Support straps and method of assembly for gas turbine engine

1. A method of assembling a portion of a gas turbine engine, comprising:

assembling a plurality of static structure rings;

attaching an outer diameter of the plurality of static structure rings to form a cartridge; and

inserting the cartridge at least partially into an outer case assembly along an engine axis.

2. The method as recited in claim 1 , wherein at least one of the plurality of static structure rings comprises a vane ring.

3. The method as recited in claim 1 , wherein at least one of the plurality of static structure rings comprises a blade outer air seal.

4. The method as recited in claim 1 , wherein attaching the outer diameter of the plurality of static structure rings comprises attaching at an anti-rotation feature on at least two of the plurality of static structure rings.

5. The method as recited in claim 1 , wherein forming the cartridge comprises installing a balanced rotor within the plurality of static structure rings.

6. The method as recited in claim 1 , wherein the outer case assembly is a mid-turbine frame with integral power turbine case.

7. A gas turbine engine, comprising:

a cartridge formed of a plurality of static structure rings and a balanced bladed rotor disk along an axis; and

an outer case assembly that at least partially surrounds the cartridge.

8. The gas turbine engine as recited in claim 7 , wherein the plurality of static structure rings comprise:

a first static structure ring; and

a second static structure ring adjacent to the first static structure ring.

9. The gas turbine engine as recited in claim 8 , wherein the first static structure ring comprises a first anti-rotation feature and the second static structure ring comprises a second anti-rotation feature, the first anti-rotation feature attached to the second anti-rotation feature.

10. The gas turbine engine as recited in claim 7 , wherein the outer case assembly is a mid-turbine frame with integral power turbine case.