Abstract: An adapter device for controlling a rocket engine nozzle under conditions of external pressure that can lead to the jet separating inside the nozzle, the nozzle being fitted with a diverging portion that is movably mounted relative to a stationary portion of the nozzle, thrust deflection then being achieved by swivelling the diverging portion so as to deflect the jet of combustion gas in contact with the inside wall of the diverging portion. The device includes a structure disposed inside the diverging portion in such a manner as to reduce the diverging nature of the flow section thereof and to increase the bearing area of pressure forces exerted by the jet on the diverging portion during swivelling thereof.

Abstract: An aft closure assembly manufactured from two separate and distinct pieces made from different materials is provided for a rocket motor case. The aft closure assembly includes at least a retaining ring piece made from a first material similar to or having a coefficient of thermal expansion similar to that of the motor case. The aft closure assembly includes a blast tube and closure piece that can be manufactured from a second material that does not need to be similar to nor have a coefficient of thermal expansion similar to the motor case and retaining ring piece. This is possible because the blast tube and closure piece includes a face seal that seals against a face of the retaining ring.

Abstract: An apparatus is provided that includes a body having a first wall and a second wall, at least one appending structure extending from an end of the body and at least one actuator positioned between the first and second walls. The actuator includes first end coupled to a portion of the body and a second end coupled to a portion of the appending structure. At least one shape memory alloy (SMA) wire is connected to and extends between the first and second ends of the actuator. The SMA wire is adapted to controllably constrict when activated by heat, whereby the constriction causes the appending structure to move from a first position to a second position.

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: 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 potion 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: An exhaust flow nozzle for use with a jet engine. The exhaust flow nozzle includes a beveled downstream edge portion that helps to direct noise generated by the jet engine upwardly away from a ground surface during takeoff and landing operations. One preferred embodiment makes use of a linearly moveable flow altering component that is positioned outside the final flow nozzle. When the flow altering component is in its retracted position it has no effect on the exhaust flow leaving the flow nozzle. Alternative embodiments involve the use of varying edge shapes for the final flow nozzle.

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: A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked. A ring rotates with another ring to control both this air flow, and a supply of cooling air to an interior of the nozzle.

Abstract: Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fashion as mechanically disposed chevrons have done in the known art. Unlike mechanically disposed chevrons of the known art, the fluid flow may be secured thereby increasing the engine efficiency. Various flow patterns, water pressures, orifice designs or other factors can be made operative to provide desired performance characteristics.

Abstract: The cowling is used around a turbine exhaust case in gas turbine engine. It comprises a substantially conical wall with a longitudinal split forming opposite ends. Each end is directly unconnectable to each other.

Abstract: A gas turbine engine has the convergent flaps and seals of an adjustable cross-sectional area nozzle connected to associated liners with a thermally compliant bracket. The bracket includes spaced feet with an intermediate notch spaced away from the liner. In this manner, a temperature gradient along the liner can be easily compensated at the connection of the bracket to the liner by adjustment within the notch. In other features, the bracket is riveted to the liner, providing further resistance to thermal expansion due to temperature gradiations.

Abstract: A quick change connection is provided for attaching a bracket and liner subassembly to convergent flaps and seals in an adjustable nozzle for a gas turbine engine. A threaded attachment member has a t-shaped head that is secured to prevent rotation by a washer. The washer is held in place in the convergent flaps and seals by spring fingers in a slot. By utilizing the washer, a simple threaded connection can be utilized even though the threaded attachment member must extend to a radially outer surface of the convergent flaps and seals, while a nut is threaded onto the threaded attachment member radially inwardly of the convergent flaps and seals. The washer prevents rotation of a head of the threaded attachment member, and thus allows the nut to be easily tightened to secure the components. This also facilitates maintenance as the threaded nut can be easily removed from the threaded attachment for replacement.

Abstract: A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked.

Abstract: An annular exhaust duct of a gas turbine engine includes inner and outer cases co-axially disposed, and radially spaced apart by a plurality of airfoils radially extending therebetween. The outer case includes a connection apparatus for supportably connecting the exhaust duct to the gas turbine engine and the inner case includes an axial end portion at a rear end thereof for connection with a tail cone. The axial end portion bends radially and inwardly at a rear extremity thereof to stiffen the rear end of the inner ease.

Abstract: A device for controlling fluid flow. The device includes an arc generator coupled to electrodes. The electrodes are placed adjacent a fluid flowpath such that upon being energized by the arc generator, an arc filament plasma adjacent the electrodes is formed. In turn, this plasma forms a localized high temperature, high pressure perturbation in the adjacent fluid flowpath. The perturbations can be arranged to produce vortices, such as streamwise vortices, in the flowing fluid to control mixing and noise in such flows. The electrodes can further be arranged within a conduit configured to contain the flowing fluid such that when energized in a particular frequency and sequence, can excite flow instabilities in the flowing fluid. The placement of the electrodes is such that they are unobtrusive relative to the fluid flowpath being controlled.

