NASA NTRS · 19860000279
Ignition System for Gaseous Propellants
Abstract
Installation of spark plug in fuel-injection manifold of coaxial injector promotes more efficient cooling of combustor walls in rocket and turbine engines. After ignition occurs in fuel injector, combustion maintained in cooled main combustor leaving spark-plug tip in cool, clean environment. Eighteen tests have proven this injector design; no ignition failures occurred in 8,000 seconds of operation with gaseous oxygen and hydrogen. System also used with other propellants gaseous in ignition phase.
Keep this discovery
Explore connections, maps & timelines
Pieron, R. A.. 1986-05-01. Ignition System for Gaseous Propellants. https://ntrs.nasa.gov/citations/19860000279
Cite the original work for its findings. Save a collection to share your selection of sources.