that the pipeline end is arranged inside the secondary flow channel, and is provided and configured for the purpose of discharging breather air directly from the pipeline end into the secondary flow channel.

Abstract: A thrust reverser may comprise a frame, a first reverser door being movable relative to the frame, and a second reverser door being movable relative to the frame and rotationally movable relative to the first reverser door via a first pivot point, the first pivot point being movable relative to the frame via a first link rotationally mounted to the frame via a second pivot point.

Abstract: An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases by injecting fluid into the exhaust plume zone.

Abstract: An example apparatus includes: a plate configured to move along an underlying surface via a layer of fluid disposed in a gap between the plate and the underlying surface, where pressurized fluid forms the layer of fluid in the gap; a first rack gear coupled to the plate and meshing with a first gear; and a second rack gear coupled to a second gear. The second rack gear is fixed, and the second gear is coupled to the first gear. The pressurized fluid in the gap repels the plate away from the underlying surface, thereby causing (i) the first rack gear to move linearly and the first gear to rotate, (ii) the second gear to rotate and move along the second rack gear, and (iii) the plate to move along the underlying surface.

Abstract: A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

Abstract: A gas turbine engine system is disclosed herein. The gas turbine engine system includes an engine core configured to discharge air through an exhaust nozzle along a central axis and a thrust director arranged near the exhaust nozzle and configured to redirect the discharge air by applying flow to the discharge air near the exhaust nozzle.

Abstract: An exhaust mixing system having an attachment flange configured to couple a lobed Oxide-CMC exhaust mixer to a turbine engine. The attachment flange includes an annulus and a plurality of projections extending from the annulus in a first direction that is substantially parallel to a central axis of the annulus. The annulus is configured to couple to the turbine engine and the plurality of projections is configured to couple to the lobed mixer.

Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.

Abstract: A turbofan engine includes a fan section with a plurality of fan blades rotatable about an engine axis generating an airflow, a bypass passage through which the airflow passes, and a fan exit guide vane. The fan exit guide vane assembly includes a plurality of airfoils disposed between an inner platform wall and an outer platform wall. At least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent airfoils. The contoured surface includes at least one concave region and at least one convex region. A method of reducing secondary flow structures in bypass air flow with the turbofan is also disclosed.

Abstract: An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone.

Abstract: Methods and systems for restricting movement in a flow mixer of an exhaust duct, the flow mixer having a first row of flutes and a second row of flutes generally opposite to the first row of flutes, each flute being elongated and defining an elongated axis. At least two flute ties connect, or couple, together at least two flutes from the first row of flutes and at least two flutes from the second row of flutes. A retainer is coupled to the flute ties and extends generally perpendicularly to the elongated axis of each of the flutes from the first and second rows of flutes. The combination of the retainer and flute ties is configured to generally restrain relative movement between the flutes from the first row and the flutes from the second row.

Abstract: A turbo-machine inlet includes a gas passage having a non-gradual bend prior to an impeller assembly. The non-gradual bend causes a localized shockwave in fluid flowing through the gas passage.

Abstract: In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

Abstract: The connector system (30) includes a pivoting member (38) pivotally attached to a guide anchor (36) that is moveable secured within a guide track (34). The guide anchor (36) is movably secured between first and second strength walls (58, 62). At least one guide shoulder (70) and the pivoting member (38) define throughbores (74, 76, 78) that receive a rod (92) of a rod-and-bracket connector (88) to pivotally secure the pivoting member (38), such as a convergent flap (26) of an exhaust nozzle assembly (22). The rod-and-bracket connector (88) utilizes an L-shaped arm (96) to eliminate need for a large thread and lock nut assembly (86) between the strength walls (58, 62) to thereby facilitate use of larger, stronger guide shoulders (70, 72) between the strength walls (58, 62) to maximize strength of the connector system (30) while minimizing its volumetric displacement.

