GASTURBINENTRIEBWERK

摘要

A gas turbine engine 10 includes counterrotating first and second turbine rotors (40,42) driving respective compressors 14,22. Means are provided (e.g. shape and orientation of the blades) for obtaining a pitch, relative outlet velocity W2 greater than the pitch, absolute inlet velocity C1 for at least one of the rotors R. Advantages include improved overall engine efficiency and decrease in weight, reduced cooling flow and complexity of the engine. The invention may be applied to a multistage propeller, engine (Figure 11). The specification contains a detailed discussion of enthalpy drops through the turbine rotor and stator stages together with a comparison of velocity vector diagrams for prior art turbines and turbines according to the invention. The invention utilises turbine blades having higher percentage reaction than prior art blades.