Blade outer air seal with cored passages

1. A blade outer air seal for a gas turbine engine, comprising:

a wall extending between a forward hook and an aft hook, wherein the forward and aft hooks are adapted to mount the blade outer air seal to a casing of the gas turbine engine;

wherein the wall includes at least a cored passage extending along at least a portion thereof, and wherein the cored passage extends radially and axially along a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook, and wherein the cored passage and the one or more apertures are configured to direct air from a first cavity to a second cavity, and wherein the first cavity is at least partially defined by the casing and disposed between the casing and the blade outer air seal, and wherein the second cavity is at least partially defined by a stator vane adjacent to the aft hook and disposed between the casing and the stator vane, and wherein the first cavity communicates with a first cooling air source and the second cavity communicates with a second cooling air source that is different from the first cooling air source.

2. The blade outer air seal of claim 1 , wherein the cored passage comprises one or more crossover passages, and wherein each crossover passage communicates through one or more inlets at an outer diameter surface of an in-line portion of the cored passage.

3. The blade outer air seal of claim 2 , wherein the inlet of the one or more crossover passages is located at a position minimizing impact to low cycle fatigue of the blade outer air seal during operation of the gas turbine engine.

4. The blade outer air seal of claim 2 , wherein the one or more crossover passages communicate with a plenum which extends laterally through the aft hook, and wherein the plenum communicates with the one or more apertures disposed along the trailing edge of the aft hook.

5. The blade outer air seal of claim 1 , wherein the cored passage extends substantially an entire length of the wall from adjacent the forward hook to the aft hook.

6. The blade outer air seal of claim 1 , wherein the cored passage has at least one of a convective zone and an impingement zone.

7. The blade outer air seal of claim 6 , wherein the impingement zone includes at least one of a plurality of radially extending passages through the wall and a cover plate with a plurality of radially extending holes therethrough.

8. The blade outer air seal of claim 6 , wherein the cored passage has a convective zone that has at least one of an augmentation surface and a flow turbulator feature.

9. The blade outer air seal of claim 8 , wherein the flow turbulator feature comprises a sinuously curved section of the cored passage.

10. The blade outer air seal of claim 1 , wherein the cored passage communicates with a cored cavity within the wall between the forward hook and the aft hook.

11. The blade outer air seal of claim 10 , wherein an impingement zone or augmentation surface is disposed within the cored cavity.

12. A turbine section of a gas turbine engine, comprising:

an engine casing;

a rotor blade disposed radially inward of the engine casing with respect to a centerline axis of the gas turbine engine;

a blade outer air seal having a wall extending between a forward hook and an aft hook, wherein the forward and aft hooks are adapted to mount the blade outer air seal to the engine casing to dispose the wall between the engine casing and the rotor blade, and wherein the wall includes a cored passage extending substantially an entire length of the wall from adjacent the forward hook to adjacent the aft hook;

a stator vane disposed axially aft of the rotor blade;

a first cavity that is at least partially defined by the engine casing and disposed between the engine casing and the blade outer air seal, wherein the first cavity communicates with a first cooling air source;

a second cavity that is at least partially defined by the stator vane and disposed between the engine casing and the stator vane, wherein the second cavity communicates with a second cooling air source that is different from the first cooling air source, and wherein the cored passage is configured to direct air from the first cavity to the second cavity.

13. The turbine section of claim 12 , further comprising:

one or more conformal seals disposed between the trailing edge of the blade outer air seal and the stator vane, and wherein one or more apertures that communicate with the cored passage are disposed radially outward of the conformal seals with respect to the centerline axis of the gas turbine engine.

14. The turbine section of claim 12 , wherein the cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.

15. The turbine section of claim 14 , wherein the cored passage comprises one or more crossover passages, and wherein each crossover passage communicates through one or more inlets at an outer diameter surface of an in-line portion of the cored passage.

16. The turbine section of claim 14 , wherein the one or more crossover passages communicate with a plenum which extends laterally through the aft hook, and wherein the plenum communicates with the one or more apertures disposed along the trailing edge of the aft hook.

17. The turbine section of claim 12 , wherein the cored passage includes at least one of a convective zone and an impingement zone.

18. A gas turbine engine comprising:

a compressor section comprising:

a high pressure stage; and

an intermediate pressure stage, wherein the high pressure stage operates at a pressure higher than the intermediate stage; and

a turbine section comprising:

an engine casing at least partially defining a first cavity, wherein the first cavity is configured to receive cooling air from the high pressure stage;

a rotor blade disposed radially inward of the engine casing with respect to a centerline axis of the gas turbine engine;

a stator vane disposed axially aft of the rotor blade and at least partially defining a second cavity, wherein the second cavity is disposed between the engine casing and the stator vane, and wherein the second cavity is configured to receive cooling air from the intermediate pressure stage; and

a blade outer air seal with a wall extending between a forward hook and an aft hook, wherein the forward and aft hooks are adapted to mount the blade outer air seal to the engine casing to dispose the wall between the engine casing and the rotor blade, and wherein the first cavity is disposed between the engine casing and the blade outer air seal;

wherein the wall includes a cored passage extending along at least a portion thereof, wherein the cored passage communicates with a cored cavity within the wall between the forward hook and the aft hook, and wherein the cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook, and wherein the cored passage is configured to direct air from the first cavity to the second cavity.

19. The gas turbine engine of claim 18 , wherein the cored passage comprises one or more crossover passages, and wherein each crossover passage communicates through one or more inlets at an outer diameter surface of an in-line portion of the cored passage.

20. The gas turbine engine of claim 18 , further comprising:

one or more conformal seals disposed between the trailing edge of the blade outer air seal and the stator vane, and wherein the one or more apertures which communicate with the cored passage are disposed radially outward of the conformal seals with respect to the centerline axis of the gas turbine engine.