Isothermal heat delivery in the turbines of aircraft engines

Abstract

 The organization of operation process according to complicated thermodynamical cycle, in particular, the cycle with heat delivery in the turbine is considered as a prospective trend of aircraft engines development. The article deals with the analysis of works, devoted to the study of the parameters of engine operating on the cycle with heat delivery as in the main combustion chamber,  as well as in the turbine and combustion process in the intrablade channel of turbine.