Catalytic bi-propellant ignition technology development
- Paper number
IAC-10.D2.5.5
- Author
Mr. François Bouquet, TNO Defence, Security & Safety, The Netherlands
- Coauthor
Mr. Bernd Brauers, Aerospace Propulsion Products bv, The Netherlands
- Coauthor
Mr. Alfons Mayer, TNO Defence, Security & Safety, The Netherlands
- Coauthor
Mr. Hans Snijders, Aerospace Propulsion Products bv, The Netherlands
- Year
2010
- Abstract
For the next generation high thrust engine Aerospace Propulsion Products (APP) and TNO Defence Security and Safety are developing technology for a high-power innovative restartable igniter working on 90\% hydrogen peroxide and a liquid or gaseous fuel (ethanol, methane or hydrogen). This development has been done in steps: from a peroxide-only device to a full-scale bi-propellant catalytic igniter with methane that delivers a minimum of 500 kW of thermal power. The latest version of the igniter has an actively cooled tube that delivers a hot core flow and a cooling flow into the combustion chamber that will combust further outside of the igniter at a stoichiometric mixture ratio. The advantages of this system are the absence of electronics to start the igniter, which contribute a considerable part of the development costs and possible failure modes of electrically started igniters. The paper describes the functional design of the bi-propellant methane igniter and will present recent test results.
- Abstract document
- Manuscript document
IAC-10.D2.5.5.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.