| Entries |
| Document | Title | Date |
|---|
| 20080256957 | Joint for a shape memory material - A joint between a first component ( | 10-23-2008 |
| 20090000304 | INTEGRATED SUPPORT AND MIXER FOR TURBO MACHINERY - A support and air mixer includes an inner annular member, an outer annular member shaped and positioned such that an annular air gap is formed between the inner annular member and the outer annular member, and a plurality of air mixing members, each air mixing member having a mixing passageway therethrough and each air mixing member having an inner portion connected to the inner annular member, an outer portion connected to the outer annular member, and first and second opposing side portions interconnecting the inner and outer portions and the inner and outer annular members such that the mixing passageway is in fluid communication with the annular air gap. | 01-01-2009 |
| 20090019857 | MODULAR CHEVRON EXHAUST NOZZLE - An exhaust nozzle for a gas turbine engine includes a modular chevron. The chevron includes dual skins fixedly joined together at a base flange, and at a rim extending along the trailing edge of the chevron between the base and apex thereof. | 01-22-2009 |
| 20090031730 | Nozzle Arrangement for a Gas Turbine Engine - 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. | 02-05-2009 |
| 20090044541 | APPARATUS AND METHOD FOR REDUCTION OF JET NOISE FROM SINGLE JETS - 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 specific 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. | 02-19-2009 |
| 20090064681 | Scalloped Flexure Ring - A scalloped flexure ring. An illustrative embodiment of the flexure ring includes a ring body having a first ring body edge and a generally scalloped second ring body edge and a plurality of spaced-apart ring fingers provided in the second ring body edge. | 03-12-2009 |
| 20090071164 | FLUTED CHEVRON EXHAUST NOZZLE - A gas turbine engine exhaust nozzle includes a fluted shell terminating in a row of chevrons. The nozzle is radially serpentine circumferentially around the shells and has a circumferentially serpentine trailing edge. | 03-19-2009 |
| 20090133405 | Combustible outgassing material lined altitude compensating rocket nozzle - A fixed sized bell rocket nozzle is lined with a layer of combustible material that is ignited during launch ignition and burns to outgas into the rocket exhaust for spatially variably confining the exhaust and perfecting an effective variably sized altitude compensating exhaust nozzle that maximizes lift during the launch of a spacecraft into orbit. | 05-28-2009 |
| 20090145133 | EXHAUST LINER ATTACHMENT ARRANGEMENT - 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. | 06-11-2009 |
| 20090145134 | ROCKET ENGINE NOZZLE SYSTEM - The rocket engine nozzle system comprises a set of individual nozzles distributed in a ring around a central core of axially symmetrical shape that presents a central axis. Each individual nozzle placed at the periphery of the central core comprises a circular section throat for receiving gas from a combustion chamber, and a diverging portion that is tangential to the central core. The diverging portion has an outlet section that presents first and second lateral sides that converge radially towards the central axis of the central core, a curved outer side having its convex side facing outwards, and an inner side situated in the vicinity of the central core. | 06-11-2009 |
| 20090199565 | STAVE AND RING CMC NOZZLE - An engine exhaust nozzle comprises a plurality of CMC staves attached to one or more support rings arranged axially. The support rings provide a circumferential load path between the staves and for attaching the exhaust nozzle to the metallic engine components. The staves are fixed to the support rings with a spacing intended to accommodate for relative movement due to the difference in CTE for the CMC and metallic components and due to thermal gradients through the wall thickness. The resulting apparatus is lightweight, relieves the nozzle of thermal stresses, and is easier to manufacture and repair. | 08-13-2009 |
| 20090211258 | Rocket nozzles for unconventional vehicles - Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance. | 08-27-2009 |
