Volume 2, 2011Progress in Propulsion Physics
|Page(s)||239 - 250|
|Section||Liquid Rocket Propulsion|
|Published online||01 October 2012|
Improved heat transfer prediction engineering capabilities for rocket thrust chamber layout
Astrium GmbH Space Transportation Launcher Propulsion, System Analysis Munich 81663, Germany
The demand for a more comprehensive engineering tool for design and parametric investigations of thrust-chamber relevant heat transfer is pushing the improvement of coolant and hot gas side prediction tools. Regenerative Coolant Flow Simulation (RCFS) , Astrium in-house developed one-dimensional (1D) tool to compute hot gas and coolant side heat transfer in a coupled approach, is based on the hot gas side Cinjarew approach which has its origin in the late 1960s. This tool was used as a starting basis for the development and validation of a further improved method. Over the past years, Astrium Space Transportation (ST) has continuously expanded the knowledge in this field. In addition, subscale hot firings, using different propellant combinations and injection conditions, relevant to open and closed cycle applications, were used for the second RCFS generation − the RCFS-II.
© Owned by the authors, published by EDP Sciences, 2011