Airfoil profile for a turbine blade
An airfoil profile for a turbine blade of a gas turbine is provided. The turbine blade may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.
1. A turbine blade comprising:
an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1,
wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system,
wherein, at each Z distance, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections, and
wherein the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.
2. The turbine blade according to claim 1 , wherein the airfoil shape lies within an envelope of +/−0.120 inches measured in a direction normal to any of the plurality of airfoil profile sections.
3. The turbine blade according to claim 1 , wherein the airfoil shape lies within an envelope of +/−0.080 inches measured in a direction normal to any of the plurality of airfoil profile sections.
4. The turbine blade according to claim 1 , wherein the airfoil shape lies within an envelope of +/−0.020 inches measured in a direction normal to any of the plurality of airfoil profile sections.
5. The turbine blade according to claim 1 , wherein the X and Y coordinate values are scalable as a function of a same constant or number and a set of corresponding nominal Z coordinate values are scalable as a function of the same constant or number to provide at least one of a scaled up or a scaled down airfoil.
6. The turbine blade according to claim 5 , wherein the airfoil shape has an increased airfoil chord length at about 25% span portion of the airfoil to reduce airfoil loading at the section.
7. The turbine blade according to claim 1 , further comprising a coating applied to the airfoil shape, the coating having a thickness of less than or equal to 0.010 inches.
8. A turbine comprising:
a rotor disk configured to be rotatable; and
a plurality of turbine blades installed on the rotor disk,
wherein each of the turbine blade comprises an airfoil having a blade-shape extending from a platform to a blade tip and including a leading edge, a trailing edge, a pressure side extending from the leading edge to the trailing edge, and a suction side extending from the leading edge to the trailing edge,
wherein the turbine blade comprises an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1,
wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system,
wherein, at each Z distance, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections, and
wherein the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.
9. The turbine according to claim 8 , wherein the airfoil shape lies within an envelope of +/−0.120 inches measured in a direction normal to any of the plurality of airfoil profile sections.
10. The turbine according to claim 8 , wherein the airfoil shape lies within an envelope of +/−0.080 inches measured in a direction normal to any of the plurality of airfoil profile sections.
11. The turbine according to claim 8 , wherein the airfoil shape lies within an envelope of +/−0.020 inches measured in a direction normal to any of the plurality of airfoil profile sections.
12. The turbine according to claim 8 , wherein the X and Y coordinate values are scalable as a function of a same constant or number and a set of corresponding nominal Z coordinate values are scalable as a function of the same constant or number to provide at least one of a scaled up or a scaled down airfoil.
13. The turbine according to claim 12 , wherein the airfoil shape has an increased airfoil chord length at about 25% span portion of the airfoil to reduce airfoil loading at the section.
14. The turbine according to claim 8 , further comprising a coating applied to the airfoil shape, the coating having a thickness of less than or equal to 0.010 inches.
15. A gas turbine comprising:
a compressor configured to compress air;
a combustor configured to mix compressed air supplied from the compressor with fuel for combustion to generate combustion gas; and
a turbine comprising a plurality of turbine nozzles and a plurality of turbine blades rotated by the combustion gas to generate power,
wherein each of the turbine blades extending from a platform to a blade tip and having an airfoil-shaped cross section and including a leading edge, a trailing edge, a pressure side extending from the leading edge to the trailing edge, and a suction side extending from the leading edge to the trailing edge,
wherein the turbine blade comprises an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1,
wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system,
wherein, at each Z distance, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections, and
wherein the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.
16. The gas turbine according to claim 15 , wherein the airfoil shape lies within an envelope of +/−0.120 inches measured in a direction normal to any of the plurality of airfoil profile sections.
17. The gas turbine according to claim 15 , wherein the airfoil shape lies within an envelope of +/−0.080 inches measured in a direction normal to any of the plurality of airfoil profile sections.
18. The gas turbine according to claim 15 , wherein the airfoil shape lies within an envelope of +/−0.020 inches measured in a direction normal to any of the plurality of airfoil profile sections.
19. The gas turbine according to claim 15 , wherein the airfoil shape has an increased airfoil chord length at about 25% span portion of the airfoil to reduce airfoil loading at the section.
20. The gas turbine according to claim 15 , further comprising a coating applied to the airfoil shape, the coating having a thickness of less than or equal to 0.010 inches.