Matches 1 - 50 out of 265 1 2 3 4 5 6 >


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US20130000273 GAS-DRIVEN PROPULSOR WITH TIP TURBINE FAN  
An engine comprises a gas generator having an exhaust plenum and a propulsor comprising a propulsion fan coaxially mounted within an annular turbine. The annular turbine comprises a turbine duct...
US20110192134 AIR INTAKE STRUCTURE FOR A TURBINE ENGINE NACELLE  
The invention relates to an air intake structure (4) for a turbine engine nacelle for directing an air flow towards the fan of the turbine engine, said structure comprising at least one outer...
US20150232194 STALL RECOVERY SYSTEM FOR A RAM AIR TURBINE  
In one aspect, a ram air turbine stall recovery system includes a ram air turbine, a hydraulic pump powered by the ram air turbine with the hydraulic pump having a pump inlet and a pump outlet, an...
US20110047960 DUAL-FLOW TURBINE ENGINE FOR AIRCRAFT WITH LOW NOISE EMISSION  
The invention relates to a dual-flow turbine engine for an aircraft with low noise emission, wherein the opening (6) for the cold flow (9) of the turbine engine is provided with short, narrow, and...
US20130219854 AIR-COOLED OIL COOLER FOR TURBOFAN ENGINE  
A turbofan gas turbine engine comprises a nacelle cowl and a core engine. A bypass duct is between an outer surface of a casing of the core engine, and an inner surface of the nacelle cowl. An air...
US20150233252 GAS TURBINE ENGINE AIRFOIL  
An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil...
US20150047315 GAS TURBINE ENGINE FLOW DUCT HAVING INTEGRATED HEAT EXCHANGER  
A gas turbine engine flow duct comprising a flow duct disposed along an engine centerline of the gas turbine engine and defining a stream flow passage, and first and second rows of heat exchangers...
US20140053532 NACELLE SCOOP INLET  
A scoop inlet for use in a gas turbine engine nacelle has a scoop inlet, and a tab extending forwardly of the scoop inlet. The scoop communicates with a downstream flowpath. The tab has at least...
US20140117152 Twin Tip Turbine Propulsors Powered by a Single Gas Turbine Generator  
A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles,...
US20150233251 GAS TURBINE ENGINE AIRFOIL  
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil...
US20120110980 VARIABLE AREA FAN NOZZLE FAN FLUTTER MANAGEMENT SYSTEM  
A system and method of controlling a fan blade flutter characteristic of a gas turbine engine includes adjusting a variable area fan nozzle in response to a neural network.
US20110011058 TURBOFAN ENGINE  
With a turbofan engine the inner sidewall (2) of the bypass duct (3) features, downstream of the flow divider (11), a straight, conically widening form which, downstream of the supports, struts...
US20130340406 FAN STAGGER ANGLE FOR GEARED GAS TURBINE ENGINE  
A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the...
US20130111873 AIRCRAFT TURBOJET ENGINE FAN CASING  
An aircraft turbojet engine fan casing in the form of a box section is provided by the present disclosure. The box section includes a radially interior wall of which is able to form an internal...
US20140202133 GAS TURBINE ENGINE MID TURBINE FRAME WITH FLOW TURNING FEATURES  
A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one...
US20150233323 GAS TURBINE ENGINE AIRFOIL  
A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial...
US20120167549 FLADE DISCHARGE IN 2-D EXHAUST NOZZLE  
An aircraft gas turbine engine has a row of FLADE fan blades disposed radially outwardly of and drivingly connected to a fan in the engine's fan section. The FLADE fan blades extend across a FLADE...
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...
US20110209458 Aircraft gas turbine engine  
The invention refers to an aircraft gas turbine engine including a core engine 1 comprising at least a high pressure turbine 6 and a downstream low pressure turbine 7, a bypass duct 18 surrounding...
US20140174055 TURBINE SECTION OF HIGH BYPASS TURBOFAN  
A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by...
US20120117940 GAS TURBINE ENGINE WITH PYLON MOUNTED ACCESSORY DRIVE  
A gas turbine engine includes an accessory gearbox within an engine pylon. The accessory components may be mounted within the engine pylon to save weight and space within the core nacelle as well...
US20140373927 LOW SHOCK STRENGTH PROPULSION SYSTEM  
A supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine is disclosed herein. A set of aerodynamic vanes may be used to shape a supersonic airflow...
US20150107222 THRUST REVERSER FAN RAMP PARTIALLY FORMED ON AFT END OF FAN CASE  
A fan ramp aerodynamically guides bypass duct air from the aft end of the fan case to the forward end of the cascades. To improve packaging of the thrust reverser assembly, the fan ramp begins on...
US20120096831 GAS TURBINE ENGINE WITH VARIABLE AREA FAN NOZZLE  
A nacelle assembly for a bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The variable area fan nozzle is in...
US20130333350 AIRFOIL INCLUDING ADHESIVELY BONDED SHROUD  
An airfoil includes an airfoil body that extends between a leading edge and a trailing edge, a suction side and a pressure side, and a first end and a second end. At least one fitting is located...
US20110167785 INTERNAL MIXING OF A PORTION OF FAN EXHAUST FLOW AND FULL CORE EXHAUST FLOW IN AIRCRAFT TURBOFAN ENGINES  
An airborne mobile platform that has at least one turbofan engine assembly having a fan driven by a core engine, a short nacelle around the fan and a forward portion of the core engine, and a fan...
US20110138772 TURBINE DETUNER FOR RECOVERING KINETIC ENERGY FROM GAS TURBINE ENGINE EXHAUST GASES  
A gas turbine engine test cell has a turbine detuner capable of recovering kinetic energy from exhaust gases emitted by a gas turbine engine while also detuning the exhaust flow to reduce unwanted...
