Patent application number | Description | Published |
20080202122 | ARRANGEMENT WITH A TWIST-LOCK COUPLING FOR A TURBOMACHINE COMBUSTION CHAMBER - The invention relates to an arrangement for a turbomachine combustion chamber, the arrangement comprising a chamber end wall pierced by at least one opening, an injector system, and a deflector mounted on the downstream side of the chamber end wall in the opening by means of an annulus, said injector system including a pinch ring mounted on the upstream side and fastened against the annulus with the pinch ring and the annulus together defining a groove, and a bowl mounted in the opening, the bowl being made up of at least two distinct parts, at least a first part forming an end plate suitable for sliding radially in the groove, and a second part forming a bowl collar that is provided with a collar extending parallel to the chamber end wall on its downstream side, said first and second bowl parts being fastened together by means of a twist-lock coupling. | 08-28-2008 |
20090013694 | COMBUSTION CHAMBER COMPRISING CHAMBER END WALL HEAT SHIELDING DEFLECTORS AND GAS TURBINE ENGINE EQUIPPED THEREWITH - The present invention relates to an annular combustion chamber for a gas turbine engine comprising an external wall, an internal wall, a wall connecting these two walls and constituting a chamber end wall, the chamber end wall being provided with openings for the fuel injection systems, heat shielding deflectors being fixed to the wall, the deflectors comprising a flat wall portion with an opening centered on said openings for the fuel injection systems, two longitudinal edges and two transverse edges, wherein, at least along one of the longitudinal edges, a deflector comprises a tongue forming a joint cover, creating a housing along said edge for the edge of the adjacent deflector so as to seal the join between the two adjacent edges of the two deflectors, said tongue being spaced away from the chamber end wall so as to create a space supplied with cooling air via orifices in the chamber end wall. | 01-15-2009 |
20090019856 | CHAMBER-BOTTOM BAFFLE, COMBUSTION CHAMBER COMPRISING SAME AND GAS TURBINE ENGINE FITTED THEREWITH - The present invention relates to a baffle ( | 01-22-2009 |
20090038312 | MULTIPOINT INJECTOR FOR TURBOMACHINE - Multipoint injector for a turbomachine according to which any risk of fuel coking is eliminated. | 02-12-2009 |
20090056337 | TURBOMACHINE WITH ANNULAR COMBUSTION CHAMBER - Turbomachine with an annular combustion chamber ( | 03-05-2009 |
20090077976 | ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE - The present invention relates to an annular gas turbine engine combustion chamber comprising an outer wall and an inner wall connected by a wall forming the chamber bottom, the walls delimiting sources of combustion with axes inclined relative to the axis of the chamber, the chamber-bottom wall, of frustoconical shape, being pierced with orifices for the fuel injection systems, the planes of the orifices being perpendicular to the axes of the sources of combustion, heat-protection baffles centered on each of the orifices comprising a shoulder by which they rest against a flat surface portion along the periphery of the orifices. The chamber is characterized in that the chamber-bottom wall is conformed in a succession of adjacent flat facets having a common edge, with one facet per orifice, the shoulder of the deflectors pressing against the plane of the facets. | 03-26-2009 |
20090078797 | ARRANGEMENT OF INJECTION SYSTEMS IN AN AIRCRAFT ENGINE COMBUSTION CHAMBER END WALL - The invention relates to an arrangement of injection systems each fixed into a hole in a combustion chamber end wall by a fixing device. | 03-26-2009 |
20090214333 | DIFFUSER-NOZZLE ASSEMBLY FOR A TURBOMACHINE - A diffuser-nozzle assembly mounted at the outlet from a centrifugal compressor comprising a plurality of vanes carried by a radially inner wall forming a surface of revolution and surrounded by an outer casing, elastically deformable means being interposed between the radially outer ends of the vanes of the nozzle and the outer casing, these means preventing air from passing between the outer casing and the radially outer ends of the vanes. | 08-27-2009 |
20100043449 | DEVICE FOR ATTACHING A COMBUSTION CHAMBER - Turbomachine comprising an annular combustion chamber ( | 02-25-2010 |
20100058765 | TURBOMACHINE COMBUSTION CHAMBER - A turbomachine combustion chamber including a substantially L-shaped fuel injector and means for mounting and fastening the injector in an orifice of the casing of the chamber, said means including an outer collar carried by the injector and a removable annular spacer surrounding the injector and designed to be interposed between the collar of the injector and the casing. | 03-11-2010 |
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 |
20110097204 | TURBINE ENGINE WITH DIFFUSER - A turbomachine including an annular combustion chamber; a centrifugal compressor; an annular diffuser with a radially oriented upstream portion presenting diffusion passages connected to the outlet of the compressor; a curved intermediate portion; and a downstream portion having a series of circularly spaced-apart deflector vanes. The turbomachine also includes an outer casing externally surrounding the combustion chamber and the downstream portion. The zone of the outer casing that is situated facing the deflector vanes is covered in a coating of abradable material, and the flow passage through the downstream portion is defined on the outside by the outer casing and by the coating. | 04-28-2011 |
20110113789 | GAS TURBINE ENGINE COMBUSTION CHAMBER COMPRISING CMC DEFLECTORS - A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector. | 05-19-2011 |
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 |
