Autoignition of two-phase n-heptane/air mixtures behind an oblique shock: insights into spray oblique detonation initiation

TL;DR

This study investigates the autoignition behavior of two-phase n-heptane/air mixtures behind an oblique shock, revealing how various parameters influence ignition and transition modes, with implications for spray oblique detonation initiation.

Contribution

It introduces a detailed analysis of two-phase n-heptane autoignition behind shocks, highlighting the role of droplet dynamics and energy absorption in detonation initiation processes.

Findings

Ignition delay decreases exponentially with Mach number.

Higher liquid equivalence ratio increases ignition delay and evaporation time.

Smooth transition to detonation is more likely at high altitude or Mach number.

Abstract

Autoignition of n-heptane droplet/vapor/air mixtures behind an oblique shock wave are studied, through Eulerian-Lagrangian method and a skeletal chemical mechanism. The effects of gas/liquid equivalence ratio (ER), droplet diameter, flight altitude, and Mach number on the ignition transient and chemical timescales are investigated. The results show that the ratio of chemical excitation time to ignition delay time can be used to predict the oblique detonation wave (ODW) transition mode. When the ratio is relatively high, the combustion heat release is slow and smooth transition is more likely to occur. In heterogeneous ignition, there are direct interactions between the evaporating droplets and the induction/ignition process, and the chemical explosive propensity changes accordingly. The energy absorption of evaporating droplets significantly retards the ignition of n-heptane vapor. In the two-phase n-heptane mixture autoignition process, the ignition delay time decreases exponentially with flight Mach number, and increases first and then decreases with the flight altitude. As the liquid ER increases, both ignition delay time and droplet evaporation time increase. With increased droplet diameter, the ignition delay time decreases, and the evaporation time increases. Besides, for Mach number is less than 10, the ratio of the chemical excitation time to ignition delay time generally increases with the flight altitude or Mach number. It increases when the liquid ER decreases or droplet diameter increases. When Mach number is sufficiently high, it shows limited change with fuel and inflow conditions. The results from this work can provide insights into spray ODW initiation. The ODW is more likely to be initiated with a smooth transition at high altitude or Mach number. Abrupt transition mode tends to happen when fine fuel droplets are loaded.