| 摘要 |
PURPOSE:To make it possible to use high-temp. gas turbine blade at a high temp. near 1,500 deg.C for a long time, by making Ti, Zr, V, Al, Mg, Ce, B etc. diffuse and permeate into the high-temp. gas turbine blade made of superalloy, then by the heat treanment of the turbine blade. CONSTITUTION:Gas turbine blade is made from Ni or Co base superalloy such as Inconel, Hastelloy. At least one metal selected from the group consisting of Ti, Zr, V, Al, Mg, Ce, and B or their alloy is made to diffuse and permeate into the surface of the turbine blade. Then the turbine blade is heated at a temp. about 1,000 deg.C to oxidize the permeated metal, thereby the bonding strength of the oxide layer to the turbine blade material through the diffused layer is increased. The shearing thermal stress caused by the difference in thermal expansion between the superalloy material and the oxide layer is reduced, so that the turbine blade is used for a long time without peeling of oxide of excellent heat resistance even at a high temp. atout 1,500 deg.C. |
