PhD, University of Cincinnati, 2024, Engineering and Applied Science: Aerospace Engineering
A rigorous literature survey on combustion instability, acoustic modeling, dynamic flame modeling, and reduced-order modeling (ROM) was presented to acknowledge the difficulty of accurately predicting combustion instability for a lean, fully premixed combustor operating at speed beyond 5% of the speed of sound while producing significantly long flame. The objective is to validate the feasibility of predicting thermoacoustic instability using ROM for changes in boundary condition (exit blockage ratio) and flow rate on a combustor that produces a non-compact flame. A revised ROM was derived with convective flow rather than assuming stationary flow to predict combustion instability in the combustor that operates at a speed beyond 5% of the speed of sound. The structure of the ROM was revised to account for spatially distributed heat release rather than assuming a singular compact flame. A proposed end boundary condition model was used to improve the solution of the ROM.
A bluff body combustor was tested to establish a combustor that can operate at speeds greater than 5% of the speed of sound. The bluff body combustor produced stable and unstable non-compact flame under the same flow condition (inlet mach number and equivalence ratio) as the combustor configuration changes (combustor length and blockage ratio). The stable flame combustor configuration is used for flame transfer function measurement. In contrast, the unstable flame combustor configuration is used for ROM prediction validation. The exit pressure reflection coefficients were measured for three different blockage ratios (69%, 56%, 0%) without combustion as the temperature, flow rate, and frequency change to validate the end boundary model proposed in the literature.
The model used to characterize the acoustic exit boundary condition for the revised ROM was successfully validated using the multiple microphone method downstream of the bluff body flame holder. An inlet Mach number of 0.06-0.13 at an equ (open full item for complete abstract)
Committee: Jongguen Lee Ph.D. (Committee Chair); Kwanwoo Kim Ph.D. (Committee Member); Paul Orkwis Ph.D. (Committee Member); Prashant Khare Ph.D. (Committee Member)
Subjects: Aerospace Materials