| 20090217670 | EXHAUST NOZZLE SEAL WITH SEGMENTED BASESHEET DISPOSED BETWEEN SIDE RAILS - An aircraft engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments having panel bodies between segment leading and trailing edges and slidable sealing joints with slidingly un-restrained center surfaces between adjacent segment leading and trailing edges. Segmented first and second basesheet side edges include first and second segment side edges of the basesheet segments respectively. Slidably sealingly engaged overlapping flanges at the segment leading and trailing edges include tacked together transversely spaced apart first and second distal ends of the overlapping flanges. A basesheet assembly includes a frame includes first and second side rails supporting the first and second basesheet side edges. An aircraft gas turbine engine exhaust nozzle includes divergent seals with the basesheet assemblies in sealing engagement against divergent flaps along the first and second side rails. | 09-03-2009 |
| 20090277181 | AIRCRAFT PROPULSION UNIT THAT COMPRISES AN EXHAUST PIPE WITH A SCALLOPED TRAILING EDGE - A propulsion unit includes at least one exhaust pipe ( | 11-12-2009 |
| 20090320486 | DUPLEX TAB EXHAUST NOZZLE - 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. | 12-31-2009 |
| 20100000219 | Systems and Methods for Supplying Cooling Air to a Gas Turbine - A system and method for supplying cooling air to the turbine section of a gas turbine. The system may include a compressed air supply, an ambient air supply, and an ejector for entraining the ambient air supply with the compressed air supply to form a cooling air supply. In a gas turbine including a compressor section and a turbine section, the method may include extracting compressed air from the compressor section, entraining ambient air with the compressed air to form cooling air, and directing the cooling air to the turbine section. | 01-07-2010 |
| 20100005806 | EDUCTOR SYSTEM FOR A GAS TURBINE ENGINE - A power plant includes a gas turbine engine contained at least partially within an enclosure; an eductor system in communication with the gas turbine engine; and a blower system in communication with the enclosure and the eductor system. A method of communicating an exhaust from a gas turbine engine includes pressurizing a secondary airflow from the enclosure with a blower system and communicating the pressurized secondary airflow into an eductor system. | 01-14-2010 |
| 20100005807 | Liquid propellant rocket engine with a propulsion chamber shutter - A liquid propellant rocket engine with a propulsion chamber shutter, the rocket engine comprises a combustion chamber, a propellant injector device placed at an upstream first end of the combustion chamber, a nozzle throat disposed at a downstream second end of the combustion chamber remote from the upstream first end, and a diverging portion disposed downstream from the nozzle throat. A selective shutter device for the nozzle throat comprises an axially-symmetrical shutter member placed downstream from the nozzle throat, and axial rod for controlling the shutter member, a first short centering member for the control rod situated at the upstream first end of the combustion chamber level with the propellant injector device, a second short centering member for the control rod situated in the combustion chamber in the vicinity of the nozzle throat and upstream therefrom, and a system for returning the control rod of the selective shutter device for the nozzle throat to the closed position. | 01-14-2010 |
| 20100024428 | Rocket Apparatus and/or Method - A rocket motor for one or more of limited re-use or single use, including a rocket motor housing, the motor housing adapted to contain propellant; an aft closure with a nozzle, the aft closure connected or connectable to the housing; a forward closure connected or connectable to the housing; wherein one or both of the aft closure and the forward closure are connectable to the housing in manner adapted for one or both of limited re-use or single use. | 02-04-2010 |
