Annular ducted lift fan VTOL aircraft

• US 20160101852A1
• Filed: 10/09/2014
• Published: 04/14/2016
• Est. Priority Date: 10/09/2014
• Status: Abandoned Application

• Current Assignee: Yun Jiang
• Original Assignee: Yun Jiang
• Inventors: Jiang, Yun
• Application Number:
  US14/510,734
• Publication Number:
  US 20160101852A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms

Abstract

The invention is an annular ducted lift fan system for a VTOL type aircraft. In detail, the invention comprises an annular duct, a lift fan set, engines, a central fuselage, a peripheral wing, and means for pneumatic coupling or mechanic coupling of engines and the lift fan set. The lift fan set is mounted in the annular duct and powered by the engines through pneumatic coupling or mechanic coupling. The annular duct is opened with the lift fan set working to provide high lift efficiency in VTOL mode and transition mode and is closed off to reduce drag in cruise mode.

Claims

1. A VTOL aircraft with an annular ducted lift fan system comprising:

an annular duct including curved inlet lips and a diffused outlet;

an annular lift fan set;

a central circular fuselage;

a peripheral wing;

engines;

means for pneumatic coupling or mechanic coupling of said lift fan set and said engines;

various configurations including circular, rhombic, triangular, etc.

2. The aircraft as set forth in claim 1 wherein said annular lift fan set can include two counter-rotating fans (vertically, horizontally or parallel positioned) or one fan with airflow deflector or stator in said annular duct.

3. The aircraft as set forth in claim 1 wherein said peripheral wing can be different shape, such as circular, rhombic, triangular, etc.

4. The aircraft as set forth in claim 1 wherein said engines can be one, two, or more, and include turbofan engine, turbojet engine, turbopropeller engine, turboshaft engine, piston engine, electric engine, etc.

5. The aircraft as set forth in claim 1 wherein said pneumatic coupling means said lift fan set is gas-driven by exhaust gases from said jet engines.

6. The aircraft as set forth in claim 1 wherein said mechanic coupling means said lift fan set is shaft-driven by drive shafts powered by said engines.

7. The aircraft as set forth in claim 1 wherein said annular duct is closed off by shutters, aperture, and louvers during forward flight to generate aerodynamic lift and reduce drag.

8. The aircraft as set forth in claim 1 has higher lift efficiency and forward propulsive efficiency compared with the same fan area conventional circular ducted fan aircraft.

9. An annular ducted lift fan system comprising:

an annular duct including curved inlet lips and a diffused outlet;

an annular lift fan set;

engines;

means for pneumatic coupling or mechanic coupling of said lift fan set and said engines;

10. The system as set forth in claim 9 wherein said annular lift fan set can include two counter-rotating fans or one fan with airflow deflector or stator in said annular duct.

11. The system as set forth in claim 9 wherein said engines can be one, two, or more, and include turbofan engine, turbojet engine, turbopropeller engine, turboshaft engine, piston engine, electric engine, etc.

12. The system as set forth in claim 9 wherein said pneumatic coupling means said lift fan set is gas-driven by exhaust gases from said jet engines.

13. The system as set forth in claim 9 wherein said mechanic coupling means said lift fan set is shaft-driven by shaft powered by said engines.

14. The system as set forth in claim 9 wherein said annular duct is closed off by shutters, aperture, and louvers during forward flight to generate aerodynamic lift and reduce drag.

15. The system as set forth in claim 9 has higher lift efficiency and forward propulsive efficiency compared with the same fan area conventional circular ducted fan system.