Experimental investigation of self-excited combustion instabilities in a LOX/LNG rocket combustor
J Martin, W Armbruster, JS Hardi, D Suslov… - Journal of Propulsion …, 2021 - arc.aiaa.org
Two types of combustion instabilities were observed in a multi-injector research combustor
with liquid oxygen and liquefied natural gas (LOX/LNG) propellants operating at conditions …
with liquid oxygen and liquefied natural gas (LOX/LNG) propellants operating at conditions …
Experimental investigation of flame anchoring behavior in a LOX/LNG rocket combustor
Hot fire tests of a multi-injector research combustor were performed with liquid-oxygen and
liquefied-natural-gas (LOX/LNG) propellants at chamber pressures from 30 up to 67 bar …
liquefied-natural-gas (LOX/LNG) propellants at chamber pressures from 30 up to 67 bar …
Numerical study of acoustic resonance in a LOX injector post induced by orifice flow
View Video Presentation: https://doi. org/10.2514/6.2021-3568. vid High-frequency
combustion instability was observed under certain conditions in a multi-injector research …
combustion instability was observed under certain conditions in a multi-injector research …
[PDF][PDF] Linearized Navier-Stokes modelling of acoustic modes in a LOX/Methane rocket thrust chamber
In this study, the acoustic modes in a methane-fueled rocket engine combustion chamber
are modelled with different approaches of increasing complexity. A sub-scale thrust chamber …
are modelled with different approaches of increasing complexity. A sub-scale thrust chamber …
[PDF][PDF] Experimental Investigation of Flame Anchoring Behavior in a LOX/LNG Rocket Combustor. Aerospace 2023, 10, 542
Hot fire tests of a multi-injector research combustor were performed with liquid-oxygen and
liquefied-natural-gas (LOX/LNG) propellants at chamber pressures from 30 up to 67 bar …
liquefied-natural-gas (LOX/LNG) propellants at chamber pressures from 30 up to 67 bar …
[PDF][PDF] LUMEN Thrust Chamber–Ignition Characteristics and Thrust Chamber Transients
The LUMEN project at the DLR Institute of Space Propulsion has the goal of producing a
bread-board demonstrator engine powered by LOX/LNG. The thrust chamber of the engine …
bread-board demonstrator engine powered by LOX/LNG. The thrust chamber of the engine …
[PDF][PDF] Preliminary study of the high-frequency instability of an aerospike rocket engine
F Rossi, R Marchan, O Nikolayev, I Bashliy - scholar.archive.org
A demonstrator aerospike engine, developed by Pangea Aerospace, has a thrust of 2 metric
tons and features a toroidal (annular) combustion chamber powered by liquid oxygen and …
tons and features a toroidal (annular) combustion chamber powered by liquid oxygen and …
Transient Model of API Injector Using EcoSimPro for Expander Bleed Engine Application
RH Dos Santos Hahn, ID Hoffmann, JC Deeken… - Proceedings of the 8th …, 2019 - elib.dlr.de
API injector system has been investigated in DLR Lampoldshausen for the last decade and
has been proved to be a reliable design for LOx/LH2 engines. In this work will be presented …
has been proved to be a reliable design for LOx/LH2 engines. In this work will be presented …