Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Snecma Moteurs

Societe Nationale D'etude Et De Construction De Moteurs 's.n.e.c.m.a.'

Alexandre Forestier

Didier Hippolyte Hernandez

Eric Conete

Gw&eacute;na&euml;lle Calvez

Thierry Feuvrier

Georges Habarou

Pierre Camy

Francois Duchene

Hernandez Didier Hyppolyte

Gilles Ulryck

Dominique P Camusso

Philippe P Avignon

Beno&icirc;t Carrere

Pascal J Autie

In a turbomachine comprising a metal material shell containing in a gas flow direction F: a fuel injection assembly; a composite material combustion chamber; and a metal material sectorized nozzle forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held by a sectorized flexible sleeve of metal material having one end fixed to the combustion chamber by first fixing means and a flange-forming opposite end fixed to the shell by second fixing means. The first fixing means also serve to connect the combustion chamber to the sectorized nozzle.

Mounting for a CMC combustion chamber of a turbomachine by means of flexible connecting sleeves

In a turbomachine comprising an annular shell of metal material containing in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material; and an annular nozzle of metal material forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held in position inside the annular metal shell by a plurality of flexible metal tongues each comprising three branches connected together in a star configuration, the ends of two of these three branches being fixed securely to a downstream end of the combustion chamber via respective first and second fixing means, and the end of the third branch being fixed securely to the annular shell via third fixing means.

Resilient mount for a CMC combustion chamber of a turbomachine in a metal casing

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, an annular combustion chamber of composite material, and an annular nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means on a ring of composite material fixed securely to said composite material combustion chamber, the flexibility of said metal fixing tongues allowing expansion to take place freely in a radial direction at high temperatures between said composite material combustion chamber and said metal annular shells.

Fastening a CMC combustion chamber in a turbomachine using brazed tabs

A turbomachine comprises an annular shell of metal material containing in a gas flow direction F a fuel injection assembly, an annular combustion chamber of composite material, and an annular nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine, said nozzle being supported by the annular shell and being fixed thereto by first releasable fixing means, and provision being made for the combustion chamber to be mounted in floating manner inside the annular shell and held in position solely by the nozzle to which it is fixed in resilient manner by second releasable fixing means.

Architecture for a combustion chamber made of ceramic matrix material

A turbomachine has inner and outer annular shells of metal material containing, in a gas flow direction F, a fuel injector assembly, a composite material annular combustion chamber, and an nozzle of metal material forming the fixed-blade inlet stage of a high pressure turbine. Provision is made for the combustion chamber to be held in position between the inner and outer metal annular shells by a plurality of flexible metal tabs having first ends interconnected by a flange-forming metal ring fixed securely to each of the annular shells by first fixing means, and second ends fixed by second fixing means firstly to the composite material combustion chamber and secondly to one end of a composite material wall whose other end forms a bearing plane for a sealing element secured to the nozzle and providing sealing for the gas stream between the combustion chamber and the nozzle.

Connection for a two-part CMC chamber

In a turbomachine comprising inner and outer annular shells of metal material containing, in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material having a plurality of air feed orifices in a primary zone and/or in a dilution zone; and an annular nozzle of metal material forming the inlet stage with fixed blades for a high pressure turbine, provision is made for the combustion chamber to be held in position between the inner and outer annular metal shells by means of a plurality of flexible metal tongues having first ends interconnected by respective metal rings fixed securely to said inner and outer annular shells by first fixing means, and second ends fixed securely to the composite material combustion chamber at it air feed orifices by second fixing means.

Fastening a CMC combustion chamber in a turbomachine using the dilution holes

In an annular combustion chamber having inner and outer axially-extending side walls of composite material and an end wall of metal material, provision is made to hold the end wall in position between the side walls of the annular combustion chamber by means of a plurality of flexible metal tongues fixed firstly to said side walls by fixing means and secondly to said end wall by brazing or welding, said end wall further comprising means for providing sealing between said end wall and said side walls.

Combustion chamber provided with a system for fixing the chamber end wall

A separator (10) for a two-head combustion chamber which comprises a plurty of segments (11) that are arrayed circumferentially and spaced apart a distance (x) from one another and that are affixed to appropriately shaped sheetmetal (12, 13) of the combustion chamber. Each segment (11) is shaped as an elongated, hollow body with an upper wall (17) and a lower wall (18). The segments are cooled by air from an upstream portion of an end of the combustion chamber entering the segments (11) and exhausting by a plurality of orifices (34) in the segment walls (17, 18). The upper and lower segment walls (17) and (18) are respectively heat-protected by two sets of tiles (40, 41), each of the tiles straddling two adjacent segments, being spaced a distance from the walls (17, 18) to subtend an enclosed space (46, 47) therebetween, and having at least one tile orifice (48, 49, 50) which allows the cooling air from the segments (11) to exhaust into the heads.

