Patent application number | Description | Published |
20110067407 | FLAME-HOLDER DEVICE COMPRISING AN ARM SUPPORT AND A HEAT-PROTECTION SCREEN THAT ARE IN ONE PIECE - A flame-holder device for the afterburning of a bypass turbojet, said turbojet comprising first and second internal annular casings, defining a passageway for a main flow, and an external annular casing defining with said first internal annular casing a passageway for a bypass flow, comprising: | 03-24-2011 |
20110120144 | ANNULAR COMBUSTION CHAMBER FOR A TURBOMACHINE - An annular combustion chamber for a turbomachine, such as a jet engine or a turboprop engine for an aircraft, including at the downstream end of one of its external or internal walls of revolution an annular flange for fastening to a casing of the turbomachine, the downstream end of the other wall of revolution of the chamber including a bearing mechanism which are spaced apart from another casing of the turbomachine when cold and bear radially on this casing when hot. | 05-26-2011 |
20110138773 | DEVICE FOR MOUNTING A FLAME-HOLDER ARM ON AN AFTERBURNER CASING - A flame-holder device for an afterburner of a turbofan, the turbofan including a first inner annular casing and a second inner annular casing, these defining a passage for a primary flow, and an outer annular casing defining with the first inner annular casing a passage for a secondary flow, including at least one arm-support made of metallic material configured to be fixed to the outer casing by an upper plate and at least one flame-holder arm of a one-piece structure of composite material including two mutually attached walls arranged to define a groove whose profile is approximately a V. The walls support, on their upper part situated in the secondary flow, a fixing mechanism for fixing to the arm-support. The upper parts are approximately planar and are positioned facing each other. | 06-16-2011 |
20120240584 | COMBUSTION CHAMBER FOR A TURBINE ENGINE - A combustion chamber for a turbine engine such as an airplane turboprop or turbojet has inner and outer annular walls forming bodies of revolution that are connected together by an annular chamber end wall. The inner wall is constituted by a single thickness of material that presents thickness and/or nature varying along the longitudinal axis and/or the circumferential direction of said wall. | 09-27-2012 |