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

Serge M Meunier

Michel A Desaulty

Xavier M Bardey

Gerard Y Barbier

Denis R Ansart

Christine J Ambrogi

Denis J Sandelis

Pierre Charles Mouton

Jerome E Jolu

Eric J Lancelot

Sylvie Poutonnet

Xavier, M Bardey

Jacques Renvier

A wall structure for a wall bounding a combustion chamber of a gas turbine engine is disclosed having a first wall with an inner surface facing towards the interior of the combustion chamber and an outer surface facing away from the interior of the combustion chamber such that the inner surface forms a boundary of the combustion chamber and the outer surface has a surface roughness to prevent the formation of a fluid flow cooling layer which would cool the outer surface. The invention also has a second wall spaced from the outer surface of the first wall in a direction away from the interior of the combustion chamber so as to define a cooling fluid circulatory space between the first and second walls. A plurality of first perforations extend through the first wall in communication with the cooling fluid circulatory space to enable passage of cooling fluid from the space through the first perforations to form a cooling fluid film on the inner surface of the first wall.

Double wall construction for a gas turbine combustion chamber

A cladded combustion chamber construction is disclosed in which the cladd tiles can be assembled and replaced without the necessity of disassembling the structural wall of the combustion chamber. The combustion chamber has a generally cylindrical wall with external and internal surfaces bounding the combustion chamber and has a plurality of cladding tiles located on one of the external and internal surfaces of the wall. To attach the cladding tiles to the combustion chamber structure, a plurality of channel shaped attaching devices are utilized extending in a generally circumferential direction around the wall of the combustion chamber and having a portion extending generally parallel to the wall, but spaced from the wall. The portion extending parallel to the wall of the combustion chamber has a circumferentially extending cut out portion whose circumferential length is slightly greater than the width of a cladding tile. The channel shaped attaching devices are spaced axially along the wall of the combustion chamber and are spaced apart a distance slightly greater than a length of a cladding tile. In order to attach the cladding tile to the combustion chamber wall, it is merely necessary to place one end of the tile in one of the channel members and to pass the other end of the tile through the circumferential cut out of the other attaching channel.

Cladded combustion chamber construction

A gas turbine engine is disclosed having an air compressor and a generally annular combustion chamber, with a generally annular diffuser located between the compressor and the combustion chamber so as to direct air exiting from the compressor toward the combustion chamber. The diffuser has inner and outer walls and defines an exit which is located adjacent to an opening in an upstream wall portion of the combustion forming a dome cowl. The dome cowl divides the air emanating from the diffuser exit into a primary air stream passing through the opening and one or more secondary air streams which pass between the walls defining the combustion chamber and the walls of a casing enclosing the combustion chamber assembly. A guide is associated with the diffuser for directing water in the air passing through the diffuser away from the opening such that it will not pass directly into the combustion chamber. Guide vanes may be located on an external surface of the dome cowl so as to direct the water in the secondary air-flow such that it does not enter openings defined by the outer combustion chamber wall, thereby preventing the water from entering the combustion chamber.

Gas turbine engine with improved water ingestion prevention

A low pollution combustion chamber for a turbojet engine is disclosed in which first and second combustion chambers are oriented in a counter-flow direction and both combustion chambers communicate with a separate and distinct exhaust chamber. The first combustion chamber has a fuel injector, as well as a primary oxidizer intake, and the wall bounding the first combustion chamber defines a plurality of dilution oxidizer intake orifices. The wall also defines a first exhaust orifice located approximately midway between the upstream and downstream ends of the first combustion chamber. A second combustion chamber has a second fuel injector, as well as a second primary oxidizer intake, but the wall defining the second combustion chamber does not define any dilution oxidizer intake orifices. A second exhaust orifice also communicates with the exhaust chamber. The orientations of the first and second combustion chambers are such that the fuel/oxidizer mixtures traveling through the combustion chambers travel in a generally counterflow arrangement. A separate exhaust chamber is included in the combustion chamber assembly and communicates with the first and second combustion chambers such that the burned gases from these chambers enter the exhaust chamber. The exhaust chamber defines a third exhaust orifice through which the burned gases exit the combustion chamber assembly. The exhaust chamber is oriented such that the exhaust gases passing through this exhaust chamber travel in a direction generally parallel to the gases traveling through the second combustion chamber. A wall defining the combustion chamber defines a second plurality of dilution oxidizer intake orifices so that oxidizer may dilute the exhaust gases passing through this chamber.

Low pollution combustion chamber for a turbojet engine

A combustion chamber suitable for use in a gas turbine engine includes a first enclosure with a fuel injector for low-power operation and a primary-oxidizer intake, a second enclosure with a fuel injector for full-power operation and a primary-oxidizer intake, and a third enclosure from which to evacuate burnt gases and which communicates with the first and second enclosures. The wall of the first enclosure includes intake orifices for a dilution oxidizer, but the wall bounding the second enclosure lacks any orifices other than the primary-oxidizer intake orifices.

Lean premixture combustion-chamber comprising a counterflow enclosure to

An oxidizer intake flow control system is disclosed for a gas turbine engine combustion chamber. The chamber has an oxidizer intake assembly which extends through the wall of the chamber such that an inlet aperture of the oxidizer intake and an exhaust aperture of the oxidizer intake are located on opposite sides of the wall defining the combustion chamber. An oxidizer intake sleeve defines a central passage through which oxidizer may pass into the combustion chamber. The intake passage extends along a central axis and the intake assembly is attached to the wall of the combustion chamber such that it is rotatable about this central axis. The inlet aperture and/or the exhaust aperture is located in a plane extending non-perpendicularly to the central axis. The combustion chamber may have several oxidizer intake assemblies extending through the combustion chamber walls. The intake assemblies may be interconnected such that they may be simultaneously rotated with respect to the combustion chamber wall.

Gas turbine engine combustion chamber with oxidizer intake flow control

A variable volume combustion chamber for a gas turbine engine that has a able wall to vary the volume of the combustion chamber. The movable wall is positioned according to the operating conditions of the gas turbine engine, achieving one extreme position under idle power and another extreme position under full power. The movement of the wall between the two extreme positions maximizes the efficiency of the combustion chamber for operating conditions between idle and full power. The combustion chamber also restricts at least a portion of the oxidizer intake when the movable wall is positioned for idle power conditions and opens the oxidizer intake when the wall is positioned for maximum power conditions to maximize the flow of oxidizer into the combustion chamber.

Variable volume combustion chamber for a gas turbine engine

The present invention relates to a combustion chamber having a counter-flow arrangement in which a first chamber portion mixes the fuel with the primary oxidizer, which mixture is ignited and burned in the first chamber portion. The exhaust gases from the first chamber portion pass into a second chamber portion in which dilution oxidizer air is added to the burned gases. The orientations of the first chamber portion and the second chamber portion are such that the gases pass through the chamber portions in substantially opposite directions, in a counter-flow arrangement. The first chamber portion in which the combustion takes place, provides only primary oxidizer to the fuel mixture, there being no further communication between the interior of the first chamber portion and the oxidizer air supply. This prevents the leaning of the fuel/air mixture in order to reduce the emissions of nitrogen oxide. The mixing of secondary oxidizer air with the exhaust gases takes place solely in the second chamber portion.

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Le Chatelet en Brie, France

Serge M Meunier