Combustion Gasses Flow through a Gas Turbine

Combustion Gasses Flow through a Turbine Points : Combustion Gasses Flow through a Gas Turbine The flow of combustion gasses through a turbine are as follows. The gas enters the raw of nozzle baldest with a static pressure and temperature P₁ , T)₁ and a velocity C₁ is expended to p₂ , T₂ and leaves with an increased velocity c₂ at an angle ß₂ he rotor blade in inlet angle will be chosen to suit the direction ß₂ of the gas velocity v₂ relative to the blade at inlet. P₂ and v₂ are found by Victoria subtraction of the blade speed U from the absolute velocity C₂ . After being deflected, and Usually further expanded ; in the rotor blade passages the gas leaves at p₃, T₃ with relative velocity V₃ at angle ß₃ Victoria addition of U yields the magnitude and direction of the gas velocity at exit from stage, C₃ and ß₃.