Turbine blade of a gas turbine having compound angled rib arrangements in cooling passage

摘要

PURPOSE: A gas turbine blade having a multangular inclined uneven part in an internal passage is provided to improve cooling efficiency, and to transfer heat evenly by forming the angle of attack in a downward flow region to be different from the angle of attack in an upward flow region. CONSTITUTION: A cooling passage is formed in a gas turbine blade, and inclined uneven parts are formed at both sides of the cooling passage for forced convective cooling of the blade. An angle of attack is formed in the downward flow range of the uneven part, and different from the angle of attack formed in the upward flow range of the uneven part. The uneven parts are bent multi-angularly in the turbine blade. The uneven parts are overlapped, moved in parallel, or arranged symmetrically in the gas turbine blade. Cooling efficiency is improved, and heat is transferred evenly.