| Issue |
Volume 11, 2019
Progress in Propulsion Physics – Volume 11
|
|
|---|---|---|
| Page(s) | 407 - 424 | |
| DOI | https://doi.org/10.1051/eucass/201911407 | |
| Published online | 08 February 2019 | |
Flame response to high-frequency oscillations in a cryogenic oxygen/hydrogen rocket combustor
1
ONERA — The French Aerospace Lab. Palaiseau 91761, France
2
DLR, German Aerospace Center Lampoldshausen 74239, Germany
3
JAXA, Japan Aerospace Exploration Agency Tsukuba 305-8505, Japan
Experiments presented in this paper were conducted with the BKH rocket combustor at the European Research and Technology Test Facility P8, located at DLR Lampoldshausen. This combustor is dedicated to study the effects of high magnitude instabilities on oxygen/hydrogen flames, created by forcing high-frequency (HF) acoustic resonance of the combustion chamber. This work addresses the need for highly temporally and spatially resolved visualization data, in operating conditions representative of real rocket engines, to better understand the flame response to high amplitude acoustic oscillations. By combining ONERA and DLR materials and techniques, the optical setup of this experiment has been improved to enhance the existing database with more highly resolved OH* imaging to allow detailed response analysis of the flame. OH* imaging is complemented with simultaneous visible imaging and compared to each other here for their ability to capture flame dynamics.
© The Authors, published by EDP Sciences, 2019
This is an Open Access article distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.