| Issue |
Volume 4, 2013
Progress in Propulsion Physics
|
|
|---|---|---|
| Page(s) | 357 - 372 | |
| Section | Chapter Four. Air-breathing and pulse detonation propulsion | |
| DOI | https://doi.org/10.1051/eucass/201304357 | |
| Published online | 05 March 2013 | |
Development and integration of a scalable low NOx combustion chamber for a hydrogen-fueled aerogas turbine
1
Aachen University of Applied Sciences
6 Hohenstaufenallee,
Aachen
50264,
Germany
2
Université Libre de Bruxelles
50 Av. F. D. Roosevelt,
Brussels
1050,
Belgium
3
Royal Military Academy
30 Av. de la
Renaissance, Brussels
1000,
Belgium
4
Diehl Aerospace GmbH
23 Alte Nußdorfer
Strasse, Uberlingen
88642,
Germany
The usage of alternative fuels in aircraft industry plays an important role of current aero engine research and development processes. The micromix burning principle allows a secure and low NOx combustion of gaseous hydrogen. The combustion principle is based on the fluid phenomenon of jet in cross flow and achieves a significant lowering in NOx formation by using multiple miniaturized flames. The paper highlights the development and the integration of a combustion chamber, based on the micromix combustion principle, into an Auxiliary Power Unit (APU) GTCP 36-300 with regard to the necessary modifications on the gas turbine and on the engine controller.
© Owned by the authors, published by EDP Sciences, 2013