Computational and experimental results in high pressure combustions of H2/air and H2/O2/H2O

The first results of a research and development program on combustion characteristics of gaseous hydrogen fuel in a 'can' type gas turbine combustor, both in combination with air or with oxygen and water, are here presented. Application of a H2/O2/H2O combustion chamber is suggested for the launch-boost phase of an advanced turboramjet. Experiments have been conducted to determine the configuration and the operation of the hydrogen-air combustion chamber test facility, to be transferred to two different kinds of small power turboshafts. Computations, project details and tests, are presented regarding high pressure and temperature stoichiometric H2/O2 combustion in which water is gradually injected. Referring to an already realized and operated (on behalf of the author) H2/O2/H2O combustor for a water steam closed cycle in a turbine/alternator electrically propelled automobile, a detailed design is developed for a quite higher steam temperature, as required in high performance boost phase of a low noxious emission advanced turboramjet, in which H2 and O2 are stored in liquid form.