Thrust Engine

• US 20100071345A1
• Filed: 09/22/2008
• Published: 03/25/2010
• Est. Priority Date: 09/22/2008
• Status: Abandoned Application

• Current Assignee: Guy Silver, Juinerong Wa
• Original Assignee: Guy Silver, Juinerong Wa
• Inventors: Wa, Juinerong, Silver, Guy
• Application Number:
  US12/235,477
• Publication Number:
  US 20100071345A1
• Time in Patent Office: Days
• US Class Current: 60/269
• CPC Class Codes: F02K 3/00 Plants including a gas turbine driving a compressor or a ducted fan
• CPC Class Codes: F02K 5/00 Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
• CPC Class Codes: F02K 7/00 Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof rocket-engine plants F02K9/00
• CPC Class Codes: F03G 3/00 Other motors, e.g. gravity or inertia motors
• CPC Class Codes: F03H 99/00 Subject matter not provided for in other groups of this subclass
• CPC Class Codes: F05D 2220/20 within closed fluid conduits, e.g. pipes
• CPC Class Codes: F05D 2270/051 Thrust
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

According to the present invention, a blade with lift-to-drag ratio greater than one can generate a lift force greater than the drag force on the blade when a fluid flows across the blade. The blade can be positioned within an enclosed engine to produce a force greater than the force required to move the fluid across the blade, thereby creating a thrust for the enclosed engine. The direction and the magnitude of the thrust may be controlled by controlling the direction of fluid flow. According to the present invention, fluid flowing inside a thrust engine may be gaseous or liquid. A thrust engine of the present invention uses one or more wings in a configurable environment to create a directional force. Thrust engines according to the present invention can be configured by varying fluid parameters, such as density or velocity, the wing parameters (such as wing geometry, lift coefficient or plane surface area of the wing), the number and the locations of wings, how the fluid receives energy, fluid motion, fixed or movable wings and the fluid path.

Claims

1. An engine, comprising:

a housing including an interior space divided into a first portion and a second portion that are connected with each other;

a working fluid filling the interior space which flows, during operation, between the first portion and the second portions; and

one or more airfoils attached to the housing and positioned within the interior space in the circulation path of the fluid flow.

2. An engine as in claim 1 wherein, during operation, a temperature difference is created between the first portion and the second portion, such that the working fluid flows between the first portion and the second portion.

3. An engine as in claim 2, wherein the temperature difference is adjustable to achieve a predetermined fluid flow velocity within the interior space.

4. An engine as in claim 1 wherein, during operation, a propeller drives the working fluid between the first portion and the second portion.

5. An engine as in claim 4, wherein the propeller'"'"'s rotational speed is adjustable to achieve a predetermined fluid flow velocity within the interior space.

6. An engine as in claim 1, wherein a fluid structure drives the working fluid between the first portion and the second portion.

7. An engine as in claim 5, wherein an amount of fluid pumped by the fluid structure is adjustable to achieve a predetermined fluid flow velocity within the interior space.

8. An engine as in claim 1, wherein the first portion and the second portion is connected by a central portion and a peripheral portion.

9. An engine as in claim 1, wherein the airfoils are positioned to create a lift force in a predetermined direction.

10. An engine as in claim 9, wherein the predetermined direction is determined by an axis of rotation of the housing.

11. An engine as in claim 1, wherein an angle of attack of each airfoil, relative to the working fluid flow, is adjustable.

12. An engine as in claim 11, wherein the angle of attack is adjustable to achieve a predetermined lift-to-drag ratio.

13. An engine as in claim 1, wherein each airfoil has a predetermined lift-to-drag ratio to provide a predetermined lift force.

14. An engine as in claim 13, wherein an angle of attack of each airfoil is adjustable to achieve a predetermined lift-to-drag ratio.

15. An engine as in claim 1, wherein the working fluid comprises a gas.

16. An engine as in claim 15, wherein the gas is pressurized.

17. An engine as in claim 1, further comprising one or more valves provided in walls of the housing for regulating fluid flow between the interior space and the exterior of the housing.