Multi-ring spacer for gas turbine engine rotor stack assembly

A gas turbine engine comprising:

• a compressor section and a turbine section, with at least one of said compressor section and said turbine section having a rotor with a rotor arm extending from a rotor body, and a rotor assembly arm together forming a portion of a rotor stack assembly;
• and
• a multi-ring spacer positioned between facing surfaces on said rotor assembly arm and said rotor arm, with the multi-ring spacer having a first ring having a first clocking position, a first kink angle, and a first axial end surface having the first kink angle defined relative to a first axis defined by the first ring, a second ring having a second clocking position, a second kink angle, and a second axial end surface having the second kink angle defined relative to a second axis defined by the second ring, wherein a total kink angle of the multi-ring spacer is dependent on an angular deviation of the second clocking position relative to the first clocking position.