| Techspace Aero S.A. Patent applications |
| Patent application number | Title | Published |
|---|
| 20120134787 | Abradable For Stator Inner Shroud - The present invention relates to a pressure seal ( | 05-31-2012 |
| 20120130617 | METHOD FOR MONITORING THE OIL SYSTEM OF A TURBOMACHINE - The present invention relates to an overall monitoring method allowing to calculate the autonomy of a lubrication system of an airplane engine and also allowing the diagnosis and prognosis of a plurality of problems and breakdowns of the engine and of its lubrication system by means of measurements taken by sensors arranged in said lubrication system, the method comprising the step of calculating the status of the lubrication system at a given moment and calculating its evolution over time in order to determine the remaining lifetime before a breakdown. | 05-24-2012 |
| 20120128466 | ADVANCED AIR AND OIL CIRCUIT ARCHITECTURE FOR TURBOMACHINE - The present invention relates to a system for lubricating a turbomachine comprising at least one enclosure, called non-ventilated, with members to be lubricated and an air-oil mixture, said enclosure being closed and pressurized using dynamic pressure seals supplied with compressed air to create an airflow from the outside toward the inside of the enclosure, said enclosure comprising an outlet for conveying the air-oil mixture toward an air/oil separator, said separator being provided with an suction function favoring the flow of the air-oil mixture between the enclosure and the separator, characterized in that the lubrication system comprises additional suction means. | 05-24-2012 |
| 20110318185 | Lightened Axial Compressor Rotor - The present invention relates to a rotor stage of a compressor drum ( | 12-29-2011 |
| 20110318174 | Compressor Rectifier Architecture - The present invention relates to a turbomachine rectifier comprising a plurality of stator vanes ( | 12-29-2011 |
| 20110243752 | METHOD FOR MANUFACTURING A RECTIFIER - The present invention relates to a method for manufacturing a turbine-engine composite rectifier comprising a ferrule provided with a plurality of stator vanes ( | 10-06-2011 |
| 20110150643 | Architecture of a Compressor Rectifier - The present invention relates to a turbine engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support | 06-23-2011 |
| 20110079378 | METHOD FOR MANUFACTURING A HEAT EXCHANGER AND EXCHANGER OBTAINED BY THE METHOD - The present invention relates to a method for manufacturing an air/fluid heat exchanger ( | 04-07-2011 |
| 20100322776 | Method for Manufacturing Braided Preforms - The present invention relates to an automatic method for manufacturing a stator or rotor blade preform for a turbine engine, comprising at least the following successive steps:
| 12-23-2010 |
| 20100322763 | METHOD FOR MANUFACTURING VANES INTEGRATED INTO A RING AND RECTIFIER BY THE METHOD - The present invention relates to a method for manufacturing a turbomachine rectifier comprising an outer ring ( | 12-23-2010 |
| 20100213010 | Automatic Shut-Off Valve For The Oil Circuit In An Airplane Engine - The present invention concerns a lubrication system in a closed circuit provided with a valve comprising a first position and a second position, as well as an IN inlet, a first BP outlet and a second M outlet, said IN inlet being connected to the outlet of the feed pump, the first BP outlet being connected to the bypass circuit and the second M outlet being connected to the feed circuit. In the first position of the valve, the flow entering via the IN inlet is diverted to the first BP outlet and in the second position, the incoming flow is diverted to the second M outlet, said valve switching from the first position to the second position and vice versa, when the incoming flow rate exceeds a predetermined threshold upwards and downwards respectively. | 08-26-2010 |
| 20100162889 | Combined Pumping And Separating Machine For The Oil Circuit Of A Turbojet - The present invention relates to a combined machine for pumping and separating into two distinct and purified phases a two-phase liquid/gas mixture or fluid, preferably oil/air, entering the machine, comprising means for the suction, pumping and partial separation of the two-phase fluid, means for drying and extracting the separated gas and means for degassing and forcing back the separated liquid, comprising at least three physically separated stages (A,B,C) intended to be activated by a means that is internal or external to the machine, and built into a single casing:
| 07-01-2010 |
| 20100159762 | Manufacture of Complex Composite Parts - The present invention relates to an automated method for manufacturing layer by layer a composite part with rotational symmetry and complex cross-section, comprising the following stages:
| 06-24-2010 |
| 20100158685 | Guide Vane Architecture - Guide vane stage of a turbine engine comprising a series of fixed blades connecting an inner collar to an outer collar, characterised in that said fixed blades comprise attachment platforms with flat surfaces that co-operate with a plurality of juxtaposed flat facets, said flat facets being located on the inner face of the outer collar in order to ensure attachment with a contact of a flat/flat type between the fixed blades and the outer collar. | 06-24-2010 |
| 20090159246 | Heat Exchange System In A Turbomachine - The present invention relates to a heat exchange system in a turbine engine comprising a number of units and equipment ( | 06-25-2009 |
| 20090159139 | Recirculation Valve In An Aircraft Engine - The present invention relates to an installation for lubricating and/or cooling in an aircraft engine comprising an oil tank ( | 06-25-2009 |
| 20080264726 | Isolation Valve For The Oil Circuit Of An Airplane Engine - The present invention relates to a turbomachine comprising an air compressor ( | 10-30-2008 |