20120073259 | TURBOMACHINE HAVING AN ANNULAR COMBUSTION CHAMBER - A turbomachine including an annular combustion chamber, the combustion chamber presenting a connection flange at its downstream end for connection to an outer casing. The connection flange bears axially against the outer casing and is blocked in an axial direction by the upstream end of an inner casing of a high pressure turbine. | 03-29-2012 |
20120186083 | MULTIPOINT INJECTOR FOR TURBOMACHINE - A multipoint injector for a turbomachine according to which any risk of fuel coking is eliminated is disclosed. The multipoint fuel which is liable to stagnate inside the circuit thereof is cooled uniformly, due to the formation of continuous baffles which each communicate with at least one separate circulation channel and of which the peripheral baffles open out into a fuel admission chamber arranged in a zone diametrically opposing the circulation channels and which communicates with the injection nozzle for pilot fuel in order to achieve uniform supply and cooling of the injector. | 07-26-2012 |
20120198853 | MULTIPOINT INJECTION DEVICE FOR A COMBUSTION CHAMBER OF A TURBINE ENGINE - A fuel injector device for an annular combustion chamber of a turbine engine, including a pilot circuit feeding an injector and a multipoint circuit feeding injection orifices formed in a front face of an annular ring mounted in an annular chamber, together with a thermal insulation mechanism insulating the front face and including an annular cavity formed around the injection orifices between the front face of the annular ring and a front wall of the annular chamber and configured to be filled in operation with air or with coked fuel. | 08-09-2012 |
20120204567 | FUEL MIXING DEVICE FOR TURBINE ENGINE COMBUSTION CHAMBER COMPRISING IMPROVED AIR FEED MEANS - A fuel mixing device for an annular combustion chamber of a turbine engine, including a member for centering a turbine engine injector head, at least one air intake ring including blades allowing swirling of air, a bowl including an annular row of air intake orifices, an annular cavity communicating with the air intake orifices, and channels arranged through the blades to feed air to the annular cavity. | 08-16-2012 |
20120291442 | WALL FOR A TURBOMACHINE COMBUSTION CHAMBER INCLUDING AN OPTIMISED ARRANGEMENT OF AIR INLET APERTURES - A rotationally symmetrical wall for an aircraft turbomachine combustion chamber, including primary holes, dilution holes positioned downstream from the primary holes, and a plug installation aperture upstream from the primary holes, wherein each first primary hole, considered as one moves away circumferentially from the median axial plane (D) in either direction is positioned at a circumferential position between the circumferential positions of the first dilution hole and of the second dilution hole considered as one moves away circumferentially from the median axial plane (D), wherein the other primary holes are distributed equidistantly, at a predefined interval P, and the distance between the two primary holes is greater than the interval P separating two of the other adjacent primary holes. | 11-22-2012 |
20120304650 | INJECTION SYSTEM FOR A TURBOMACHINE COMBUSTION CHAMBER, INCLUDING AIR INJECTION MEANS IMPROVING THE AIR-FUEL MIXTURE - An air and fuel injection system for the back of a turbomachine's annular combustion chamber, including a central injector and a peripheral annular fuel injector including at least one fuel injection aperture made in an annular wall and emerging in a peripheral annular channel separated from a central channel by the annular wall and having an annular space of admission of air. The system also includes multiple air ejection apertures made in the annular wall downstream from the fuel ejection aperture or apertures in reference to the flow of the air stream, for an additional injection of air into the channel. | 12-06-2012 |
20130160452 | AERODYNAMIC SHROUD FOR THE BACK OF A COMBUSTION CHAMBER OF A TURBOMACHINE - An annular shroud has an internal face intended to cover the back end wall of an annular combustion chamber of a turbomachine fitted with a centrifugal compressor, together with an external face opposite the internal face. The shroud includes multiple apertures intended to allow fuel injectors supported by the back end wall to pass through. The shroud includes multiple bosses which extend as projections on the external face radially towards the interior respectively from the respective radially internal edges of the apertures. Each of the bosses delimits an extension of the corresponding aperture open radially towards the exterior so as to form an air intake scoop. | 06-27-2013 |
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 |
20140090382 | ANNULAR COMBUSTION CHAMBER FOR A TURBINE ENGINE - An annular combustion chamber for a turbine engine, the chamber including an annular row of fuel injectors including heads engaged in fuel injection systems mounted in openings in the chamber end wall, each injector head including at least one fuel-passing helical channel for causing fuel to rotate about the longitudinal axis of the head, and each injection system including at least one swirler including air-passing channels of sections with axes that are inclined relative to the plurality axis of the swirler at an angle that is substantially equal to a helix angle of the helical channel, to within ±10°, and are oriented in a same direction as the channel about the longitudinal axis of the swirler. | 04-03-2014 |
20140116065 | TURBINE NOZZLE GUIDE IN A TURBINE ENGING - A sectorized nozzle for a turbine engine turbine including an inner sectorized annular platform and an outer sectorized annular platform connected together by radial airfoils, at least one of the platforms including a plurality of orifices for passing air in a neighborhood of its upstream end, the orifices being distributed over the circumference of the platform and opening out at their ends remote from the airfoils into a circumferential annular cavity of the sector of the platform, which cavity is closed by a metal sheet fastened to the platform sector and pierced by orifices for feeding cooling air. | 05-01-2014 |