04.1 - Aerospace Grade Materials, Structural Analysis, Fatigue and Damage Tolerance
NUMERICAL SOLUTION OF LOX FLOW IN A LIQUID ROCKET ENGINE ADDITIVELY MANUFACTURED COOLING CHANNEL
N. Monokrousos¹, L. Könözsy¹, V. Pachidis¹, E. Sozio², F. Rossi²; ¹Cranfield University, United Kingdom ;²Pangea Aerospace, Spain
The numerical solution of an LOx flow in an AM cooling channel of an aerospike engine demonstrator is presented. Roughness is generated and modeled through a Gaussian method, instead of being measured. This is of great industrial importance, in terms of cost and time reduction. For the solution of the coolant flow, turbulence models available in commercial CFD packages are employed.