Numerical simulation of variable thrust engine combustion chamber

Tsung-Leo Jiang, Wei Tang Chiang, Shyh Dihng Jang

Research output: Contribution to conferencePaperpeer-review

2 Citations (Scopus)

Abstract

The combustion and aerodynamic processes of liquid bipropellants in the combustion chamber of a Variable Thrust Engine(VTE), to be used in the Orbital Maneuvering Vehicle(OMV), have been predicted at the choking condition of two different power level. The computation is conducted from the injector face down to the nozzle throat. Appropriate physical submodels are adopted to account for the two-phase interaction between bipropellant droplet flows and gas-phase flow. The nozzle throat conditions are determined by the mass con. servation and the thermodynamic relations. The optimal atomization condition is suggested V, considering the high combustion performance and the relatively cool chamber. Therefore, the conventional design concept linked with the corollary “the finer the spray, the better the efficiency” must be reassessed.

Original languageEnglish
Publication statusPublished - 1992 Jan 1
EventAIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992 - Nashville, United States
Duration: 1992 Jul 61992 Jul 8

Other

OtherAIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992
CountryUnited States
CityNashville
Period92-07-0692-07-08

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering
  • Aerospace Engineering
  • Energy Engineering and Power Technology
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

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