Abstract: A masking arrangement for a gas turbine engine includes a plurality of annular elements arranged overlapping one another when these are viewed in an axial direction so as to mask at least a substantial portion of any interior hot and rotating gas turbine engine part at an aft end of the gas turbine engine from rear view when the masking arrangement is applied downstream the interior part in the gas turbine engine.

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

Abstract: In order to assembly together two parts (154, 162) of materials having different coefficients of expansion vis mutually engaged edge portions (154a, 162a), tongues (170) are formed in the thinned edge of one of the parts, the tongues being separated by slots (172) obtained by cutting or machining the material of the part, and the parts are assembled together by fastening (174) via the tongues. The edge portions are mutually engaged in such a manner as to be in substantially leaktight contact at the high temperatures encountered in operation. The invention is applicable in particular to assembling together parts made respectively of metal and of ceramic composite material, in particular in an aviation gas turbine, e.g. upstream and downstream secondary nozzles.

Abstract: This grid thrust reverser cover comprises a seal support and a seal mounted in this support by means of two fastening lugs, this seal being capable of interacting with a diversion edge of this thrust reverser. At least one of the said lugs is turned up and the said support has a section matching that defined by the said lugs.

Abstract: A jet flow discharge nozzle includes a tubular partition wall, a tubular casing which covers an outer periphery of the tubular partition wall, and a bifurcation which extends in an axial direction of the tubular partition wall and the casing so as to support downstream ends of the tubular partition wall and the casing from outside. Inside of the tubular partition wall is defined as a flow path for a high-speed core flow. A space between the tubular partition wall and the casing is defined as a flow path for a low-speed bypass flow. A pair of first projections is provided at a downstream edge of the tubular partition wall near the bifurcation at positions symmetric about the bifurcation. One of ridges of each of the first projections faces an upstream side. The invention reduces noise by avoiding adverse effects of the presence of the bifurcation on an increase in noise.

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

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

Abstract: A showerhead for chemical vapor deposition (CVD) includes a head storing reaction gas flowing thereinto and feeding the stored reaction gas to a reaction chamber, and at least one support member passing through and coupled with the head and the reaction chamber so as to support the head.

Abstract: An exhaust nozzle for a gas turbine engine includes a nozzle casing having top and bottom walls and side walls. A liner is provided within the nozzle casing to define a cooling passage. The top and bottom walls each include mutually inclined planar wall portions which meet at respective creases. The creases increase the rigidity of the top and bottom walls. In addition, the inclined wall portions cause the cooling passage to taper in the direction outwardly from the creases, so assisting in the cooling air distribution over the liner.

Abstract: A propulsion system, such as for use in a missile, includes a multinozzle grid having a pair of plates that are separably mechanically coupled together. When coupled together in a first configuration, the plates provide multiple nozzles in a first nozzle configuration (geometry). Separation of the plates, such as by separating an aft plate from a forward plate that remains with the missile, reconfigures the multinozzle grid to a second configuration that has nozzles in a second nozzle configuration (geometry). The nozzle configurations may be suitable for different types of propulsion mechanisms. The hybrid propulsion system utilizing the multinozzle grid may include a pair of pressurized gas sources, for example a solid rocket fuel and a combustion chamber for a ramjet.

Abstract: A turbine engine exhaust nozzle is disclosed that includes an exhaust liner having a first attachment structure. A liner support member includes a second attachment structure. A pin cooperates with the first and second attachment structures and is configured to secure the exhaust liner relative to the liner support member. The pin includes first and second dimensions that are different than one another. The pin is inserted into apertures provided by the attachment structures, in one example. The pin is oriented to position the first and second dimensions in a manner providing increased clearance within the apertures. The pin is rotated to load the components and firmly secure the liner to the liner support member.

Abstract: An exhaust flow system for use with a turbofan jet engine that provides separate fan flow and core flow streams that are not mixed. The system includes a fan nozzle and a primary flow nozzle. The primary flow nozzle includes a downstream edge portion that is either beveled with one or more beveled surfaces, or that contains a curving edge surface or a combination of a beveled edge and a curved edge to help direct noise generated by the jet engine upwardly away from a ground surface during take-off and landing procedures. The primary exhaust nozzle can also be orientated with an elongated lip portion thereof formed by the beveled edge surface such that the lip portion is orientated between a top dead center and a bottom dead center position, to thus help direct noise away from a cabin area of a fuselage of a mobile platform during cruise conditions.

