| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide advantageous configurations of root and platform regions for rotor blades having non-integral platforms. <P>SOLUTION: A rotor blade assembly for the turbine engine includes: the turbine blade that includes a shank situated between attachment means and an airfoil, the shank having a forward part and a backward part; and a platform including a platform pressure side and a platform negative pressure side, each of which including non-integral components to the other and the turbine blade. The platform may include an interface between the platform pressure side and the platform negative pressure side. Also the platform may be configured such that the interface aligns with at least one of the platform pressure side and the platform negative pressure side. <P>COPYRIGHT: (C)2012,JPO&INPIT |
