System and method for supplying fuel to combustion chamber of aircraft turboshaft engine

A supply system (S) for supplying fuel (C) to a combustion chamber (5) of an aircraft turboshaft engine (6) comprises an injector (1) comprising a first pilot branch (10), a second pilot branch (16) and a main branch (13), the pilot branches (10, 16) being configured to deliver a constant flow of fuel (C), the main branch (13) being configured to deliver an intermittent flow of fuel (C); a distribution device (2) for distributing fuel (C) to an injector (1) comprises a main circuit (21) connected to a first pilot branch (10) and a main branch (13), a secondary circuit (22) connected to a second pilot branch (16), and a valve (20) configured to distribute fuel (C) between the main circuit (21) and the secondary circuit (22); and a control (3) for controlling the valve (20). 一种用于向飞行器涡轮轴发动机(6)的燃烧室(5)供应燃料(C)的供应系统(S)包括喷射器(1)，该喷射器包括第一引燃支线(10)、第二引燃支线(16)以及主支线(13)，引燃支线(10、16)被配置为输送恒定流量的燃料(C)，主支线(13)被配置为输送间歇流量的燃料(C)；用于向喷射器(1)分配燃料(C)的分配装置(2)包括主回路(21)、次回路(22)以及被配置为在主回路(21)与次回路(22)之间分配燃料(C)的阀(20)，主回路(21)连接至第一引燃支线(10)和主支线