In an integrated rocket ramjet engine: Part I. Transition from rocket booster to ramjet sustainer

Hong Gye Sung, Shih Yang Hsieh, Vigor Yang

Research output: Contribution to conferencePaperpeer-review

Abstract

A comprehensive numerical analysis has been conducted to study ramjet operation in an integrated rocket ramjet (IRR) propulsion system. This study consists of two parts. Part I, this paper, details the transition from rocket booster to ramjet sustainer while part II, another paper1, consists of combustion dynamics and system diagnostics during the ramjet operation. The computational geometry consists of the entire IRR engine, including the inlet, the combustion chamber, and the exhaust nozzle. The theoretical formulation is based on the complete conservation equations of mass, momentum, energy, and species concentration, with consideration of finite-rate chemical kinetics and variable properties. Turbulence closure is achieved using a low-Reynolds-number κ-ε two-equation model. The governing equations are solved numerically by means of a finite-volume, preconditioned flux-differencing scheme capable of treating chemical reacting flow over a wide range of Mach number. Various important physical processes are investigated systemically, including unsteady inlet aerodynamics, fuel/air mixing, ignition and so on.

Original languageEnglish
Publication statusPublished - 2001
Event37th Joint Propulsion Conference and Exhibit 2001 - Salt Lake City, UT, United States
Duration: 2001 Jul 82001 Jul 11

Conference

Conference37th Joint Propulsion Conference and Exhibit 2001
CountryUnited States
CitySalt Lake City, UT
Period01-07-0801-07-11

All Science Journal Classification (ASJC) codes

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

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