Abstract: A fan assembly for creating an air current is described, the fan assembly having a nozzle, a system for creating an air flow through the nozzle and a filter for removing particulates from the air flow, the nozzle having an interior passage, a mouth for receiving the air flow from the interior passage, and a Coanda surface located adjacent the mouth and over which the mouth is arranged to direct the air flow, wherein the fan provides an arrangement producing an air current and a flow of cooling air created without requiring a bladed fan, i.e. air flow is created by a bladeless fan.

Abstract: The present application provides a process for preventing rotating stall and surge in a turbomachine compressor. The compressor may include air extraction pipes connecting the compressor to a turbomachine exhaust area or to the atmosphere, at least one of the pipes is fitted with a flow regulation valve, and each valve has an adjustable degree of opening. The process includes, for at least one of the valves, a complete opening command when the compressor rotation speed is less than a predetermined threshold value beyond which there is no longer any risk of rotating stall and surge and a command for lowering the degree of opening of the valve when the rotation speed of the compressor exceeds the threshold value.

Abstract: A nozzle for a fan assembly has an air inlet, an annular air outlet, and an interior passage for conveying air from the air inlet to the air outlet. The interior passage is located between an annular inner wall, and an outer wall extending about the inner wall. The inner wall at least partially defines a bore through which air from outside the nozzle is drawn by air emitted from the air outlet. The inner wall is eccentric with respect to the outer wall so that the cross-sectional area of the interior passage varies about the bore. The variation in the cross-sectional area of the interior passage can control the direction in which air is emitted from around the air outlet to reduce turbulence in the air flow generated by the fan assembly.

Abstract: An interface device between first and second turbomachine elements is provided. The interface device includes an annular air inlet structure including opposite first and second parts, designed to come into contact with the first and second turbomachine elements respectively, in which the first part is configured to be in swivel contact with the first element; and an elastic return device that can be placed around the air inlet structure and designed to come into contact with at least the first turbomachine element.

Abstract: A gas ejection cone includes a cylindrical-shaped front cone portion, a conical-shaped rear cone portion, a ventilation tube and a support bearing of this drainage and/or ventilation tube. The ventilation tube extends inside the cylindrical-shaped front and conical-shaped rear cone portions and emerges at the end of the conical-shaped rear cone portion. In particular, the conical-shaped rear cone portion includes a front sub-portion connected to the cylindrical-shaped front cone portion, and a rear sub-portion removably secured to the front sub-portion. The rear sub-portion is further equipped with an outlet port of the ventilation tube.

Abstract: The invention relates to a method and device for controlling the mass flow rate of a sonic gas stream in a pipe. To carry out the above operation, an electric discharge is applied inside the pipe so as to create a plasma in the pipe. The electric discharge allows for an increase in the temperature of the gas stream and thus a variation in the mass flow rate or the pressure of the gas stream. By periodically emitting the electric discharge, a pulsed or adjustable gas jet is obtained at the outlet of the device. The gas jet can then be used to control a main stream.

Abstract: A method and device for adding special substances to the gaseous outflow of the jet engine in order to create a “virtual wall” of increased pressure zone behind the jet engine nozzle which can serve as a support for the jet engine gas outflow to push against, thus increasing the thrust power of the jet engine. This increase in acceleration power results in the accelerated movement of the jet engine equipped vehicle or higher fuel efficiency. A device that adds the special substances to the gaseous outflow is proposed. Characteristics of the special substances, which if added into the jet engine gaseous outflow may create a “virtual wall” of increased pressure zone behind the jet engine, are proposed.

Abstract: The thrust vectoring apparatus comprises: a housing defining a primary outlet for emitting the primary jet; Coanda surfaces extending from opposing regions of said housing, and radially spaced from the primary outlet such that a step is defined between each Coanda surface and the primary outlet; ducts leading from a fluid source to secondary outlets; and flow control means operable to control the mass flow through the secondary outlets. When the jet engine operates to exhaust a primary jet through the primary outlet, low pressure regions are formed in the vicinity of the steps. Each secondary outlet is located adjacent one of the Coanda surfaces so as to emit a secondary flow into a low pressure region. On activation of the secondary flow by the flow control means, the primary jet is entrained by the Coanda surface opposing the Coanda surface adjacent said the secondary outlet from which the secondary flow has been emitted.

