High pressure tandem turbine

• US 20060018753A1
• Filed: 04/23/2005
• Published: 01/26/2006
• Est. Priority Date: 07/20/2004
• Status: Abandoned Application

• Current Assignee: Harry H. Menian
• Original Assignee: Harry H. Menian
• Inventors: Menian, Harry H.
• Application Number:
  US11/112,275
• Publication Number:
  US 20060018753A1
• Time in Patent Office: Days
• US Class Current: 416/175
• CPC Class Codes: F01D 5/146 of blades with tandem configuration, split blades or slotted blades
• CPC Class Codes: F04D 29/384 characterised by form
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The present invention relates to an improved apparatus used for moving gases or air in a single stage for the purposes of either causing a vacuum upstream as in vacuum pumps or high-pressure downstream as in industrial blowers, turbochargers for automotive engines, ducted fan propulsion devices, and compressors for gas turbines. In this improved concept, two matching sets of rotor vanes are paired, rotating in the same direction, without a stator between them, having continuous and progressive pitch angles, the same number of blades, and designed to complement each other. Therefore, the turbo apparatus can yield extreme high-pressure ratios at high flow rates.

Claims

1. A single stage turbo apparatus comprising:

a common hub to support two or more rows of matching sets of rotating rotor blades, with attachment provision to facilitate the connection to a rotating shaft, and two or more rows of matching rotating blades configured in such a manner so that they allow a small portion of the high energy fluid from a leading blade to be directed behind a chaser blade for the purposes of boundary layer control.

2. The turbo apparatus of claim 1, wherein no stator blades are present between said matching sets of rotor blades.

3. The turbo apparatus of claim 1, wherein the chaser blades are advanced ahead of the leading set of rotor blades at any angle.

4. The turbo apparatus of claim 2, wherein the chaser blades are advanced ahead of the leading set of rotor blades at any angle.

5. The turbo apparatus of claim 1, wherein the fluid flow angle exiting from the leading blade is matched to the entry angle of the chaser blade.

6. The turbo apparatus of claim 2, wherein the fluid flow angle exiting from the leading blade is matched to the entry angle of the chaser blade.

7. The turbo apparatus of claim 3, wherein the fluid flow angle exiting from the leading blade is matched to the entry angle of the chaser blade.

8. The turbo apparatus of claim 4, wherein the fluid flow angle exiting from the leading blade is matched to the entry angle of the chaser blade.

9. The turbo apparatus of claim 1, wherein the blade pitch at any point for a matched pair of blades is continuous and progressive from the leading blade through the chaser blade, thereby forming a continuous spline contour.

10. The turbo apparatus of claim 5, wherein the blade pitch at any point for a matched pair of blades is continuous and progressive from the leading blade through the chaser blade, thereby forming a continuous spline contour.

11. The turbo apparatus of claim 6, wherein the blade pitch at any point for a matched pair of blades is continuous and progressive from the leading blade through the chaser blade, thereby forming a continuous spline contour.

12. The turbo apparatus of claim 7, wherein the blade pitch at any point for a matched pair of blades is continuous and progressive from the leading blade through the chaser blade, thereby forming a continuous spline contour.

13. The turbo apparatus of claim 8, wherein the blade pitch at any point for a matched pair of blades is continuous and progressive from the leading blade through the chaser blade, thereby forming a continuous spline contour.

14. The turbo apparatus of claim 1, wherein a matching pair of leading and chaser blades do not share a common pitch.

15. The turbo apparatus of claim 1, whereby the trailing edge of the chaser blades are facing forward in the direction of rotation.

16. The turbo apparatus of claim 1, wherein the angular exit velocity of the fluid is significantly higher than the rotational velocity of the rotor.

17. A turbo apparatus according to claim 1, where the lead angle between the leading and chaser set of blades is adjustable while in operation, to yield the optimum efficiency possible for a given angular velocity and pressure ratio.

18. The turbo apparatus of claim 1, wherein the blade pitch at any point for a matched pair of blades is continuous and progressive from the leading blade through the chaser blade, thereby forming a continuous spline contour.

19. The turbo apparatus of claim 18, wherein the blade pitch at any point for a matched pair of blades is continuous and progressive from the leading blade through the chaser blade, thereby forming a continuous spline contour.

20. The apparatus of claim 10, wherein the leading and chaser blades are joined to form one single sweep.