초록 ▼

A vane for use in a gas turbine engine has a leading edge facing an upstream combustor. The vane has hollow areas that receive an impingement tube for delivering impingement air. The impingement tube includes a radially outer portion and a radially inner portion. An end wall of the radially outer po

A vane for use in a gas turbine engine has a leading edge facing an upstream combustor. The vane has hollow areas that receive an impingement tube for delivering impingement air. The impingement tube includes a radially outer portion and a radially inner portion. An end wall of the radially outer portion is angled relative to a rotational axis of the turbine such that air entering the impingement tube from a radially outer source has dirt directed away from the leading edge. Thus, dirt is less likely to clog leading edge air supply holes. In one embodiment, the inner and outer portions are formed as separate pieces, and in another embodiment, the inner and outer portions are formed as a single piece.

대표청구항 ▼

What is claimed is: 1. A gas turbine engine comprising: at least one rotor for rotating about a central axis; at least one vane, said vane having a leading edge and a trailing edge, said vane receiving an impingement tube adjacent said leading edge, said impingement tube having a leading edge and a

What is claimed is: 1. A gas turbine engine comprising: at least one rotor for rotating about a central axis; at least one vane, said vane having a leading edge and a trailing edge, said vane receiving an impingement tube adjacent said leading edge, said impingement tube having a leading edge and an aft end spaced from said leading edge and towards said trailing edge of said vane; an outer air source for directing air from a radially outer location into said impingement tube, and an inner air source for directing air from a radially inner location into said impingement tube; and said impingement tube including a radially outer portion and a radially inner portion, with said radially inner portion receiving air from said inner air source and said radially outer portion receiving air from said outer air source, said radially inner and outer portions having impingement air holes for directing impingement air to a position adjacent said leading edge of said vane, and at least said radially outer portion being configured to direct a greater volume of impingement air toward said aft end of said vane than the volume directed toward said leading edge. 2. The gas turbine engine as set forth in claim 1, wherein said radially inner portion directs a greater volume of impingement airflow toward said leading edge of said vane than it does toward said aft end. 3. The gas turbine engine as set forth in claim 2, wherein both said radially outer and radially inner portions have end walls. 4. The gas turbine engine as set forth in claim 3, wherein said end wall of said radially outer portion being angled from said leading edge toward said aft end in a radially inner direction such that a leading edge of said radially outer portion is shorter than said aft end. 5. The gas turbine engine as set forth in claim 4, wherein said end wall of said radially inner portion being angled from said leading edge toward said aft end in a radially inner direction such that a leading edge of said radially inner portion is longer than a aft end. 6. The gas turbine engine as set forth in claim 5, wherein said end walls of said radially outer portion and said radially inner portion are generally parallel to each other. 7. The gas turbine engine as set forth in claim 4, wherein an angle between said end wall and said aft end of said radially outer portion is between 20�� and 60��. 8. The gas turbine engine as set forth in claim 1, wherein said radially outer portion and said radially inner portion are formed as separate pieces. 9. The gas turbine engine as set forth in claim 1, wherein said radially outer portion and said radially inner portion are formed as a single piece. 10. A turbine component comprising: a body having a leading edge and a trailing edge, said body having a radially outer edge and a radially inner edge; an impingement tube receiving within said body and including a radially outer portion and a radially inner portion, with said radially inner portion for receiving air from a radially inner source and said radially outer portion for receiving air from a radially outer source, said radially inner and outer portions having impingement air holes for directing impingement air to a position adjacent said leading edge of said body, and at least said radially outer portion being configured to direct a greater volume of impingement air to a aft end, spaced from said leading edge and in a direction toward said trailing edge of said body, than is directed toward said leading edge. 11. The turbine component as set forth in claim 10, wherein said body is a vane airfoil. 12. The turbine component as set forth in claim 11, wherein said radially inner portion directs a greater volume of impingement airflow toward said leading edge of said vane than it does toward said aft end. 13. The turbine component as set forth in claim 12, wherein both said radially outer and radially inner portions have end walls. 14. The turbine component as set forth in claim 13, wherein said end wall of said radially outer portion being angled from said leading edge toward said aft end in a radially inner direction such that said leading edge of said radially outer portion is shorter than said second end. 15. The turbine component as set forth in claim 14, wherein said end wall of said radially inner portion being angled from said leading edge toward said aft end in a radially inner direction such that said leading edge of said radially inner portion is longer than said aft end. 16. The turbine component as set forth in claim 15, wherein said end walls of said radially outer portion and said radially inner portion are generally parallel to each other. 17. The turbine component as set forth in claim 14, wherein an angle between said end wall and said second end of said radially outer portion is between 20�� and 60��. 18. The turbine component as set forth in claim 10, wherein said radially outer portion and said radially inner portion are formed as two separate pieces. 19. The turbine component as set forth in claim 10, wherein said radially outer portion and said radially inner portion are formed as a single piece. 20. A method of reducing dirt flow toward a leading edge of a hollow airfoil comprising the steps of: (1) providing a airfoil, and an impingement tube within said airfoil, with a radially outer impingement tube portion and a radially inner impingement tube portion, directing a radially outer air source into said radially outer impingement tube portion, and directing a radially inner source into said radially inner impingement tube portion; (2) shaping said outer impingement tube portion such that it minimizes dirt moving toward a leading edge of said radially outer impingement tube portion; and (3) directing air from said radially inner impingement tube portion and said radially outer impingement tube portion through impingement air holes toward a leading edge of said airfoil. 21. The method as set forth in claim 20, wherein an end wall of said radially outer impingement tube portion is shaped such that a greater volume of airflow is directed from said radially outer source to a aft end of said radially outer impingement tube portion that is spaced toward a trailing edge of said air foil, than is directed to said leading edge.