HIGH EFFICIENCY HUB FOR PRESSURE JET HELICOPTERS

• US 20130161444A1
• Filed: 12/22/2011
• Published: 06/27/2013
• Est. Priority Date: 12/22/2011
• Status: Abandoned Application

• Current Assignee: Pegasus Helicopter, Inc.
• Original Assignee: Pegasus Helicopter, Inc.
• Inventors: Logan, Andrew H., SPANOS, MIKE
• Application Number:
  US13/335,887
• Publication Number:
  US 20130161444A1
• Time in Patent Office: Days
• US Class Current: 244/17.11
• CPC Class Codes: B64C 27/18 the means being jet-reaction apparatus
• CPC Class Codes: B64C 27/46 Blades
• CPC Class Codes: F01D 1/32 with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines the working fluid being a combustion products F02C3/165; jet propulsion plants per se F02K
• CPC Class Codes: F05D 2220/329 in helicopters

Abstract

The various implementations of the present invention provide a high efficiency “wye” rotor hub that is introduced into the airflow of the compressed air as the compressed air is delivered to the blades of the helicopter. The hub assembly has a plurality of hollow tubes that more efficiently guide the compressed air into the hollow blades, thereby improving the efficiency and performance of the engine. The hollow rotor tube hub insert looks much like a “ram'"'"'s horn” where the flow area of the compressed air entering the hollow mast from the air compressor is diverted equally into a plurality of generally circular tubes, with each tube having a substantially equal cross-sectional diameter and area and where the number of circular tubes is equal to the number of rotor blades.

Claims

1. An apparatus comprising:

an air compressor;

a hollow mast coupled to the air compressor;

a hub connected to the hollow mast, the hub comprising a plurality of air channels for channeling the compressed air from the air compressor into a plurality of substantially curvilinear air streams; and

a plurality of hollow rotor blades connected to the hub.

6. The apparatus of claim 1 further comprising:

an exhaust stream from the air compressor; and

a rudder positioned in the exhaust stream.

7. The apparatus of claim 1 further comprising a tip nozzle at the end of each of the plurality of hollow rotor blades.

8. The apparatus of claim 1 wherein each of the plurality of air channels comprises a cross-sectional diameter and area that is substantially equal to a cross-sectional diameter and area for each of the other plurality of air channels.

9. The apparatus of claim 1 further comprising:

an exhaust stream from the air compressor;

a rudder positioned in the exhaust stream, and wherein;

the air compressor is contained within a helicopter fuselage;

the plurality of substantially curvilinear air channels comprises two substantially curvilinear air channels;

the plurality of air streams comprises two air streams;

the plurality of hollow rotor blades comprises two hollow rotor blades and further comprising a tip nozzle at the end of each of the two hollow rotor blades; and

the hollow rotor blades are used to propel the helicopter fuselage during flight.

10. The apparatus of claim 1 wherein the hub comprising a plurality of air channels is provided as an after market product to replace a conventional “

T”

-shaped hub.

2. The apparatus of claim one wherein the plurality of substantially curvilinear air channels comprises two substantially curvilinear air channels and the plurality of air streams comprises two air streams and the plurality of hollow rotor blades comprises two hollow rotor blades.

3. The apparatus of claim one wherein the plurality of air channels comprises three air channels and the plurality of substantially curvilinear air streams comprises three substantially curvilinear air streams and the plurality of hollow rotor blades comprises three hollow rotor blades.

4. The apparatus of claim one wherein the plurality of air channels comprises four air channels and the plurality of substantially curvilinear air streams comprises four substantially curvilinear air streams and the plurality of hollow rotor blades comprises four hollow rotor blades.

5. The apparatus of claim one further wherein the air compressor is contained within a helicopter fuselage and the hollow rotor blades are used to propel the helicopter fuselage during flight.

11. A method comprising the steps of:

transmitting a flow of compressed air through a hollow mast to a hub, the hub comprising a plurality of substantially circular tubes, thereby creating a plurality of substantially curvilinear air streams; and

supplying the plurality of substantially curvilinear air streams to a plurality of hollow rotor blades, where the number of substantially curvilinear air streams is equal to the number of hollow rotor blades;

transforming the substantially curvilinear air streams into substantially linear air streams within the hollow rotor blades; and

discharging the substantially linear air streams through a tip nozzle in the end of each of the plurality of hollow rotor blades, thereby inducing a rotational movement in the plurality of hollow rotor blades.

12. The method of claim 11 wherein the step of supplying the plurality of substantially curvilinear air streams to the plurality of hollow rotor blades comprises the step of supplying a substantially curvilinear air stream to each of two hollow rotor blades.

13. The method of claim 11 wherein the step of supplying the plurality of substantially curvilinear air streams to the plurality of hollow rotor blades comprises the step of supplying a substantially curvilinear air stream to each of three hollow rotor blades.

14. The method of claim 11 wherein the step of supplying each of the plurality of substantially curvilinear air streams to each of a plurality of hollow rotor blades comprises the step of supplying a substantially curvilinear air stream to each of four hollow rotor blades.

15. The method of claim 11 further comprising the step of using the rotational movement in the plurality of rotor blades to power a helicopter in flight.

16. The method of claim 11 wherein the flow of compressed air is generated by an air compressor and further comprising the step of positioning a rudder in an exhaust stream from the air compressor.

17. The method of claim 11 wherein each of the plurality of substantially circular tubes comprises a substantially equal cross-sectional diameter and area.

18. The method of claim 11 wherein the step of supplying the plurality of substantially curvilinear air streams to the plurality of hollow rotor blades comprises the step of supplying a substantially curvilinear air stream to each of two hollow rotor blades and discharging the substantially linear air streams through a tip nozzle in the end of each of the plurality of hollow rotor blades, thereby inducing a rotational movement in the plurality of hollow rotor blades.

19. A helicopter comprising a plurality of components, the plurality of components comprising:

a helicopter fuselage;

an air compressor;

a hollow mast coupled to the air compressor;

a hub coupled to the air compressor, the hub comprising a pair of substantially tubular air channels; and

a pair of hollow rotor blades attached to the hub wherein each of the pair of hollow rotor blades is supplied an air stream from the pair of substantially tubular air channels.

20. The helicopter of claim 19 wherein at least the hub is provided in a kit.