Abstract: The invention relates to an annular cover for a turbomachine nozzle, the cover having a plurality of patterns extending a trailing edge of said cover and spaced apart circumferentially from one another, each pattern having an outline that is substantially triangular in shape, with a base formed by a portion of the trailing edge of the cover and a vertex spaced downstream from the base and connected thereto by two sides. For each pattern, the vertex presents an outline that is substantially curved; each side is connected to the trailing edge of the cover following an outline that is substantially curved having a radius of curvature that is greater than the radius of curvature of the outline of the vertex; and the outline of each of the sides includes at least one point of inflexion having a tangent that is substantially parallel to the base.

Abstract: Nozzles having variable geometry are disclosed that are comprised of a plurality of vanes that contact one another and can slide with respect to one another. A control element forces the vanes to slide, with contacting sides of the vanes defining an inner flow path through which a fluid may pass. The vanes may be self-similar or different from one another to define the desired geometries of the opening in the nozzles. The vanes may be configured to provide convergent, divergent and convergent-divergent nozzles for a range of applications.

Abstract: An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachment hanger system. The foldable attachment hanger system provides a low profile (foldable up/down) for a limited access installation envelope typical of a three bearing swivel duct (3BSD) which rotates about three bearing planes to permit transition between a cruise configuration and a hover configuration. In this way, each cooling liner segment may be formed as a complete cylindrical member requiring joints only between the swivelable duct sections.

Abstract: The invention relates to an exhaust nozzle for a bypass turbomachine, the nozzle comprising a central body, a primary cowl surrounding the central body to define a primary channel, and a secondary cowl surrounding the primary cowl to define a secondary annular channel, the secondary cowl comprising a stationary portion and a movable portion disposed to extend the stationary portion and capable of moving longitudinally upstream and downstream relative to the stationary portion and relative to the primary cowl so as to vary the exhaust section and/or the throat section of the nozzle, the stationary portion of the secondary cowl presenting a plurality of spaced-apart repetitive patterns disposed extending its trailing edge, and the movable portion of the secondary cowl including in its outside surface a plurality of indentations of shapes complementary to the patterns of the stationary portion.

Abstract: A vectorable nozzle includes convergent and divergent sections and a throat therebetween. Heightwise spaced apart upper and lower walls outwardly bound a nozzle flowpath and extend aftwardly through the convergent and divergent sections from the nozzle inlet to the nozzle outlet. The upper wall includes triangular left and right side convergent upper panels pivotably mounted to a triangular convergent upper ramp in the convergent section along left and right side convergent angled hinge lines respectively. The upper wall further includes triangular left and right side divergent upper panels pivotably attached to a triangular divergent upper ramp in the divergent section along left and right side divergent angled hinge lines respectively. The left and right side convergent upper panels are in sealing engagement with the left and right side divergent upper panels along left and right side upper interfaces, respectively.

Abstract: A fan variable area nozzle (FVAN) selectively rotates a synchronizing ring relative the static ring to adjust a flap assembly through a linkage to vary an annular fan exit area through which fan air is discharged. By adjusting the FVAN, engine thrust and fuel economy are maximized during each flight regime.

Abstract: A sprung seal assembly includes a flexible sprung seal having a center section disposed between opposing curved and cantilevered first and second end sections. First and second free edges of the first and second end sections respectively are trapped within a retainer. First and second sliding lugs attached to the first and second free edges respectively are slidably disposed in first and second channels respectively. The first and second free edges are trapped in the retainer by the first and second sliding lugs disposed in the first and second channels between a mounting surface and the retainer attached to the mounting surface. The center section may have a wear strip. The sprung seal assembly may be disposed between a relatively fixed sidewall and a relatively movable flap of a nozzle assembly. The retainer is mounted to the flap and the center section is in sealing engagement with a sealing surface of the sidewall.

Abstract: The invention relates to a device for mixing two fluid flows, initially guided separately from one another, in a two-circuit reaction engine, a mixing tube which encloses a hot core stream being provided, along the outer shaped lateral surface of which a cold bypass flow flows. The mixing tube is designed in the form of a truncated cone narrowing in the direction of flow and has openings arranged at the downstream end in the circumferential direction of the mixing-tube lateral surface in a cross-sectional plane lying perpendicularly to the longitudinal axis of the mixing tube. The hot core stream flowing through the mixing tube penetrates through the openings into the cold bypass flow flowing around the mixing-tube lateral surface. The openings have passage areas of elliptical shape with a major axis and a minor axis, the major axis of the passage areas running on the lateral surface of the mixing tube in the direction of flow of the fluids and the minor axis running perpendicularly thereto.

