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US20110120076 STRUCTURE FOR AN AIR INLET LIP OF AN ELECTRIC DE-ICING POD COMPRISING AN ACOUSTIC ATTENUATION ZONE  
The present invention relates to a structure (7) for a lip (4a) of an air inlet (4) of a turbojet pod (1) comprising an outer skin (12), designed to be oriented towards the outside of the lip, and...
US20110277443 ELECTRIC DE-ICING DEVICE AND RELATED MONITORING SYSTEM  
The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source (3) and...
US20120017564 SUPERCONDUCTIVE HEAT TRANSFER SYSTEM  
A system, including a superconductive heat transfer assembly, including, a first superconductive heat transfer pipe, a second superconductive heat transfer pipe, and a superconductive heat...
US20110005188 AIR INTAKE LIP FOR TURBOJET NACELLE  
The invention relates to a lip that includes, on the inner surface thereof, an electric de-icing device (11) comprising at least one panel including a cellular structure (13), made of electrically...
US20120036827 ROTATING INLET COWL FOR A TURBINE ENGINE, COMPRISING AN ECCENTRIC FORWARD END  
A rotating inlet cowl for a turbine engine, having a rotation axis and for which the forward end is arranged to be eccentric relative to this rotation axis. Furthermore, a forward cone of the cowl...
US20110247313 SYSTEM FOR HEATING AN AIRSTREAM BY RECIRCULATING WASTE HEAT OF A TURBOMACHINE  
An embodiment of the present invention takes the form of an application and process that incorporates a waste heat source to increase the temperature of the airstream entering an inlet section of...
US20090020647 SYSTEM FOR DEICING AN AIR INLET COWL FOR A TURBINE ENGINE  
According to the invention, a scaled articulation device (27) is mounted on at least one (14) of the branches (14; 18, 9) of said hot-air circulation circuit in the form of a bracket so as to...
US20100319358 Nosecone ice protection system for a gas turbine engine  
A system includes a first anti-icing electrothermal heater located at tip of a gas turbine engine nosecone, and a plurality of anti-icing electrothermal heater strips extending rearward from the...
US20130247541 GAS TURBINE INTAKE ANTI-ICING DEVICE  
The gas turbine intake anti-icing device is used for a gas turbine electric power generation system (1) having a gas turbine (2) and a power generator (20) coupled to the gas turbine (2) and...
US20140008497 APPARTUS AND METHOD FOR PREVENTING GAS TURBINE ENGINE FREEZING  
A system for reducing moisture in a gas turbine engine with one or more air ducts includes one or more one or more covers, each with an outer face and an inner face, with the inner face...
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...
US20120036826 ENGINE AND POD ASSEMBLY FOR AN AIRCRAFT, EQUIPPED WITH AN ANTI-ICING DEVICE  
An engine and pod assembly for an aircraft includes a pod receiving an engine having an air intake. A rotating nose cone extends on the nose cone, as well as a device for limiting the formation of...
US20130099944 FLUID PRESSURE BASED ICING DETECTION FOR A TURBINE ENGINE  
An icing detection subsystem for an aircraft turbine engine is presented. The icing detection subsystem includes a plurality of air pressure sampling ports formed within structure that surrounds a...
US20150166194 HELICOPTER ENGINE AIR INTAKE WITH INCREASED BYPASS FLOW  
A helicopter engine air intake including an anti-icing grid that provides a large bypass flow in event of icing. The air intake includes air intake lips and an anti-icing grid mounted on outer...
US20110011056 PIEZOELECTRIC DE-ICING OF AN AIR INLET  
The invention relates to a lip assembly (1) for the air inlet of a turbojet engine nacelle, that comprises an inner surface (9), an outer surface (11) and de-icing means, wherein the de-icing...
US20110167781 TURBOMACHINE NACELLE AND ANTI-ICING SYSTEM AND METHOD THEREFOR  
An anti-icing system and method for an aircraft engine nacelle. The nacelle has an inlet lip that defines a leading edge of the nacelle and has a cross-sectional shape and oppositely-disposed...
US20090060707 COMPRESSOR INLET GUIDE VANE DE-ICE CONTROL SYSTEM AND METHOD  
A system and method are provided for effectively removing ice that may have formed on gas turbine engine compressor inlet guide vanes and/or preventing, or at least inhibiting, reformation of ice...
