Contact coupled singlets

1. An airfoil assembly, comprising:

a first segment comprising a first shroud and a second shroud radially outward of the first shroud, the first segment comprising a first circumferential side and a second circumferential side;

a second segment comprising a third shroud and a fourth shroud radially outward of the third shroud; and

a first coupling coupled to at least one of the first shroud or the second shroud of the first segment on the first circumferential side of the first segment and a second coupling coupled to at least one of the third shroud or the fourth shroud of the second segment;

wherein the first segment and the second segment are coupled together by a first land of the first coupling and a second land of the second coupling, and wherein the second circumferential side is free of a coupling.

2. The airfoil assembly of claim 1 , wherein the first coupling further comprises a first mating wall and a second mating wall radially outward of the first mating wall.

3. The airfoil assembly of claim 2 , wherein the second coupling further comprises a third mating wall and a fourth mating wall radially outward of the third mating wall.

4. The airfoil assembly of claim 3 , wherein the first mating wall of the first coupling is configured to mate with the third mating wall of the second coupling and the second mating wall of the first coupling is configured to mate with the fourth mating wall of the second coupling.

5. The airfoil assembly of claim 1 , wherein the first coupling is on a suction side edge of the first shroud of the first segment and the second coupling is on a pressure side edge of the third shroud of the second segment.

6. The airfoil assembly of claim 5 , further comprising a third coupling on the suction side edge of the second shroud of the first segment and further comprising a fourth coupling on the pressure side edge of the fourth shroud of the second segment.

7. The airfoil assembly of claim 1 , wherein the first coupling is on a pressure side edge of the first shroud of the first segment and the second coupling is on a suction side edge of the third shroud of the second segment.

8. The airfoil assembly of claim 7 , further comprising a third coupling on the pressure side edge of the second shroud of the first segment and further comprising a fourth coupling on the suction side edge of the fourth shroud of the second segment.

9. The airfoil assembly of claim 1 , wherein the first coupling is cast as a first monolithic portion of the first segment and the second coupling is cast as a second monolithic portion of the second segment.

10. The airfoil assembly of claim 1 , wherein the airfoil assembly comprises a vane assembly comprising a first vane body extending radially outward from the first shroud to the second shroud of the first segment and a second vane body extending radially outward from the third shroud to the fourth shroud of the second segment.

11. The airfoil assembly of claim 1 , wherein the airfoil assembly comprises a blade assembly comprising a first blade body extending radially outward from the first shroud to the second shroud of the first segment and a second blade body extending radially outward from the third shroud to the fourth shroud of the second segment.

12. A gas turbine engine, comprising:

an airfoil assembly, comprising

a first segment comprising a first coupling and a circumferential side disposed circumferentially opposite the first coupling; and

a second segment comprising a second coupling;

wherein the first segment and the second segment are coupled together by a first angled surface of the first coupling and a second angled surface of the second coupling, and

wherein the circumferential side is free of a coupling.

13. The gas turbine engine of claim 12 , wherein the first segment further comprises a first shroud and a second shroud radially outward of the first shroud, the first coupling coupled to at least one of the first shroud or the second shroud.

14. The gas turbine engine of claim 12 , wherein the second segment further comprises a third shroud and a fourth shroud radially outward of the third shroud, the second coupling coupled to at least one of the third shroud or the fourth shroud.

15. The gas turbine engine of claim 12 , wherein the first coupling further comprises a first mating wall and a second mating wall radially outward of the first mating wall.

16. The gas turbine engine of claim 12 , wherein the second coupling further comprises a third mating wall and a fourth mating wall radially outward of the third mating wall.

17. A method of manufacturing an airfoil assembly, the method comprising:

casting a first segment comprising a first shroud, a second shroud, a circumferential side, and a first coupling attached to at least one of the first shroud or the second shroud and disposed circumferentially opposite the circumferential side, wherein the circumferential side is free of a coupling;

casting a second segment comprising a third shroud, a fourth shroud, and a second coupling attached to at least one of the third shroud or the fourth shroud;

heating the first segment to allow thermal expansion of the first segment;

cooling the second segment to avow thermal shrinking of the second segment;

coupling the first segment and the second segment together by mating the first coupling of the first segment to the second coupling of the second segment; and

allowing the first segment and the second segment to return to an ambient temperature.