| Patent application number | Description | Published |
|---|
| 20090199536 | PROCESS FOR REVERSING THE THRUST PRODUCED BY A PROPULSION UNIT OF AN AIRCRAFT, DEVICE FOR ITS IMPLEMENTATION, NACELLE EQUIPPED WITH SAID DEVICE - The object of the invention is a process whose purpose is to reduce, cancel or reverse the thrust generated by at least one air flow exiting from a propulsion unit of an aircraft by deflecting at least a portion of the flow that is able to assist the thrust, characterized in that it consists in injecting at the level of the propulsion unit a fluid called a thrust reversal fluid to deflect by an entrainment effect, from the inside of the nacelle toward the outside of the nacelle, at least a portion of the flow that is able to assist the thrust. | 08-13-2009 |
| 20090272842 | DEVICE TO HANDLE AND LOCK A COVER OF AN AIRCRAFT NACELLE - The object of the invention is an aircraft nacelle that comprises, on the inside, an inside pipe ( | 11-05-2009 |
| 20090277155 | NACELLE FOR AIRCRAFT JET ENGINE AND AIRCRAFT INCLUDING SUCH NACELLE - The invention relates to a nacelle, for an aircraft jet engine ( | 11-12-2009 |
| 20090301057 | TURBOREACTOR FOR AIRCRAFT - The invention concerns a turbojet for aircraft including engine located in nacelle, and thermal exchanger intended to cool a fluid participating in the engine propulsive system, characterized in that said thermal exchanger is located on engine external wall, an interstitial space within which air can circulate being arranged between the engine external wall and a lower wall of said thermal exchanger. The invention also concerns an aircraft provided with at least one such turbojet. | 12-10-2009 |
| 20100028139 | TURBOJET FOR AIRCRAFT - A turbojet for an aircraft includes an engine housed in a nacelle and a thermal exchanger that can be traversed by a hot fluid designed to be cooled by thermal exchange with a cold fluid external to the thermal exchanger. The thermal exchanger is disposed in an internal volume of the nacelle, between an internal wall of the nacelle and an external wall of the engine, in such a way as to present two thermal exchange surfaces in the flow of the air stream from the turbojet. The disclosed embodiments also relate to an aircraft equipped with such a jet turbine engine. | 02-04-2010 |
| 20100044503 | JET ENGINE NACELLE FOR AN AIRCRAFT AND AIRCRAFT COMPRISING SUCH A NACELLE - A nacelle for an aircraft high-bypass jet engine, in which a jet engine having a longitudinal axis is mounted, the nacelle including a wall concentrically and at least partially surrounding the jet engine and defining with the latter an annular duct for fluid inner flow, including at the downstream end of the nacelle wall a passage section of a flow outlet. The nacelle includes a displacement mechanism displacing on request a portion of the nacelle wall to modify the passage section of the flow outlet through which a major portion of the flow escapes, the displacement forming in the nacelle wall at least one opening through which a small portion of a leak flow, naturally escapes. The nacelle further includes a fluid device that uses a fluid for compelling the leak flow to flow along the outer face of the portion of the nacelle wall located downstream relative to the at least one opening. | 02-25-2010 |
| 20100071638 | SYSTEM FOR MANAGING THE HEAT FLUXES OF AN AIRCRAFT - A system for managing the heat fluxes of an aircraft including at least one propulsion system that integrates a turbomachine and a cell including at least one fuel tank to supply the turbomachine via a fuel supply circuit, and at least one source of thermal effluents connected to a cell cooling circuit that integrates first elements for ensuring heat transfer between a coolant circulating in the cell cooling circuit and an air flow channeled into at least one cooling air channel extending from at least one air intake up to at least one air exhaust, whereby the system includes second elements for ensuring heat transfer between a coolant circulating in the cell cooling circuit and the fuel, a fuel circuit connecting the at least one tank to the second heat transfer elements, whereby the air intake includes blocking elements that can occupy a first open state for air to pass inside the channel and a second closed state to block the air intake. The fuel circuit includes at least one control valve that orients the fuel either in the direction of the tank or of the circuit designed for the propulsion system. | 03-25-2010 |
| 20100107648 | Method and System for Starting a Turboshaft Engine by Cold Weather - According to the invention, when starting a turboshaft engine ( | 05-06-2010 |
| 20100212857 | SYSTEM FOR COOLING AND ADJUSTING THE TEMPERATURE OF APPARATUSES IN THE PROPULSION ASSEMBLY OF AN AIRCRAFT - A system for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft, that includes first means for heat exchange between lubrication circuits of at least two of the aforementioned apparatuses and a heat-carrier fluid contained in a closed circuit, a second means for heat exchange between the heat-carrier fluid and at least one coolant, the first heat exchange means being arranged locally at each of the aforementioned apparatuses, the second heat exchange means being remote from the aforementioned first means, the closed circuit extending between at least two of the aforementioned apparatuses and the aforementioned second means. | 08-26-2010 |
| 20100288244 | METHOD FOR CONTROLLING THERMAL EFFLUENTS GENERATED BY AN AIRCRAFT AND COOLING DEVICE FOR AN AIRCRAFT IMPLEMENTING SAID METHOD - A process for management of thermal effluents of an aircraft that includes an airframe ( | 11-18-2010 |
| 20100300066 | TURBOJET ENGINE FOR AIRCRAFT - A turbojet engine for an aircraft that includes an engine provided in a nacelle and at least one heat exchanger for cooling down a hot fluid collected in the propulsion system of the turbojet engine before re-injecting the aforementioned partially-cooled hot flow into the aforementioned propulsion system, wherein at least one heat exchanger is a radial heat exchanger extending in the lower portion of the turbojet engine at a lower branching of the turbojet engine. | 12-02-2010 |
| 20110155846 | ANCILLARY DEVICE WITH AN AIR TURBINE FOR TAXIING AN AIRCRAFT ON THE GROUND - Device for driving at least one wheel of an aircraft landing gear, which includes at least one turbine machine incorporated into the landing gear of the aircraft. Advantageously, the turbine machine is a pneumatic turbine. | 06-30-2011 |
