MODELLING AND WATER TUNNEL VISUALIZATION OF AIR/FUEL MIXING IN A DUCTED ROCKET COMBUSTOR IRRDP-DREV/TNO-TN-9707(1)

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Authors
  1. Stowe, R.A.
  2. De Champlain, A.
  3. Mayer, A.E.H.J.
  4. Niemeijer, S.F.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
The Defence Research Establishment Valcartier (DREV) in Canada and the TNO Prins Maurits Laboratory (TNO-PML) in the Netherlands have undertaken a collaborative demonstrate several of the key technologies of an airbreathing propulsion unit for a medium-range air-launched missile. An essential component of the airbreathing 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 subscale 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, understand the phenomena involved, and help interpret the data from the tests. The first step was to find out which geometries and test conditions had been investigated by other researchers and identify which parameters were the most important for good air/fuel and combustor performance. Secondly, visualization of flowfield within a model combustor was carried out in a water tunnel to better understand the air/fuel mixing, including flow stability.
Keywords
CFD (Computational Fluid Dynamics);Direct connect;Gas generator;Tactical missiles;Airbreathing engines;Combustors;Ducted rockets;Tactical missiles;Airbreathing engines;Combusters;Ducted rockets;Ducted rocket;Ducted rocket engines;Integral rocket ramjet
Report Number
DREV-TM-9828 — Technical Memorandum
Date of publication
01 Feb 1999
Number of Pages
78
DSTKIM No
99-00423
CANDIS No
510444
Format(s):
Hardcopy;Document Image stored on Optical Disk

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