A disk spacer for a gas engine turbine and a method for providing a rotor assembly

A disk spacer (54) for a gas turbine engine includes a rim (56), a bore (58), a web (60) and a load path spacer (62). The web (60) extends between the rim (56) and the bore (58). The load path spacer (62) is positioned between the rim (56) and the bore (55). Fins (70) are provided in the web (60).