초록

An airfoil suitable for use in a gas turbine engine having at least one feed passage at least in part defined along a feed axis which is at least perpendicular to a cavity axis to reduce dirt ingestion into a trailing edge passage.

대표청구항 ▼

1. An airfoil suitable for use in a gas turbine engine comprising: an airfoil which defines an internal cavity along a cavity axis, said internal cavity in communication with a trailing edge passage through at least one feed passage, said at least one feed passage at least in part defined along a fe

1. An airfoil suitable for use in a gas turbine engine comprising: an airfoil which defines an internal cavity along a cavity axis, said internal cavity in communication with a trailing edge passage through at least one feed passage, said at least one feed passage at least in part defined along a feed axis which is at least perpendicular to said cavity axis, wherein said feed axis defines an acute angle relative to said cavity axis; andwherein said at least one feed passage is raked in a direction opposite a particle direction generally within said internal cavity. 2. The airfoil as recited in claim 1, further comprising an exit from said internal cavity to eject said particle from said internal cavity. 3. The airfoil as recited in claim 1, wherein said cavity axis is defined generally along a length of the airfoil which extends radially from an engine axis. 4. The airfoil as recited in claim 1, wherein said airfoil is a rotary airfoil. 5. The airfoil as recited in claim 1, wherein said airfoil is a static airfoil. 6. The airfoil as recited in claim 1, where said at least one feed passage is twisted along an axis thereof. 7. The airfoil as recited in claim 1, wherein said at least one feed passage comprises a feed passage entrance defined along said feed axis, and wherein said at least one feed passage extends from said feed passage entrance in a direction generally toward a platform of said airfoil to define said acute angle. 8. The airfoil as recited in claim 7, wherein, at a point downstream of said feed passage entrance, said at least one feed passage extends toward said trailing edge passage in a direction generally toward a tip of said airfoil. 9. The airfoil as recited in claim 8, wherein said at least one feed passage extends from said feed passage entrance toward said trailing edge. 10. The airfoil as recited in claim 9, wherein said airfoil includes said platform, a tip opposite of said platform, an airfoil portion between said platform and said tip, and a root supporting said platform. 11. A method of reducing dirt ingestion into a trailing edge passage for an airfoil suitable for use in a gas turbine engine comprising: arranging at least one feed passage in communication with a trailing edge passage within an airfoil, the at least one feed passage at least partially defined along a feed axis, the feed axis at least perpendicular to a cavity axis defined by an internal cavity in communication with the at least one feed passage;arranging the feed axis at an acute angle relative to the cavity axis; andtwisting the at least one feed passage between the internal cavity and the trailing edge passage. 12. A method as recited in claim 11, further comprising: arranging the at least one feed passage at an acute angle relative to the cavity axis. 13. A method as recited in claim 11, further comprising: arranging an entrance to the at least one feed passage transverse to the trailing edge passage. 14. A method as recited in claim 11, further comprising: at least partially supporting the trailing edge passage with a multiple of pedestals. 15. A method of manufacturing a trailing edge passage for an airfoil suitable for use in a gas turbine engine comprising: fabricating a refractory metal form to have a trailing edge passage section and at least one feed passage section;arranging the refractory metal form such that the at least one feed passage section is in communication with an internal cavity within a airfoil; andremoving the refractory metal form to fabricate a trailing edge passage with the trailing edge passage section and at least one feed passage with the at least one feed passage section, the internal cavity in communication with the trailing edge passage through the least one feed passage, the at least one feed passage at least in part defines a feed axis which is at least perpendicular to said cavity axis, wherein said feed axis defines an acute angle relative to said cavity axis; andtwisting the at least one feed passage section between the internal cavity and the trailing edge passage section. 16. The airfoil as recited in claim 15, wherein fabricating a refractory metal form further comprises: forming at least one aperture in the trailing edge passage section. 17. The method recited in claim 15, wherein said at least one feed passage comprises a feed passage entrance defined along said feed axis, and wherein said at least one feed passage extends from said feed passage entrance in a direction generally toward a platform of said airfoil to define said acute angle. 18. An airfoil suitable for use in a gas turbine engine comprising: an airfoil which defines an internal cavity along a cavity axis, said internal cavity in communication with a trailing edge passage through at least one feed passage, wherein said at least one feed passage is twisted between said internal cavity and said trailing edge passage, and wherein said feed axis defines an acute angle relative to said cavity axis. 19. The airfoil as recited in claim 18, wherein said at least one feed passage is twisted along an axis thereof. 20. The airfoil as recited in claim 18, wherein said at least one feed passage is twisted along a length thereof. 21. The airfoil as recited in claim 18, wherein said at least one feed passage comprises a feed passage entrance defined along said feed axis, and wherein said at least one feed passage extends from said feed passage entrance in a direction generally toward a platform of said airfoil to define said acute angle.