An experimental study of the aerodynamic performance of a double annular combustor system

An experimental investigation has been carried out into the performance of an advanced twin combustor system for use in modern aircraft gas turbines. Measurements were made on a 48° sector test rig, the working section of which generically represented the geometry of a dump diffuser system. The flow entered the test rig through an inlet duct containing straight vanes and then passed immediately into the pre-diffuser. From the dump region downstream, the flow was allowed to enter the three annuli and two combustors in the correct mass flow proportions. The combustors were outwardly canted at an angle of 11.5° and although they were not engine representative in terms of dilution holes and cooling rings, the burner porosity was modelled correctly. [Continues.]