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A gas turbine engine component includes a pressurized fluid source, an airfoil, and a seal member for selectively providing sealing at an end of the airfoil. The seal member includes a stowed position for non-sealing and a deployed position for sealing. The seal member is operatively connected with

A gas turbine engine component includes a pressurized fluid source, an airfoil, and a seal member for selectively providing sealing at an end of the airfoil. The seal member includes a stowed position for non-sealing and a deployed position for sealing. The seal member is operatively connected with a pressurized fluid source for moving the seal member between the stowed position and the deployed position.

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1. A gas turbine engine component comprising: a fluid passage for providing a pressurized fluid;an airfoil; anda seal member for selectively providing sealing at an end of the airfoil, the seal member having a stowed position for non-sealing and a deployed position for sealing, wherein the seal memb

1. A gas turbine engine component comprising: a fluid passage for providing a pressurized fluid;an airfoil; anda seal member for selectively providing sealing at an end of the airfoil, the seal member having a stowed position for non-sealing and a deployed position for sealing, wherein the seal member is operatively connected with the fluid passage for moving the seal member between the stowed position and the deployed position, wherein the seal member is formed from a ceramic material, a metal alloy material, or a composite material, wherein the seal member is a substantially planar plate, wherein the plate includes a thickness, a width that is greater than the thickness at all points along the plate, and a length that is greater than the width, wherein the width varies along the length. 2. The gas turbine engine component as recited in claim 1, wherein the fluid passage comprises an internal cooling passage within the airfoil. 3. The gas turbine engine component as recited in claim 1, wherein the end of the airfoil includes a pocket having the seal. 4. The gas turbine engine component as recited in claim 3, wherein the pocket includes a floor, side walls, and an open side. 5. The gas turbine engine component as recited in claim 4, wherein the seal member includes a first surface corresponding to the floor and a second surface corresponding to the open side of the pocket, and a portion of the second surface comprises a seal surface. 6. The gas turbine engine component as recited in claim 1, wherein the thickness varies along the length. 7. The gas turbine engine component as recited in claim 1, wherein the seal member comprises a wedge. 8. The gas turbine engine component as recited in claim 1, wherein the seal member is silicon nitride. 9. The gas turbine engine component as recited in claim 1, wherein the seal member is a nickel-based alloy. 10. The gas turbine engine component as recited in claim 1, wherein the seal member is a ceramic matrix composite. 11. The gas turbine engine component as recited in claim 1, wherein the seal member includes a protective coating. 12. The gas turbine engine component as recited in claim 11, wherein the protective coating includes at least one of titanium dioxide or carbide. 13. A gas turbine engine component comprising; a fluid passage for providing a pressurized fluid;an airfoil; anda seal member for selectively providing sealing at an end of the airfoil, the seal member having a stowed position for non-sealing and a deployed position for sealing, wherein the seal member is operatively connected with the fluid passage for moving the seal member between the stowed position and the deployed position, wherein the end of the airfoil includes a pocket having the seal, wherein the pocket includes a floor, sidewalls, and an open side, wherein at least one of the side walls includes a surface that forms a non-perpendicular angle with the floor. 14. A gas turbine engine component comprising; a fluid passage for providing pressurized fluid;an airfoil; anda seal member for selectively providing sealing at an end of the airfoil, the seal member having a stowed position for non-sealing and a deployed position for sealing, wherein the seal member is operatively connected with the fluid passage for moving the seal member between the stowed position and the deployed position, wherein the seal member includes internal cooling passages. 15. A gas turbine engine component comprising: a fluid passage for providing a pressurized fluid;an airfoil; anda seal member for selectively providing sealing at an end of the airfoil, the seal member having a stowed position for non-sealing and a deployed position for sealing, wherein the seal member is operatively connected with the fluid passage for moving the seal member between the stowed position and the deployed position, wherein the seal member includes seal side walls and a seal wall connecting the seal side walls, the seal side walls and the seal wall forming a cavity that opens to an open side of the seal member. 16. A gas turbine engine component comprising: a fluid passage for providing pressurized fluid;an airfoil; anda seal member for selectively providing sealing at an end of the airfoil, the seal member having a stowed position for non-sealing and a deployed position for sealing, wherein the seal member is operatively connected with the fluid passage for moving the seal member between the stowed position and the deployed position, the seal member comprises a wedge, the wedge includes a first seal surface and a second seal surface that form an acute angle. 17. The gas turbine engine of claim 16, further including a pocket located near an axial end of the airfoil, wherein a wedge surface which engages a sloped wall of the pocket. 18. A method of providing sealing, comprising: selectively moving a seal member relative to an end of an airfoil between a stowed position for non-sealing and a deployed position for sealing, wherein the seal member comprises a wedge including a first seal surface and a second seal surface that form an acute angle. 19. The method as recited in claim 18, further including fluidly connecting the seal member with a pressurized fluid source for moving the seal member between the stowed position and the deployed position. 20. The method as recited in claim 18, further including moving the seal member using cooling fluid from an internal cooling passage of the airfoil.