Abstract: A nozzle arrangement for a gas turbine engine includes an engine nozzle and an ejector nozzle arranged axially downstream thereof. A gap S is formed between the outlet of the engine nozzle and the inlet of the ejector nozzle, and a flange which reduces the gap S is arranged at the outlet of the engine nozzle.

Abstract: A method and device to reduce the noise produced by jet aircraft engines and/or other supersonic nozzles involves the use of corrugated engine seals (30) for the secondary internal divergent flaps (14) of the nozzle (10). Such corrugated seals (30) serve not only to eliminate shock-generated noise, but also generate a counter-rotating vorticity to force low speed mixing of surrounding ambient air with the high-speed jet exhaust. Lower exhaust velocities, combined with reduced levels of the turbulent Reynolds shear stress, lead to reduction of turbulence-generated noise, including Mach wave emission.

Abstract: The present invention features a fluid flow regulator that functions to significantly influence fluid flow across the surface of an object, as well as to significantly effect the performance of the object subjected to the fluid. The fluid flow regulator comprises a pressure recovery drop that induces a sudden drop in pressure at an optimal pressure recovery point on said surface, such that a sub-atmospheric barrier is created that serves as a cushion between the molecules in the fluid and the molecules at the object's surface. More specifically, the present invention fluid flow regulator functions to significantly regulate the pressure gradients that exist along the surface of an object subject to fluid flow. Regulation of pressure gradients is accomplished by selectively reducing the pressure drag at various locations along the surface, as well as the pressure drag induced forward and aft of the object, via the pressure recovery drop.

Abstract: An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure.

Abstract: A fluid mixer for mixing two fluid streams 40, 42 includes a set of main lobes 26 defining alternating primary and secondary main chutes 30, 32, one or more auxiliary lobes 28 intermediate two of the main lobes, and an auxiliary fluid capture duct 62. The auxiliary lobes are defined, at least in part, by the discharge end of the duct. In operation, the duct conveys secondary fluid to secondary chutes 36 defined by the lobes thereby improving the performance of the mixer despite the presence of an obstruction 18 that would otherwise impede thorough mixing of two fluid streams.

Abstract: A retractable thrust vector control system (10) for a rocket motor (26) that can generate an exhaust plume comprises at least one control vane (12) connectable to an attitude control assembly (20) that rotates the vane (12) about a control axis (44). The system also includes a retraction mechanism (14) for withdrawing the control vane (12) along the control axis (44) from an extended position at least partially within a path of a rocket exhaust plume and a retracted position substantially out of a path of a rocket exhaust plume.

Abstract: A propulsion system for a jet- or rocket-propelled vehicle in which the resulting jet exhaust nozzle profile is a 3D spiral. The propulsion system can be applied to any jet- or rocket-propelled vehicle, including aircraft and watercraft.

Abstract: A mixer for a separate-stream turbojet nozzle, the mixer comprising along a longitudinal axis (X-X?) both a fastener shroud (10) for connecting said mixer to the exhaust casing of the nozzle, and a lobe structure (20) presenting a succession of inner and outer lobes (22 and 21) distributed circumferentially around the longitudinal axis (X-X?) of the mixer. The lobe structure (20) is made of a ceramic matrix composite material and further comprises a stiffener ring (30) that forms a connection between at least some of the lobes of said structure. Thus, the major portion of the mixer, i.e. the lobe structure, is made of a ceramic matrix composite material, thereby significantly reducing the weight of the mixer, and consequently reducing the weight of the nozzle.

Abstract: The invention relates to a mixer for a bypass turbomachine, the mixer comprising a cylindrical member having a sinusoidal portion at its downstream end defining inner lobes and outer lobes distributed circumferentially, each outer lobe comprising a pair of radial walls interconnected by an outer curvilinear dome, each inner lobe comprising a pair of radial walls interconnected by an inner curvilinear dome, the walls of the outer lobes radially extending the walls of the inner lobes, the radial walls of the outer lobes and of the inner lobes presenting an outline that is substantially curved with at least one point of inflection.

Abstract: A device for controlling a gas flow comprises an outlet part which defines an internal space for the gas flow and a body arranged in the internal space in the vicinity of the outlet of the outlet part, a gap being formed between the body and the inner boundary wall of the outlet part. At least one opening is provided at the outlet of the outlet part for injection of a fluid into the gas flow for the purpose of controlling the direction of the gas flow out of the outlet part.

