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Transient fluid-combustion phenomena in a model scramjet

Published online by Cambridge University Press:  28 March 2013

S. J. Laurence ,
S. Karl ,
J. Martinez Schramm  and
K. Hannemann
S. J. Laurence*
Affiliation:
Institute of Aerodynamics and Flow Technology, Spacecraft Department, German Aerospace Center, Bunsenstraße 10, 37073 Göttingen, Germany
S. Karl
Affiliation:
Institute of Aerodynamics and Flow Technology, Spacecraft Department, German Aerospace Center, Bunsenstraße 10, 37073 Göttingen, Germany
J. Martinez Schramm
Affiliation:
Institute of Aerodynamics and Flow Technology, Spacecraft Department, German Aerospace Center, Bunsenstraße 10, 37073 Göttingen, Germany
K. Hannemann
Affiliation:
Institute of Aerodynamics and Flow Technology, Spacecraft Department, German Aerospace Center, Bunsenstraße 10, 37073 Göttingen, Germany
*
†Email address for correspondence: stuart.laurence@dlr.de
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Abstract

An experimental and numerical investigation of the unsteady phenomena induced in a hydrogen-fuelled scramjet combustor under high-equivalence-ratio conditions is carried out, focusing on the processes leading up to unstart. The configuration for the study is the fuelled flow path of the HyShot II flight experiment. Experiments are performed in the HEG reflected-shock wind tunnel, and results are compared with those obtained from unsteady numerical simulations. High-speed schlieren andOH∗ chemiluminescence visualization, together with time-resolved surface pressure measurements, allow links to be drawn between the experimentally observed flow and combustion features. The transient flow structures signalling the onset of unstart are observed to take the form of an upstream-propagating shock train. Both the speed of propagation and the downstream location at which the shock train originates depend strongly on the equivalence ratio. The physical nature of the incipient shock system, however, appears to be similar for different equivalence ratios. Both experiments and computations indicate that the primary mechanism responsible for the transient behaviour is thermal choking, though localized boundary-layer separation is observed to accompany the shock system as it moves upstream. In the numerical simulations, the global choking behaviour is dictated by the limited region of maximum heat release around the shear layer between the injected hydrogen and the incoming air flow. This leads to the idea of ‘local’ thermal choking and results in a lower choking limit than is predicted by a simple integral analysis. Such localized choking makes it possible for new quasi-steady flow topologies to arise, and these are observed in both experiments and simulation. Finally, a quasi-unsteady one-dimensional analytical model is proposed to explain elements of the shock-propagation behaviour.

JFM classification

Reacting Flows: Combustion Compressible Flows: Gas dynamics Compressible Flows: Shock waves

Information

Type
Papers
Information
Journal of Fluid Mechanics , Volume 722 , 10 May 2013 , pp. 85 - 120
Copyright
©2013 Cambridge University Press

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