Separator for a two-head combustor chamber

An oxidizer control device for controlling the amount of oxidizer passing into a combustion chamber of a gas turbine engine. The device has first and second diaphragm assemblies located adjacent to each other at a front portion of the chamber. The first diaphragm assembly has a first, generally annular member with a plurality of circumferentially spaced apart vanes, adjacent vanes forming first oxidizer passageways therebetween, the first passageways opening through a periphery of the first member, and a second generally annular member extending around the periphery of the first member, the second member having a plurality of circumferentially spaced apart first orifices equal in number to the number of first passageways and being fixedly attached to the engine structure. The second diaphragm assembly has a third generally annular member with a plurality of circumferentially spaced apart vanes, adjacent vanes forming second oxidizer passageways therebetween, the second passageways opening through a periphery of the third member, which is fixedly attached to the engine structure and a fourth generally annular member extending around the periphery of the third member, the fourth member having a plurality of circumferentially spaced apart second orifices equal in number to the number of second passageways. An actuator is connected to the first and fourth members of each pair of assemblies so as to simultaneously rotate the first member relative to the second member, and the fourth member relative to the third member, such relative movement opening or closing the first and second oxidizer passageways.

Oxidizer control device for a gas turbine engine

An oxidizer supply control system for a combustion chamber of a gas turbine ngine is disclosed wherein a plurality of oxidizer intake diaphragms are regulated by a synchronized, fluid actuated system. The oxidizer intake diaphragms are arranged in pairs and a fluid actuator operates the sleeves of each respective pair of oxidizer intake diaphragms. Synchronization of the movement of all of the sleeves is achieved by a common manifold interconnecting all of the fluid actuators such that they actuate their respective piston rods at substantially the same time with the same amount of movement. Additional synchronization is provided by interconnecting one of the sleeves of a pair of oxidizer intake diaphragms to one of the sleeve members of an adjacent pair of oxidizer intake diaphragms. This ensures that the sleeves all rotate simultaneously. The piston rods of the fluid actuators are connected to a pair of sleeves by a swivel member mounted in housings attached to the adjacent sleeves. A similar swivel member is used to interconnect the sleeves of adjacent pairs of oxidizer intake diaphragms so as to synchronize their movements.

Oxidizer supply control system for a gas turbine engine

An apparatus is disclosed for temporarily attaching a pre-atomization bowl to a wall of a generally annular combustion chamber during assembly of the combustion chamber with the fuel injector assembly. The attachment apparatus holds each of the pre-atomization bowls in a position so as to minimize the stress imparted to the fuel injectors during assembly of the engine components. The apparatus utilizes a magnetic attachment device to hold the pre-atomization bowls in their assembly positions. The force of the magnetic attachment device is sufficient to hold the pre-atomization bowls in these positions against the effect of gravity, but is insufficient to prevent the radial movement of the pre-atomization bowls relative to the combustion chamber once the turbojet engine has been assembled. Thus, the device does not inhibit the radial play of the pre-atomization bowls once the engine has been asssembled.

Apparatus for attaching a pre-atomization bowl to a gas turbine engine

A system for controlling oxidizer intake diaphragms for a gas turbine engine combustion chamber is disclosed having a single, linear actuator for each pair of intake diaphragms. The movable member of each of an adjacent pair of intake diaphragms is connected to a movable piston rod of the linear actuator. A cam mechanism urges the piston rod in a first direction so as to simultaneously move the movable members of each of the pair of diaphragms. Pressurized gases from the combustion chamber act on the piston to urge it in a second, opposite direction. The forces of the pressurized gases also maintain contact between the cam member and the piston to insure accurate movement of the movable members. A plurality of such linear actuators may be disposed around the periphery of the combustion chamber, each actuator controlling a pair of adjacent intake diaphragms. The actuators may be interconnected by a flexible drive shaft to insure uniformity of movement of all of the cam elements in the system. This insures accurate and simultaneous control of all the intake diaphragms.

Control system for oxidizer intake diaphragms

A system is disclosed for mounting the pre-vaporizing bowl to a wall of a turbine engine combustion chamber in such a manner that it is centered and in alignment with an opening, through the combustion chamber wall during assembly. Not only does the system provide for the centering of the pre-vaporizing bowl in the combustion chamber wall opening, but it also allows relative radial movement between these elements after the engine has been assembled. The system includes a support collar fixedly attached to the combustion chamber wall so as to extend around the generally circular opening in the upstream portion of the combustion chamber, as well as a locating flange fixedly attached to the pre-vaporizing bowl. A stud extending from the locating flange extends through a slot in the support collar such that only radial movement between the locating lfange and the support collar (and consequently between the pre-vaporizing bowl and the combustion chamber wall) is permitted. A resilient snap clip is interposed between the support collar and the locating flange.

System for mounting a pre-vaporizing bowl to a combustion chamber

The cartridge of a fan outlet for a multiple flow turbojet engine is made of composite material and includes two thick lateral strips (8a, 8b) positioned in the interior of the outer case and a narrow central band pierced with slots (10) in which guide vanes (5), provided with an in-molded cover, come to be fixed. The outer cartridge can be integral with the support of soundproofing panels (7 and 9) and support the abradable part (6) facing fan (3).

Multiple flow turbojet engine with an outer ring of the fan outlet

A sound insulating lining for a gas flow path, particularly the bypass flow ath in a jet engine, is made up of a succession of acoustic panels including a perforated skin bonded to a stiffening frame, and a cellular structure formed by a ribbed skin clamped with prestressing via of resilient tongues to transverse struts of the stiffening frame so that the ribs engage the perforated skin to form resonant acoustic cavities. The panels forming the lining are screwed to the casing constituting the wall of the flow path to be insulated.

Growing community of inventors

Boissise la Bertrand, France

Alexandre Forestier