Flame response to acoustic excitation in a rectangular rocket combustor with LOx/H2 propellants
Hardi, J. and Oschwald, M. and Dally, B. (2011) Flame response to acoustic excitation in a rectangular rocket combustor with LOx/H2 propellants. In: Proceedings. 60. Deutscher Luft- und Raumfahrtkongress, 27. - 29. Sept. 2011, Bremen, Deutschland.
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Research efforts are currently underway at DLR Lampoldshausen which aim to understand the mechanisms by which self-sustaining oscillations in combustion chamber pressure, known as high frequency combustion instabilities, are driven. Testing has been conducted in the rectangular combustor ‘BKH’, running cryogenic oxygen and hydrogen propellants under pressure and injection conditions which are representative of real rocket engines and with acoustic forcing. Optical access to the combustor allowed the application of high speed OH* chemiluminescence imaging of the flame during periods of forced excitation of acoustic resonance modes of the combustion chamber. This paper reports the investigation of flame response to acoustic excitation. Both fluctuation in OH* emission intensity and deflection of the flame at frequencies corresponding to the excitation frequency have been observed. These responses are then discussed as potential indicators of driving mechanisms for combustion instabilities.
|Document Type:||Conference or Workshop Item (Speech, Paper)|
|Title:||Flame response to acoustic excitation in a rectangular rocket combustor with LOx/H2 propellants|
|Journal or Publication Title:||Proceedings|
|In ISI Web of Science:||No|
|Keywords:||liquid propellant, rocket engine, combustion|
|Event Title:||60. Deutscher Luft- und Raumfahrtkongress|
|Event Location:||Bremen, Deutschland|
|Event Type:||international Conference|
|Event Dates:||27. - 29. Sept. 2011|
|HGF - Research field:||Aeronautics, Space and Transport|
|HGF - Program:||Space|
|HGF - Program Themes:||W RP - Raumtransport|
|DLR - Research area:||Space|
|DLR - Program:||W RP - Raumtransport|
|DLR - Research theme (Project):||W - Antriebsystemtechnik - Schubkammertechnologie und Hochdruckverbrennung (old)|
|Institutes and Institutions:||Institute of Space Propulsion > Raketenantriebe|
|Deposited By:||Michaela Hanke|
|Deposited On:||30 Nov 2011 11:27|
|Last Modified:||23 Jan 2012 11:05|
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