System And Method For Supplying Fuel To A Combustion Chamber In An Aircraft Turbine Engine

Abstract: A system (S) for supplying fuel (C) to the combustion chamber (5) in an aircraft turbine engine (6), comprising injectors (1) comprising a first pilot stage (10), a second pilot stage (16) and a main stage (13), the pilot stages (10, 16) being configured to supply a permanent flow of fuel (C), the main stage (13) being configured to supply an intermittent flow of fuel (C), a device (2) for distributing the fuel (C) to the injectors (1), comprising a primary circuit (21), a secondary circuit (22) and a valve (20) which is configured to distribute the fuel (C) between the primary circuit (21) and the secondary circuit (22), the primary circuit (21) being connected to the first pilot stage (10) and the main stage (13), the secondary circuit (22) being connected to the second pilot stage (16), and a control unit (3) for controlling the valve (20).

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