Patent application number | Description | Published |
20090049840 | OPTIMIZING AN ANTI-COKE FILM IN AN INJECTOR SYSTEM - The invention relates to the field of fuel injector systems. More particularly, the invention relates to an annular expansion ring centered on a main axis and suitable for being mounted on a fuel injector coaxial with said ring, the ring presenting holes that are distributed around said main axis and open out into its upstream face to enable air to pass towards the zone that is downstream from the ring. The ring includes a conical annular groove that converges downstream, that is open downstream, and that has the holes opening out into the upstream portion thereof, the axis of each of the holes making an angle relative to the main axis that is strictly greater than the angle between the generator line of the cone defining the annular groove and the main axis, such that the air exiting from the holes impacts against the inner wall of the annular groove, i.e. its wall that is closer to the main axis. | 02-26-2009 |
20090060723 | SEPARATOR FOR FEEDING COOLING AIR TO A TURBINE - The invention relates to the field of combustion chambers. A combustion chamber is fitted with a separator disposed between the radially inner wall of the chamber and the inner flange of the chamber, the separator having both a tubular portion and a fastener portion, the tubular portion being centered on the main axis of the combustion chamber, with the upstream end thereof being situated upstream from orifices in the radially inner wall of the chamber, and the fastener portion being secured to the combustion chamber, such that the tubular portion splits the flow of air running along the said radially inner wall into an inner air flow passing between said tubular portion and the inner flange of the chamber, and an outer air flow passing between the radially inner wall and said tubular portion. | 03-05-2009 |
20090107148 | ANNULAR COMBUSTION CHAMBER OF A GAS TURBINE ENGINE - The present invention relates to an annular combustion chamber of a gas turbine engine comprising a casing with at least one air tapping outlet situated at the chamber inlet, a fuel supply device with a plurality of fuel injectors in the chamber distributed annularly of which at least one is situated close to said tapping outlet. | 04-30-2009 |
20090199564 | DEVICE FOR MOUNTING AN IGNITER PLUG IN A COMBUSTION CHAMBER OF A GAS TURBINE ENGINE - The present invention relates to a device for mounting an igniter plug in a combustion chamber of a gas turbine engine contained in a casing, in which the combustion chamber has an axis YY, the mounting device comprising a hollow shaft, of axis XX, a floating igniter plug sleeve absorbing expansion along an axis perpendicular to the axis XX of the hollow shaft. The device is one which further comprises a hollow shaft sleeve such that the igniter plug sleeve is housed in the hollow shaft sleeve, and means of inclining said hollow shaft sleeve relative to the axis XX. Inclining the hollow shaft sleeve allows the chamber to be inclined relative to the axis XX. | 08-13-2009 |
20090266080 | OPTIMIZING THE ANGULAR POSITIONING OF A TURBINE NOZZLE AT THE OUTLET FROM A TURBOMACHINE COMBUSTION CHAMBER - A turbomachine including an annular combustion chamber fitted with fuel injectors and nozzle vanes arranged at the outlet from the chamber, the number of nozzle vanes being an integer multiple of the number of fuel injectors, and the head of each injector being situated angularly half-way between the leading edges of two consecutive nozzle vanes, these leading edges being in alignment with primary air holes and/or with dilution air holes. | 10-29-2009 |
20100132363 | TURBOMACHINE WITH SEPARATE FUEL INJECTION SYSTEMS, USING IDENTICAL SEALING JOINTS - The present invention concerns a unit ( | 06-03-2010 |
20100326078 | TURBOMACHINE COMBUSTION CHAMBER - A turbomachine combustion chamber in which a chamber end wall presents an opening for receiving a pre-vaporization bowl, and including a device for injecting air and fuel mounted on the axis thereof, the bowl being floatingly mounted relative to the chamber end wall to move in a predetermined radial direction and flaring downstream so as to form a collar, a deflector forming a thermal shield being made integrally with the bowl beside the chamber end wall so that the floating movement of the bowl-and-deflector assembly takes place in a sliding plane situated between the deflector and the chamber end wall. | 12-30-2010 |
20110113747 | GUIDE FOR AN IGNITION PLUG IN A TURBOMACHINE COMBUSTION CHAMBER - The invention relates to a turbomachine combustion chamber including at least one ignition plug carried by an outer casing and extending within guide means carried by a wall of the chamber, said wall forming a body of revolution, and including a tubular guide having the plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber, the guide extending at least in part in an air flow stream outside the chamber. The guide means comprise a deflector surrounding the portion of the guide that is situated in the air flow stream so as to reduce the aerodynamic pressure on the guide and reduce the contact pressure of the guide on the plug. | 05-19-2011 |
20110113748 | GUIDING AN IGNITION SPARK PLUG IN A TURBOMACHINE COMBUSTION CHAMBER - The invention relates to a turbomachine combustion chamber including at least one ignition spark plug carried by an outer casing and extending in guide means carried by a wall of the chamber, the wall forming a body of revolution, the guide means comprising a tubular guide having the spark plug passing axially therethrough and mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out into the chamber. In order to reduce wear of the spark plug in operation, the spark plug is mounted by being fastened in a sheath, the tubular guide being slidably mounted around the sheath. | 05-19-2011 |
20110179798 | SEALING BETWEEN A COMBUSTION CHAMBER AND A TURBINE NOZZLE IN A TURBOMACHINE - A turbomachine including an annular combustion chamber, a sectorized turbine nozzle arranged at an outlet from the chamber, and a sealing mechanism interposed axially between the chamber and the nozzle, the sealing mechanism including an annular gasket that is axially resilient. The gasket includes a first axial bearing mechanism for bearing against a downstream end of the chamber and a downstream annular lip that is sectorized, each sector of the downstream lip being in alignment with a sector of the nozzle and including a second axial bearing mechanism for bearing against an upstream end of the nozzle sector. | 07-28-2011 |
20110203294 | FUEL INJECTION SYSTEM FOR A COMBUSTION CHAMBER OF A TURBOMACHINE - A fuel injection system for an annular combustion chamber of a turbomachine, the system comprising support means for supporting and centering a fuel injector head, and a bowl arranged downstream from the support means and including at its downstream end an annular collar that extends radially outwards and that is cooled by air impacting against its upstream radial surface, and including on said surface means for disturbing the flow of cooling air and for increasing the heat exchange area between the air and the collar. | 08-25-2011 |
20130118181 | PROCEDURE FOR IGNITING A TURBINE ENGINE COMBUSTION CHAMBER - A procedure for igniting a combustion chamber of a turbine engine, the chamber being fed with fuel by injectors and including an igniter mechanism igniting the fuel injected into the chamber. The procedure includes an initial stage during which fuel is injected into the chamber at a constant rate while simultaneously exciting the igniter mechanism, and in event of non-ignition of the chamber at an end of the initial stage, a second stage during which a rate at which fuel is injected is increased rapidly by 20% to 30%. | 05-16-2013 |
20150040569 | ANNULAR COMBUSTION CHAMBER FOR A TURBINE ENGINE - An annular combustion chamber including inner and outer walls forming surfaces of revolution that are connected together upstream by an annular chamber end wall having injection systems passing therethrough. Each injection system includes at least one swirler for producing a rotating stream of air downstream from a fuel injector, and a frustoconical bowl downstream from the swirler and formed with an annular row of air injection orifices, the outer wall having an annular row of primary dilution orifices. The orifices of the bowls are distributed and dimensioned such that sheets of air/fuel mixture present a local enlargement circumferentially intersecting an adjacent sheet of fuel upstream from the primary dilution orifices. | 02-12-2015 |