Dimensioning of automated regenerative cooling: Setting of high-end experiment

Regenerative cooling is widely used in high-pressure and high-thrust fuel-cooled rocket engines, also suitable for hypersonic structures. The propellant duality in terms of functions (fuel and coolant) makes the thermal and combustion management quite challenging. Dynamics of the system must be stud...

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Bibliographic Details
Published in:Aerospace science and technology 2015-06, Vol.43, p.350-359
Main Authors: Taddeo, L., Gascoin, N., Fedioun, I., Chetehouna, K., Lamoot, L., Fau, G.
Format: Article
Language:English
Subjects:
Analytical chemistry
Chemical and Process Engineering
Chemical Sciences
Control
Density
Dynamical systems
Dynamics
Energy saving strategies
Engineering Sciences
Fluids mechanics
Fuels
Heat transfer
Hydrocarbon fuel pyrolysis
Lab scale testing
Mathematical models
Mechanics
Ramjet engine cooling efficiency
Reactive fluid environment
Regenerative cooling
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Summary:Regenerative cooling is widely used in high-pressure and high-thrust fuel-cooled rocket engines, also suitable for hypersonic structures. The propellant duality in terms of functions (fuel and coolant) makes the thermal and combustion management quite challenging. Dynamics of the system must be studied to develop regulation and control strategies which should be performed with a response time lower than the lowest characteristic time found in supersonic combustion ramjets, i.e. about 1 ms. The present work aims at setting experiments at lab scale by simplifying the additional difficulty of supersonic flow, to determine appropriate regulation dynamics for latter model and control developments. A combustion chamber was dimensioned with similitude rules in terms of heat flux density, conversion rate, chemical compositions, dynamics. Computational Fluid Dynamics and analytical calculations were developed to dimension the experimental bench. It was found that a pyrolysis rate up to 100% can be obtained using ethylene as fuel at 50 bar and 1200 K and with a residence time of about 100 s. Combustion with air (adiabatic flame temperature up to 2400 K) will provide the required heat flux density. The operating range in terms of fuel pressure (10–50 bar), of fuel mass flow rates (50–100 mg s−1) and of equivalence ratio (0.8 to 1.0) have been certified.
ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2015.03.015