Evolutions of combusting flow in rocketramjet transition regime

Hyun Ko, Byung Hoon Park, Woong Sup Yoon

Research output: Contribution to conferencePaper

1 Citation (Scopus)

Abstract

Numerical analysis is performed on the transition of the Integral Rocket Ramjet using the Reynolds-Averaged Navier-Stokes equations with low Reynolds number k-e turbulence model and finite rate chemistry. Two-dimensional axisymmetric coaxial ramjet is considered from the boost end phase to the steady ramjet operating mode. The mode transition accompanies a certain amount of complex phenomena such as fuel spreading, mixing, ignition and chemical reaction. The detailed transient sequence will be described in the paper. For a fixed total fuel mass flow rate, the unsteady/unstable combusting flow field is driven when the fuel/air mixture ratio is locally changed at the flame holding region. By the investigation of pressure oscillation, heat release rate fluctuation and vortex shedding, it is numerically demonstrated that unsteady vortex shedding is one of the possible reasons of the low frequency combustion instability in ramjet.

Original languageEnglish
Publication statusPublished - 2005
Event41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Tucson, AZ, United States
Duration: 2005 Jul 102005 Jul 13

Other

Other41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
CountryUnited States
CityTucson, AZ
Period05/7/1005/7/13

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

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  • Cite this

    Ko, H., Park, B. H., & Yoon, W. S. (2005). Evolutions of combusting flow in rocketramjet transition regime. Paper presented at 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Tucson, AZ, United States.