HELICOPTER AND AIRCRAFT POWER DEVICE

• US 20140312166A1
• Filed: 01/18/2013
• Published: 10/23/2014
• Est. Priority Date: 01/18/2012
• Status: Active Grant

• Current Assignee: Xiaoyi Zhu
• Original Assignee: Xiaoyi Zhu
• Inventors: ZHU, Xiaoyi
• Granted Patent: US 9,315,264 B2
• Time in Patent Office: Days
• US Class Current: 244/17.11
• CPC Class Codes: B64C 11/18 Aerodynamic features
• CPC Class Codes: B64C 11/20 Constructional features
• CPC Class Codes: B64C 21/025 for simultaneous blowing and sucking
• CPC Class Codes: B64C 21/08 adjustable
• CPC Class Codes: B64C 23/00 Influencing air flow over aircraft surfaces, not otherwise provided for
• CPC Class Codes: B64C 27/467 Aerodynamic features
• CPC Class Codes: B64C 27/473 Constructional features
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A helicopter and aircraft power device has a plurality of fluid inlets on a windward side of a blade housing and a plurality of fluid outlets on a leeward side in a manner that the fluid inlets communicate with the fluid outlets. The path where the fluid flows in the lengthwise direction on the windward side of the blade housing is far greater than the path where the fluid flows in the widthwise direction on the leeward side of the blade housing, generating a very large pressure difference between the leeward side and the windward side. The action of the centrifugal force and a suction force from a suction motor significantly increase the flowing speed on the windward side of the blade and in the fluid passage, generating bigger pressure difference on either sides of the propeller and thus forming more powerful lift force and driving force.

Claims

1. A helicopter power device, comprising a propeller and a fuselage, the propeller comprising a cover body, a blade and a blade housing, the helicopter power device being characterized in that a fluid passage which is hollow for the fluid to flow through is provided in the lengthwise direction in the blade;

at least one fluid inlet is provided on a windward side of the blade;

at least one fluid outlet is provided on a leeward side of the blade in a manner to communicate with the fluid inlet; and

the fluid passage allows different paths for the fluid to pass in the lengthwise direction of windward side and in the widthwise direction of the leeward side to generate pressure difference give more lift force.

2. The helicopter power device of claim 1, characterized in that the fluid passage is locally or wholly provided in the lengthwise direction in the blade.

3. The helicopter power device of claim 1, characterized in that a centerline of the fluid inlet is in parallel to the rotating direction of the propeller.

4. The helicopter power device of claim 1, characterized in that the fluid discharged by the fluid outlet surrounds the fluid discharged by the propeller to form a fluid layer which blocks the fluid discharged by the propeller from being diffused outward and generates a more power driving force.

5. The helicopter power device of claim 1, characterized in that a spoiler surface which increase the fluid path is further provided in the fluid passage, and the spoiler surface can be arc, spiral, regular or irregular.

6. The helicopter power device of claim 1, characterized in that a suction motor, a connection tube and a suction tube are further comprised;

the suction tube can be a spiral tube, a straight tube and an arc tube;

the suction motor has a suction port communicating with the fluid passage; and

the action of the suction motor in the lengthwise direction of the windward side of the blade and the natural status in the widthwise direction of the leeward side form a larger pressure difference to generate more power lift force.

7. The helicopter power device of claim 6, characterized in that the fluid passage has two sub-passages, one communicating with the fluid inlet and the other communicating with the suction motor;

these two sub-layers communicate with each other;

the fluid flows through at least one of the two sub-passages and then the fluid inlet communicating with the sub-passages so that the fluid will not split from the blade housing and no stall phenomenon will occur.

8. The helicopter power device of claim 6, characterized in that the suction motor is provided in the cover body;

the suction port of the suction motor communicates with the suction tube disposed in the fluid passage;

a discharge port of the suction motor communicates with a plurality of ejecting ports surrounding a lower part of the cover body;

the fluid ejected by the ejecting ports next to the propeller to form a hollow fluid layer surrounding a fuselage, further blocking the fluid from entering the fuselage.

9. The helicopter power device of claim 6, characterized in that the suction motor is provided inside the fuselage or outside the fuselage, and the suction port of the suction motor communicates with the fluid passage through the connection tube.

10. An aircraft power device, comprising a propeller and a fuselage, the propeller comprising a plurality of blades, the aircraft power device being characterized in that a fluid passage which is hollow for the fluid to flow through is provided in the lengthwise direction in the blade;

the blade has at least one fluid inlet and at least one fluid outlet in a manner to communicate with each other; and

the fluid passage allows different paths for the fluid to pass in the lengthwise direction of windward side and in the widthwise direction of the leeward side to generate pressure difference give more lift force.

11. The aircraft power device of claim 10, characterized in that the fluid inlet is provided on a windward side of the blade in a manner to communicate with the fluid passage which is locally or wholly provided in the lengthwise direction in the blade.

12. The aircraft power device of claim 10, characterized in that the fluid outlet is provided on a leeward side of the blade in a manner to communicate with the fluid passage which is locally or wholly provided in the lengthwise direction in the blade.

13. The aircraft power device of claim 10, characterized in that a centerline of the fluid inlet is in parallel to the rotating direction of the propeller.

14. The aircraft power device of claim 10, characterized in that the fluid discharged by the fluid outlet surrounds the fluid discharged by the propeller to form a fluid layer which blocks the fluid discharged by the propeller from being diffused outward and generates a more power driving force.

15. The aircraft power device of claim 10, characterized in that a spoiler surface which increase the fluid path is further provided in the fluid passage, and the spoiler surface can be arc, spiral, regular or irregular.

16. The aircraft power device of claim 10, characterized in that a suction motor, a connection tube and a suction tube are further comprised;

the suction tube can be a spiral tube, a straight tube and an arc tube;

the suction motor has a suction port communicating with the fluid passage; and

the action of the suction motor in the lengthwise direction of the windward side of the blade and the natural status in the widthwise direction of the leeward side form a larger pressure difference to generate more power lift force.

17. The aircraft power device of claim 16, characterized in that the fluid passage has two sub-passages, one communicating with the fluid inlet and the other communicating with the suction motor;

and these two sub-layers communicate with each other;

the fluid flows through at least one of the two sub-passages and then the fluid inlet communicating with the sub-passages so that the fluid will not split from the blade and no stall phenomenon will occur.

18. The aircraft power device of claim 16, characterized in that the suction motor is provided in the cover body;

the suction port of the suction motor communicates with the suction tube disposed in the fluid passage;

a discharge port of the suction motor communicates with a plurality of ejecting ports surrounding a lower part of the cover body; and

the fluid ejected by the ejecting ports next to the propeller to form a hollow fluid layer surrounding a fuselage, further blocking the fluid from entering the fuselage.

19. The aircraft power device of claim 16, characterized in that the suction motor is provided inside the fuselage or outside the fuselage, and the suction port of the suction motor communicates with the fluid passage through the connection tube.