Patent application number | Description | Published |
20080236165 | DUAL-INJECTOR FUEL INJECTOR SYSTEM - A fuel injector system for injecting fuel into a turbomachine combustion chamber, the system comprising first and second fuel injectors wherein the first injector ( | 10-02-2008 |
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 |
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 |
20090077977 | COMBUSTION CHAMBER OF A TURBOMACHINE - Annular combustion chamber of a turbomachine, comprising two walls of revolution each having an annular groove extending around the longitudinal axis of the chamber and opening out inside the chamber, this groove having in cross section a substantially U or V shape that is splayed towards the downstream end and having lateral annular surfaces that are inclined with respect to the area of the wall at which the groove is situated. | 03-26-2009 |
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 |
20090178385 | ARRANGEMENT OF A SEMICONDUCTOR-TYPE IGNITER PLUG IN A GAS TURBINE ENGINE COMBUSTION CHAMBER - The present invention relates to an arrangement comprising an igniter plug of the semiconductor in shell type, a duct secured to a combustion chamber of a gas turbine engine, a floating sleeve via which the igniter plug is mounted in the duct, in order to accommodate expansion along an axis perpendicular to the axis of the igniter plug. It notably comprises means for guiding air to cool the semiconductor of the igniter plug, the shell and the semiconductor defining, at their combustion-chamber end, an annular igniter plug cavity, and the shell comprising orifices in the region of the igniter plug annular cavity that communicate with the annular cavity of the sleeve and orifices on its planar surface. | 07-16-2009 |
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 |
20100218505 | AFTERBURNER CHAMBER FOR A TURBOMACHINE - An afterburner chamber ( | 09-02-2010 |
20100229559 | FUEL INJECTION SYSTEMS IN A TURBOMACHINE COMBUSTION CHAMBER - Turbomachine, comprising a combustion chamber provided with systems ( | 09-16-2010 |
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 |
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 |
20110271682 | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL INTO A TURBOMACHINE COMBUSTION CHAMBER - A device for injecting a mixture of air and fuel into a turbomachine combustion chamber includes a centering ring for centering an injector and a primary swirler situated downstream from the ring, the ring including axial air-passing orifices and the swirler including curved air-passing channels, a number of orifices in the ring being no greater than a number of channels in the swirler, and downstream outlets of the orifices in the ring being situated between the channels in the swirler. | 11-10-2011 |
20120137697 | COMBUSTION CHAMBER FOR A TURBOMACHINE INCLUDING IMPROVED AIR INLETS - A combustion chamber for a turbomachine, including two coaxial walls including air inlets, each of which is configured such that its orthogonal projection, in a plane passing through the axis of the injection system closest to the inlet and perpendicular to an axial plane passing through this axis and through the axis of the combustion chamber, has an upstream edge of convex shape when seen from downstream. | 06-07-2012 |
20130042623 | CONICAL REVERSE-FLOW COMBUSTION CHAMBER FOR A TURBOMACHINE - Assembly consisting of a reverse-flow combustion chamber for a turbomachine and a diffuser intended to be positioned at the outlet of a centrifugal compressor and comprising two faces running parallel to one another, the said combustion chamber comprising a first annular part configured to bear at least one injection system and a second annular part extending beyond this first part so as to form a guide canal for turning back the direction in which the gases passing through the chamber flow, with reference to the axis of rotation of the said turbomachine, the axis Y-Y of the said first part being secant with the said axis of rotation, the assembly being characterized in that the said faces of the diffuser have a curved shape which evolves parallel to that of the outer wall of the chamber at its turn-back canal. | 02-21-2013 |
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 |
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 |
20150020501 | AN ANNULAR COMBUSTION CHAMBER IN A TURBINE ENGINE - An annular combustion chamber of a turbine engine, the chamber including inner and outer coaxial walls forming two surfaces of revolution, which are connected together upstream by an annular chamber end wall including injection systems passing therethrough, each including an injector and at least one swirler for producing a rotating air stream that mixes downstream with fuel from the injector, and at least one ignition spark plug mounted in an orifice of the outer wall downstream from the injection systems. The spark plug is situated circumferentially between two adjacent injection systems that are configured to produce two air/fuel mixture sheets rotating in opposite directions. | 01-22-2015 |
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 |
20150059344 | TURBOMACHINE COMBUSTION CHAMBER SHELL RING - A turbomachine combustion chamber shell ring in which dilution holes in the turbomachine combustion chamber shell ring are covered with inserts defining chambers around same on an inner face of the shell ring. Ventilation holes, through the insert, induce ventilation of portions of the shell ring surrounding the dilution holes, cool the portions, and prevent crack formation. | 03-05-2015 |