Supersonic compressor rotor and method of assembling same

1. A supersonic compressor rotor comprising:

a rotor disk comprising an upstream surface, a downstream surface, and a radially outer surface that extends between said upstream surface and said downstream surface, said radially outer surface comprising an inlet surface, an outlet surface, and a transition surface extending between said inlet surface and said outlet surface, said rotor disk defining a centerline axis;

a plurality of vanes coupled to said radially outer surface, adjacent said vanes forming a pair and oriented such that a flow channel is defined between each said pair of adjacent vanes, said flow channel extending between an inlet opening and an outlet opening, said inlet surface defining an inlet plane extending between said inlet opening and said transition surface, said outlet surface defining an outlet plane extending between said outlet opening and said transition surface that is not parallel to said inlet plane; and

at least one supersonic compression ramp comprising a trailing edge defining a uniform throat positioned within said flow channel to facilitate forming at least one compression wave within said flow channel.

2. The supersonic compressor rotor in accordance with claim 1 , wherein said inlet surface is oriented substantially parallel with respect to said centerline axis such that said flow channel defines an axial flow path from said inlet opening to said transition surface, said outlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said transition surface to said outlet opening.

3. The supersonic compressor rotor in accordance with claim 1 , wherein said inlet surface is oriented substantially parallel with respect to said centerline axis such that said flow channel defines an axial flow path from said inlet opening to said transition surface, said outlet surface is oriented substantially perpendicular with respect to said centerline axis such that said flow channel defines a radial flow path from said transition surface to said outlet opening.

4. The supersonic compressor rotor in accordance with claim 1 , wherein said inlet surface is oriented substantially perpendicular with respect to said centerline axis such that said flow channel defines a radial flow path from said inlet opening to said transition surface, said outlet surface is oriented substantially parallel with respect to said centerline axis such that said flow channel defines an axial flow path from said transition surface to said outlet opening.

5. The supersonic compressor rotor in accordance with claim 1 , wherein said inlet surface is oriented substantially perpendicular with respect to said centerline axis such that said flow channel defines a radial flow path from said inlet opening to said transition surface, said outlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said transition surface to said outlet opening.

6. The supersonic compressor rotor in accordance with claim 1 , wherein said inlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said inlet opening to said transition surface, said outlet surface is oriented substantially parallel with respect to said centerline axis such that said flow channel defines an axial flow path from said transition surface to said outlet opening.

7. The supersonic compressor rotor in accordance with claim 1 , wherein said inlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said inlet opening to said transition surface, said outlet surface is oriented substantially perpendicular with respect to said centerline axis such that said flow channel defines a radial flow path from said transition surface to said outlet opening.

8. The supersonic compressor rotor in accordance with claim 1 , wherein said inlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said inlet opening to said transition surface, said outlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said transition surface to said outlet opening.

9. A supersonic compressor system comprising:

a casing defining a cavity extending between a fluid inlet and a fluid outlet;

a drive shaft positioned within said casing and defining a centerline axis, said drive shaft rotatably coupled to a driving assembly; and

a supersonic compressor rotor coupled to said drive shaft, said supersonic compressor rotor positioned between said fluid inlet and said fluid outlet for channeling fluid from said fluid inlet to said fluid outlet, said supersonic compressor rotor comprising:

a rotor disk comprising an upstream surface, a downstream surface, and a radially outer surface that extends between said upstream surface and said downstream surface, said radially outer surface comprising an inlet surface, an outlet surface, and a transition surface extending between said inlet surface and said outlet surface;

a plurality of vanes coupled to said radially outer surface, adjacent said vanes forming a pair and oriented such that a flow channel is defined between each said pair of adjacent vanes, said flow channel extending between an inlet opening and an outlet opening, said inlet surface defining an inlet plane extending between said inlet opening and said transition surface, said outlet surface defining an outlet plane extending between said outlet opening and said transition surface that is not parallel to said inlet plane; and

at least one supersonic compression ramp comprising a trailing edge defining a uniform throat positioned within said flow channel to facilitate forming at least one compression wave within said flow channel.

