초록

A blade includes an airfoil having a base and a free, tip end. The tip end includes at least one porous, abradable element.

대표청구항 ▼

1. A blade comprising: an airfoil including a base and a free, tip end, the tip end including at least one porous, abradable element that includes a honeycomb that has cell walls that are tapered in wall thickness. 2. The blade as recited in claim 1, wherein the tip end includes a platform and the a

1. A blade comprising: an airfoil including a base and a free, tip end, the tip end including at least one porous, abradable element that includes a honeycomb that has cell walls that are tapered in wall thickness. 2. The blade as recited in claim 1, wherein the tip end includes a platform and the at least one porous, abradable element is on the platform. 3. The blade as recited in claim 2, wherein the at least one porous, abradable element includes a first porous, abradable element and a second porous, abradable element that define sides of a channel, with the platform defining a bottom of the channel and the channel having an open top opposite the bottom. 4. The blade as recited in claim 1, wherein the at least one porous, abradable element includes a random array of pores. 5. The blade as recited in claim 1, wherein the at least one porous, abradable element includes geometric pores. 6. The blade as recited in claim 1, wherein the at least one porous, abradable element includes a first porous, abradable element and a second porous, abradable element spaced apart from the first porous, abradable element. 7. The blade as recited in claim 6, wherein the first porous, abradable element and the second porous, abradable element are elongated along the same direction and offset from each other along the direction. 8. The blade as recited in claim 1, wherein the at least one porous, abradable element has a first composition and the airfoil has a second composition that is equivalent to the first composition. 9. The blade as recited in claim 1, wherein the at least one porous, abradable element has a first composition and the airfoil has a second composition that is different than the first composition. 10. The blade as recited in claim 1, wherein the cell walls taper away from the tip. 11. The blade as recited in claim 1, wherein the tip end includes a platform and the at least one porous, abradable element is on the platform, and the cell walls have a thicker base at the platform that tapers to a thinner portion at a distal end thereof. 12. A turbine engine comprising: optionally, a fan;a compressor section;a combustor in fluid communication with the compressor section; anda turbine section in fluid communication with the combustor, the turbine section being coupled to drive the compressor section and the fan, andat least one of the fan, the compressor section and the turbine section including a plurality of blades, each of the plurality of blades having an airfoil including a base and a free, tip end, the tip end including at least one porous, abradable element that includes a honeycomb that has cell walls that are tapered in wall thickness. 13. The turbine engine as recited in claim 12, further including a static shroud extending circumferentially around the plurality of blades adjacent the porous, abradable elements, and the static shroud includes at least one edge extending circumferentially and radially inwardly toward the porous, abradable elements. 14. The turbine engine as recited in claim 13, wherein the at least one edge is circumferentially continuous over multiple ones of the plurality of blades. 15. A method for processing a blade, the method comprising: depositing multiple layers of a powdered metal onto one another;joining the layers to one another with reference to data relating to a particular cross-section of a blade; andproducing the blade with an airfoil including a base and a free, tip end, the tip end including at least one porous, abradable element that includes a honeycomb that has cell walls that are tapered in wall thickness. 16. A method for processing a blade, the method comprising: providing a blade having an airfoil including a base and a free, tip end; andforming at the tip end at least one porous, abradable element that includes a honeycomb that has cell walls that are tapered in wall thickness. 17. The method as recited in claim 16, further including, prior to the forming, removing a prior porous, abradable element from the tip end. 18. The method as recited in claim 17, wherein the removing includes machining the tip end to form a flat surface. 19. The method as recited in claim 18, wherein the forming includes forming the at least one porous, abradable element on the flat surface. 20. The method as recited in claim 16, wherein the forming includes depositing multiple layers of a powdered metal on to one another and joining the layers to one another with reference to data relating to a particular cross-section of the at least one porous, abradable element.