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.]
A Master's Thesis. Submitted in partial fulfilment of the requirements for the award of Master of Philosophy at Loughborough University.