Patent application number | Description | Published |
20080199308 | AIR TAPPING CIRCUIT ARRANGEMENT, A COMPRESSOR STAGE COMPRISING SAME, THE COMPRESSOR COMPRISING SAME AND A TURBOJET COMPRISING SAME - In a compressor stage ( | 08-21-2008 |
20080202094 | AEROENGINE FITTED WITH HEAT EXCHANGER MEANS - The invention relates to an aeroengine comprising:
| 08-28-2008 |
20080226458 | TURBOMACHINE FAN - A turbomachine fan ( | 09-18-2008 |
20080232969 | ROTARY ASSEMBLY FOR A TURBOMACHINE FAN - A rotary assembly for a turbomachine fan comprises: a disk rotatable about an axis; a plurality of blades fastened by their roots to said disk and extending radially outwards from said disk; and a plurality of inter-blade platforms, each extending between two adjacent blades and defining the inner profile for the flow section of the fluid passing through the fan. On their facing side faces, these adjacent blades present slides between which said platform can slide, these slides limiting outward radial movement of said platform. | 09-25-2008 |
20080236133 | TURBOMACHINE FRONT PORTION COMPRISING A DEFLECTOR SYSTEM FOR DEFLECTING FOREIGN BODIES, SUCH AS HAILSTONES - The present invention relates to a turbomachine front portion ( | 10-02-2008 |
20080289315 | SYSTEM FOR DISSIPATING ENERGY IN THE EVENT OF A TURBINE SHAFT BREAKING IN A GAS TURBINE ENGINE - The present invention relates to a device for, in a gas turbine engine, braking a turbine comprising a rotor, having at least one disk ( | 11-27-2008 |
20090049841 | GAS TURBINE ENGINE WITH A MEANS OF DRIVING THE ACCESSORY GEAR BOX, AND METHOD OF FITTING SAID ENGINE - The invention relates to a twin-spool gas turbine engine comprising a high-pressure rotor (and a low-pressure rotor, which rotors are mounted in bearings supported by an intermediate casing, at least one accessory gear box, a drive means, driving radial and coaxial shafts for transmitting movement to the accessory gear box, the drive means comprising a high-pressure drive gear driving one of said radial shafts and connected to the high-pressure rotor, a low-pressure drive gear connected to the low-pressure rotor upstream of the high-pressure rotor and driving the other of said radial shafts, the low-pressure drive gear being supported in the intermediate casing by an axial-positioning bearing. | 02-26-2009 |
20090056302 | COMPONENT VENTILATION AND PRESSURIZATION IN A TURBOMACHINE - A dual-flow turbomachine ( | 03-05-2009 |
20090058089 | ELECTRICITY GENERATION IN A TURBOMACHINE - A turbomachine comprising at least one Stirling cycle thermal engine which is mounted at the end of a radial arm ( | 03-05-2009 |
20090123269 | DEVICE FOR DETECTING BREAKAGE OF A TURBOMACHINE SHAFT - The present invention relates to detecting breakage of a shaft of a turbomachine, in particular of the aviation type. The invention relates in particular to a device designed to perform such detection. According to the invention, the device for detecting breakage of a turbomachine shaft comprises:
| 05-14-2009 |
20090126336 | SYSTEM PROVIDING BRAKING IN A GAS TURBINE ENGINE IN THE EVENT OF THE TURBINE SHAFT BREAKING - The present invention relates to a device for, in a gas turbine engine, braking a turbine comprising a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking. The device is one which comprises a first braking member ( | 05-21-2009 |
20090185768 | TURBOMACHINE SHAFT GUIDANCE - A support for a bearing that guides a shaft in a turbomachine, comprising an annular part made of a shape memory material which retains an initial shape when the load applied to it remains below a threshold value and which deforms, absorbing energy when the applied load becomes at least equal to the threshold value, this annular part being capable of reverting at least approximately to its initial shape when the applied load drops back below the threshold value. | 07-23-2009 |
20090191046 | DEOILING DEVICE AND TURBOMACHINE COMPRISING THIS DEVICE - The invention relates to a deoiling device. It comprises a tube ( | 07-30-2009 |
20090282679 | CENTERING A PART INSIDE A SHAFT - A device for centering a tube inside a hollow shaft, the device comprising deformable means interposed between the tube and the hollow shaft and including bearing members for bearing against the inside surface of the shaft and suitable for being spaced away from the inside surface of the shaft in order to enable them to be moved inside the shaft, the deformable means being made of a shape-memory material suitable for deforming to press the bearing members against the inside surface of the shaft or to space them away therefrom on being subjected to a predetermined temperature. | 11-19-2009 |
20090297083 | DEVICE FOR THE AXIAL LOCKING OF A GUIDE SHAFT BEARING IN A TURBOMACHINE - Guide shaft bearing comprising an internal ring mounted on a cylindrical contact surface of a shaft and means for the axial locking of the ring comprising a ring mounted sliding on the cylindrical contact surface and an annular rib made of shape memory material mounted in two annular grooves of the cylindrical contact surface and of the ring, the annular rib being able to expand radially by shape memory effect when it is subjected to a temperature greater than a transition temperature of its material to pass to a locking position of the ring on the cylindrical contact surface. | 12-03-2009 |
