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

Michel Francois Le Texier

Patrick Samuel Ciccia

A burner is disclosed for a combustion chamber of a gas turbine engine having a fuel injector mounted in an end of the combustion chamber for injecting fuel into the combustion chamber, the fuel injector having an associated air swirler for feeding primary air into the combustion chamber to mix with the fuel, and at least one fuel feed tube for supplying fuel, with an end of the fuel feed tube spaced from the fuel injector nozzle. A control member for controlling the amount of air entering the air swirler is located between the fuel injector nozzle and the end of the fuel feed tube, the control member having a passage to pass fuel from the fuel feed tube to the fuel injector nozzle. The control member is attached to the end of the fuel feed tube by an elastic bellows having a cross-sectional dimension D1 and to the fuel injector nozzle by a second elastic bellows having a cross-sectional dimension D2 such that D2&gt;D1. When the fuel pressure in the passage is below a predetermined value, such as a under low operating conditions, the control member is moved towards the fuel injector so as to restrict the amount of air passing through the air swirler, thereby richening the mixture in the combustion chamber. As the engine operating speed increases, the fuel pressure in the passage also increases which causes movement of the control member away from the fuel injector towards the end of the fuel feed tube, opening the intakes of the air swirler.

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Epinay Sous Senart, France

Michel Francois Le Texier