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

Jacques E Caruel

Philippe M Gastebois

Herve Alain Quillevere

Guy D Stora

Roland Robert Beyler

Marc F Buisson

Jean Robert Bedue

Marcel R Soligny

Roger A Vandenbroucke

Jacques Eloi Pidebois

Jean-Claude M Arliguie

Michel Bernard Schenher

Simone Coutor

Gilles M-j Schmitt

Andre M Barbot

Ernest J Barou

Bernard Andre Cantaloube

Bruno Deroide

Jean-Paul R Gaillac

This device embodies a centrifugal compressor secured to a joint-carrier disk secured to an upstream flange of the rotor disk to be cooled. The recompressed air is ejected through channels near the roots of the blades of the disk.

Device for cooling and gas turbine rotor

A flameholder structure for a turbojet engine afterburner is disclosed in which a generally 'V' shaped flameholder ring has a plurality of substantially radially extending fins attached to and extending radially outwardly from its outer surface. A portion of each of the fins is disposed at an angle to the gas flow so as to impart a cylindrical rotation to that portion of the flow passing over the fins. The cylindrical rotation of the flow increases the shear effect to thereby improve the stability of the flame front and increase the efficiency of the afterburner.

Flameholder for a turbojet engine afterburner

A device for cooling the wall of a combustion chamber, in which air is taken from the space outside the chamber by means of an annular protuberance which extends beyond the outside of the chamber and forms an annular pocket, which is provided with outside air by means of holes and communicates with the interior of the chamber by means of an annular slot between the downstream internal wall of the chamber and a small annular tongue which is an extension of the upstream wall. The air intake holes for the pocket are arranged in the wall of the protuberance which is more or less perpendicular to the wall of the chamber which faces the air flow and have a sufficiently small diameter to make it possible to arrange them in at least three concentric rows, which are offset from one row to the next.

Cooling of combustion chamber walls using a film of air

The invention concerns a fuel distribution device in a high velocity gase flow. The device consists of two coaxial, toric injection manifolds placed in close proximity with respect to each other, pierced by small diameter uniformly distributed orifices and arranged to introduce fuel into the flow. The orifices in the manifold located downstream with respect to the direction of the flow of gases, are arranged on the face turned upstream of the manifold, in a circular row coaxial with it. It is the object of the invention to reduce the drag induced in the flow by the devices presently in use, while improving the distribution of the fuel; it finds particularly advantageous applications in the afterburner ducts of gas turbine engines.

Fuel distribution device

The invention concerns a combustion chamber for turbojet engines. The comtion chamber is of the annular type and consists of two coaxial flame tubes opening into a common dilution and mixing zone. The inner tube is designed for low operating ratings of the engine, the outer tube for high ratings. Air is injected as far upstream as possible into the dilution zone, to enhance the homogenization of the gaseous flow issuing from the two tubes prior to their passage into the turbine and to assure the optimum radial distribution of temperatures. The combustion chamber according to the invention finds application in a particularly advantageous manner in turbojet engines used in aircraft propulsion because of the reduced emission of pollutants it affords.

Antipollution combustion chamber

The disclosure is of a combustion chamber having prevaporizing pipes for the injection of fuel and shield cups intended to play the role of thermal barriers, upon which the hot jets issuing from the injectors are broken up. The shield cups have ribs toward which high velocity jets of air are directed, the jets of air issuing from small orifices. Other small orifices may addtionally open on a ridge of the ribs, so as to form supplementary jets of air convergent with the first set of jets of air.

Combustion chamber of gas turbine engines

A fuel injection nozzle for a turbo engine is mounted at the base of a costion chamber, either tubular or annular, by means of an intermediate inwardly flared member having openings through its sides for admitting cooling air. An annular flange structure around the intermediate member supports the same and defines an annular space with the base of the chamber for a layer of cooling air admitted to that space through holes in the base. Several forms are disclosed in each of which the various holes and air inlets are dimensioned and positioned to provide a stoichiometric mixture of air and fuel under substantially all conditions of operation.

Combustion chamber for turbo engines

An auxiliary chamber or ignition 'prechamber' for afterburners of aeronautical turbine engines draws in, through a perforated plate, a carbureted mixture produced by fuel projected against an anvil by an injection manifold, and the injection manifold also issues a jet of fuel into a tube which discharges into the chamber downstream of a spark plug. The produced flame is guided into a flame stabilizer.

Device for igniting fuel injected into a rapidly flowing gaseous medium

A combustion chamber shell, particularly for aircraft turbojet engines, cisting of an assembly of sleeves each of which comprises two parallel facings connected and braced to each other by multiple longitudinal ribs which form an equal number of channels for the passage of the cooling air. The sleeves are connected to each other by annular parts which, to the front and to the rear of the sleeve facings, form vents which are arranged with respect to each other in such a fashion that the air entering into the chamber through the said channels flows in them from rear to front.

Double-walled combustion chamber shell having combined convective wall

A combustion chamber for, for example, an aircraft gas turbine engine, has n upstream end wall protected by a plate serving as a heat shield, the shield-plate being spaced from the dome and cooled by fluid flowing through orifices in the dome. The shield plate is itself formed with a plurality of small dimension orifices which create fluid jets of considerable velocity which serve to atomize any liquid fuel which may stream over the shield-plate and to increase turbulence.

Gas-turbine combustor having an air-cooled shield-plate protecting its

Combustion chamber comprising a first combustion zone opening into a wider second combustion zone into which the combustion air is admitted through a practically frontal air entry comprising obstacles which impart a coefficient of blocking of about 60% to 80% to it. The first zone is supplied with air and fuel in substantially stoichiometric proportion in idling. At the other running rates, a supplementary fuel flow is injected into the chamber and burns in the second zone in the wake of the obstacles.

Gas turbine combustion chambers

A device for injecting and igniting a fuel in a flow of air, comprising a bular duct in which are generated an internal flow of rotating air and an intermediate flow containing fuel which is sandwiched between the internal flow and an external flow of rotating air, in which ignition is effected by a central electrode placed in the axis of the tubular duct and defining within the latter an annular channel which narrows around the downstream end of the central electrode to form an annular gap of uniform width along the entire extent of its circumference, in such a way that a difference in electrical potential applied between the electrode and the tubular duct causes sparks to jump between the free end of the electrode and the tubular duct across the internal flow and the intermediate flow.

Injecting and igniting device

A fuel injector in which, an annular intermediate flow containing fuel is ndwiched between an inner and an outer flow of air caused to rotate by swirl-promoting bladed devices called 'swirlers,' the inner flow being generated in a tubular duct which is closed at its upstream end with a bottom plate, and the 'swirler' associated with said inner flow being a centripetal bladed device that opens to the tubular duct upstream of an annular duct supplied with fuel and itself opening at its downstream end to the tubular duct, thus forming a sharp enlargement within the tubular duct.

Fuel injector for atomizing and vaporizing fuel

A combustion chamber for a gas turbine engine, comprising an upstream porn divided longitudinally into a first chamber and a second chamber supplied with air in parallel, and a downstream portion in which the flows issuing from these two chambers mix, the first chamber comprising a primary combustion zone into which fuel is injected at an idling rating forming a substantially stoichiometric air - fuel mixture, and a secondary combustion zone supplied with secondary combustion air, and the second chamber, of the premixed burning type, being formed by a simple conduit upstream of which, for driving the gas turbine at the maximum rating, supplementary fuel is injected which burns on contact with a flame synchronizer.

Growing community of inventors

Dammarie les Lys, France

Jacques E Caruel