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

Patrick Samuel Ciccia

Denis R Ansart

Michel A Desaulty

Eric J Lancelot

Michel Francois Le Texier

A gas turbine engine combustion chamber bounded by inner and outer annular walls extending around a longitudinal axis of the engine and connected by an end wall, through which extend a plurality of fuel injectors, each with an intake air swirler. The outer annular wall has a plurality of first orifices arranged in a common plane and spaced apart in a circumferential direction such that each first orifice is circumferentially associated with a fuel injector and is located on one side of a radius line extending from the longitudinal axis and passing through the axis of the associated fuel injector, and a plurality of second orifices in the inner annular wall arranged in a common plane and spaced apart in a circumferential direction such that each second orifice is circumferentially associated with a fuel injector and is located on an opposite side of the radius line from the first orifice associated with the same fuel injector.

Gas turbine engine combustion chamber for optimizing the mixture of

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.

Fuel pressure actuated air control for a combustion chamber burner

A combustion chamber, particularly for a turbomachine, has at least one generally axially extending wall provided with a plurality of through holes defining a multi-hole cooling system for the wall. The wall also has a plurality of dilution holes which affect locally the flow of burnt gases in the chamber, and the cooling through holes are oriented according to the local flow of burnt gases in the chamber. In particular the wall is subdivided into first zones, downstream of the dilution holes, in which the through holes are oriented substantially in countercurrent to the overall flow direction of the burnt gases in the chamber, second zones and third zones which are disposed on opposite sides of the first zones and in which the orientation of the through holes is inclined both axially and circumferentially, and a fourth zone covering the remainder of the wall and in which the through holes are inclined axially in the overall flow direction of the burnt gases.

Combustion chamber having a multi-hole cooling system with variably

A generally annular combustion chamber for a gas turbine engine is disclosed having fuel injector assemblies, each with an oxidizer swirler, extending through an upstream end wall of the combustion chamber and control means connected to the control diaphragms of the oxidizer swirlers in order to move the control diaphragms between maximum and minimum flow positions. The upstream end wall of the combustion chamber defines complementary oxidizer intake orifices which have movable closure plates to selectively open or close the complementary oxidizer intake orifices. A mechanical linkage connects the closure plates to the control diaphragm of an adjacent air swirler such that, when the control diaphragms are in their maximum flow positions, the closure plates close the complementary oxidizer intake orifices, and when the control diaphragms are in their minimum flow positions, the closure plates are moved such that the complementary oxidizer intake orifices are fully open.

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Paris, France

Patrick Samuel Ciccia