Patent application number | Description | Published |
20130098066 | TURBINE ENGINE COMPRISING A CONTRAROTATING PROPELLER RECEIVER SUPPORTED BY A STRUCTURAL CASING ATTACHED TO THE INTERMEDIATE HOUSING - The present invention relates to an open rotor type aircraft turbine engine ( | 04-25-2013 |
20130101419 | TURBOMACHINE BLADE INCIDENCE CONTROL SYSTEM AND TURBOMACHINE - Turbomachine blade incidence control system including a fluidic cylinder with a first and a second chamber and having a pressurized fluid network adapted to selectively supply pressurized fluid to the first and/or the second chamber, the fluid network having one fluid routing device having a first normal position and a second protection position. The fluidic cylinder includes a fluid inlet positioned to be in fluid communication with the first chamber when the fluidic cylinder is in the blocked position, the routing device being adapted to set up a fluid communication between the inlet and the second chamber when it is in the protection position and to inhibit the fluid supply to the inlet when it is in the normal position. | 04-25-2013 |
20130111873 | 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 skin of a cold air flow duct of a nacelle in which said turbojet engine is intended to be mounted, and a radially exterior wall of which is able to form an external skin of said nacelle, the box forming a module forming an entire thickness of the nacelle, and placed between an upstream portion of the nacelle, forming the air intake, and a downstream casing portion, on which a cascade edge of a thrust reverser can be fixed. | 05-09-2013 |
20130115055 | SYSTEM FOR CONTROLLING A PNEUMATIC VALVE OF A TURBINE ENGINE | 05-09-2013 |
20130121814 | TURBOJET ENGINE NACELLE - A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure. | 05-16-2013 |
20130136575 | METHOD FOR MONITORING THE CLEARANCE OF A KINEMATIC LINK BETWEEN A CONTROL MEMBER AND A RECEIVING MEMBER - The method consists, based on an operating parameter of the turbojet engine, in: | 05-30-2013 |
20130139520 | METHOD FOR MONITORING A CONTROL DEVICE OF A FUEL METERING VALVE OF A TURBOJET ENGINE - A method for monitoring a control device of a fuel metering valve of an aircraft turbojet engine, the control device supplying a control current) to a servo valve in order to modify the position of the fuel metering valve, the method comprising:
| 06-06-2013 |
20130142668 | COOLED TURBINE BLADE FOR GAS TURBINE ENGINE - A cooled turbine blade for a gas turbine engine including a pressure surface wall, a suction surface wall and a distal wall connecting the pressure surface wall and the suction surface wall, arranged so as to create in the region of the distal end of the blade at least one external cavity forming a bathtub-shaped cavity and at least one internal cavity separated by the distal wall, the blade having at least one opening for the introduction of a flow of cooling air into the external cavity, wherein, on the one hand, at least one part of the distal wall is inclined relative to the verticals of the pressure surface wall and, on the other hand, the opening is created in the vicinity of the distal wall so that the flow of cooling air is directed towards the distal end of the pressure surface wall. | 06-06-2013 |
20130179097 | METHOD FOR MONITORING A MEASURING CHAIN OF A TURBOJET ENGINE - A method for monitoring a measuring chain of an aircraft turbojet engine, the measuring chain including at least two replicated channels for measuring a variable of the turbojet engine, the method including a step for measuring the position of a fuel metering valve of the turbojet engine during the flight of the aircraft and a step for normalizing the deterioration indicator according to the position of the fuel metering valve. | 07-11-2013 |
20130183142 | ARRANGEMENT FOR THE GUIDING OF THE FLOW OF A LIQUID IN RELATION TO THE ROTOR OF A TURBOMACHINE - An arrangement for the guiding of the flow of a liquid in relation to the rotor of a turbomachine, which includes an intermediary disc and a downstream disc of which the internal diameter and the axial position of the discs are defined in such a way that the tank is arranged inside the discs. The rotor supports a guide flange with an element of revolution of which the diameter of the section increases in the downstream direction, according to the direction of flow of the gases in the turbomachine. The downstream axial end of the flange is fixed to a portion of the rotor located downstream of the downstream disc and the upstream axial end of the flange is connected to the internal radial end of the intermediate disc. | 07-18-2013 |
20130186096 | METHOD FOR MONITORING A FUEL CIRCUIT SHUT-OFF VALVE - The invention relates to a method for monitoring the operation of a fuel circuit shut-off valve comprising an LPSOV, a flow regulator, the shut-off valve, characterised in that it comprises:
| 07-25-2013 |
20130197747 | SYSTEM FOR DETECTING AN IMPACT ON AN AIRCRAFT ENGINE IMPELLER WHEEL - The invention relates to a method and a system for detecting an impact on an impeller wheel ( | 08-01-2013 |
20130202430 | GAS TURBINE ENGINE FAN CASING HAVING A FLANGE FOR FASTENING PIECES OF EQUIPMENT - The invention provides a fan casing for a gas turbine engine, the casing having a substantially cylindrical portion that terminates at one end in an annular flange made of composite material. The flange includes at least one setback in a fraction of its thickness and at least one bolt for fastening pieces of equipment passing right through the flange in the axial direction, the bolt for fastening pieces of equipment having a head that presents a flat that is to bear flat against a rim of the setback, and a shank forming a stud for fastening pieces of equipment on the casing. | 08-08-2013 |
20130202449 | AXISYMMETRIC PART FOR AN AVIATION TURBINE ENGINE ROTOR - A link part for a turbine engine, in particular such as a turbojet, the link part being mounted between a fan cone and a fan disk supporting fan blades, the link part having an annular wall pierced by a plurality of orifices, each for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface that provides an aerodynamic extension of the fan between an outer surface of the fan cone and an outer surface of a fan blade platform, the annular wall being made of a first material that is composite and is provided on an inner surface of the rim with a ring made of a second material that is different from the first and that is suitable for radially retaining the fan blade platform. | 08-08-2013 |