10. The supersonic compressor system in accordance with claim 9 , wherein said inlet surface is oriented substantially parallel with respect to said centerline axis such that said flow channel defines an axial flow path from said inlet opening to said transition surface, said outlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said transition surface to said outlet opening.

11. The supersonic compressor system in accordance with claim 9 , wherein said inlet surface is oriented substantially parallel with respect to said centerline axis such that said flow channel defines an axial flow path from said inlet opening to said transition surface, said outlet surface is oriented substantially perpendicular with respect to said centerline axis such that said flow channel defines a radial flow path from said transition surface to said outlet opening.

12. The supersonic compressor system in accordance with claim 9 , wherein said inlet surface is oriented substantially perpendicular with respect to said centerline axis such that said flow channel defines a radial flow path from said inlet opening to said transition surface, said outlet surface is oriented substantially parallel with respect to said centerline axis such that said flow channel defines an axial flow path from said transition surface to said outlet opening.

13. The supersonic compressor system in accordance with claim 9 , wherein said inlet surface is oriented substantially perpendicular with respect to said centerline axis such that said flow channel defines a radial flow path from said inlet opening to said transition surface, said outlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said transition surface to said outlet opening.

14. The supersonic compressor system in accordance with claim 9 , wherein said inlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said inlet opening to said transition surface, said outlet surface is oriented substantially parallel with respect to said centerline axis such that said flow channel defines an axial flow path from said transition surface to said outlet opening.

15. The supersonic compressor system in accordance with claim 9 , wherein said inlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said inlet opening to said transition surface, said outlet surface is oriented substantially perpendicular with respect to said centerline axis such that said flow channel defines a radial flow path from said transition surface to said outlet opening.

16. The supersonic compressor system in accordance with claim 9 , wherein said inlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said inlet opening to said transition surface, said outlet surface is oriented at an oblique angle with respect to said centerline axis such that said flow channel defines an oblique flow path from said transition surface to said outlet opening.

17. A method of assembling a supersonic compressor rotor, said method comprising:

providing a rotor disk that includes an upstream surface, a downstream surface, and a radially outer surface that extends between the upstream surface and the downstream surface, the radially outer surface including an inlet surface, an outlet surface, and a transition surface extending between the inlet surface and the outlet surface, the rotor disk defining a centerline axis;

coupling a plurality of vanes to the radially outer surface, adjacent vanes forming a pair and oriented such that a flow channel is defined between each pair of adjacent vanes, the flow channel extending between an inlet opening and an outlet opening, the inlet surface defining an inlet plane extending between the inlet opening and the transition surface, the outlet surface defining an outlet plane extending between the outlet opening and the transition surface that is not parallel to the inlet plane; and

coupling at least one supersonic compression ramp to one of a vane of the plurality of vanes and the radially outer surface, the supersonic compression ramp positioned within the flow channel and configured to facilitate forming at least one compression wave within the flow channel.

18. The method in accordance with claim 17 , further comprising:

providing the inlet surface oriented substantially parallel with respect to the centerline axis and defining an axial flow path; and

providing the outlet surface oriented with respect to the centerline axis to define one of a radial flow path and an oblique flow path.

19. The method in accordance with claim 17 , further comprising:

providing the inlet surface oriented substantially perpendicular with respect to the centerline axis and defining a radial flow path from the inlet opening to the transition surface; and

providing the outlet surface oriented with respect to the centerline axis to define one of an axial flow path and an oblique flow path.

20. The method in accordance with claim 17 , further comprising:

providing the inlet surface oriented at an oblique angle with respect to the centerline axis and defining an oblique flow path from the inlet opening to the transition surface; and

providing the outlet surface oriented with respect to the centerline axis to define one of an axial flow path, a radial flow path, and an oblique flow path.