AIR CYCLE MACHINE COMPRESSOR ROTOR

• US 20120156026A1
• Filed: 12/21/2010
• Published: 06/21/2012
• Est. Priority Date: 12/21/2010
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Merritt, Brent J., Hipsky, Harold W.
• Granted Patent: US 8,529,210 B2
• Time in Patent Office: Days
• US Class Current: 415/207
• CPC Class Codes: F04D 29/284 for compressors
• CPC Class Codes: F04D 29/286 multi-stage rotors
• CPC Class Codes: F04D 29/30 Vanes
• CPC Class Codes: Y10T 29/4932 Turbomachine making

Abstract

A compressor rotor for an air cycle machine (ACM) includes a plurality of blades that each includes a root, a tip, a first surface and second surfaces. The first and second surfaces are defined as a set of X-coordinates, Y-coordinates and Z-coordinates set out in any of Table M-1 and M-2 or Table S1 and S-2 scaled by a desired factor. The X-coordinates being in the tangential direction, the Y-coordinates being in the axial direction and the Z-coordinates being in the radial direction.

Claims

1. A compressor rotor for an air cycle machine comprising:

a hub including a plurality of blades extending therefrom, each of the plurality of blades including a root, a tip, first and second surfaces, wherein the each of the first and second surfaces are defined as a set of X-coordinates, Y-coordinates and Z-coordinates set out in any of Table M-1 and M-2 or Table S1 and S-2 scaled by a desired factor, the X-coordinates being in the tangential direction, the Y-coordinates being in the axial direction and the Z-coordinates being in the radial direction.

2. The compressor rotor as recited in claim 1, wherein the plurality of blades include a tip contour defined by a set of points as defined in Table T-1 scaled to a desired factor, the set of points including paired axial dimensions K from a reference surface and radial dimensions J from a center line of the compressor rotor.

3. The compressor rotor as recited in claim 1, wherein a surface between the plurality of blades includes a hub contour defined as a set of points defined in Table H-1 scaled to a desired factor, the set of points including paired axial dimensions M from a reference surface and a radial dimension L from a center line of the compressor rotor.

4. The compressor rotor as recited in claim 1, wherein the plurality of blades comprise a plurality of main blades defined by the X-coordinates, Y-coordinates and Z-coordinates set out in tables M1 and M2, and a corresponding plurality of splitter blades disposed between the plurality of main blades defined by the X-coordinates, Y-coordinates and Z-coordinates set out in tables S1 and S2.

5. The compressor rotor as recited in claim 1, wherein each of the plurality of blades include a substantially uniform width between the first and second surfaces.

6. The compressor rotor as recited in claim 1, wherein each of the surfaces defined by said Tables is adjusted by a manufacturing tolerance.

7. The compressor rotor as recited in claim 6, wherein said manufacturing tolerance is about +−

0.030 inches (0.76 mm).

8. A compressor rotor for an air cycle machine comprising:

a hub including a plurality of blades extending therefrom, each of the plurality of blades including a root, a tip, a first surface and a second surface, wherein a tip contour is defined by a set of points as defined in Table T-1 scaled to a desired factor, the set of points including paired axial dimensions K from a reference surface and radial dimensions J from a center line of the compressor rotor.

9. The compressor rotor as recited in claim 8, wherein a hub surface disposed between the plurality of blades is defined by a set of points defined in Table H-1 scaled to a desired factor, the set of points including paired axial dimensions M from a reference surface and a radial dimension L from a center line of the compressor rotor.

10. The compressor rotor as recited in claim 8, wherein the plurality of blades comprise a plurality of main blades defined by a set of X-coordinates, Y-coordinates and Z-coordinates set out in tables M1 and M2, and a corresponding plurality of splitter blades disposed between the plurality of main blades defined by the X-coordinates, Y-coordinates and Z-coordinates set out in tables S1 and S2.

11. The compressor rotor as recited in claim 8, wherein each of the surfaces defined by the Tables is adjusted by a manufacturing tolerance.

12. An air cycle machine comprising:

a main shaft having a fan, a turbine rotor and a compressor rotor mounted for rotation about an axis;

a housing supporting rotation of the main shaft; and

a compressor diffuser mounted proximate the compressor rotor for directing airflow from compressor rotor, wherein the compressor rotor includes a plurality of blades extending therefrom, each of the plurality of blades including a root, a tip, first and second surfaces, wherein the each of the first and second surfaces are defined as a set of X-coordinates, Y-coordinates and Z-coordinates set out in any of Table M-1 and M-2 or Table S1 and S-2 scaled by a desired factor, the X-coordinates being in the tangential direction, the Y-coordinates being in the axial direction and the Z-coordinates being in the radial direction.

13. The air cycle machine as recited in claim 12, wherein the plurality of blades comprise a plurality of main blades defined by a set of X-coordinates, Y-coordinates and Z-coordinates set out in tables M1 and M2, and a corresponding plurality of splitter blades disposed between the plurality of main blades defined by the X-coordinates, Y-coordinates and Z-coordinates set out in tables S1 and S2.

14. The air cycle machine as recited in claim 12, wherein a tip contour is defined by a set of points as defined in Table T-1 scaled to a desired factor, the set of points including paired axial dimensions K from a reference surface and radial dimensions J from a center line of the compressor rotor.

15. The air cycle machine as recited in claim 12, wherein the tip contour corresponds with a surface of the compressor diffuser.

16. The air cycle machine as recited in claim 12, wherein the compressor rotor includes a hub surface disposed between the plurality of blades is defined by a set of points defined in Table H-1 scaled to a desired factor, the set of points including paired axial dimensions M from a reference surface and a radial dimension L from a center line of the compressor rotor.

17. The air cycle machine as recited in claim 12, wherein each of the surfaces defined in each of the Tables is adjusted by a manufacturing tolerance.

18. The method of installing a compressor rotor into an air cycle machine, the method including:

mounting a compressor rotor for rotation about an axis proximate a diffuser to define at least a portion of a compressor airflow path where the compressor rotor comprises a plurality of blades extending therefrom, each of the plurality of blades including a root, a tip, first and second surfaces, wherein the each of the first surface and the second surface are defined as a set of X-coordinates, Y-coordinates and Z-coordinates set out in any of Table M-1 and M-2 or Table S1 and S-2 scaled by a desired factor, the X-coordinates being in the tangential direction, the Y-coordinates being in the axial direction and the Z-coordinates being in the radial direction.

19. The method of installing a compressor rotor as recited in claim 18, wherein the plurality of blades comprise a plurality of main blades defined by a set of X-coordinates, Y-coordinates and Z-coordinates set out in tables M1 and M2, and a corresponding plurality of splitter blades disposed between the plurality of main blades defined by the X-coordinates, Y-coordinates and Z-coordinates set out in tables S1 and S2.

20. The method of installing a compressor rotor as recited in claim 18, wherein a tip contour of the plurality of blades is defined by a set of points as defined in Table T-1 scaled to a desired factor, the set of points including paired axial dimensions K from a reference surface and radial dimensions J from a center line of the compressor rotor.

21. The method of installing a compressor rotor as recited in claim 18, including defining the tip contour to correspond with a contoured surface of the diffuser.

22. The compressor rotor as recited in claim 18, including adjusting each surface defined in each of the Tables by a manufacturing tolerance.