Abstract: The invention relates to a mixer for a bypass turbomachine, the mixer comprising a member having a sinusoidal portion at its end defining inner lobes and outer lobes, each outer lobe comprising a pair of plane radial walls spaced apart from each other in the circumferential direction and interconnected by an outer dome, each inner lobe comprising a pair of plane radial walls spaced apart from each other in the circumferential direction and connected together by an inner dome, the walls of the outer lobes being disposed to extend the walls of the inner lobes radially, the radial walls of a given outer lobe extending radially in mutually parallel directions, with these walls, when extended geometrically, defining a zone from which the axis of symmetry of the cylindrical member is excluded.

Abstract: The present invention features a fluid flow regulator that functions to significantly influence fluid flow across the surface of an object, as well as to significantly effect the performance of the object subjected to the fluid. The fluid flow regulator comprises a pressure recovery drop that induces a sudden drop in pressure at an optimal pressure recovery point on said surface, such that a sub-atmospheric barrier is created that serves as a cushion between the molecules in the fluid and the molecules at the object's surface.

Abstract: A method and device to reduce the noise produced by jet aircraft engines and/or other supersonic nozzles involves the use of corrugated engine seals (30) for the secondary internal divergent flaps (14) of the nozzle (10). Such corrugated seals (30) serve not only to eliminate shock-generated noise, but also generate a counter-rotating vorticity to force low speed mixing of surrounding ambient air with the high-speed jet exhaust. Lower exhaust velocities, combined with reduced levels of the turbulent Reynolds shear stress, lead to reduction of turbulence-generated noise, including Mach wave emission.

Abstract: A method and apparatus for dumping surge bleed air into a primary nozzle of a free gas turbine engine. The surge bleed air is introduced into gas turbine exhaust flow within the primary nozzle to create a mixed flow which may be used as a combined driver flow to compensate for reduced engine exhaust flow during periods when operation of the turbine engine may be exclusively dedicated to only electric load operation. The surge bleed air may not be the educted flow or the secondary driven flow, while cooling air passing through an oil cooler may be an educted flow. Surge bleed air may flow through, for example, mixer lobes, hollow struts, or the center body before mixing with the gas turbine exhaust flow.

Abstract: In a fluid pump and cartridge assembly, a cartridge includes a material inlet port, a material outlet port, and a feed screw. The feed screw delivers fluid to be dispensed from the fluid inlet to the outlet port. The fluid inlet is preferably elongated in a direction along a longitudinal axis of the feed screw to enhance consistency in material flow through the cartridge. The feed screw is preferably driven by a closed-loop servo motor to achieve high-performance dispensing resolution. The assembly is preferably compatible with fixed-z and floating-z cartridges. A optional vented dispense tip, in combination with the fluid pump, allows for repeatable deposit of fillet patterns while maintaining optimal consistency. A dispense controller allows for reverse-compatibility such that the fluid pump of the present invention can be mounted to, and controlled by, conventional pump position controllers.

Abstract: A gas turbine engine nacelle includes an inner skin surrounded by a radially outer skin. The inner skin terminates at an exhaust outlet. The outer skin terminates at a recess in the inner skin extending into a closed cavity under the outer skin.

Abstract: In a fluid pump and cartridge assembly, a cartridge includes a material inlet port, a material outlet port, and a feed screw. The feed screw delivers fluid to be dispensed from the fluid inlet to the outlet port. The fluid inlet is preferably elongated in a direction along a longitudinal axis of the feed screw to enhance consistency in material flow through the cartridge. The feed screw is preferably driven by a closed-loop servo motor to achieve high-performance dispensing resolution. The assembly is preferably compatible with fixed-z and floating-z cartridges. A optional vented dispense tip, in combination with the fluid pump, allows for repeatable deposit of fillet patterns while maintaining optimal consistency. A dispense controller allows for reverse-compatibility such that the fluid pump of the present invention can be mounted to, and controlled by, conventional pump position controllers.

Abstract: A turbofan exhaust nozzle includes a fan duct defined between a fan nacelle and a core engine cowling. The fan duct includes a longitudinal endwall and a partition spaced therefrom to define a secondary flow duct. The fan duct also includes a primary outlet, and the secondary duct includes a secondary outlet. The partition between the two ducts includes an aperture covered by a selectively movable flap.

Abstract: A nozzle extension including flange elements of C/SiC is able to be manufactured relatively simply and provides sufficient physical properties. The carbon-fiber structure of the nozzle extension is wound, and a flange for fastening the nozzle extension to the nozzle outlet of the combustion chamber is integrated in the nozzle extension by a continuous fiber flow of the wound carbon-fiber structure. The foregoing may be intended for use in rocket propulsion units.

