Matches 1 - 48 out of 48


Match Document Document Title
US20140086739 TRANSITION DUCT FOR USE IN A TURBINE ENGINE AND METHOD OF ASSEMBLY  
A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow...
US20100326048 GAS TURBINE ENGINE DUCT HAVING A COUPLED FLUID VOLUME  
A fluid tank structure is disclosed that is integrated within a bypass duct of a turbofan gas turbine engine. The fluid tank structure includes a hollow interior that is closed off when the fluid...
US20140230404 GAS TURBINE ENGINE EXHAUST MIXER  
An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer...
US20110036068 GAS TURBINE ENGINE EXHAUST MIXER  
An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer...
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...
US20130056553 METHOD FOR MIXING AIRFLOWS IN A TURBOFAN AND ENGINE OUTLET FOR OPERATION  
The invention aims at providing a sufficient air exchange in the engine area without raising the static pressure in the outlet area of the air exchange duct. In order to do this, the invention...
US20090188234 SHARED FLOW THERMAL MANAGEMENT SYSTEM  
A thermal management system includes at least two of a multiple of heat exchangers arranged in an at least partial-series relationship.
US20140224940 PROPULSION SYSTEM USING LARGE SCALE VORTEX GENERATORS FOR FLOW REDISTRIBUTION AND SUPERSONIC AIRCRAFT EQUIPPED WITH THE PROPULSION SYSTEM  
A propulsion system for a supersonic aircraft includes an engine, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the...
US20150107225 VARIABLE IMMERSION LOBE MIXER FOR TURBOFAN JET ENGINE EXHAUST AND METHOD OF FABRICATING THE SAME  
A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that...
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...
US20070245711 Aeroengine ventilation system  
A gas turbine engine comprising a ventilation zone defined between a core engine casing and a core fairing and having a discharge nozzle, the engine further comprises a pre-cooler having a flow of...
US20140083079 GEARED TURBOFAN PRIMARY AND SECONDARY NOZZLE INTEGRATION GEOMETRY  
A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core...
US20090235641 T-Jet  
The following is the design of a personal, strap-on the back flight device. It is my version of an air breathing jetpack; it is designed to give an individual pilot vertical take-off, horizontal...
US20080098719 Aircraft propulsion systems  
Disclosed are propulsion systems 30 providing reduced fuel burn, weight and cost. A single gas generator core 38 drives multiple bladed propulsion elements 36 with a power train 48. The core 38...
US20090211222 Rear propulsor for a variable cycle gas turbine engine  
A gas turbine propulsion system comprises a turbofan engine, a peripheral duct, an annular frame, an auxiliary turbine and an auxiliary fan. The turbofan engine is configured to produce bypass air...
US20120227375 GAS TURBINE ENGINE  
A cowl cavity is defined between a core engine cowl and an engine inner casing. A core fairing is provided at the forward end of the engine inner casing and has a radially outer surface which,...
US20080105487 CURVED LOBE MIXER FOR A CONVERGING-STREAM NOZZLE FOR A TURBOMACHINE  
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...
US20080141656 BYPASS TURBOMACHINE WITH ARTIFICIAL VARIATION OF ITS THROAT SECTION  
The invention relates to a bypass turbomachine comprising a gas turbine engine provided with a fan disposed on a longitudinal axis of the turbomachine, and an annular nacelle surrounding the...
US20070235080 Adjustment assembly  
A fluid flow control device (26, 28) comprising a guide member (30) to guide a fluid passing through a duct (22, 24, 76), the guide member (30) being movable between first and second positions;...
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...
US20140137538 Fast Response Bypass Engine  
A gas turbine engine has a compressor, a fan for delivering air into the compressor and into a bypass duct, a combustion section and a turbine section. A control for the gas turbine engine is...
US20090235638 VARIABLE AREA NOZZLE ASSISTED GAS TURBINE ENGINE RESTARTING  
A turbofan engine starting system includes a core nacelle housing (12), a compressor (16) and a turbine (18). The core nacelle is disposed within a fan nacelle (34). The fan nacelle includes a...
US20100031631 GAS TURBINE COMPRISING A GUIDE RING AND A MIXER  
A gas turbine is disclosed. The gas turbine includes a rotor which is driven by a turbine, a stator, struts that are fixed to the stator downstream from the turbine and that configure a guide ring...
US20090241505 RE-HEAT COMBUSTOR FOR A GAS TURBINE ENGINE  
A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second...
US20090211221 Auxiliary propulsor for a variable cycle gas turbine engine  
A core engine of a variable cycle gas turbine engine includes a low pressure spool for generating streams of bypass air and pressurized air, and a high pressure spool for further pressurizing the...
US20090217643 Gas discharge device for a vehicle engine  
The present invention provides gas discharge technique useful on vehicle engines. The technique comprises an s-shaped duct having an ejector formed therein to mix hot exhaust gas with a relatively...