20090304495 | DEVICE FOR SUPPLYING VENTILATION AIR TO THE LOW PRESSURE BLADES OF A GAS TURBINE ENGINE - The present invention relates to a device for supplying ventilation air to a turbine rotor of a gas turbine engine comprising a first and a second turbine disk ( | 12-10-2009 |
20090309432 | TURBOMACHINE WITH INTEGRAL GENERATOR/STARTER - A turbomachine such as an aircraft turbojet including an electrical generator/starter that can be mounted and dismounted by axial translation in an upstream enclosure of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables which extend inside the structural arms of the intermediate casing of the turbomachine. | 12-17-2009 |
20100047059 | BYPASS TURBOJET - The invention relates to a bypass turbojet engine comprising an outer fan duct and an inner fan duct (IFD), between which the secondary flow passes, and a high pressure compressor having an outer casing. In characteristic manner, the IFD is fastened on the outer casing. The invention is applicable to a turbojet engine having a high pressure compressor of the axial-centrifugal type. | 02-25-2010 |
20110073717 | AIRCRAFT WITH A HYBRID ENERGY SUPPLY - An aircraft with a hybrid power supply, the aircraft comprising:
| 03-31-2011 |
20110273724 | DEVICE FOR MEASURING THE TWIST OF A ROTATING SHAFT - Measuring the twist of a rotating shaft by means of a laser beam and polarizing filters. The measurement device includes a laser beam generator, two polarizing filters secured to the shaft and spaced apart from each other, and a laser radiation receiver receiving the laser beam after it has passed through both filters. | 11-10-2011 |
20110311349 | ROTOR ELEMENT WITH A FLUID PASSAGE AND PASSAGE-BLOCKING MEMBER AND TURBINE ENGINE INCLUDING THE ROTOR ELEMENT - A rotor element including an annular surface portion about the rotor rotational axis, a fluid passage being formed through the surface portion, a passage-blocking mechanism including a blocking element that is deformable depending on the rotor rotating speed and arranged so as to adjust the fluid flow depending on the rotor rotating speed, and an annular collar with a free edge engaging with the blocking element so as to form the blocking mechanism. The free edge of the annular collar defines, together with the blocking portion of the blocking element, a diaphragm that blocks the fluid passage. | 12-22-2011 |
20120055137 | FAN BLADES WITH CYCLIC SETTING - A fan portion of a dual flow turbojet engine including a plurality of fan blades, a disk supporting the blades and configured to be rotated relative to a stator portion of the fan, along a longitudinal axis of the fan, and a system for setting the angle of attack associated with each fan blade, the systems configured such that the angle of attack of each blade varies according to a same setting law according to the angular position of the blade relative to the stator portion, along the longitudinal axis, the same setting law being periodic with a period of P=360°/n, where n is an integer at least equal to 1. | 03-08-2012 |
20140105727 | MEASUREMENT INSTALLATION FOR BLADE FAILURE TESTING IN A TURBOMACHINE - Turbomachine fitted with a device for gathering the information recorded during operation of the former by a strain gauge positioned on a fan blade borne by a fan disc of said turbomachine, said device comprising a hollow cylindrical pipe positioned inside one of the rotating shafts of said turbomachine in order to guide at least one wire for transmitting this information, characterized in that said device further comprises a part for attaching said pipe to said rotating shaft. | 04-17-2014 |
20140123726 | DEVICE FOR CLASSIFYING STRAIN GAUGES - A device for classifying strain gauges includes a holder capable of receiving strain gauges and capable of being rotated by a rotating device, the holder being connected to the rotating device by a linking device; and a heater capable of heating the holder and arranged about the mounting, the linking device including a cooling device capable of limiting the heating of the rotating device. | 05-08-2014 |
20140307992 | INSTALLATION OF CALIBRATION GAUGE FOR MEASURING CONSTRAINTS - An installation for calibration of a stress gauge for an external bearing block of a turbomachine roller bearing, the bearing block including a radially internal roller bearing race. The installation includes a support table on which the bearing block is attached; an internal roller bearing ring mounted coaxial with the bearing block; a drive shaft driving the ring. The installation also includes a device for applying an axial stress to the bearing block including a support drum on which the internal ring is removably fixed and a connection with the device for applying the axial stress. | 10-16-2014 |