US20140165531 HEATED RIGID ELECTRICAL SYSTEM  
A rigid electrical raft has electrical conductors embedded in a rigid material. The electrical conductors transmit electrical signals through the rigid electrical raft, which may form part of an...
US20140102113 EXHAUST HEAT RECOVERY FOR A GAS TURBINE SYSTEM  
A system includes a gas turbine and an anti-icing system coupled to the gas turbine. The gas turbine is configured to receive air and fuel and to combust a mixture of the air and the fuel into...
US20110162340 METHOD FOR MAKING A NACELLE DE-ICING ELEMENT  
The invention relates to a method for making a nacelle element (2) that includes the steps of: (A) forming an array of heating resistors on a substrate using a photolithographic method; (B)...
US20130192247 GAS TURBINE ENGINE VARIABLE AREA FAN NOZZLE WITH ICE MANAGEMENT  
A method of managing a gas turbine engine variable area fan nozzle includes the steps of evaluating an icing condition to determine the likelihood of ice presence. A variable area fan nozzle...
US20130180227 Fastening element and de-icing device of an aircraft gas-turbine engine  
The present invention relates to a fastening element, in particular to its use in a de-icing device of an aircraft gas-turbine engine, for connecting two components, with the fastening element...
US20060101802 Air intake appliance for an aircraft engine  
The invention relates to an air intake appliance for an aircraft engine. At least one channel wall (1) of the air intake appliance (20) is provided on at least a part of its inner surface with...
US20140345292 RETURN FLUID AIR COOLER SYSTEM FOR TURBINE COOLING WITH OPTIONAL POWER EXTRACTION  
In an aircraft including a gas turbine engine, a system for cooling the gas turbine engine includes a tank provided in a wing of the aircraft, the tank being configured to store a cooling fluid...
US20120241561 METHOD AND APPARATUS FOR PROTECTING AIRCRAFT AND AIRCRAFT ENGINES AGAINST ICING  
An aircraft engine generates engine power by burning hydrocarbon fuel such as Jet-A. A minute quantity of the fuel is burned in such a manner as to generate no engine power, and the heat generated...
US20140077039 Heated Screen For Air Intake Of Aircraft Engines  
An aircraft includes a fuselage and wings mounted on opposite sides of the fuselage for sustained forward flight. An engine is mounted in the fuselage or at least one of the wings and includes an...
US20100043390 CONTROLLING ICE BUILDUP ON AIRCRAFT ENGINE AND NACELLE STATIC AND ROTATING COMPONENTS  
A turbofan engine deicing system includes a core nacelle (12) housing a turbine. A turbofan (20) is arranged upstream from the core nacelle. A controller (50) manipulates the turbofan in response...
US20150033698 ANTI-ICING SYSTEM FOR A GAS TURBINE  
A system includes a gas turbine system that has a turbine, a combustor, and a compressor having an air intake. The air intake is configured to supply an air flow to the compressor. The system also...
US20130219916 APPARATUS AND METHOD FOR CONDITIONING AIR RECEIVED BY A POWER GENERATION SYSTEM  
According to one aspect of the invention, a method for conditioning air received by a power generation system includes flowing ventilation air through a turbine system to control a temperature of...
US20150198061 AIRCRAFT ANTI-ICING SYSTEMS HAVING DEFLECTOR VANES  
Apparatus and methods to lower peak temperatures and improve performance of aircraft anti-icing systems are described herein. One described example apparatus includes a skin on an inlet side of a...
US20120240593 FUEL SYSTEM FOR GAS TURBINE ENGINE  
A method and apparatus for heating fuel in an aircraft gas turbine engine, for example to provide fuel anti-icing to the fuel, comprises directing a fuel flow through a heat exchanger associated...
US20100064660 JET ENGINE NACELLE MEMBER  
The invention relates to an nacelle member (1) comprising at least one mobile cowling (2) pivotally or slidably mounted in an essentially longitudinal direction of the nacelle, capable of...
US20090241509 TURBINE ENGINE INLET STRUT DEICING  
A gas turbine engine is disclosed that includes an inlet case having circumferentially spaced, radially extending inlet struts. Each inlet strut has a leading and trailing end. Spaced apart...
