Diagnostic in a reverse-flow aeroengine model combustor under elevated inlet pressure and temperature using spontaneous Raman

Measurements of multi-scalar field within a combustor are of particular interest for engine performance promotion and failure diagnosis. Due to the harsh operating conditions and extremely limited space, direct measurements of combustion state in a near-real conditioned engine combustor were rarely reported. Therefore, this paper reports spontaneous Raman scattering (SRS) measurements of temperature and major species, such as N 2 , H 2 O, O 2 , and CO 2 within a single sector reverse-flow model combustor fuelled with kerosene under elevated incoming pressure and temperature. Geometry of the model combustor was designed to simulate a real engine combustor as much as possible and the point SRS measurement was conducted at 10 characteristic locations of the main combustion region. The measured temperature and major species concentration exhibited a non-uniform distribution in space and highly dynamic variation in time. Strong turbulence-chemistry interaction and deviation from chemical equilibrium were observed according to the measurement. This research demonstrates the feasibility of conducting detailed thermochemistry measurements in a combustor with complicated geometry.