Gas turbine airfoil
First Claim
1. A gas turbine engine component comprising:
- a root and a tip separated along a longitudinal axis;
an airfoil portion having a leading edge, a trailing edge, an external suction side wall, and an external pressure side wall, the external walls extending between said leading edge and said trailing edge, said external walls enclosing a central cavity for the passage of cooling air between the root and the tip;
at least one longitudinally extending first web connecting said suction side wall with said pressure side wall, said at least one first web partitioning said cavity into a leading edge region and a trailing edge region and defining a leading edge chamber in the leading edge region;
a second longitudinally extending web connecting said at least one first web with the suction side wall and defining a first entry chamber on the suction side of the second web and a second entry chamber for cooling air in the trailing edge region;
wherein said at least one first web comprises at least one cross-over hole between the first entry chamber and the leading edge chamber, and wherein the second web is devoid of openings;
wherein the at least one cross-over hole in the at least one first web between the first entry chamber and the leading edge chamber comprises a longitudinally extending row of holes, and wherein the cross-sectional area of the holes of said row is larger in a region of the tip than in a region of the root.
3 Assignments
0 Petitions
Accused Products
Abstract
A turbine component (25) includes a root (21), a tip (22), and an airfoil portion (7) having a leading and a trailing edge (8,9), an external suction side and pressure side wall (13, 14) between the leading and trailing edge. The walls enclose a central cavity (1-6) for the passage of cooling air, the cavity being partitioned into a leading edge- and a trailing edge region (7a, 7b) by at least one longitudinally extending first web (15) connecting the suction side wall with the pressure side wall and a second longitudinally extending web (16), connecting the first web with the suction side wall, thereby defining a first and second entry chamber (2, 3). The first web (15) is provided with at least one cross-over hole (H1) between the first entry chamber and the leading edge chamber (1), whereas the second web has no openings.
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Citations
36 Claims
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1. A gas turbine engine component comprising:
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a root and a tip separated along a longitudinal axis; an airfoil portion having a leading edge, a trailing edge, an external suction side wall, and an external pressure side wall, the external walls extending between said leading edge and said trailing edge, said external walls enclosing a central cavity for the passage of cooling air between the root and the tip; at least one longitudinally extending first web connecting said suction side wall with said pressure side wall, said at least one first web partitioning said cavity into a leading edge region and a trailing edge region and defining a leading edge chamber in the leading edge region; a second longitudinally extending web connecting said at least one first web with the suction side wall and defining a first entry chamber on the suction side of the second web and a second entry chamber for cooling air in the trailing edge region; wherein said at least one first web comprises at least one cross-over hole between the first entry chamber and the leading edge chamber, and wherein the second web is devoid of openings; wherein the at least one cross-over hole in the at least one first web between the first entry chamber and the leading edge chamber comprises a longitudinally extending row of holes, and wherein the cross-sectional area of the holes of said row is larger in a region of the tip than in a region of the root. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28, 29, 30, 31, 32, 33, 34, 35, 36)
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Specification