Support straps and method of assembly for gas turbine engine
A method of assembling a portion of a gas turbine engine, includes assembling a plurality of static structure rings; attaching a plurality of support straps to an outer diameter of the plurality of static structure rings to form a cartridge; inserting the cartridge at least partially into an outer case assembly along an engine axis.
1. A method of assembling a portion of a gas turbine engine, comprising:
assembling a plurality of static structure rings;
attaching a plurality of support straps to 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 shroud.
4. The method as recited in claim 1 , wherein attaching the plurality of support straps comprises attaching each of the plurality of support straps parallel to the engine axis.
5. The method as recited in claim 1 , wherein attaching the plurality of support straps comprises attaching each of the plurality of support straps to an anti-rotation feature on at least two of the plurality of static structure rings.
6. The method as recited in claim 1 , wherein attaching the plurality of support straps comprises attaching each of the plurality of support straps through an aperture in an anti-rotation feature on at least two of the plurality of static structure rings.
7. A method of assembling a portion of a gas turbine engine, comprising:
forming a cartridge of a plurality of axially assembled components with a plurality of support straps; and
inserting the cartridge at least partially into an outer case assembly along an engine axis.
8. The method as recited in claim 7 , wherein forming the cartridge comprises:
stacking a first, a second, a third, and a fourth static structure ring; and
attaching the plurality of support straps to an outer diameter of the first static structure ring and the fourth static structure ring to form the cartridge.
9. The method as recited in claim 8 , wherein the first and the third static structure rings are vane rings.
10. The method as recited in claim 9 , wherein the second and the fourth static structure rings each comprise shroud rings.
11. The method as recited in claim 10 , wherein forming the cartridge comprises installing a rotor within the first, the second, the third, and the fourth static structure rings.
12. The method as recited in claim 7 , wherein attaching the plurality of support straps comprises attaching each of the plurality of support straps parallel to an engine axis.
13. The method as recited in claim 7 , wherein attaching the plurality of support straps comprises attaching each of the plurality of support straps through an aperture in an anti-rotation feature on the first static structure ring and an aperture in an anti-rotation feature on the fourth static structure ring.
14. A gas turbine engine, comprising:
a first static structure ring;
a second static structure ring adjacent to the first static structure ring;
a support strap attached to the first static structure ring and the second static structure ring to form a cartridge; and
an outer case assembly that at least partially surrounds the cartridge.
15. The gas turbine engine as recited in claim 14 , 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 support strap attached to the first anti-rotation feature and the second anti-rotation feature.
16. The gas turbine engine as recited in claim 14 , 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 support strap at least partially extends through a first aperture in the first anti-rotation feature and a second aperture in the second anti-rotation feature.
17. The gas turbine engine as recited in claim 14 , wherein the support strap comprises a first tab in a first end section and a second tab in a second end section.
18. The gas turbine engine as recited in claim 17 , wherein the support strap forms an arc between the first end section and the second end section.
19. The gas turbine engine as recited in claim 14 , wherein the outer case assembly is a mid-turbine frame with integral power turbine case.
20. The gas turbine engine as recited in claim 14 , wherein the second static structure ring and the first static structure ring contain a balanced bladed rotor disk.