Modelling Combustor Performance Of A Ducted Rocket PDF Download

The Defence Research Establishment Valcartier (DREV) in Canada and the TNO Prins Maurits Laboratory, Netherlands, have undertaken a collaborative activity (Integral Rocket Ramjet Demonstration Program - IRRDP) to demonstrate several of the key technologies of an air-breathing propulsion unit for a medium-range air-launched missile. An essential component of the propulsion system is the ducted rocket combustor, and as part of its development, experiments were conducted at TNO's direct-connect combustion test facility using existing sub-scale combustor hardware. To make the best use of the limited number of tests that could be carried out, a test matrix had to be carefully developed to determine which geometries and test conditions should be considered. This document presents much of the information used to develop this test matrix, to understand the phenomena investigated by other researchers, and identify which parameters were the most important for good air/fuel and combustor performance. Research work described includes visualization of flowfield within a model combustor in a water tunnel to better understand the air/fuel mixing, including flow stability; computational fluid dynamic modelling of the flow fields inside the combustor to determine whether the modelling was representative of the water tunnel tests; and modelling of additional combustor geometries.