US20090241549 SUBSONIC AND STATIONARY RAMJET ENGINES  
A ramjet engine (3, 4, 5), flying at Mach 3 has 64% efficiency, and at Mach 4 has 76% efficiency. Ramjet engines are currently only used for supersonic flight and have not been used as stationary...
US20080112798 Compound clearance control engine  
A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled...
US20130145744 SYSTEM FOR DIRECTING AIR FLOW TO A PLURALITY OF PLENA  
A system for directing air flow to separate plena of a compartment that is defined at least by a compartment wall includes a NACA scoop, and a Pitot scoop. The NACA scoop is formed in the...
US20070163230 CORE EXHAUST MIXER, HAVING A VARIABLE AREA, FOR TURBO-FAN JET ENGINES OF SUPERSONIC AIRCRAFT  
The invention relates to a core exhaust mixer, having a variable area, for turbo-fan jet engines of supersonic aircraft, comprising a nozzle (24) intended to be arranged about a gas generator of...
US20080105488 ROTARY MOTION MIXER FOR A CONVERGING-STREAM NOZZLE OF A TURBOMACHINE  
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...
US20070240424 Gas turbine engine having bypass ducts  
A gas turbine engine having a bypass flow in which the bypass flow includes a central bypass passage formed by a rotary shaft of the engine, and an outer bypass passage located between the casing...
US20150211441 VARIABLE EXHAUST MIXER AND COOLER FOR A THREE-STREAM GAS TURBINE ENGINE  
A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case...
US20050091963 Aircraft turbine engine and an air ejection assembly for use therewith  
An air ejection assembly for unsteadying an exhaust plume discharged from an exhaust end of a turbine engine during operation. A turbine engine incorporating the air ejection assembly and a method...
US20070144141 Pulsed combustion fluidic nozzle  
A propulsion system for producing thrust includes a turbine engine. The engine has a compressor, a combustor downstream of the compressor along a flow path, and a turbine downstream of the...
US20090158704 Gas Turbine Engine  
Variation in the available mixing plane areas in an exhaust arrangement of a gas turbine engine enables alteration and configuration for better thermal cycle performance of that engine. A shaped...
US20100218483 CONTROLLED FAN STREAM FLOW BYPASS  
A turbine engine component of a turbofan engine fitted with a bypass air valve includes at least one turbine engine component having a surface with at least one aperture, said turbine engine...
US20090000304 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...
US20100180571 MODULATING FLOW THROUGH GAS TURBINE ENGINE COOLING SYSTEM  
A gas turbine engine system includes a fan bypass passage in a cooling passage having an inlet that receives a bleed flow from the fan bypass passage and an outlet that discharges the bleed flow...
US20130232949 PRESSURE BALANCED AREA CONTROL OF HIGH ASPECT RATIO NOZZLE  
An apparatus for minimizing signature of an engine having an exhaust gas path and a fan gas path includes a casing, and a liner disposed within the casing. The exhaust gas path passes within the...
US20100005780 METHOD OF MANUFACTURING A CMC FLOW MIXER LOBED STRUCTURE FOR A GAS TURBINE AEROENGINE  
A method of fabricating a lobed structure for a gas turbine flow mixer having an annular upstream portion extended downstream by a portion forming a multilobed skirt, the method comprising: making...
US20070251212 Aeroengine noise reduction  
A gas turbine engine comprising an afterbody, which extends rearwardly from a nozzle exit plane, having an outer surface comprising acoustic liners.
US20130232948 Noise-Reducing Engine Nozzle System  
A method and apparatus for reducing noise generated during operation of an engine. In one illustrative embodiment, a nozzle system comprises a first nozzle and a second nozzle at least partially...
US20100269485 INTEGRATED VARIABLE AREA NOZZLE AND THRUST REVERSING MECHANISM  
A variable area fan nozzle for use with a gas turbine engine system includes a nozzle having a cross-sectional area associated with a discharge air flow from a fan bypass passage. The nozzle is...
US20170145955 HYBRID EXHAUST NOZZLE  
An exhaust system or nozzle for use in a gas turbine engine is disclosed herein. The exhaust system is adapted to adjust various streams of pressurized air produced by the gas turbine engine to...
US20160153397 Gas Turbine Engine System for Modulating Flow of Fan By-Pass Air and Core Engine Air  
The system (10) provides a modulator ring (54) secured adjacent an exhaust end (56) of an inner wall of a by-pass fan air duct (40) and secured adjacent a convergent nozzle section (38) of the...
US20160102634 REVERSE FLOW SINGLE SPOOL CORE GAS TURBINE ENGINE  
A bypass housing receives a fan and defines a front end. An airflow path delivers air into an inlet duct over a limited circumferential extent of the bypass housing. An airflow path passes across...
US20150369172 SERPENTINE BAFFLE FOR A GAS TURBINE ENGINE EXHAUST DUCT  
A serpentine baffle for a liner assembly of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a wall that defines a serpentine shape and a...

Matches 1 - 48 out of 48