Conventional annular combustion chamber with several injectors - includes base mounted circumferentially alternately for pilot and full gas providing idling or take off power with air blown to fuel cone

摘要

The combustion chamber has axial walls (1,2) joined at a base (3), with an open downstream end (16) for gas output. The base has numerous orifices mounting fuel injectors (5) circumferentially in the same plane. Fuel is provided by a first "pilot" injector group to an idling head (6) and a second "full gas" group to a take off head (7). These injectors are mounted alternately. Each head has a tubular burner (11) surrounding the corresponding "full gas" injector, extending into the combustion chamber. Entries in the tubular burner blow air into the fuel cone (10). USE/ADVANTAGE - Turbojet aircraft engines, for Rich Quick Lean operation. Reduces nitrogen oxide pollutants, in reasonable size.