Abstract: A thrust control valve includes a nozzle having a gas supply chamber, a gas jetting chamber and a connecting passage therebetween. The nozzle has an upstream inner surface defining the gas supply chamber and a downstream inner surface defining the gas jetting chamber. The valve also includes a plug axially movably inserted into the gas supply chamber, the connecting passage and the gas jetting chamber. The plug has an upstream outer surface facing the upstream inner surface to define an upstream passage and a downstream outer surface facing the downstream inner surface to define a downstream passage. The plug can control thrust by simultaneously changing sectional areas of the upstream and downstream passages by an axial movement of the plug.

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 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: EGR mass fraction or a value indicative thereof can be calculated based on temperature measurements rather than mass flow and/or pressure measurements, hence negating the need for expensive and relatively unreliable measurement devices in an active EGR system for an internal combustion engine. The EGR system may be a low pressure EGR system configured to direct cooled, filtered EGR to the engine's air intake system using an effective, simple venturi and/or a continuously regenerated catalytic particulate trap. The resultant system can reduce NOx emissions in a diesel engine on the order of 50% and approximately 90% for CO, HC, and PM. NOx and other emissions can be reduced still further when the EGR system is combined with other pretreatment and/or after treatment devices. Many components of the low pressure EGR system are also usable in a passive EGR system.

Abstract: The rocket motor nozzle assembly of this invention includes a throat insert and a carbon or silica protective eyelid. The throat insert has a carbon throat support and a refractory metal shell. The shell is positioned radially inside the throat support to cover the inner surface of the throat support. The protective eyelid covers a sufficient portion of the forward surface region of the shell and the underlying converging portion of the throat support to protect these components against particle impingement. The protective eyelid extends sufficiently far forward along the converging/diverging pathway to cover and protect the forward face or edge of the throat insert and prevent the combustion gases from passing under the throat insert and reaching the radially outer surface of the throat insert. However, the protective eyelid leaves the throat surface region of the shell exposed to the converging/diverging pathway.

Abstract: Thrust chamber housing for a driving mechanism for space travel applications which is fastened to an injection head with its first end and which includes a combustion chamber housing of a highly heat-resistant steel, a nozzle element of a platinum-iridium alloy, and an expansion nozzle housing of a highly heat-resistant steel, whereby the combustion chamber housing is welded through a first intermediate ring with the nozzle element and the nozzle element is welded through a second intermediate ring with the expansion nozzle housing by means of welded connections, whereby the first and the second intermediate ring are made of a platinum-rhodium alloy.

Abstract: A high temperature sealing system is operative to seal an interface between adjacent hot structures and to minimize parasitic flow between such structures that move relative to one another in-plane or out-of-plane. The sealing system may be used to seal thrust-directing ramp structures of a reusable launch vehicle and includes a channel and a plurality of movable segmented sealing elements. Adjacent ramp structures include edge walls which extend within the channel. The sealing elements are positioned along the sides of the channel and are biased to engage with the inner surfaces of the ramp structures. The segmented sealing elements are movable to correspond to the contour of the thrust-directing ramp structures. The sealing system is operative to prevent high temperature thrust gases that flow along the ramp structures from infiltrating into the interior of the vehicle.

Abstract: Insulation for a rocket motor is provided, as is a method for insulating a rocket motor. The insulation includes a cured elastomer and vapor-grown carbon fibers dispersed in the cured elastomer. The cured elastomer is preferably formed from a precursor composition comprising an EPDM terpolymer. Generally, the vapor-grown carbon fibers have an internal graphitized tube surrounded by a sheath of vapor-deposited amorphous carbon.

Abstract: The invention relates to an apparatus for increasing the heat transfer to the coolant at the inside of a nozzle wall provided with coolant channels of expander cycle rocket engines. To achieve this the invention proposes that, to disturb the boundary layer at the nozzle wall and thereby increasing the heat transfer, the inside of the nozzle wall facing the flame has a particularly chosen increased surface roughness of such a magnitude that it penetrates the viscous sub-layer of the boundary layer at the nozzle wall.

Abstract: A nozzle where the sector into which noise reduction is sought (the direction of populated areas) has a moving lip, driven by actuators in an oscillatory, periodic or sinusoidal motion, around the mid position, to and from the axis, so as to cause the shear layer to become more irregular and turbulent, thus enhancing scattering effects on the sound of internal sources, including back reflection into the jet, widening the directivity pattern and spreading the acoustic energy into a broader spectrum, so as to reduce the acoustic energy transmitted in these sensitive directions; the nozzle lip may also be corrugated, ondulated or have vortex generators, in the sector over which noise reduction is sought. In all other sectors, for which noise radiation is of no concern, even if enhanced, the nozzle lip is smooth and fixed, leading to a thin shear layer, across which sound is more easily, so that acoustic energy exits from the jet in these harmless directions.

