Turbine blade tip dirt removal feature

1. A gaspath component for a gas turbine engine comprising:

a platform;

a body extending outward from the platform and including at least one internal cooling passage, the at least one internal cooling passage includes at least one particulate redirection feature defined at an end of the body opposite the platform;

the at least one particulate redirection feature having a chevron cross section including a first face oblique to and facing an expected flow of fluid through the at least one internal cooling passage and a second face oblique to and facing the expected flow of fluid through the at least one internal cooling passage, the first and second faces joining at a point and defining at least one corresponding opening;

wherein the point is the upstream most position of the particulate redirection feature relative to the expected flow of fluid through the at least one internal cooling passage; and

wherein the at least one corresponding opening includes an opening to a squealer tip pocket of the body or an opening to a tip shelf of the body.

2. The gaspath component of claim 1 , wherein the first face defines an angle of at least 15 degrees relative to the expected flow of fluid.

3. The gaspath component of claim 1 , wherein the at least one particulate redirection feature is integral to the body.

4. The gaspath component of claim 1 , wherein the first face is a planar surface.

5. The gaspath component of claim 1 , wherein the at least one corresponding opening includes the opening to the squealer tip pocket of the body.

6. The gaspath component of claim 1 , wherein the at least one corresponding opening includes the opening to the tip shelf of the body.

7. The gaspath component of claim 1 , wherein the second face is configured to redirect particulate to a second opening of the at least one corresponding opening.

8. The gaspath component of claim 1 , wherein the particulate redirection feature is disposed at a radially outermost tip of the body.

9. The gaspath component of claim 1 , wherein the particulate redirection feature is inset from a radially outermost tip of the body.

10. The gas turbine engine of claim 1 , wherein the body is a rotor blade.

11. A gas turbine engine comprising:

a compressor section;

a combustor section fluidly connected to the compressor section;

a turbine section fluidly connected to the compressor section and including a plurality of turbine stages; and

a rotor body disposed in one of said turbine stages, the rotor body including at least one internal cooling passage, the at least one internal cooling passage includes at least one particulate redirection feature defined at an end of the body opposite a platform and the at least one particulate redirection feature having a chevron cross section including a first face oblique to and facing an expected fluid flow direction through the at least one internal cooling passage and a second face oblique to and facing the expected fluid flow direction, the first and second faces joining at a point and defining at least one corresponding opening;

wherein the point is the upstream most position of the particulate redirection feature relative to the expected flow of fluid through the at least one internal cooling passage; and

%wherein the at least one corresponding opening includes an opening to a squealer tip pocket of the body or an opening to a tip shelf of the body.

12. The gas turbine engine of claim 11 , wherein the rotor body is a turbine blade of a high pressure turbine in said turbine section.

13. The gas turbine engine of claim 12 , wherein the rotor body is a first stage turbine blade of the high pressure turbine in said turbine section.