| 20100037623 | High Efficiency Turbine Engine - A by-pass turbofan gas turbine engine, comprises: a by-pass fan with a by-pass fan outlet; a generally annular core engine duct with a core engine duct inlet coupled to the by-pass fan outlet and a core engine duct outlet; a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct with a by-pass duct inlet coupled to the by-pass fan outlet and a by-pass duct outlet; an upstream axial compressor with an axial upstream compressor inlet coupled to the core engine duct outlet and an axial upstream compressor outlet; a downstream radial compressor with an axial downstream compressor inlet coupled to the upstream compressor outlet and a radial downstream compressor outlet; a generally annular recuperator with a cool side inlet coupled to the downstream compressor outlet, a cool side outlet, a warm side inlet and a warm side outlet; a generally annular combustor with a combustor inlet coupled to the recuperator cool side outlet and a combustor outlet; a radial turbine with a radial turbine inlet coupled to the combustor inlet and a turbine outlet coupled to the recuperator warm side inlet; at least one exhaust nozzle with an exhaust nozzle inlet coupled to the recuperator warm side outlet and an exhaust nozzle outlet that discharges into the by-pass duct between the by-pass duct inlet and outlet; and a propelling nozzle coupled to the by-pass duct outlet. | 02-18-2010 |
| 20100050651 | Variable Slope Exhaust Nozzle - A turbine exhaust nozzle includes an inner shell disposed coaxially inside an outer shell to define a flow duct terminating in an outlet at a trailing edge of the outer shell. The inner shell is non-axisymmetric and varies in axial slope angle circumferentially around the duct. | 03-04-2010 |
| 20100139284 | Jet nozzle plug with varying, non-circular cross sections - 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. | 06-10-2010 |
| 20100146980 | MASKING ARRANGEMENT FOR A GAS TURBINE ENGINE - 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. | 06-17-2010 |
| 20100192590 | THERMALLY BALANCED MATERIALS - A material includes inner and outer skins joined together by a core. The core has a different thermal conductivity than the inner skin to balance heat conduction therethrough. | 08-05-2010 |
| 20100251724 | Aircraft jet engine provided with a device for reducing propulsion jet noise - A nozzle allowing the reduction of noise generated by aircraft jet engines having at least one output ring which disturbs the propulsion jet, and having at least one pair of conduits from which the propulsion of jet air is ejected at the output of the nozzle. The conduits of each pair are disposed convergent with respect to each other in order to generate a triangle of interaction of the air jets at the output ring. | 10-07-2010 |
| 20100257865 | Jet engine nozzle exit configurations and associated systems and methods - Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. | 10-14-2010 |
| 20100281874 | Airflow vectoring member - One embodiment is an apparatus comprising an aircraft airflow duct, and a rotatable member disposed within the duct. The rotatable member is rotatable to vector airflow and is capable of being spun in different directions at a variety of rotational rates. Some embodiments include stationary rotatable members. | 11-11-2010 |
| 20100307163 | FIBER-BASED ABLATIVE AND HIGH TEMPERATURE PRE-PREG MATERIAL - A fabric-matrix composite structure [ | 12-09-2010 |
| 20110048025 | NOZZLE PLASMA FLOW CONTROL UTILIZING DIELECTRIC BARRIER DISCHARGE PLASMA ACTUATORS - Dielectric barrier discharge plasma actuators are used to manipulate exhaust flow within and behind a jet engine nozzle. The dielectric barrier discharge plasma actuators may be used to direct cooling airflow near the surface of the nozzle to reduce heating of the nozzle, create thrust vectoring, and reduce noise associated with the exhaust flow exiting the nozzle. | 03-03-2011 |
| 20110192167 | NOISE CONTROL CHEVRON FOR A NOZZLE, AND NOZZLE AND TURBOSHAFT ENGINE PROVIDED WITH SUCH A CHEVRON - According to the invention, the shape of each of said chevrons is defined: by two lateral sides ( | 08-11-2011 |
| 20120240587 | NOISE REDUCTION SYSTEM - A noise reduction system includes: a microjet ring ( | 09-27-2012 |
| 20120279225 | FLOW EVACUATION SYSTEM FOR AN AIRCRAFT ENGINE - A flow evacuation system for an aircraft engine including an engine nozzle that conveys the engine exhaust flow and an eductor receiving the engine exhaust flow and engine ventilation flow is disclosed. The engine nozzle has a final section in contact by its outer surface with the ventilation flow. The engine exhaust flow has a low swirl when the engine operates under design conditions and a high swirl when the engine operates out of design conditions. The engine nozzle includes a plurality of local flow conditioners placed in its inner surface in the final section for reducing the swirl of the engine exhaust flow at the exit of the engine nozzle. | 11-08-2012 |
