In the blade/the disk blade/disk dovetail back cutting (6FA+e, 2nd step) for the stress decrease

摘要

Eluding the blade loading path on the gas turbine disk in side, it can obtain the substantial advantage of disk fatigue life. The plural gas turbine blades install and vis-a-vis the gas turbine disk it is possible, each of the gas turbine blade includes the engagement possible blade dovetail inside the dovetail slot of the form to which the gas turbine disk corresponds. In order to decrease gas turbine disk stress, optimum material removal area, in order of service life of stress decrease and the gas turbine blade in the gas turbine disk and to make the balance with maintenance or improvement of aerodynamics action of the gas turbine blade maximum, the blade and/or following to disk geometry, it is decided. You can obtain largest balance by removing the material from material removal area. Selective figure Figure 12