Gas turbine equipment and turbine blade

Details Gas turbine equipment and turbine blade Gas turbine equipment and turbine blade

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01) F01D 5/14 (2006.01)

Patent

CA 2322924

The turbine blade of a gas turbine and gas turbine equipment using the turbine blade, as disclosed, suppresses the occurrence of thermal stress caused by a difference in temperature thereby providing a highly reliable gas turbine blade and gas turbine equipment. The gas turbine equipment of the present invention comprises a rotational portion of a rotor (1), a moving blade (2), a stationary portion of casing (3), a stationary blade (4), various supporting members and a combustor. A thermal stress reducing portion is provided in one or both of the moving blade joint adjacent portion (14a), between the moving blade trailing edge portion (14) and the platform (15), and the stationary blade joint adjacent portion (20a), between the stationary blade trailing edge portion (20) and the shroud (18, 19). The thermal stress reducing portion, as disclosed, reduces undesirable thermal stress occurring in the blade joint adjacent portions (14a, 20a), and reliability of the turbine blade and gas turbine equipment is enhanced.

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