Patent application number | Description | Published |
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 |
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 |
20090165995 | AIR-OIL HEAT EXCHANGER PLACED AT THE LOCATION OF THE AIR SEPARATOR NOSE OF A TURBOJET, AND A TURBOJET INCLUDING SUCH AN AIR-OIL HEAT EXCHANGER - The invention relates to an air-oil heat exchanger located at the inner shroud of the secondary duct of a turbojet. In characteristic manner, it comprises an oil circuit placed inside the separator nose and fins placed outside the top wall of the separator nose, between the leading edge of the separator nose and the outlet guide vanes. | 07-02-2009 |
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 |
20110150634 | Integration of an Air-Liquid Heat Exchanger on an Engine - A bypass axial turbomachine includes a fan, a low pressure stator stage, a high pressure stator stage, the compressors being traversed by a flow referred to as primary flow of the turbomachine, at least one passage of discharge flow rate controlled from the primary flow in one of the stator stages toward the secondary flow, a heat exchanger of the surface air-oil (ACOC) type arranged flat on or in the wall surrounding the stator stages and defining the internal surface of the secondary flow, directly downstream of the junction of the passage of the discharge flow rate with said wall, so as to be run through by the secondary flow enriched with the discharge flow rate. | 06-23-2011 |
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 |
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 |
20120168115 | INTEGRATION OF A SURFACE HEAT-EXCHANGER WITH REGULATED AIR FLOW IN AN AIRPLANE ENGINE - The present invention relates to a surface air-cooled oil cooler ( | 07-05-2012 |