Patent application number | Description | Published |
20080245053 | GAS TURBINE ENGINE DIFFUSER AND COMBUSTION CHAMBER AND GAS TURBINE ENGINE COMPRISING SAME - The present invention relates to a gas turbine engine diffuser ( | 10-09-2008 |
20090019856 | CHAMBER-BOTTOM BAFFLE, COMBUSTION CHAMBER COMPRISING SAME AND GAS TURBINE ENGINE FITTED THEREWITH - The present invention relates to a baffle ( | 01-22-2009 |
20090047127 | TURBOMACHINE DIFFUSER - A turbomachine comprising:
| 02-19-2009 |
20090056337 | TURBOMACHINE WITH ANNULAR COMBUSTION CHAMBER - Turbomachine with an annular combustion chamber ( | 03-05-2009 |
20090100839 | COMBUSTION CHAMBER WALL WITH OPTIMIZED DILUTION AND COOLING, AND COMBUSTION CHAMBER AND TURBOMACHINE BOTH PROVIDED THEREWITH - The invention applies to the field of turbomachines and relates to a combustion chamber in which the supply of dilution air and cooling air is optimized. The invention is concerned more particularly with optimizing the position of the dilution holes present on the walls of the combustion chamber. | 04-23-2009 |
20090100840 | COMBUSTION CHAMBER WITH OPTIMISED DILUTION AND TURBOMACHINE PROVIDED WITH SAME - The invention relates to the field of turbomachines and concerns a combustion chamber ( | 04-23-2009 |
20100043449 | DEVICE FOR ATTACHING A COMBUSTION CHAMBER - Turbomachine comprising an annular combustion chamber ( | 02-25-2010 |
20110056207 | DIFFUSER FOR TURBINE ENGINE INCLUDING INDENTED ANNULAR WEBS - A diffuser for a turbine engine that includes two annular webs extending inside one another and connected between them by substantially radial vanes, wherein the downstream peripheral edge of at least one of the webs includes indentions evenly distributed about the longitudinal axis of the diffuser. | 03-10-2011 |
20110088402 | ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE - An annular combustion chamber for a gas turbine engine includes radially inner and outer walls connected together by a chamber end wall including openings, each of which receives a fuel injection system. Heat protection deflectors are fastened to the chamber end wall. Holes are formed through the chamber end wall to pass cooling air onto an upstream face of each deflector. The inner or outer edge of a deflector presents a sealing rim engaging the respective inner or outer wall of the chamber. | 04-21-2011 |
20120186222 | COMBUSTION CHAMBER OF AN AERONAUTICAL TURBINE ENGINE WITH COMBUSTION HOLES HAVING DIFFERENT CONFIGURATIONS - A combustion chamber for an aviation turbine engine, the combustion chamber being annular about a longitudinal axis and including an outer side wall, an inner side wall, and an annular chamber end wall connecting one end of the outer side wall to one end of the inner side wall. The outer side wall includes, distributed along its circumference, spark plugs, primary holes, and dilution holes situated downstream from the primary holes in the direction of the longitudinal axis. The primary holes situated in each of the adjacent zones adjacent to one of the spark plugs present a configuration that is different from the configuration of the primary holes situated outside the zones, such that the supply of air in the adjacent zones is different from the supply of air outside the zones. | 07-26-2012 |
20130312420 | CHAMBER-BOTTOM BAFFLE, COMBUSTION CHAMBER COMPRISING SAME AND GAS TURBINE ENGINE FITTED THEREWITH - A baffle for the bottom of a combustion chamber of a gas turbine engine is disclosed. The baffle includes a flat portion of wall with an opening for an injector of the combustion chamber to pass through, two longitudinal edges for the assembly to two adjacent baffles and two transverse edges. At least one of the edges includes a joint cover arranging a housing along the edge for an edge of an adjacent baffle so as to seal the junction between the two edges. A combustion chamber incorporating the baffles is also disclosed. | 11-28-2013 |