Turbine engine component and method of cooling

1. A turbine engine comprising:

a core comprising a compressor section, a combustion section, and a turbine section, which are axially arranged to define a combustion air flow path passing through the core;

a casing surrounding the core;

an annulus defined between the core and the casing;

a cooling air flow path passing through at least one of the core and the casing;

an annular isolation chamber at least partially surrounding the core and formed in the cooling air flow path, with the isolation chamber at least partially fluidly isolated from the annulus; and

a cyclone separator having a cooling air inlet fluidly coupled to the cooling air flow path, a clean air outlet fluidly coupled to the isolation chamber, and a scavenge outlet fluidly coupled to the cooling air flow path.

2. The turbine engine of claim 1 further comprising a barrier wall located within the cooling air flow path and at least partially forming the isolation chamber.

3. The turbine engine of claim 2 wherein the barrier wall comprises a perforated baffle.

4. The turbine engine of claim 1 wherein the cyclone separator is located within the isolation chamber.

5. The turbine engine of claim 1 wherein at least one of the compressor section and turbine section comprises an airfoil having at least one of an outer band or an inner band at least partially forming the isolation chamber.

6. The turbine engine of claim 5 wherein the airfoil further comprises an interior cooling passage fluidly coupled to the clean air outlet of the cyclone separator.

7. The turbine engine of claim 5 further comprising a barrier wall located within the cooling air flow path and cooperating with the at least one of the outer band or inner band to collectively form at least part of the isolation chamber.

8. The turbine engine of claim 7 wherein the barrier wall abuts the inner band and the cooling air flow path passes through the core.

9. The turbine engine of claim 8 wherein the airfoil is part of a nozzle within the turbine section.

10. The turbine engine of claim 9 wherein the inner band is supported by the casing which, in combination with the inner band and barrier wall, at least partially defines the isolation chamber.

11. The turbine engine of claim 5 further comprising a barrier wall extending between the casing and the outer band to form at least part of the isolation chamber.

12. The turbine engine of claim 1 wherein the casing comprises a frame and a hanger that define an interstitial space that at least partially forms the cooling air flow path.

13. The turbine engine of claim 12 further comprising a barrier wall extending between the frame and the hanger to at least partially define the isolation chamber.

14. The turbine engine of claim 1 wherein the casing comprises a combustor casing and a turbine casing, wherein the cyclone separator is mounted to a dedicated hanger secured to at least one of the combustor casing and the turbine casing.

15. The turbine engine of claim 14 wherein the dedicated hanger at least partially defines the isolation chamber.

16. The turbine engine of claim 15 wherein the isolation chamber is fluidly coupled to an interior of an airfoil forming part of a nozzle in the turbine section.

17. The turbine engine of claim 1 further comprising multiple cyclone separators having corresponding clean air outlets fluidly coupled to the isolation chamber.

18. A turbine engine component comprising:

a body having a wall separating a combustion air flow path from a cooling air flow path, the body comprising an airfoil body extending between an inner band and an outer band;

an isolation chamber formed in the cooling air flow path and fluidly isolated from the cooling air flow path, with at least one of the inner band or the outer band at least partially defining the isolation chamber; and

at least one cyclone separator having a cooling air inlet fluidly coupled to the cooling air flow path, a clean air outlet fluidly coupled to the isolation chamber, and a scavenge outlet.

19. The turbine engine component of claim 18 wherein the at least one cyclone separator further comprises multiple cyclone separators having corresponding clean air outlets fluidly coupled to the isolation chamber.

20. The turbine engine component of claim 18 wherein the isolation chamber is fluidly coupled to an interior of the airfoil body.

21. The turbine engine component of claim 18 , further comprising a nozzle support coupled to the inner band and at least partially defining the isolation chamber.

22. The turbine engine component of claim 21 , further comprising a perforated baffle positioned between the nozzle support and the inner band and at least partially defining the isolation chamber.

23. A turbine engine comprising:

a core comprising a compressor section, a combustion section, and a turbine section, which are axially arranged to define a combustion air flow path passing through the core;

a casing surrounding the core and comprising a frame and a hanger that define an interstitial space therebetween;

an annulus defined between the core and the casing;

a cooling air flow path passing through at least one of the core, the casing, and the interstitial space;

a barrier wall in the cooling air flow path extending between the frame and the hanger to at least partially define an isolation chamber, with the isolation chamber at least partially fluidly isolated from the annulus; and

a cyclone separator having a cooling air inlet fluidly coupled to the cooling air flow path, a clean air outlet fluidly coupled to the isolation chamber, and a scavenge outlet fluidly coupled to the cooling air flow path.

24. The turbine engine of claim 23 wherein the isolation chamber is fluidly coupled to an interior of an airfoil.

25. The turbine engine of claim 24 wherein the airfoil forms part of a nozzle in the turbine section.