Gas turbine blade configuration
AssigneeSiemens Energy, Inc.
InventorsEric Munoz, Edwin Lee Kite, Robert J. McClelland, Charles M. Evans
Life of this patent
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Abstract
A gas turbine engine blade (22), including an airfoil substrate (10) having an exterior surface, wherein: a base (14) of the airfoil substrate is located at a 0% radial on an inner platform surface (20) and a tip (16) of the airfoil substrate is located at a 100% radial; wherein at the 0% radial a cross-sectional profile of the exterior surface is substantially characterized by nominal X and Y coordinates present in Table 1; and wherein at a 50% radial location a cross-sectional profile of the exterior surface is characterized by nominal X and Y coordinates present in Table 6.
Claims20
A gas turbine engine blade, comprising:
- an airfoil substrate comprising an exterior surface, wherein a base of the airfoil substrate is located at a 0% radial on an inner platform surface and a tip of the airfoil substrate is located at a 100% radial,
- wherein at the 0% radial a cross-sectional profile of the exterior surface is substantially characterized by nominal X and Y coordinates present in Table 1, and
- wherein at a 50% radial location a cross-sectional profile of the exterior surface is characterized by nominal X and Y coordinates present in Table 6.
A gas turbine engine blade, comprising:
- an airfoil substrate comprising an exterior surface, wherein a base of the airfoil substrate is located at a 0% radial on an inner platform and a tip of the airfoil substrate is located at a 100% radial,
- wherein at the 0% radial a cross-sectional profile of the exterior surface is substantially characterized by nominal X and Y coordinates present in Table 1, and wherein a lowest nominal X value in Table 1 defines a 0% radial leading edge point and a 0% radial leading edge point nominal Y value;
- wherein at a 50% radial a cross-sectional profile of the exterior surface comprises a 50% radial leading edge point characterized by a lowest nominal X value in Table 6.
A gas turbine engine blade, comprising:
- an airfoil comprising an exterior surface, wherein a base of the airfoil is located at a 0% radial on an inner platform surface and a tip of the airfoil is located at a 100% radial,
- wherein at the 0% radial a cross-sectional profile of the exterior surface lies within a 0% radial envelope based on nominal X and Y coordinates present in Table 1,
- wherein at a 50% radial location a cross-sectional profile of the exterior surface lies within a 50% radial envelope based on nominal X and Y coordinates present in Table 6,
- wherein respective envelopes are defined by a respective nominal profile connecting respective nominal X and Y coordinates, minus an maximum inward variation of 0.015 inches inward from the respective nominal profile in a direction normal to the surface at that location, and plus a maximum outward variation of 0.060 inches outward from the respective nominal profile in a direction normal to the surface at that location.
Dependencies are inferred from the claim text.