Thesis-1993-Shedden.pdf (5.26 MB)
An experimental study of the aerodynamic performance of a double annular combustor system
thesis
posted on 2018-03-05, 09:31 authored by Paul S.R. SheddenAn 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.]
Funding
Rolls Royce PLC (contract no. B1F1309DC).
History
School
- Aeronautical, Automotive, Chemical and Materials Engineering
Department
- Aeronautical and Automotive Engineering