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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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. |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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,... |
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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... |
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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... |
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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;... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |
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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. |
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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... |
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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... |
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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... |
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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... |
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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... |
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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... |