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A turbine rotor for an Air Cycle Machine includes a hub with a multiple turbine blades which extend therefrom, each of the multiple of turbine blades defined by a set of coordinates.

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1. A turbine rotor for an Air Cycle Machine comprising: a hub with a multiple turbine blades which extend therefrom, each of said multiple of turbine blades defined by a set of X-coordinates, Y-coordinates and Z-coordinates in any of Table B-1 and B-2 scaled by a desired factor or Table S-1 and S-2

1. A turbine rotor for an Air Cycle Machine comprising: a hub with a multiple turbine blades which extend therefrom, each of said multiple of turbine blades defined by a set of X-coordinates, Y-coordinates and Z-coordinates in any of Table B-1 and B-2 scaled by a desired factor or Table S-1 and S-2 scaled by a desired factor, said X-coordinate is the tangential direction, said Y-coordinate is the axial direction, and said Z-coordinate is the radial direction. 2. The turbine rotor as recited in claim 1, wherein said multiple turbine blades have a tip contour defined by a set of points in Table C-1 scaled by a desired factor, said set of points include paired axial dimension K from a centerline of the turbine rotor and a radial dimension J from a reference surface. 3. The turbine rotor as recited in claim 2, wherein said hub has a hub contour defined by a set of points in Table C-1 scaled by a desired factor, said set of hub contour points include paired axial dimension M from a centerline of the turbine rotor and a radial dimension L from a reference surface. 4. The turbine rotor as recited in claim 1, wherein said hub has a hub contour defined by a set of points in Table C-1 scaled by a desired factor, said set of points include paired axial dimension M from a centerline of the turbine rotor and a radial dimension L from a reference surface. 5. The turbine rotor as recited in claim 1, wherein each of said Tables is adjusted by a manufacturing tolerance. 6. The turbine rotor as recited in claim 5, wherein said manufacturing tolerance is about +−0.03 inches (0.76 mm). 7. A turbine rotor for an Air Cycle Machine comprising: a hub with a multiple turbine blades which extend therefrom, each of said multiple of turbine blades have a tip contour defined by a set of points in Table C-1 scaled by a desired factor, said set of points include paired axial dimension K from a centerline of the turbine rotor and a radial dimension J from a reference surface. 8. The turbine rotor as recited in claim 7, wherein each of said multiple of turbine blades are defined by a set of X-coordinates, Y-coordinates and Z-coordinates in any of Table B-1 and B-2 scaled by a desired factor or Table S-1 and S-2 scaled by a desired factor, said X-coordinate is the tangential direction, said Y-coordinate is the axial direction, and said Z-coordinate is the radial direction. 9. The turbine rotor as recited in claim 7, wherein said hub has a hub contour defined by a set of points in Table C-1 scaled by a desired factor, said set of hub contour points include paired axial dimension M from a centerline of the turbine rotor and a radial dimension L from a reference surface. 10. The turbine rotor as recited in claim 7, wherein each of said Tables is adjusted by a manufacturing tolerance. 11. A turbine rotor for an Air Cycle Machine comprising: a hub with a multiple turbine blades which extend therefrom, said hub has a hub contour defined by a set of points in Table C-1 scaled by a desired factor, said set of points include paired axial dimension M from a centerline of the turbine rotor and a radial dimension L from a reference surface. 12. The turbine rotor as recited in claim 11, wherein said multiple turbine blades have a tip contour defined by a set of points in Table C-1 scaled by a desired factor, said set of tip contour points include paired axial dimension K from a centerline of the turbine rotor and a radial dimension J from a reference surface. 13. The turbine rotor as recited in claim 11, wherein each of said multiple of turbine blades are defined by a set of X-coordinates, Y-coordinates and Z-coordinates in any of Table B-1 and B-2 scaled by a desired factor or Table S-1 and S-2 scaled by a desired factor, said X-coordinate is the tangential direction, said Y-coordinate is the axial direction, and said Z-coordinate is the radial direction. 14. The turbine rotor as recited in claim 11, wherein each of said Tables is adjusted by a manufacturing tolerance. 15. An Air Cycle Machine comprising: a turbine rotor with a multiple turbine blades, each of said multiple of turbine blades having a set of X-coordinates, Y-coordinates and Z-coordinates defined in any of Table B-1 and B-2 scaled by a desired factor or Table S-1 and S-2 scaled by a desired factor, said X-coordinate is the tangential direction, said Y-coordinate is the axial direction, and said Z-coordinate is the radial direction. 16. The Air Cycle Machine as recited in claim 15, wherein said multiple turbine blades have a tip contour defined by a set of points in Table C-1 scaled by a desired factor, said set of points include paired axial dimension K from a centerline of the turbine rotor and a radial dimension J from a reference surface. 17. The Air Cycle Machine as recited in claim 15, wherein said hub has a hub contour defined by a set of points in Table C-1 scaled by a desired factor, said set of points include paired axial dimension M from a centerline of the turbine rotor and a radial dimension L from a reference surface. 18. The Air Cycle Machine as recited in claim 15, wherein said turbine rotor is within a turbine shroud. 19. The Air Cycle Machine as recited in claim 15, further comprising a turbine nozzle upstream of said turbine rotor. 20. The Air Cycle Machine as recited in claim 15, wherein each of said Tables is adjusted by a manufacturing tolerance. 21. A method of installing a turbine rotor in an Air cycle Machine, comprising: mounting a turbine rotor with a multiple turbine blades within a turbine shroud to at least partially define a turbine flowpath, each of said multiple of turbine blades having a set of X-coordinates, Y-coordinates and Z-coordinates defined in any of Table B-1 and B-2 scaled by a desired factor or Table S-1 and S-2 scaled by a desired factor, said X-coordinate is the tangential direction, said Y-coordinate is the axial direction, and said Z-coordinate is the radial direction. 22. A method as recited in claim 21, further comprising: mounting the turbine rotor downstream of a turbine nozzle. 23. A method as recited in claim 21, further comprising: defining said multiple turbine blades to have a tip contour defined by a set of points in Table C-1 scaled by a desired factor, said set of points include paired axial dimension K from a centerline of the turbine rotor and a radial dimension J from a reference surface to follow a contour of the turbine shroud. 24. A method as recited in claim 21, further comprising: adjusting a wall inner surface defined by the set of points in each of the Tables by a manufacturing tolerance.