Matches 1 - 50 out of 129 1 2 3 >


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US20150075169 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...
US20140260283 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...
US20130104555 TURBOFAN ENGINE MIXER ASSEMBLY  
A mixer for mixing flows in a turbofan engine is provided. The mixer includes a plurality of chevron lobes, each of the plurality of lobes comprising a crown, a keel, a first trailing edge, a...
US20150000289 GAS EJECTION CONE FOR AIRCRAFT TURBOJET ENGINES  
A gas ejection cone includes a cylindrical-shaped front cone portion, a conical-shaped rear cone portion, a ventilation tube and a support bearing of this drainage and/or ventilation tube. The...
US20140165574 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...
US20110126512 TURBOFAN GAS TURBINE ENGINE AERODYNAMIC MIXER  
A mixer for a turbofan engine includes a centerbody and a mixer nozzle. The mixer nozzle surrounds at least a portion of the centerbody and is spaced apart to define a core flow path between the...
US20130305727 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)...
US20150240745 ANGLED REVERSE CORE GAS TURBINE ENGINE WITH WIDENED NOZZLE  
A propulsion system for an aircraft includes a furcated nozzle that has at least a first duct that extends from a first propulsor to a first trailing end duct opening and a second duct that...
US20140202164 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...
US20150013303 ENGINE PROPULSION SYSTEM  
An engine propulsion system is configured to utilize bursts of media in order to create mechanical energy. The engine propulsion system includes at least one cannon, wherein each cannon is...
US20140053563 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...
US20140075919 TEC MIXER WITH VARIABLE THICKNESSES  
A mixer of a bypass turbine aeroengine according to one embodiment, includes circumferential inner and outer flow surfaces in a wavy configuration to form a plurality of lobes of the mixer. The...
US20140102112 ONE-PIECE FUEL NOZZLE FOR A THRUST ENGINE  
A nozzle formed of one piece for a jet engine includes a mixing tube, a fuel conduit integrally formed with the mixing tube, and an opening through the fuel conduit and directed radially into the...
US20140096510 SLOTTED MULTI-NOZZLE GRID WITH INTEGRATED COOLING CHANNELS  
An apparatus includes a slotted multi-nozzle grid with a plate having multiple elongated slotlettes through the plate. Each of at least some of the slotlettes has a convergent input, a divergent...
US20120079803 Exhaust plume heat effect reducing method and apparatus  
An apparatus for reducing heating effects of an exhaust plume of a jet engine on an impinged surface includes fluid injectors disposed adjacent and aimed into an exhaust plume zone that's to be...
US20120067023 ROCKET ENGINE AND METHOD FOR CONTROLLING COMBUSTION IN THE ROCKET ENGINE ITSELF  
Supply of a liquid component in a combustion chamber of a rocket engine is controlled by a feed valve provided with an obturator mobile between a pen position and a closed position of at least one...
US20090277181 AIRCRAFT PROPULSION UNIT THAT COMPRISES AN EXHAUST PIPE WITH A SCALLOPED TRAILING EDGE  
A propulsion unit includes at least one exhaust pipe (62, 76) that includes an air discharge that is delimited by a trailing edge (78, 82). The end part of the exhaust pipe (62, 76) includes two...
US20080022689 Low profile attachment hanger system for a cooling liner within a gas turbine engine swivel exhaust duct  
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...
US20140373550 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 (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped...
US20090133405 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...
US20090133406 FAN NOZZLE OF ADJUSTABLE SECTION  
Varying the flowsection for air leaving the fan as a function of flying conditions. According to the invention, the nozzle has a ring of deformable panels arranged close to its trailing edge, each...
US20110192167 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 (21, 22) having front ends (21A, 22A) that are connected to said nozzle (4, 10) and that, when...
US20140130503 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 (35) and a diverging duct (14) transform this exhaust energy...
US20100307163 FIBER-BASED ABLATIVE AND HIGH TEMPERATURE PRE-PREG MATERIAL  
A fabric-matrix composite structure [10] for making parts [13] suitable for use in hostile, high-temperature environments, such as rocket exhaust nozzles. The structure [10] includes a fabric [11]...
US20090145134 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...
US20120291443 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...
US20090145133 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...
US20090064660 NOZZLE WITH YAW VECTORING VANE  
An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located...
US20090084111 TURBOMACHINE NOZZLE COWL HAVING JET NOISE REDUCTION PATTERNS  
The invention relates to a cowl for a turbomachine nozzle, the cowl including a plurality of repetitive patterns disposed to extend a trailing edge of said cowl and spaced circumferentially apart...
US20150101337 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...
US20120317957 AIRCRAFT POWERPLANT  
A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass...
US20080078163 Gas turbine engine nozzle liner with thermally compliant attachment brackets  
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...
US20100050651 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...
US20080078162 TURBINE EXHAUST CASE COWLING FOR A GAS TURBINE ENGINE  
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...
US20080060344 EXHAUST DUCT AND TAIL CONE ATTACHMENT OF AIRCRAFT ENGINES  
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...
US20080047273 TURBOMACHINE NOZZLE COVER PROVIDED WITH TRIANGULAR PATTERNS HAVING PAIRS OF VERTICES FOR REDUCING JET NOISE  
The pattern relates to a cover for a turbomachine nozzle, the cover having a plurality of patterns each with an outline of triangular shape having a base and two vertices that are spaced...
US20090019857 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...
US20080041061 Multiple vane variable geometry nozzle  
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...
US20070214767 Low noise exhaust ducting system  
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...
US20120297779 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...
US20090013663 METHANE ENGINE FOR ROCKET PROPULSION  
Disclosed is a methane engine for rocket propulsion. A methane supply pump (36) operated by a turbine (30) supplies a part of methane to a nozzle cooling channel (56, 156) installed on a nozzle...
US20100024428 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...
US20080236939 Exhaust silencer assembly  
An exhaust silencer assembly for use with a gas turbine engine, the exhaust silencer assembly comprising an exhaust duct extension disposed downstream from an exhaust diffuser of the gas turbine...
US20130318944 Jet Exhaust Noise Reduction  
Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.
US20080072604 Pressure balance control for gas turbine engine nozzle  
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...
US20130125527 REVERSIBLE FLOW DISCHARGE ORIFICE  
A rocket engine fluid-flow system includes a pump fluidly interconnecting a fluid source to a combustion chamber. A nozzle is in fluid communication with the combustion chamber and includes...
US20060266045 Protection process and control system for a gas turbine  
In a process for protection of a gas turbine (1) from damage caused by pressure pulsations (P), pressure pulsations (P) occurring during the operation of the gas turbine (1) are measured, from the...
US20090320486 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...
US20140102109 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...
US20140090359 MIXER THAT PERFORMS RECIPROCATING ROTARY MOTION FOR A CONFLUENT-FLOW NOZZLE OF A TURBINE ENGINE, AND A METHOD OF CONTROLLING IT  
The invention provides a mixer for a confluent-flow nozzle of a turbine engine, the mixer comprising an annular cap designed to be centered on a longitudinal axis of the nozzle and having a...

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