초록 ▼

An airfoil for a stator vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I is provided. The profile is carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y

An airfoil for a stator vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I is provided. The profile is carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform.

대표청구항 ▼

What is claimed is: 1. An airfoil for a stator vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I carried only to four decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are

What is claimed is: 1. An airfoil for a stator vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I carried only to four decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform. 2. An airfoil in accordance with claim 1 wherein said airfoil comprises a ninth stage of a compressor. 3. An airfoil in accordance with claim 1 wherein said airfoil profile lies in an envelope within +/-0.160 inches in a direction normal to any airfoil surface location. 4. An airfoil in accordance with claim 1 wherein said airfoil profile facilitates optimizing an aerodynamic efficiency of said airfoil. 5. An airfoil in accordance with claim 1 in combination with a base extending integrally from said platform, said airfoil being formed via a casting process. 6. A compressor comprising at least one row of stator vanes wherein each of said stator vanes comprises a base and an airfoil extending therefrom, at least one of said airfoils having an airfoil shape, said airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I carried only to three decimal places wherein Z is a distance from an upper surface of said base from which said airfoil extends and X and Y are coordinates defining the profile at each distance Z from said base. 7. A compressor in accordance with claim 6 wherein each said airfoil shape is defined by the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape. 8. A compressor in accordance with claim 6 wherein said at least one airfoil further comprises a coating extending upon said at least one airfoil, said coating having a thickness of about 0.100 inches or less. 9. A compressor in accordance with claim 6 wherein said at least one row of stator vanes comprises a ninth stage of said compressor. 10. A compressor in accordance with claim 6 wherein said airfoil profile lies in an envelope within +/-0.160 inches in a direction normal to any airfoil surface location. 11. A compressor in accordance with claim 6 wherein said airfoil shape facilitates improving an operating efficiency of said compressor. 12. A compressor in accordance with claim 6 wherein said airfoil shape facilitates optimizing an aerodynamic efficiency of said airfoil. 13. A compressor in accordance with claim 6 wherein each said stator vane base is cast integrally with a respective one of said airfoils. 14. A stator assembly comprising at least one stator vane comprising a base and an airfoil extending from said base, wherein said airfoil comprises an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I carried only to three decimal places wherein Z is a distance from an upper surface of said from which said airfoil extends and X and Y are coordinates defining the profile at each distance Z from said base, said profile scalable by a predetermined constant n and manufacturable to a predetermined manufacturing tolerance. 15. A stator assembly in accordance with claim 14 wherein said predetermined manufacturing tolerance is about ��0.160 inches. 16. A stator assembly in accordance with claim 14 wherein said stator assembly forms a portion of a compressor, said stator assembly comprises a portion of a ninth stage of the compressor. 17. A stator assembly in accordance with claim 14 further comprising a coating upon said airfoil, said coating having a thickness of about 0.100 inches or less.