| 20120291443 | ROCKET PROPULSION DEVICE AND METHOD FOR ASSEMBLING ROCKET PROPULSION DEVICE - A rocket propulsion device including, a case having a propellant therein, the case in the form of a tube, a nozzle having at least part inserted in the case, and configured to discharge gas upon burning the propellant, and a locking unit disposed to be wound on the nozzle, the locking unit in the form of a band having both ends open, wherein a through hole for inserting the locking unit therein is formed at one region on a circumference of the case, and the both ends of the locking unit are located at a region facing the one region, whereby a rocket propulsion device having a simplified structure and a facilitated alignment of a thrust line can be implemented. | 11-22-2012 |
| 20120297779 | CORROSION RESISTANT CATALYSTS FOR DECOMPOSITION OF LIQUID MONOPROPELLANTS - Ceramic catalyst carriers that are mechanically, thermally and chemically stable in a ionic salt monopropellant decomposition environment and high temperature catalysts for decomposition of liquid high-energy-density monopropellants are disclosed. The ceramic catalyst carrier has excellent thermal shock resistance, good compatibility with the active metal coating and metal coating deposition processes, melting point above 1800° C., chemical resistance to steam, nitrogen oxides and acids, resistance to sintering to prevent void formation, and the absence of phase transition associated with volumetric changes at temperatures up to and beyond 1800° C. | 11-29-2012 |
| 20130104555 | TURBOFAN ENGINE MIXER ASSEMBLY | 05-02-2013 |
| 20130219901 | COMBUSTION CHAMBER PROVIDED WITH A TUBULAR ELEMENT - A combustion chamber including a diverging portion. The combustion chamber extends along a longitudinal axis and includes a fluid injection system from which there extends in a downstream direction a wall presenting a throat and a diverging portion situated downstream from the throat. The chamber further includes a tubular element surrounding the wall at least in part and configured to take up most of forces generated during operation of the chamber on the downstream end of the wall to transfer the forces to a structure situated upstream from the chamber. | 08-29-2013 |
| 20130227952 | SANDWICH STRUCTURE WITH SHEAR STIFFNESS BETWEEN SKINS AND COMPLIANCE IN THE THICKNESS DIRECTION - A sandwich structure includes a first skin, a second skin, a first hinge member, and a second hinge member. The first hinge member may be movably coupled to the first skin and a first skin joint. The second hinge member may be movably coupled to the second skin and second skin joint. The first hinge member and the second member may be movably coupled to one another and a member joint located between the first and second skin joint. | 09-05-2013 |
| 20130232981 | JET NOISE REDUCTION USING EDUCTION EFFECT - An exhaust duct through which an exhaust gas jet from a gas turbine engine flows comprises a duct wall, an inlet, an outlet and an eductor. The inlet, through which the exhaust gas jet enters the exhaust duct, is positioned at an upstream end of the exhaust duct. The outlet, through which the exhaust gas jet exits the exhaust duct, is positioned at a downstream end of the exhaust duct. The eductor is positioned proximate the downstream end. In one embodiment, the eductor comprises a perforated wall segment of the duct wall through which ambient air from outside of the duct wall is permitted to enter the exhaust duct. In yet another embodiment, the eductor is diverging. | 09-12-2013 |
| 20130305727 | BUILT-UP COMPOSITE STRUCTURES WITH A GRADED COEFFICIENT OF THERMAL EXPANSION FOR EXTREME ENVIRONMENT APPLICATIONS - An integrated composite structure with a graded coefficient of thermal expansion (CTE) is formed by selecting a plurality of layers of materials with a graded CTE and using build-up (bottom-up) fabrication approaches such as metal deposition or powder metallurgy to produce a CTE-graded layered composite preform, which is then consolidated and heat treated to create the CTE graded integrated composite billet or near net shape. The integrated composite billet or near net shape is then processed to produce a first surface for attachment of a first structural member having a first CTE and to produce a second surface of for attachment of a second structural member having a second CTE. | 11-21-2013 |