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: The present invention relates to a propulsion gas exhaust assembly, in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a transition element (21) emerging in two duct elements (22, 23) each communicating with an ejection half-nozzle (24, 26), wherein each of the two duct elements (22, 23) forms an elbow downstream of the transition element.

Abstract: The invention relates to a central body of a turbojet nozzle comprising a wall forming a cavity. The central body comprises a plurality of orifices pierced over at least one upstream portion of its wall and a single resonance cavity forming a Helmholtz resonator. Such a central body makes it possible to attenuate the low frequency noises.

Abstract: A turbine engine exhaust diffuser assembly having a tuneable exhaust velocity profile is disclosed. The assembly includes structure that generates a desired, tunable velocity profile within working fluid exiting the exhaust diffuser assembly. The exhaust assembly includes an concentric boundary sleeves that extend along a central axis and form an exhaust flowpath between them. A flow deflecting member disposed within the flowpath longitudinally divides the flowpath into a first region and a second region. The first region is characterized by a first predetermined velocity profile, and the second region is characterized by a second predetermined velocity profile. The second velocity profile is determined by at least one pre-selected dimension of the flow deflecting member. Methods of maximizing HRSG energy extraction capacity and extending HRSG lifespan are also disclosed.

Abstract: An exhaust duct system for a gas turbine engine that mounts within a tail cone of an aircraft, comprises an exhaust exit that exits one side of the tail cone offset from the axial centreline of the tail cone and an exhaust duct that couples the engine to the offset exhaust exit, with a straight section of the exhaust duct extending from the exhaust exit for a length that corresponds to at least one diameter of the exhaust duct.

Abstract: A nozzle for use in a hot gas valve is provided that includes a housing, an insert, and a throat retainer. The housing is constructed of an insulating material and has a flow path formed therein. The flow path has a throat section. The insert is made of material capable of maintaining structural integrity at a temperature up to about 5000° F. and is disposed at least partially in the throat section and has a flow path extending therethrough in fluid communication with the housing flow path. The throat retainer is constructed of material having insulating and ablative properties and is coupled between the housing and the insert and configured to retain the insert within the housing throat section.

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 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 method enables modeling of a gas turbine engine that includes a pulse detonation system. The method includes providing a pulse detonation modeling system, predicting characteristics of the engine using the pulse detonation modeling system, and predicting characteristics of the pulse detonation system using the pulse detonation modeling system.

Abstract: A fluid flow nozzle is formed by a plurality of adjacent L-shaped channels forming successive channel pairs. Each channel has a linking member joined to a radial member. Each linking member is welded to an adjacent linking member forming a contiguous surface of linking members. Each radial member is oriented approximately perpendicular to a first side of the contiguous surface. A circumferentially enclosed chamber is formed on a second side of the contiguous surface. Each radial member is laser welded to a jacket at a distal end of each radial member. The jacket is oriented approximately parallel with the contiguous surface and separably spaced from the contiguous surface by the radial members. Each radial member forms one of a plurality of flow chambers between its adjacent radial member, the jacket and the contiguous surface. The flow chambers advantageously contain fluid in the event of a radial member rupture.

Abstract: A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a centerbody.

Abstract: A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud surrounds the centerbody and cooperates with the centerbody to define the throat of the nozzle. An outer shroud surrounds the inner shroud and cooperates with the centerbody to define the exit area of the nozzle. Both shrouds are independently translatable to provide independent control of the nozzle throat area and the nozzle expansion ratio.

Abstract: A device for controlling propulsive gas mixing at an outlet of an aircraft jet engine, wherein propulsive jets are composed of a hot primary jet exiting from a nozzle of the jet engine and a secondary flux flowing between an external wall of the nozzle and an internal wall of the jet engine including a divergent trailing edge on the wall that generates conditions of a separation of the primary jet close to an existence limit value and a primary jet controller that enables control of passage of the primary jet from a separated state to a reattached state, and vice versa.

Abstract: A thrust vector control system for a plug nozzle rocket engine for propelling and maneuvering a vehicle is disclosed. The plug nozzle rocket engine includes a housing having a nozzle throat, a plug disposed within the housing and positioned within the nozzle throat to define a space between the plug and the nozzle throat, and a thrust diverter moveably disposed relative to the housing to define an asymmetric pressure distribution along the plug for thrust-vectoring. In one embodiment, the thrust diverter is normally biased to a non-thrust-vectoring position, but is moveable in a plane substantially perpendicular to an axis extending longitudinally through the plug.

