Outer drum rotor assembly

1. An outer drum rotor assembly for a gas turbine engine, the outer drum rotor assembly defining a radial direction, a circumferential direction, and a longitudinal direction, the outer drum rotor assembly comprising:

a first outer drum comprising a first radially extended flange;

a second outer drum comprising a second radially extended flange adjacent to the first radially extended flange; and

first and second outer drum airfoils that are adjacent to each other and each extended inward along the radial direction from between the first radially extended flange at the first outer drum and the second radially extended flange at the second outer drum,

wherein the first and second outer drum airfoils respectively comprise first and second airfoil flanges extended outward along the radial direction and at least partially along the circumferential direction,

wherein the first and second airfoil flanges are positioned between the first radially extended flange at the first outer drum and the second radially extended flange at the second outer drum,

wherein the first and second airfoil flanges are arranged side by side in the circumferential direction,

wherein a first side of the first airfoil flange and a second side of the second airfoil flange are joined to each other at a joint,

wherein the joint is formed by a first circumferential joint extension of the first airfoil flange that extends towards the second airfoil flange on a downstream end of the first airfoil flange and a second circumferential joint extension of the second airfoil flange that extends towards the first airfoil flange on an upstream end of the second airfoil flange, and

wherein the first and second circumferential joint extensions overlap each other in the longitudinal direction such that the first and second circumferential joint extensions contact each other in the longitudinal direction.

2. The outer drum rotor assembly of claim 1 , comprising:

a disk coupled to inner diameters of the first and second outer drum airfoils.

3. The outer drum rotor assembly of claim 2 ,

wherein the disk comprises a first retaining wall extended along the radial direction,

wherein the first retaining wall is positioned adjacent along the longitudinal direction to the first and second outer drum airfoils, and

wherein the first retaining wall provides retention of the first and second outer drum airfoils along the longitudinal direction.

4. The outer drum rotor assembly of claim 2 , wherein the disk defines comprises a cooling passage extended therethrough at least partially along the longitudinal direction.

5. The outer drum rotor assembly of claim 2 , comprising:

a retaining ring coupled to the disk,

wherein the retaining ring comprises a wall extended along the circumferential direction and along the radial direction,

wherein the wall is positioned adjacent along the longitudinal direction to the first and second outer drum airfoils, and

wherein the retaining ring provides retention of the first and second outer drum airfoils along the longitudinal direction.

6. The outer drum rotor assembly of claim 2 ,

wherein the disk comprises slots extended along the longitudinal direction through which the first and second outer drum airfoils are positioned, and

wherein the slots provide retention of the first and second outer drum airfoils along the circumferential direction and the radial direction.

7. The outer drum rotor assembly of claim 2 , wherein the disk is an integral annular structure.

8. The outer drum rotor assembly of claim 2 , wherein the first and second outer drum airfoils are extended along the radial direction at an angle relative to an axial centerline.

9. The outer drum rotor assembly of claim 8 , wherein outer radial ends of the first and second outer drum airfoils are positioned upstream along the longitudinal direction relative to inner radial ends of the first and second outer drum airfoils.

10. The outer drum rotor assembly of claim 1 ,

wherein the first outer drum airfoil, the first outer drum, and the second outer drum each form an opening through which a mechanical fastener extends,

wherein the mechanical fastener couples together the first outer drum airfoil, the first outer drum, and the second outer drum.

11. The outer drum rotor assembly of claim 1 ,

wherein the first airfoil flange, the first radially extended flange, and the second radially extended flange each form an opening through which a mechanical fastener is positioned,

wherein the mechanical fastener retains the first outer drum airfoil to the outer drum rotor assembly.

12. The outer drum rotor assembly of claim 1 ,

wherein the first outer drum is positioned on an upstream side of the first and second airfoil flanges, and

wherein the second outer drum is positioned on a downstream side of the first and second airfoil flanges.

13. The outer drum rotor assembly of claim 1 , comprising:

a rotatable torque frame coupled to the outer drum rotor assembly,

wherein the torque frame comprises an inner shroud and an outer shroud each extended annularly around an axial centerline, and

wherein the torque frame comprises a structural member extended along the radial direction and coupled to the inner shroud and the outer shroud.

14. The outer drum rotor assembly of claim 13 ,

wherein the outer drum rotor assembly comprises a third flange positioned at one or more of the first outer drum or the second outer drum, and

wherein the torque frame is coupled to the third flange.

15. A gas turbine engine, the gas turbine engine defining a radial direction, a circumferential direction, and a longitudinal direction, comprising:

an outer drum rotor assembly comprising:

an annular outer drum rotor assembly comprising a first outer drum comprising a first radially extended flange;

a second outer drum comprising a second radially extended flange adjacent to the first radially extended flange; and

a plurality of outer drum airfoils extended inward along the radial direction from between the first radially extended flange at the first outer drum and the second radially extended flange at second outer drum,

wherein the plurality of outer drum airfoils comprises first and second outer drum airfoils that are adjacent to each other,

wherein the first and second outer drum airfoils respectively comprise first and second airfoil flanges extended outward along the radial direction and at least partially along the circumferential direction,

wherein the first and second airfoil flanges are positioned between the first radially extended flange at the first outer drum and the second radially extended flange at the second outer drum,

wherein the first and second airfoil flanges are arranged side by side in the circumferential direction,

wherein a first side of the first airfoil flange and a second side of the second airfoil flange are joined to each other at a joint,

wherein the joint is formed by a first circumferential joint extension of the first airfoil flange that extends towards the second airfoil flange on a downstream end of the first airfoil flange and a second circumferential joint extension of the second airfoil flange that extends towards the first airfoil flange on an upstream end of the second airfoil flange, and

wherein the first and second circumferential joint extensions overlap each other in the longitudinal direction such that the first and second circumferential joint extensions contact each other in the longitudinal direction.

16. The gas turbine engine of claim 15 , wherein the outer drum rotor assembly comprises:

a disk coupled to inner diameters of the plurality of outer drum airfoils,

wherein the disk is rotatable with the outer drum rotor assembly.

17. The gas turbine engine of claim 16 , comprising:

a retaining ring coupled to the disk,

wherein the retaining ring comprises a wall extended along the circumferential direction and along the radial direction,

wherein the wall is positioned adjacent along the longitudinal direction to the plurality of outer drum airfoils, and

wherein the retaining ring provides retention of the plurality of outer drum airfoils along the longitudinal direction.

18. The gas turbine engine of claim 15 ,

wherein the outer drum rotor assembly comprises:

a rotatable torque frame coupled to the outer drum rotor assembly,

wherein the torque frame comprises an inner shroud and an outer shroud each extended annularly around an axial centerline, and

wherein the torque frame comprises a structural member extended along the radial direction and coupled to the inner shroud and the outer shroud.

19. The gas turbine engine of claim 18 , wherein outer radial ends of the first and second outer drum airfoils and the structural member are positioned upstream along the longitudinal direction relative to inner radial ends of the first and second outer drum airfoils.