Abstract
In the present study, an aerothermodynamic analysis of high-speed flow fields through a divergent duct (similar to a supersonic combustor: hereafter referred to as supersonic combustor in the paper), without injection and with high enthalpy cross injection, has been performed. Initially, the thermal and flow analyses of the combustor are carried out by passing vitiated air at a temperature of 607.5 K, and this is followed by a computational analysis of the interaction of the flow field with the structure, when high enthalpy air is injected. The flow is turbulent in the combustor and the k-ω model has been considered to be appropriate for such cases, as it can resolve vorticity and highly strained flows. The study also emphasizes on the advantages of two-dimensional modelling over three dimensional modelling for cold flow cases in supersonic combustors, which could serve as an alternative, for wind tunnel tests as well as computationally expensive three dimensional numerical analysis. A comparison of various turbulence models for supersonic flows without cross injection has been carried out to arrive at the suitable model. For the cases of cross/transverse injection, the Mach numbers considered for investigation are 2, 2.5 and 3. The pressure, temperature and heat flux predictions for the cases with and without injection compare well with the experimental results.
Highlights
In the past few decades of hypersonic research, though adequate attention has been bestowed on fluid structural thermal interaction of external high-speed flows, not many studies have looked at fluid structural interaction in internal high-speed flows
Many researchers have numerically investigated a number of high-speed flow problems, notable being the investigation of non stationary compressible flows through convergent ducts with varying cross section by Igra et al [2]
The study clearly brings out the adequacy of a two-dimensional numerical analysis which was found to give fair agreement with experimental results
Summary
In the past few decades of hypersonic research, though adequate attention has been bestowed on fluid structural thermal interaction of external high-speed flows, not many studies have looked at fluid structural interaction in internal high-speed flows. The investigation of an inviscid compressible flow through a convergent divergent nozzle itself was difficult during the 1970s [1]. Earlier computational facilities and algorithms were incapable of producing results for complex, viscous, compressible, turbulent multi-dimensional flows. With the advent in current day high capacity computers, the solution of complex high-speed internal flows could be sought with much ease and less investment. Many researchers have numerically investigated a number of high-speed flow problems (excluding structural interactions), notable being the investigation of non stationary compressible flows through convergent ducts with varying cross section by Igra et al [2]. The study of the interaction of shock waves and boundary layer due to compressible flows through ducts has remained a challenging task even though much work has been done on this [2−8]
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