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: A controlled hot flap shutter for a turbojet nozzle includes a friction surface made of metal, and including straight lateral flanks to reduce the gap between each controlled hot flap shutter and the tracking flap shutters adjacent thereto.

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 system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft end of the nozzle. There is a predetermined clocking relationship between the plurality of mixer lobes and the plurality of nozzle tabs that results in reduced exhaust noise emission, most evident in the lower frequency range. A method for reducing jet noise emission from an internally mixed gas turbine engine exhaust comprises selectively aligning a circumferential distribution of a mixed flow vorticity field produced by a fan/core mixer with a circumferentially distributed exhaust flow vorticity field produced by a modified common flow nozzle at an exit plane of the engine exhaust.

Abstract: A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas turbine engine; and a plurality of airfoils extending between the inner and outer case portions, airfoils structurally connecting the inner case portion to the outer case portion.

Abstract: An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross sectional area of the nozzle in a throat region, and a bridge member positioned intermediate adjacent ones of the flaps. The bridge member includes a bridge bracket and a sealing element joined to the bridge bracket. The sealing element has an upper surface. The bridge bracket has a lower surface which diverges from the upper surface of the sealing element. In a preferred embodiment of the present invention, the bridge bracket has a shape which allows variable slot size depending on nozzle throat jet area.

Abstract: An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received within the transition duct such that a combustion liner seal is in contact with an inner wall of the transition duct inlet ring. Increasing the dedicated cooling air supply to the combustion liner aft end, coupled with a modified combustion liner aft end geometry, significantly reduces turbulence and flow re-circulation, thereby resulting in lower metal temperatures and increased component life. Multiple embodiments of the interface region are disclosed depending on the amount of cooling required.

Abstract: A nozzle includes a sideways split and aftwardly swept nozzle ramp extends between a fixed lower nozzle wall and a pivotal upper nozzle wall pivotally connected to an aft end of the nozzle and operable to vary a throat area of a throat of the nozzle. The upper and lower nozzle walls and the ramp extend transversely between first and second nozzle sidewalls. A sideways pivotable ramp structure pivotally connected to the lower nozzle wall and pivotable between the sidewalls includes a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls. Right hand and left hand upper ramp sections of the nozzle ramp may be connected to right hand and left hand upper nozzle wall sections respectively of the upper nozzle wall which are pivotally connected to right and left handed triangular side walls of the aft end.

Abstract: A method of assembling a gas turbine engine includes coupling an annular exhaust duct to the gas turbine engine, coupling a plurality of chevrons to the annular exhaust duct, and coupling a chevron actuation system to the annular exhaust duct such that selective operation of the chevron actuation system repositions the plurality of chevrons to adjust an amount convergence of the annular exhaust duct.

Abstract: A can combustor for an industrial turbine includes a transition piece transitioning directly from a combustor head-end to a turbine inlet using a single piece transition piece. In an exemplary embodiment, the transition piece is jointless.

Abstract: A vectorable nozzle includes a longitudinally extending upper fixed wall spaced upwardly and aftwardly of a longitudinally extending lower fixed wall and an aftwardly swept fixed ramp extending between the upper and lower fixed walls. The upper and lower fixed walls and the fixed ramp extend transversely between first and second fixed sidewalls. An outer nozzle wall is spaced apart from the upper and lower fixed walls and extends transversely between first and second fixed sidewalls. A nozzle flowpath is defined between the upper and lower fixed walls and the outer nozzle wall and the first and second fixed sidewalls. A sideways pivotable ramp structure pivotally connected to the lower fixed wall and pivotable between the sidewalls includes a longitudinally extending upper pivotable wall spaced upwardly and aftwardly of a longitudinally extending lower pivotable wall and an aftwardly swept pivotable ramp extending between the upper and lower pivotable walls.

Abstract: A method enables a gas turbine engine to be operated. The method comprises channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface, and selectively operating a noise suppression system extending from the at least one flow boundary surface to facilitate attenuating noise generated during engine operation.

Abstract: This disclosure relates to a method and an arrangement for preventing explosives such as rocket engines from exploding while subjected to an external fire in an ammunition bunker. The basic principle underlying the invention is that the casing surrounding the explosive includes a number of parts which are held together by mounting components made from a shape memory alloy, the properties of which are selected in such a manner that these mounting components no longer hold the various parts of the casing together if the surrounding temperature rises to approach the ignition temperature of the explosive in the rocket engine.