| 20140053563 | METHOD FOR ASSEMBLING A NOZZLE AND AN EXHAUST CASE OF A TURBOMACHINE - A method for assembling a nozzle and an exhaust case of a turbomachine is disclosed. The exhaust case includes a hub and an outer ferrule connected to each other by a plurality of arms. The nozzle is attached to the outer ferrule of the exhaust case substantially at the trailing edges of the arms. | 02-27-2014 |
| 20140102108 | SEAL ASSEMBLY FOR LINERS OF EXHAUST NOZZLE - An exhaust nozzle liner assembly of a gas turbine engine includes a first liner, a second liner spaced from the first liner by a gap, a seal assembly located at least partially within the gap to provide a continuous surface defined by the first liner, the seal assembly and the second liner, and a seal retainer to retain the seal assembly | 04-17-2014 |
| 20140102109 | PROPULSION SYSTEM AND ROCKET HAVING THE SAME - Disclosed is a propulsion system and a rocket having the same. The propulsion system includes: a combustion tube having a propellant therein; a nozzle installed at a rear end of the combustion tube, and configured to discharge combustion gas generated when the propellant is ignited; and a nozzle separation unit coupled to the combustion tube and the nozzle, respectively, and configured to mount the nozzle to the combustion tube, and configured to separate the nozzle from the combustion tube as at least part thereof melts when reaching a preset temperature. | 04-17-2014 |
| 20140130503 | TURBOFAN ENGINE WITH CONVERGENT - DIVERGENT EXHAUST NOZZLE - With the speedy and hot airplane turbojet exhaust gases a lot of energy is blown away and wasted nowadays. By this invention a venturi ( | 05-15-2014 |
| 20140165574 | EXHAUST PLUG FOR AN AIRCRAFT TURBOJET ENGINE - An exhaust plug for an aircraft turbojet engine is provided. The exhaust plug includes a front part being attached to a rear part, and the front and rear parts each have an outer skin. In particular, the front part and the rear part are connected by a connecting flange which is shared by the front and rear parts. The outer skins of the front and rear parts are placed side by side on the connecting flange. | 06-19-2014 |
| 20140202164 | GAS TURBINE ENGINE NOZZLE INCLUDING HOUSING HAVING SCALLOPED ROOT REGIONS - A gas turbine engine exhaust nozzle comprises a housing having an aft end that terminates in a row of chevrons. At least one surface of the housing has scalloped root regions proximate bases of adjacent chevrons. The scalloped root regions have a reduced thickness relative to the rest of the aft end. | 07-24-2014 |
| 20140260283 | GAS TURBINE ENGINE EXHAUST MIXER WITH AERODYNAMIC STRUTS - An exhaust mixer for a gas turbine engine has a plurality of circumferentially distributed alternating inner and outer lobes, and a plurality of aerodynamic struts positioned and oriented between adjacent inner lobes in the core flow passage. The struts are configured for diverting a portion of the core flow radially outwardly in troughs formed by the outer lobes on the core flow side of the mixer. | 09-18-2014 |
| 20140373550 | TAIL CONE FOR A MICROJET ROTARY TURBINE ENGINE - The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow ( | 12-25-2014 |
| 20150033747 | CONVERGENT-DIVERGENT NOZZLE FOR A TURBINE ENGINE - A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value. | 02-05-2015 |
| 20150047362 | LAUNCHER STAGE COMPRISING A TEMPORARY SUPPORT STRUCTURE FOR TEMPORARILY SUPPORTING NOZZLE SECTIONS ALLOWING ACCESS TO THE CORE OF THE ENGINE - A stage of a space launcher including an engine core, a tank secured above the engine core, and a nozzle including a first deployable nozzle section secured below the engine core, the nozzle further including a second and a third section configured to be situated extending from each other when the nozzle is in a deployed propulsion configuration. The stage further includes a structure for temporarily supporting nozzle sections mounted on the tank, configured to change the nozzle to a configuration for accessing the engine core wherein the nozzle sections are inserted into each other, with the third section bearing against a lower support of the temporary structure. | 02-19-2015 |