US20150143794 Geared Turbofan Engine Gearbox Arrangement  
A three-spool turbofan engine (20) has a variable fan nozzle (35). The fan blades have a peak tip radius RT and an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of...
US20100293920 PROPFAN ENGINE  
A propfan engine has a power-producing core, a plurality of nozzles for exhausting exhaust gas from the core, and a row of propeller blades rotatable about an axis. The blades are positioned...
US20110083416 PROPULSION ENGINE  
A propulsion engine (100) for an aircraft, the propulsion engine comprising: one or more fans (110, 120); driving means (132) arranged to drive the one or more fans; and power transfer means (134)...
US20110056183 ULTRA-EFFICIENT PROPULSOR WITH AN AUGMENTOR FAN CIRCUMSCRIBING A TURBOFAN  
An ultra-efficient “green” aircraft propulsor utilizing an augmentor fan is disclosed. A balanced design is provided combining a fuel efficient and low-noise high bypass ratio augmentor fan and a...
US20110030336 COANNULAR DUCTED FAN  
Secondary air flow is provided for a ducted fan having an engine core driving a fan blisk. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and a set of integral...
US20150128562 ENGINE DUCT AND AIRCRAFT ENGINE  
A projecting part is formed on an inner circumferential wall surface of a nacelle so that the projecting part projects inward in a diametral direction and extends from a front edge of each of...
US20130104523 GAS TURBINE ENGINE WITH AUXILIARY FAN  
A propulsion system and a method of operating the propulsion system according to an exemplary aspect of the present disclosure includes powering an auxiliary fan with a gas turbine engine, the...
US20100212285 TURBOPROP PROPULSION UNIT WITH PUSHER PROPELLER  
A turboprop propulsion unit includes at least one pusher propeller 5, 6 driven by an aircraft gas-turbine engine, with the aircraft gas-turbine engine being arranged in front of the pusher...
US20120192543 EXHAUST NOZZLE FOR A BYPASS AIRPLANE TURBOJET HAVING A DEPLOYABLE SECONDARY COVER AND A RETRACTABLE CENTRAL BODY  
The invention relates to an exhaust nozzle for a bypass airplane turbojet comprising an annular central body, an annular primary cover surrounding the central body to define a hot stream flow...
US20130305686 COMBINED TURBOJET AND RAMJET ENGINE  
A combined engine includes a turbopump including a pump injecting hydrogen into a heater arranged in an outer casing downstream from a central body, and a subsonic turbine driving the pump, which...
US20120117939 TURBOSHAFT ENGINE WITH REDUCED NOISE EMISSION FOR AIRCRAFT  
According to the invention, a plurality of embossments (20) having a rectangular section is provided at the inner periphery of the outlet opening (7) of the fan duct (12), said embossments being...
US20130047579 GAS TURBINE ENGINE FAN VARIABLE AREA NOZZLE WITH SWIVABLE INSERT SYSTEM  
An example nacelle assembly for a gas turbine engine includes a nacelle defined about an axis and defining a boundary of a fan bypass flow path. A fan variable area nozzle includes a plurality of...
US20060179818 Jet engine inlet-fan system and design method  
A supersonic aircraft engine axial fan that includes a rotating blade row having blades that receive a supersonic entry flow in the absolute frame and decelerate the flow to a lower supersonic or...
US20120192544 HEATED BOOSTER SPLITTER PLENUM  
A splitter apparatus for a gas turbine engine includes: a splitter including: an annular outer wall which defines a convex-curved leading edge at a forward end thereof; an annular floorplate...
US20140075918 NACELLE LEADING EDGE ELECTRICAL LATCHING SYSTEM  
A nacelle structure for a gas turbine engine includes an outer nacelle surrounding a fan section and defining an outer boundary of a bypass flow passage and an inner nacelle surrounding a core...
US20150113942 Phosphor Thermometer with Two Waveguides  
A phosphor thermometer is disclosed. The phosphor thermometer may comprise a light source configured to emit an excitation light, and an input waveguide configured to transmit at least a portion...
US20140099198 DUCT ASSEMBLY  
A duct for a gas turbine engine system is used to convey exhaust gas and bypass air away from the engine system, towards an exhaust nozzle. The duct includes an inlet face having at least two...
US20130192196 GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION  
A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine...
US20130097997 RAM AIR FAN DIFFUSER  
A diffuser for a ram air fan assembly includes a perforated cone, an inlet ring seal, and an outlet ring seal. The perforated cone has a frustoconical shape symmetrical about an axis of the...
US20140208714 Thermal Management for Gas Turbine Engine  
A gas turbine engine has an inlet duct, which is configured to communicate with an inlet to a compressor. The inlet duct is further configured to communicate air outwardly of an outer casing of...
US20120011826 TURBOJET ENGINE WITH AN ELEMENT OF THE NACELLE ATTACHED TO THE INTERMEDIATE CASING  
The present invention relates to a turbojet engine with a fan (2) and a nacelle element (2) forming the secondary duct downstream of the fan, the turbojet engine comprising an intermediate casing...
US20110138773 DEVICE FOR MOUNTING A FLAME-HOLDER ARM ON AN AFTERBURNER CASING  
A flame-holder device for an afterburner of a turbofan, the turbofan including a first inner annular casing and a second inner annular casing, these defining a passage for a primary flow, and an...
US20090178386 Aircraft Propulsion System  
The invention is a novel aircraft propulsion system architecture that delivers thrust at minimum fuel consumption rates with the side benefits of noise and pollution emission abatement. The...

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