Turbine engine with soaring air conduit

1. An assembly for a turbine engine, comprising:

a case structure extending circumferentially about and axially along an axis; and

an air conduit having a conduit centerline, a conduit first end and a conduit second end, the air conduit extending longitudinally along the conduit centerline between the conduit first end and the conduit second end, the conduit first end connected to the case structure at a first location, the conduit second end connected to the case structure at a second location, the air conduit displaced from the case structure longitudinally between the conduit first end and the conduit second end, and at least a majority of the conduit centerline following a non-straight trajectory;

wherein the case structure and the air conduit are formed together as a monolithic body.

2. The assembly of claim 1 , wherein the non-straight trajectory is a continuously curved trajectory.

3. The assembly of claim 1 , wherein an entirety of the conduit centerline follows the non-straight trajectory.

4. The assembly of claim 1 , wherein

the conduit centerline is angularly offset from the case structure at the conduit first end by a first included angle; and

the conduit centerline is angularly offset from the case structure at the conduit second end by a second included angle that is different than the first included angle.

5. The assembly of claim 1 , wherein the first location is displaced from the second location axially along the axis.

6. The assembly of claim 1 , wherein the first location is displaced from the second location circumferentially about the axis.

7. The assembly of claim 1 , wherein at least a portion of the air conduit has a polygonal cross-sectional geometry.

8. The assembly of claim 1 , wherein at least a portion of the air conduit has an elongated cross-sectional geometry.

9. The assembly of claim 1 , further comprising:

an air source; and

an air cooled component within the case structure;

the air conduit configured to receive air from the air source and direct the received air to the air cooled component.

10. The assembly of claim 9 , wherein at least one of

the air source comprises a compressor section of the turbine engine; and

the air cooled component comprises a turbine vane.

11. The assembly of claim 1 , further comprising:

a stator vane with one or more internal passages;

the air conduit fluidly coupled with the one or more internal passages.

12. The assembly of claim 1 , further comprising:

a second air conduit within the case structure;

the second air conduit extending radially across a flowpath of the turbine engine; and

the second air conduit fluidly coupled with and downstream of the air conduit.

13. The assembly of claim 1 , wherein the air conduit is fluidly coupled with a bleed orifice in the case structure at the conduit first end.

14. The assembly of claim 1 , further comprising:

a scoop connected to the case structure;

the scoop projecting into a flowpath of the turbine engine; and

the air conduit fluidly coupled with and downstream of the scoop.

15. An assembly for a turbine engine, comprising:

a case structure extending circumferentially about and axially along an axis; and

an air conduit having a conduit centerline, a conduit first end and a conduit second end, the air conduit extending longitudinally along the conduit centerline between the conduit first end and the conduit second end, the conduit first end connected to the case structure at a first location, the conduit second end connected to the case structure at a second location, the air conduit displaced from the case structure longitudinally between the conduit first end and the conduit second end, and at least a majority of the conduit centerline following a non-straight trajectory;

wherein the conduit first end is an upstream end of the air conduit;

wherein the conduit second end is a downstream end of the air conduit; and

wherein a maximum displacement between the case structure and the air conduit is longitudinally along the conduit centerline closer to the conduit second end than the conduit first end.

16. An assembly for a turbine engine, comprising:

a case structure extending circumferentially about and axially along an axis; and

an air conduit having a conduit centerline, a conduit first end and a conduit second end, the air conduit extending longitudinally along the conduit centerline from the conduit first end to the conduit second end, the conduit first end connected to the case structure at a first location, and the conduit second end connected to the case structure at a second location that is circumferentially displaced from the first location about the axis, wherein an intermediate portion of the air conduit, longitudinally between the conduit first end and the conduit second end, is radially separated from the case structure;

wherein the case structure and the air conduit are formed together as a monolithic body.

17. The assembly of claim 16 , wherein more than fifty percent of the conduit centerline follows a curved trajectory.

18. The assembly of claim 16 , further comprising:

a compressor section at least partially housed within the case structure; and

a turbine vane configured with one or more internal passages;

the air conduit fluidly coupled with and between the compressor section and the one or more internal passages.