The aim of this project is to extend the well-established jet-in-hot-coflow (JHC) burner design approach to enable operation at higher pressure. To achieve this aim, the basic operating principle is retained, but the coflow annulus is extended to form a shroud. By adding a flow-restricting-device to the exhaust of the system the pressure inside the chamber can be increased. The motivation of this work is to resolve the role of pressure on the reaction zone structure of the MILD combustion regime.

1. MILD combustion under high pressure conditions
Paul Medwell1
, Michael Evans1
, Zhao Tian1
, Shaun Chan2
, Alessio Frassoldati3
, Alberto Cuoci3
, David Bluck4
, Mel Roquemore5
1
University of Adelaide, 2
University of New South Wales, 3
Politecnico di Milano, 4
Oregon State University, 5
Air Force Research Laboratory
1. Background and Aims
 Benefits of MILD combustion are well-established
 Reduced noise / pressure fluctuation
 Improved efficiency and fuel flexibility
 MILD combustion at high-pressure is not well understood
 MILD combustion of liquid fuels is not well understood
 Aim to develop understanding of MILD combustion under
high pressure conditions and for liquid fuels
2. Methodology
 Jet in hot coflow (JHC) type burners have provided detailed
understanding of the structure of MILD combustion
 Extend coflow shroud duct to cover length of central fuel jet
to confine flame and facilitate pressurisation
 Same principle as JHC to generate vitiated laminar coflow
independent of the jet flow (not complex recirculation)
3. Potential Application
 Fuel issuing into exhaust products from a secondary burner
shares similarities with sequential combustion gas turbines
(also known as reheat combustors or inter-turbine burners)
Güthe, Hellat, and Flohr (2009) Journal of Engineering for Gas Turbines and Power 131, 021503.
4. Burner Layout 5. Preliminary Results
 Mean coflow velocity profile
 Mean coflow temperature profile
6. Conclusions
 A prototype confined jet in hot coflow burner has been built
 This design is suitable for fundamental studies of MILD
combustion under pressurised conditions (and liquid fuels)
 Furthermore, the burner concept shares similarities with
sequential combustion gas turbines, which are a potential
application for this technology
7. Acknowledgements
 Australian Research Council (ARC), Santos Pty Ltd and
United States Air Force (AOARD) for funding support
For more details: paul.medwell@adelaide.edu.au
SECONDARY
TURBINE
SECONDARY
COMBUSTOR
PRELIMINARYBURNER
(PRIMARYCOMBUSTORANDTURBINE)