| 20150075169 | INTEGRATED TURBINE EXHAUST STRUTS AND MIXER OF TURBOFAN ENGINE - A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and an annular shroud with the mixer attached to a downstream end of the shroud, the shroud and the mixer surrounding the hub to form an annular exhaust gas duct positioned radially therebetween, a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC and located within an axial length of the mixer between an upstream end and a downstream end of the mixer, the deswirling struts each having a cambered profile and extending radially across the annular exhaust gas duct and interconnecting the mixer and the hub. | 03-19-2015 |
| 20150101337 | NOZZLE ARRANGEMENT FOR AN ENGINE - A nozzle arrangement for an engine that is operable in both an air-breathing mode, in which the engine combusts air taken in from atmosphere with hydrogen from a store thereof, and in a rocket mode, in which the engine combusts oxygen from a store thereof with hydrogen from the store thereof. The nozzle arrangement may include a rocket combustion chamber fluidly coupled by a rocket throat to a rocket nozzle. The rocket nozzle includes a first portion adjacent the rocket throat and a second portion remote from the rocket throat and axially moveable relative to the first portion between a rocket position in which they form a substantially contiguous rocket nozzle and an air-breathing position in which they overlap to define an annular throat therebetween. The nozzle arrangement may also include at least one air-breathing combustion chamber arranged to be fluidly coupled to the annular throat when the first and second portions of the nozzle are in the air-breathing position. | 04-16-2015 |
| 20150101338 | EXHAUST CENTERBODY FOR A TURBINE ENGINE - Exhaust centerbody ( | 04-16-2015 |
| 20150322890 | Center Body Attachment System - A center body attachment system is disclosed. A center body attachment system may permit a center body to be attached to an engine, while permitting various components to expand and contract independently when heated and cooled. In this manner, a center body may be made of a material having a different coefficient of thermal expansion than various components of the engine, such as an engine flange to which the center body is mounted. Thus, a center body may be made of materials having advantageous different material properties, for example, lighter and/or more heat-tolerant materials. | 11-12-2015 |
| 20160069299 | ORIENTABLE ROCKET-MOTOR SYSTEM - A system allowing for the tilting of the rocket motor such that, in the tilted position, the centre of the nozzle is located at least approximately on the neutral orientation axis of said rocket motor. | 03-10-2016 |
| 20160115904 | NOZZLE SUPPORT SYSTEM - A nozzle support system for a nozzle of a gas turbine includes an outer ring, an inner ring disposed within the outer ring, and a plurality of links pivotally attaching the outer ring to the inner ring. Each one of the links may have an outer end that is pivotally attached to the outer ring, and each one of the links may have an inner end that is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring. | 04-28-2016 |
| 20160131077 | FAIRING FOR A MIXER OF A NOZZLE OF A DUAL-FLOW TURBOMACHINE - The invention relates to a fairing ( | 05-12-2016 |
| 20160153398 | GAS TURBINE ENGINE EXHAUST MIXER | 06-02-2016 |
| 20160177789 | TURBOSHAFT ENGINE EXHAUST NOZZLE HAVING ITS OUTLET PERPENDICULAR TO THE AXIS OF ROTATION OF THE ENGINE | 06-23-2016 |
| 20160194968 | HIGH PERFORMANCE CONVERGENT DIVERGENT NOZZLE | 07-07-2016 |
| 20160195038 | CONVERGENT DIVERGENT EXIT NOZZLE FOR A GAS TURBINE ENGINE | 07-07-2016 |
| 20160377288 | ROUNDED EDGES FOR GAS PATH COMPONENTS - A gas turbine engine section has a housing and a plurality of panels attached to the housing. The panels face toward a flow path of hot products of combustion. The panels include a central web and extending legs. A bend between the central web and the extending legs is formed at a radius. A gas turbine engine is also disclosed. | 12-29-2016 |
| 20190145350 | LIQUID PROPELLANT ROCKET ENGINE WITH PASSIVE CONDENSATE COOLING | 05-16-2019 |