US20080302081 Method for detecting ice ingestion in a gas turbine engine  
A method of detecting an ice shedding event in a gas turbine engine, the engine having a rotor comprising a compressor drivingly connected via a shaft to a turbine; the method for detecting an ice...
US20080279688 HEATED ENGINE NOSE CONE USING SPIRAL CHANNELS  
A nose cone of a turbomachine, such as an aircraft engine, is heated to prevent ice formation. The nose cone is configured as a conical shell positioned concentrically over an inner shell with a...
US20090260341 Distributed zoning for engine inlet ice protection  
An engine inlet ice protection system and method for ice protection includes a plurality of grouped structural elements having electrical components that provide ice protection where power is...
US20130019608 METHOD OF INHIBITING ICE ACCRETION WITHIN A TURBINE ENGINE AND CONTROL SYSTEM THEREFOR  
A method of inhibiting ice accretion within a turbine engine 4, 6, comprising the steps: (a) operating the turbine engine 4, 6 at a predetermined engine speed; and (b) driving the compressor 8, 10...
US20090272850 ICE SHED REDUCTION FOR LEADING EDGE STRUCTURES  
A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner...
US20130239542 STRUCTURES AND METHODS FOR INTERCOOLING AIRCRAFT GAS TURBINE ENGINES  
A turbine engine has a fan comprising a duct and supporting struts, a first compressor configured to pressurize inlet air, and a second compressor configured to further pressurize the inlet air. A...
US20100101206 DEVICE FOR DE-ICING THE AIR INTAKE OF A GAS TURBINE  
A de-icer device for de-icing an air inlet of a gas turbine, such as a helicopter turbine engine. The de-icer device includes an essentially metallic enclosure for admitting air into the engine,...
US20100107594 TURBINE INTEGRATED BLEED SYSTEM AND METHOD FOR A GAS TURBINE ENGINE  
A bleed system for a gas turbine engine includes: (a) a bleed air turbine having a turbine inlet adapted to be coupled to a source of compressor bleed air at a first pressure; (b) a bleed air...
US20110179764 TURBO-ENGINE COMPRESSOR TIP COMPRISING DE-ICING MEANS  
The de-icing system comprises a flexible bladder (5) filled with de-icing fluid, pressed by the centrifugal forces produced when the rotor tip (1) is rotating against the inner wall thereof to...
US20130340439 Systems and Methods for De-Icing a Gas Turbine Engine Inlet Screen and Dehumidifying Inlet Air Filters  
A system for de-icing a gas turbine engine is provided. A manifold is coupled to an inlet screen. A first conduit is coupled to a stage of the compressor and a first input of a mixing component. A...
US20120240594 METHOD AND APPARATUS FOR PROTECTING AIRCRAFT ENGINES AGAINST ICING  
An aircraft engine generates engine power by burning hydrocarbon fuel such as Jet-A. A minute quantity of the fuel is burned in such a manner as to generate no engine power, and the heat generated...
US20080307769 GAS TURBINE ENGINE ANTI-ICE FORMATION DEVICE AND SYSTEM  
An anti-ice formation device for a gas turbine engine is configured to be mounted within an inlet duct of the engine, and adjacent the gas turbine engine compressor inlet. The device is configured...
US20140144124 Gas Turbine Anti-Icing System  
Embodiments of the present disclosure are directed towards a system that includes a recirculation system. The recirculation system includes a compressor discharge air line extending from a...
US20110225975 METHOD FOR CONTROLLING AN ELECTRICAL DEICING SYSTEM  
The present invention relates to a method for commanding and controlling at least one resistive heating element (1) belonging to an aircraft turbojet engine nacelle deicing set, characterized in...
US20110179765 Jet engine shield and deicer  
A shield or protective grille assembly constructed of non-corrosive and heat conductive metal members (10, 12 & 14), conforming to the configurations shown on the drawings, said assembly design...
US20120255274 FLOW DEVICE AND METHOD AND SYSTEM USING THE FLOW DEVICE  
A flow device adapted to operate as a restrictor as well as provide a pressure relief capability in the event of an over-pressurization event within a fluid system containing the device. The flow...
US20070234704 Methods and apparatus for operating gas turbine engines  
A method for assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method includes coupling a manifold to the gas turbine engine...

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