Non-Equilibrium Pulsed Plasma Ignitor

"The proposed program is directed toward the development of a plasma ignitor to address relight and flame-holding problems experienced by high-altitude aircraft. Conventional spark ignitors are insufficient to overcome these problems that are associatedwith the reduced temperature and pressure of air-breathing aircraft at high altitude. The proposed ignitor is based on highly non-equilibrium pulsed discharges that initiate low-temperature chemistry which then drives ignition. The proposed Phase I effortcombines measurements made in a non-equilibrium, single-component low-molecular-weight hydrocarbon discharge with detailed chemistry modeling to a) characterize the nascent radical pool in the discharge and b) determine the key radical-initiatedpre-ignition chemical pathways. This information would permit the "tuning" of the electrical characteristics of the discharge to optimize the ignition capability of the plasma kernel. The Phase II effort would extend this work to heavy-molecular-weighthydrocarbons and mixtures, leading to the design of a prototype plasma ignitor for testing on model combustors. The proposed plasma ignitor will augment or replace conventional spark ignitors in high-altitude aircraft. The plasma ignitor will initiatehydrocarbon ignition and promote flame holding in the reduced temperature and pressure environment that is characteristic of subsonic, high-altitude, air-breathing aircraft engines."