Conjugate heat transfer methodology was employed to simulate the a turbine vane with compound cooling structure which include film cooling, impingent cooling and trailing edge cooling. The paper discussed distribution of the turbine vane temperature and focused on the effects of gas Reynolds number, cooling flow rate and gas temperature rate on average wall temperature and vane cooling efficiency. Results showed that the leading edge temperature increased first and then decreased while the pressure and suction side temperature decreased with increasing of flow rate. Average wall temperature decreased with increasing temperature rate and had little difference with increasing Reynolds number. Vane cooling efficiency increased with increasing flow rate and had little difference with increasing temperature rate or Reynolds number.