Aeral injector for combustor of small unmanned aircraft – results of investigation

The conception of the construction of the fuel spray injector for a turbo engine of a small unmanned aircraft is proposed in this paper. The work out of the injector model made in rapid prototyping method is shortly presented. Methods of the injector investigation were described. The results of the injector flow parameters and macrostructure parameters investigation were presented and discussed. They were used to formulate the main conclusion connected with the relation between the injector construction, the injector feeding parameters and spray parameters.

Submit your paper

For Authors

Archive

Send by email

Assessment of the effectiveness of mounting the aircraft piston combustion engine on a test stand

Tests of exhaust gas toxicity of jet turbine engine for take off and landing phases of flight

Numerical fatigue analysis of the turbine components under low cycle fatigue (LCF) conditions

Performance characteristic of C-130E Hercules aircraft engine under variable work conditions

Studying a construction of pistons for the aircraft CI engine

Indexes

Keywords index

Topics index