Abstract: A multi stream aircraft fixed geometry nozzle includes an inner nozzle, an outer nozzle, and a supersonic ejector. The outer nozzle is configured to channel a third stream from an aft end of a third stream duct surrounding a bypass duct of a multi stream aircraft engine to the supersonic ejector to merge the third stream with the primary stream. The fixed geometry nozzle is configured to operate between an SFC mode and a thrust mode such that, when the inner nozzle accelerates the primary stream supersonically to the supersonic ejector, at which the primary stream is merged with the third stream, in the SFC mode the total pressure of the primary stream is substantially the same as the total pressure of the third stream, and in the thrust mode the total pressure of the primary stream is substantially greater than the total pressure of the third stream.

Abstract: The invention relates to a primary cowl for a turbofan comprising a primary body generating a primary stream to be ejected through a primary nozzle, and a secondary body generating a secondary stream to be ejected through a secondary nozzle, the primary cowl being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbofan, the path followed by the primary stream downstream from the primary nozzle and, on the outside, the path followed by the secondary stream downstream from the secondary nozzle. The primary cowl comprises a coupling to a system for supplying a pressurised gas and at least one perforation for injecting the pressurised gas, through the perforation, into the secondary stream. The primary cowl preferably comprises a ring which has perforations and which is rotated about the axis of rotation of the turbofan.

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

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: One embodiment of the present invention is a unique flight vehicle. Another embodiment is a unique propulsion system. Another embodiment is a unique thrust vectoring system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for flight vehicles, propulsion systems and thrust vectoring systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: An external accessory for a portable fan including a base having an air inlet located in a side wall of the base, and an air outlet detachably connectable to the base, the accessory including a high energy particle arrester filter and connectors for detachably connecting the accessory to the fan so that the filter is located upstream from the air inlet of the fan.

Abstract: An aircraft jet engine with a longitudinal axis, including a wall enclosing a gas flow ejected from a downstream end of the wall in the longitudinal axis, plural ducts being distributed around the periphery of the downstream end of the wall each including a terminal section, including an outlet opening. Each duct can eject a fluid jet through the outlet opening thereof. The ducts are configured to eject the fluid jets essentially parallel to each other, each fluid jet ejected through the corresponding outlet opening forming a lateral angle with the longitudinal axis in a projection view in a plane with the longitudinal axis.

Abstract: A gas turbine engine augmentor includes an inter-liner cavity including an axially extending annular gap separating augmentor and tailpipe liners. A purge flow cavity is in fluid communication with a fan bypass duct and with the cavity. An ejector in fluid communication with the bypass duct includes an ejector nozzle positioned and aimed to direct an ejector nozzle flow from inside the ejector nozzle across the cavity. The purge flow cavity may be bifurcated into forward and aft purge flow cavities which are in fluid communication with the ejector and inter-liner cavity respectively. An annular dividing wall having ejector metering apertures may be disposed between the forward purge flow cavity and an ejector plenum of the ejector. An annular trapped vortex cavity pilot may be located upstream of the annular gap. The aft purge flow cavity may be outwardly bounded by a seal having purge metering apertures disposed therethrough.

Abstract: A mixer of a bypass turbine aeroengine according to one embodiment, includes circumferential inner and outer flow surfaces in a wavy configuration to form a plurality of lobes of the mixer. The mixer has an upstream end portion of sheet metal with a first thickness and a downstream end portion of sheet metal with a second thickness less than the first thickness.

Abstract: An improved bypass turbojet engine includes a particularly shaped hot flow nozzle arranged about a particularly shaped type of boss. The boss is bulbous in shape and is connected by a first connecting surface to a turbine casing. The hot flow nozzle is formed as a single skin that extends in a rearward direction from an engine cowl, with the hot flow nozzle being connected to the engine cowl along a second connecting surface. The hot flow nozzle and the bulbous boss are positioned relative to one another to delimit a nominal nozzle throat section and a nominal outlet section for hot flow from a hot flow generator. The hot flow nozzle single skin is also approximately bulbous in shape and widens from the second connecting surface in a direction toward the engine cowl's external wall.