Performance prediction of a ducted rocket combustor

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Authors
  1. Stowe, R.A.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
The ducted rocket is a supersonic flight propulsion system that takes the exhaust from a solid fuel gas generator, mixes it with air, and burns it to produce thrust. To develop such systems, the use of numerical models based on Computational Fluid Dynamics (CFD) is increasingly popular, but their application to reacting flow requires specific attention and validation. Through a careful examination of the governing equations and experimental measurements, a CFD-based method was developed to predict the performance of a ducted rocket combustor. It uses an equilibrium-chemistry probability Density Function (PDF) combustion model, with a gaseous and a separate stream of 75 nm diameter carbon spheres to represent the fuel. After extensive validation with water tunnel and direct-connect combustion experiments over a wide range of geometries and test conditions, this CFD-based method was able to predict, within a good degree of accuracy, the combustion efficiency of a ducted rocket combustor.

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Keywords
Ducted rockets;Combustors;Ducted rocket engines;CFD (Computational Fluid Dynamics);Gas generator;Integral rocket ramjet;Air breathing propulsion;Direct connect;GAP (Glycidyl azide polmer) propellants;FLUENT;Particle decomposition model;Scaling;Soot
Report Number
DREV-TR-2001-200 — Technical Report
Date of publication
01 Nov 2001
Number of Pages
275
DSTKIM No
CA020190
CANDIS No
516901
Format(s):
Hardcopy;CD ROM

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