Effects of airstream Mach number on H2/N2 plasma igniter

Goro Masuya, Kenichi Takita, Katsuyoshi Takahashi, Fumio Takatori, Hiroyuki Ohzeki

Research output: Contribution to journalArticlepeer-review

28 Citations (Scopus)

Abstract

Experimental study of the plasma igniter was conducted in nonheated high-speed air stream. The effects of the Mach number, from 0.9 to 2.4, and the stagnation pressure of the airstream, from 64 to 100 kPa, as well as the hydrogen fraction in the H2/N2 feedstock of the torch, from 0 to 50%, were investigated. In the higher Mach number airstream, more input power to the torch was required to ignite hydrogen fuel. The stagnation pressure of the airstream had complicated effects relating to chemistry and aerodynamics. Improvement of ignition performance due to the increased hydrogen fraction in the feedstock was well correlated with the sum of the electric input energy and the heat of combustion of the hydrogen fed as the feedstock of the torch.

Original languageEnglish
Pages (from-to)679-685
Number of pages7
JournalJournal of Propulsion and Power
Volume18
Issue number3
DOIs
Publication statusPublished - 2002

ASJC Scopus subject areas

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science

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