The variations of different parameters such as Temperature (T), Pressure (P), Velocities (v), Mach No. (Ma), Degree of reaction (Λ), Flow coefficient (Φ) etc. on the blade passage has been presented. These calculations were done for a high pressure ratio and at very high temperatures which are usually associated with the gas turbines. The thermal and structural stress distributions due to the flow of gases were analyzed and the impact of flow of gases on the blade is also considered. An attempt is made to confirm the analytical results with the result obtained from software. An analysis of gas turbine blade was performed to determine the regions of maximum stress which occur on a typical gas turbine engine at variable rotational speeds. The results document the effect of velocities, pressure, temperatures and Mach numbers etc. on the blade profile and the distribution of stresses.