Numerical and boundary condition effects on the prediction of detonation engine behavior using detailed numerical simulations

Sato, Takuma; Van Beck, Caleb; Raman, Venkat

doi:10.3389/fpace.2023.1123249

Numerical and boundary condition effects on the prediction of detonation engine behavior using detailed numerical simulations

Journal Article · Wed Apr 26 00:00:00 EDT 2023 · Frontiers in Aerospace Engineering

DOI:https://doi.org/10.3389/fpace.2023.1123249· OSTI ID:1995207

Sato, Takuma ^[1]; Van Beck, Caleb ^[2]; Raman, Venkat ^[2]

Univ. of Michigan, Ann Arbor, MI (United States); University of Michigan
Univ. of Michigan, Ann Arbor, MI (United States)

High-fidelity numerical simulations of an experimental rotating detonation engine with discrete fuel/air injection were conducted. A series of configurations with different feed-plenum pressures but with constant equivalence ratio were studied. Detailed chemical kinetics for the hydrogen/air system is used. A resolution study for the full rotating detonation engine (RDE) system simulation is also conducted. Two kinds of boundary conditions, a total pressure boundary and a constant mass flow rate boundary, are used to assess the effects of the inlet boundary. As mass flow rate is increased, the total pressure boundary causes more error in the axial pressure distribution while the constant mass flow rate gives a better solution for all cases ran. The simulations confirm experimental findings, and reproduce qualitative as well as some of the quantitative trends. These results demonstrate that a) fuel-air mixing is highly non-uniform within the detonation chamber, leading to variations in local equivalence ratio, b) the fuel and oxidizer injectors experience significant backflow as the detonation wave passes over, but recover at different rates which further augments the inefficiencies in mixing, and c) parasitic combustion in the mixing region makes the detonation wave weak by extending the reaction zone across the wave.

View Accepted Manuscript (DOE)

Research Organization:: Univ. of Michigan, Ann Arbor, MI (United States)

Sponsoring Organization:: USDOE Office of Fossil Energy and Carbon Management (FECM)

Contributing Organization:: NCSA Blue Waters System; NASA Pleiades Supercomputer

Grant/Contract Number:: FE0031228; FE0025315

OSTI ID:: 1995207

Journal Information:: Frontiers in Aerospace Engineering, Journal Name: Frontiers in Aerospace Engineering Vol. 2; ISSN 2813-2831

Publisher:: Frontiers Media S.A.Copyright Statement

Country of Publication:: United States

Language:: English

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Numerical and boundary condition effects on the prediction of detonation engine behavior using detailed numerical simulations

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