Hybrid thermal analysis on film cooled ramjet combustor

J. Song, M. G. Oh, M. S. Yu, H. H. Cho, K. Y. Hwang

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Thermal analysis has been conducted numerically on a film cooled ramjet combustor with combining experimental data. The film cooling effectiveness and heat transfer coefficient on the exposed combustor wall were taken experimentally in a cold flow test to obtain the thermal boundary conditions. Distributions of temperature and thermal stresses on the combustor liner were calculated by using the boundary conditions from experimental data and a commercial code, ANSYS. The high thermal stress appears after the stabilizer wall. That is also the region attached by combustion flame. Thermal fracture will occur on the region of high thermal stress due to high temperature difference. The present results of temperature and stress distributions provide a guide line for thermal design in a film cooled ramjet combustor.

Original languageEnglish
Title of host publication44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Publication statusPublished - 2008 Dec 1
Event44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Hartford, CT, United States
Duration: 2008 Jul 212008 Jul 23

Publication series

Name44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Other

Other44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
CountryUnited States
CityHartford, CT
Period08/7/2108/7/23

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Space and Planetary Science
  • Energy(all)
  • Electrical and Electronic Engineering
  • Mechanical Engineering

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  • Cite this

    Song, J., Oh, M. G., Yu, M. S., Cho, H. H., & Hwang, K. Y. (2008). Hybrid thermal analysis on film cooled ramjet combustor. In 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit (44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).