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

Guy D Stora

Jacques E Caruel

Gilles M-j Schmitt

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 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.

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Melun, France

Guy D Stora