Conjugate Heat Transfer Analysis of the Wall Heat Flux in a Liquid Rocket Engine
Abstract
The accurate prediction of the wall heat flux in liquid rocket engines is critical to the design of the engine and its thermal management. The measurement of the wall heat flux in liquid rocket engines is difficult to obtain experimentally. Computational tools often utilize an adiabatic thermal boundary condition which makes the prediction of wall heat flux impossible. In the present work, we apply a conjugate heat transfer model which couples the solid conduction in the wall with the fluid dynamics in the combustor. The validity of the solid conduction model is verified using exact solutions. The conjugate heat transfer model is applied to a H2-O2 rocket engine combustor. The developed computational model predicts the experimentally measured heat flux within 4% for three of the four operating conditions.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 03, 2022
- Accession Number
- AD1208627
Entities
People
- Matthew E. Harvazinski
- Tomas Houba
Organizations
- Air Force Research Laboratory