TY - GEN
T1 - Thermo-Mechanical Response of a Hot Surface Ignition Device under Aircraft Compression Ignition Engine Conditions
AU - Kang, Sang Guk
AU - Ryu, Je Ir
AU - Motily, Austen H.
AU - Numkiatsakul, Prapassorn
AU - Lee, Tonghun
AU - Kriven, Waltraud M.
AU - Kim, Kenneth S.
AU - Kweon, Chol Bum M.
N1 - Funding Information:
This work was supported in part by high-performance computer time and resources from the DoD High Performance Computing Modernization Program.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - Aircraft compression ignition (CI) engines, originally developed for ground applications, exhibit significant ignition problems due to various fuel compositions and reactivities encountered in the field. Energy addition via a hot surface ignition assistant is one potential remedy; however, its durability against harsh engine conditions should be bolstered. Analysis of the thermo-mechanical stress within the device during operation can provide useful inputs for design improvements and material selection. In the present study, the effect of several parameters (fuel injection pressure, hot surface temperature, and the vertical and horizontal location of hot surface tip) on the thermo-mechanical stress of an ignition assistant device during combustion events inside a rapid compression machine (RCM) was investigated using the design of experiments (DoE) analysis approach. For 37 cases sampled from our previous study, numerical experiments via transient thermo-mechanical finite element analysis (FEA) were carried out using the boundary conditions coupled from the computational fluid dynamics (CFD) results. A full quadratic response surface model was obtained from the DoE analysis. The relationship between the input parameters and the maximum stress of the ignition assistant was investigated and dominant factors were identified. In addition, the thermo-mechanical behavior of the ignition assistant in response to thermal shock imposed by cold fuel spray impingement was reviewed in detail for the case where the maximum stress was observed.
AB - Aircraft compression ignition (CI) engines, originally developed for ground applications, exhibit significant ignition problems due to various fuel compositions and reactivities encountered in the field. Energy addition via a hot surface ignition assistant is one potential remedy; however, its durability against harsh engine conditions should be bolstered. Analysis of the thermo-mechanical stress within the device during operation can provide useful inputs for design improvements and material selection. In the present study, the effect of several parameters (fuel injection pressure, hot surface temperature, and the vertical and horizontal location of hot surface tip) on the thermo-mechanical stress of an ignition assistant device during combustion events inside a rapid compression machine (RCM) was investigated using the design of experiments (DoE) analysis approach. For 37 cases sampled from our previous study, numerical experiments via transient thermo-mechanical finite element analysis (FEA) were carried out using the boundary conditions coupled from the computational fluid dynamics (CFD) results. A full quadratic response surface model was obtained from the DoE analysis. The relationship between the input parameters and the maximum stress of the ignition assistant was investigated and dominant factors were identified. In addition, the thermo-mechanical behavior of the ignition assistant in response to thermal shock imposed by cold fuel spray impingement was reviewed in detail for the case where the maximum stress was observed.
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U2 - 10.2514/6.2021-3615
DO - 10.2514/6.2021-3615
M3 - Conference contribution
AN - SCOPUS:85123274960
SN - 9781624106118
T3 - AIAA Propulsion and Energy Forum, 2021
BT - AIAA Propulsion and Energy Forum, 2021
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy Forum, 2021
Y2 - 9 August 2021 through 11 August 2021
ER -