TURBINE BLADE HAVING FILM COOLING HOLE ARRANGEMENT
First Claim
1. A turbine blade comprising:
- a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides;
an airfoil that extends radially outwardly from the platform to a free tip end, the airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides; and
a root that extends radially inwardly from the platform, andthe platform and the airfoil include film cooling holes having external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).
3 Assignments
0 Petitions
Accused Products
Abstract
A turbine blade includes a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides. An airfoil extends radially outwardly from the platform to a free tip end. The airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides. A root extends radially inwardly from the platform. The platform and the airfoil include film cooling holes arranged in substantial conformance with the Cartesian coordinates set forth in Table 1 herein. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).
15 Citations
16 Claims
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1. A turbine blade comprising:
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a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides; an airfoil that extends radially outwardly from the platform to a free tip end, the airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides; and a root that extends radially inwardly from the platform, and the platform and the airfoil include film cooling holes having external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm). - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A gas turbine engine comprising:
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a compressor section; a combustor fluidly connected to the compressor section; a turbine section fluidly connected to the combustor, the turbine section includes an array of turbine blades, each turbine blade comprising; a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides; an airfoil that extends radially outwardly from the platform to a free tip end, the airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides; and a root that extends radially inwardly from the platform, and the platform and the airfoil include film cooling holes having external breakout points that are located in substantial conformance with to the Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm). - View Dependent Claims (10, 11, 12, 13, 14, 15, 16)
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Specification