International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Measurement of Heat Flux in Rocket Combustors Using Plug-Type Heat Flux Gauges

  • Kim, Min Seok (Department of Aerospace Engineering, Chungnam National University) ;
  • Yu, I Sang (Department of Aerospace Engineering, Chungnam National University) ;
  • Kim, Wan Chan (Department of Aerospace Engineering, Chungnam National University) ;
  • Shin, Dong Hae (Department of Aerospace Engineering, Chungnam National University) ;
  • Ko, Young Sung (Department of Aerospace Engineering, Chungnam National University)
  • Received : 2017.04.17
  • Accepted : 2017.11.08
  • Published : 2017.12.30
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Abstract

This paper proposes a new measurement method to improve the shortcomings of an existing integral method for measuring heat flux in plug-type heat flux gauges in the high-temperature and high-pressure environments of liquid-rocket combustors. Using the existing integral measurement method, the calculation of the surface area for the heat flux in the gauge exhibits error in relation to the actual surface area. To solve this problem, transient profiles obtained from ANSYS Fluent were used to calculate unsteady heat flux as it adjusted to the measured temperature. First, a heat flux gauge was designed and manufactured specifically for use in the high-temperature and high-pressure conditions that are similar to those of liquid rocket combustors. A calibration test was performed to prove the reliability of the manufactured gauge. Then, a combustion experiment was conducted, in which the gauge was used to measure unsteady heat flux in a liquid rocket combustor that used kerosene and liquid oxygen as propellants. Reasonable heat flux values were obtained using the gauge. Therefore, the proposed measurement method is considered to offer significant improvement over the existing integral method.

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References

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