Flash-evaporation of oxidizer spray during start-up of an upper-stage rocket engine

R. Schmehl, J. Steelant

Research output: Chapter in Book/Conference proceedings/Edited volumeConference contributionScientificpeer-review

10 Citations (Scopus)

Abstract

The low-pressure oxidizer preflow during start-up of an upper-stage rocket engine is analyzed computationally. An iterative Euler-Lagrange approach is used to describe the three-dimensional two-phase flow of oxidizer vapour and spray which is characterized by intense phase transfer. Multipoint injection and flash-atomization of liquid oxidizer is modelled by stochastic droplet injection according to injector locations and spray characteristics. Based on the framework of classical D2-theory, a flash-evaporation model is developed to describe heat and mass transfer between superheated liquid droplets and vapour flow. The computed transsonic flow field agrees well with experimental characteristics such as pressure level and temperature decrease and further provides detailed local information on vapour flow homogeneity and liquid wall deposit.

Original languageEnglish
Title of host publication39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Publication statusPublished - 1 Dec 2003
Externally publishedYes
Event39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2003 - Huntsville, AL, United States
Duration: 20 Jul 200323 Jul 2003

Conference

Conference39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2003
Country/TerritoryUnited States
CityHuntsville, AL
Period20/07/0323/07/03

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