Gas turbine airfoil with leading edge cooling
First Claim
1. A gas turbine airfoil comprising:
- a pressure sidewall and a suction sidewall defining and extending from a root to a tip and from a leading edge region to a trailing edge;
at least one cooling passage between the pressure sidewall and the suction sidewall configured and arranged to permit cooling air to pass through and cool the airfoil from within;
wherein at least one of the at least one cooling passage extends along the leading edge of the airfoil;
a plurality of film cooling holes extending from the at least one cooling passage along the leading edge region to the outer surface of the leading edge region, the plurality of film cooling holes each having a shape that is diffused in a radial outward direction of the leading edge of the airfoil at least over a part of the length of the film cooling hole;
wherein the plurality of film cooling holes each comprise a principal axis and a shape that is asymmetrically diffused, said shape being diffused in the radial outward direction from the principal axis along a forward inclination axis, and additionally diffused in a second lateral direction from the principal axis along a lateral inclination axis; and
wherein the shape is diffused cylindrically in the radial outward direction along the forward inclination axis and in the second lateral direction along a lateral inclination axis.
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Accused Products
Abstract
A gas turbine airfoil (1) includes a pressure sidewall (15) and a suction sidewall (16), extending from a root to a tip and from a leading edge region to a trailing edge and having at least one cooling passage between the pressure sidewall (15) and the suction sidewall (16) for cooling air to pass through and cool the airfoil from within. One or several of the cooling passages (3) extend along the leading edge of the airfoil (1) and several film cooling holes (1,2) extend from the internal cooling passages (3) along the leading edge region to the outer surface of the leading edge region. The film cooling holes (1,2) each have a shape that is diffused in a radial outward direction of the leading edge of the airfoil (1) at least over a part of the length of the film cooling hole (1,2). Improved cooling in the leading edge region can be achieved because the cooling holes (1, 2) have a principal axis (17), and the shape is asymmetrically diffused in that it is diffused in the radial outward direction from the principal axis (17) along a forward inclination axis (20), and it is additionally diffused in a second lateral direction from the principal axis (17) along a lateral inclination axis (21).
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Citations
24 Claims
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1. A gas turbine airfoil comprising:
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a pressure sidewall and a suction sidewall defining and extending from a root to a tip and from a leading edge region to a trailing edge; at least one cooling passage between the pressure sidewall and the suction sidewall configured and arranged to permit cooling air to pass through and cool the airfoil from within; wherein at least one of the at least one cooling passage extends along the leading edge of the airfoil; a plurality of film cooling holes extending from the at least one cooling passage along the leading edge region to the outer surface of the leading edge region, the plurality of film cooling holes each having a shape that is diffused in a radial outward direction of the leading edge of the airfoil at least over a part of the length of the film cooling hole; wherein the plurality of film cooling holes each comprise a principal axis and a shape that is asymmetrically diffused, said shape being diffused in the radial outward direction from the principal axis along a forward inclination axis, and additionally diffused in a second lateral direction from the principal axis along a lateral inclination axis; and wherein the shape is diffused cylindrically in the radial outward direction along the forward inclination axis and in the second lateral direction along a lateral inclination axis. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22)
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23. A method for producing cooling holes in an airfoil, the method comprising:
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drilling a cylindrical, fully penetrating hole defining a principal axis and a cylindrical section; and subsequently performing two cylindrical drillings along a lateral inclination axis and along a forward inclination axis from the outer side of the airfoil. - View Dependent Claims (24)
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Specification