· Combustion chamber and turbine blade materials must have a high melting point, T_m. This will also increase their resistance to Creep which becomes important for (T/T_m) > 0.5.
· Turbine blades are in tensile loading, and for a light/strong structure, shape independent selection is based on (E/ρ) and (σ_y/ρ).
· Turbine blades also experience fluctuating aerodynamic loading which may excite high frequency (kHz) vibrations in the blades.  These vibrations can cause high cycle fatigue blade failure - and potentially destroy the engine.
· Temperature fluctuations during the flight program can induce thermal fatigue in both the combustion chamber and turbine blades. Thermal expansion considerations are important.
· Nickel, with a melting point of 1726 K, and its alloys are potential materials for these chamber and blade applications. 
· The performance of the nickel alloy blades may need to be improved by application of ceramic coatings and use of internal blade cooling.