Abstract: The invention refers to an apparatus for controlling the flow separation line of rocket nozzles for reducing side loads. For obtaining this control it is suggested according to the invention that the inside of the nozzle (1) has circumferentially regular spaced areas (2) with increased surface roughness compared with the rest of the inside of the nozzle.

Abstract: The invention refers to a full-flow rocket nozzle having a longitudinal contour essentially corresponding to a parabola. For obtaining a flow separation control and also a side load reduction the invention suggests that the parabola contour shape from the point of 50% expansion ratio onwards or more distant from the throat of the nozzle is changing over into (i) strictly conical shape having an angle to the center line of between 15° and 25°, (ii) a slight outward curvature, i.e. implying a contour shape with positive 2nd derivative of the radius r, or (iii) a slight inward curvature, i.e. with a negative 2nd derivative of r but lying externally of the parabola contour, in the last case the 3rd derivative of r being constantly equal to zero (0).

Abstract: To control the separation of a hot gas ejection jet within a rocket engine nozzle, the device includes a jettisonable annular structure for placing around the outside wall of the nozzle at the gas cutlet section thereof, which structure defines a radial extension around the nozzle so that in the presence of an outlet jet coming from the nozzle, it creates a low pressure zone in the vicinity of the bottom face of the device, thereby displacing in the gas outlet direction jet separation from the interior wall of the nozzle.

Abstract: The invention discloses an aeroengine nacelle afterbody of the type comprising a common nozzle for exhausting the mixed hot and cold gases originating respectively from the fan duct and from the aeroengine combustion chamber, the said nozzle having a longitudinal axis more or less coincident with the axis of the said engine. The common exhaust nozzle consists of two half-nozzles which are more or less symmetric with respect to a plane containing the said longitudinal axis, the said half-nozzles being, on the one hand, individually hinged via one of their longitudinal edges to a support structure hanging down from the wing structure or from the fuselage of the aircraft and, on the other hand, lockable together along their opposite longitudinal edges.

Abstract: A rocket motor assembly is insulated or thermally protected with a rocket motor ablative material formed from a prepreg. The prepreg contains at least an impregnating resin matrix and, as a precursor prior to carbonization, either carded and yarn-spun solvent-spun staple cellulosic fibers, solvent-spun cellulosic filaments, or a combination thereof. When patterned and carbonized, the rocket motor ablative material can be lined or otherwise placed into a rocket motor assembly, such as between the solid propellant and case, in the bulk area of the exit nozzle liner, or at susceptible portions of a re-entry vehicle, such as the nose cone.

Abstract: The invention refers to an apparatus for controlling the flow separation line of rocket nozzles for reducing side loads. For obtaining this control it is suggested according to the invention that the inside of the nozzle (1) has circumferentially regular spaced areas (2) with increased surface roughness compared with the rest of the inside of the nozzle.

Abstract: A method to form a sealed, partially or fully densified fiber reinforced composite preform which comprises: impregnating said preform with a major portion of a liquid, ceramic-forming precursor; initiating cure of the outer surface of said precursor with radiation, such as actinic radiation; a thereby forming a sealing barrier or skin on the surface of said preform. In a second embodiment the preform is infiltrated with a thermoplastic as liquid, frozen, excess frozen infiltrate optionally removed from the preform surface, then the preform is coated with a liquid which is curable with radiation, cure is initiated with radiation and the preform is sealed with a barrier coat.

Abstract: The invention relates to an apparats for increasing the heat transfer to the coolant at the inside of a nozzle wall provided with coolant channels of expander cycle rocket engines. To achieve this the invention proposes that, to disturb the boundary layer at the nozzle wall and thereby increasing the heat transfer, the inside of the nozzle wall facing the flame has a particularly chosen increased surface roughness of such a magnitude that it penetrates the viscous sub-layer of the boundary layer at the nozzle wall.

Abstract: A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the nozzle wherein the nozzle further comprises an actuation mechanism capable of moving the tabs between a first deployed position, where the tabs interact with a gas stream to reduce exhaust noise thereof, and a second non-deployed position, where the tabs are substantially aerodynamically unobtrusive.