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논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 지도교수
- Jeong Yeol Choi
- 발행연도
- 2016
- 저작권
- 부산대학교 논문은 저작권에 의해 보호받습니다.
이용수2
이 논문의 연구 히스토리 (4)
2015
Numerical Studies of Supersonic Planar Mixing and Turbulent Combustion using a Detached Eddy Simulation (DES) Model
K
,
ithika Vyasap
,
asath
외 3명
International Journal of Aeronautical and Space Sciences
2015.12
학술저널
Factors Affecting the Reaction Zone in Supersonic Planar Mixing Combustion : A Comprehensive Study
K
,
ithika Vyasap
,
asath
외 2명
한국추진공학회 학술대회논문집
2015.11
학술대회자료
Numerical Simulation of Supersonic Combustion in Mixing Layer
K
,
ithika Vyasap
,
asath
외 3명
한국추진공학회 학술대회논문집
2015.05
학술대회자료
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초록· 키워드
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The present study represents the simulation of a hybrid Reynolds-averaged Navier Stokes / Large Eddy Simulation (RANS/LES) based on detached eddy simulation (DES) for a Burrows and Kurkov supersonic planar mixing experiment. The preliminary simulation results are checked in order to validate the numerical computing capability of the current code. Mesh refinement studies are performed to identify the minimum grid size required to accurately capture the flow physics. A detailed investigation of the turbulence/chemistry interaction is carried out for a nine species 19-step hydrogen-air reaction mechanism. In contrast to the instantaneous value, the simulated time-averaged result inside the reactive shear layer underpredicts the maximum rise in H2O concentration and total temperature relative to the experimental data. The reason for the discrepancy is described in detail.
Further, this study focus on the factors affecting the reaction zone of the supersonic planar mixing combustor. Factors such as variation in wall temperature, boundary layer and the measure of unmixedness is computed and compared with the adiabatic wall temperature cases,
for better understanding of the physics behind the reaction zone. It is found that the ignition delay distance and pre-ignition greatly depend on the incoming boundary layer temperature,corresponds to the fixed temperature of the wall. Combustion parameters such as OH mass fraction, flame index, scalar dissipation rate, and mixture fraction are analyzed in order to study the flame structure.
Key words: Hybrid LES/RANS, supersonic combustion, turbulence/chemistry interaction, planar
mixing, flame structure.
Further, this study focus on the factors affecting the reaction zone of the supersonic planar mixing combustor. Factors such as variation in wall temperature, boundary layer and the measure of unmixedness is computed and compared with the adiabatic wall temperature cases,
for better understanding of the physics behind the reaction zone. It is found that the ignition delay distance and pre-ignition greatly depend on the incoming boundary layer temperature,corresponds to the fixed temperature of the wall. Combustion parameters such as OH mass fraction, flame index, scalar dissipation rate, and mixture fraction are analyzed in order to study the flame structure.
Key words: Hybrid LES/RANS, supersonic combustion, turbulence/chemistry interaction, planar
mixing, flame structure.
목차
Introduction 11.1 Numerical Simulation of Turbulent Combustion in Scramjets . . . . . . . . . . . . . . . . 21.1.1 Previous Studies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21.2 Flow field of Supersonic Planar Reacting Wall Jet . . . . . . . . . . . . . . . . . . . . . . 31.2.1 Burrows and Kurkov Experimental setup . . . . . . . . . . . . . . . . . . . . . . . 41.3 Thesis Objective . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 Governing Equation and Numerical Approach 62.1 Governing Equation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62.2 Thermochemical Model . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82.3 Turbulence Model . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92.4 Detached- Eddy Simulation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103 Computational Grids, Boundary Condition and Initial Condition 124 Results and Discussion 154.1 Scheme Comparison and Mesh Refinement Study . . . . . . . . . . . . . . . . . . . . . . . 154.2 Reactive flow case simulation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 184.2.1 Analysis of preliminary results . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 194.3 Non-reactive flow simulation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 214.4 Factors Affecting Reaction Zone . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 244.4.1 Reaction Zone Temperature Sensitivity Analysis . . . . . . . . . . . . . . . . . . . 244.4.2 Incoming Boundary Layer Temperature Sensitivity Analysis . . . . . . . . . . . . . 254.5 Turbulence/chemistry interaction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 274.6 Implications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 315 Conclusion 33
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