Propeller and impeller blade configuration

• US 6,164,919 A
• Filed: 12/14/1998
• Issued: 12/26/2000
• Est. Priority Date: 12/12/1997
• Status: Expired due to Fees

• Current Assignee: Arthur Vanmoor
• Original Assignee: Arthur Vanmoor
• Inventors: Vanmoor, Arthur
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): NGUYEN, NINH H
• Application Number:
  US09/211,106
• Time in Patent Office: 743 Days
• Field of Search: 416/242, 416/243, 416/223 R, 416/DIG. 2, 416/DIG. 5
• US Class Current: 416/243
• CPC Class Codes: B63H 1/26 Blades
• CPC Class Codes: B64C 11/16 Blades
• CPC Class Codes: F04D 29/384 characterised by form
• CPC Class Codes: Y02T 50/10 Drag reduction
• CPC Class Codes: Y10S 416/02 Formulas of curves

Abstract

A novel concept for a propeller blade configuration incorporates the model of the natural wave behavior. The leading edge of the propeller blade is parallel to the trailing edge, but offset by a given amplitude. The surfaces between the leading and trailing edges are rounded so as to promote proper fluid sheet formation along the surface and to reduce undesirable vortice formation. Best results are obtained by modeling the surfaces along a sine or tangent function.

Claims

1. A propeller configuration, comprising:

a rotatable hub defining an axis of rotation;

a plurality of blade structures attached to said hub substantially perpendicular to said axis of rotation;

each of said blade structures having a leading edge, a trailing edge, a forward surface extending from said leading edge to said trailing edge, and a rear surface extending from said leading edge to said trailing edge;

said forward surface and said rear surface at said leading edge extending substantially parallel to and offset from said forward surface and said rear surface at said trailing edge, and converging smoothly at said trailing and leading edges to form a sharp leading edge and a sharp trailing edge.

2. The propeller configuration according to claim 1, wherein said forward surface and said rear surface are defined by a function y=a cos x, where 0≦

x≦

π

in radians, x being approximately equal to zero at said leading edge and x being approximately equal to π

at said trailing edge, and a is a real number defining a given thickness of said blade structures.

3. The propeller configuration according to claim 2, wherein a is a constant.

4. The propeller configuration according to claim 2, wherein a is a variable having a miximum value smaller than a maximum value of x.

5. The propeller configuration according to claim 1, wherein said forward surface and said rear surface are defined by a tangent function.

6. The propeller configuration according to claim 1, wherein the offset between said leading edge and said trailing edge increases with a distance from a point of attachment of said blade structure.

7. The propeller configuration according to claim 6, wherein said forward surface and said rear surface are defined by a function y=d cos x, where 0≦

x≦

π

in radians, x being approximately equal to zero at said leading edge and approximately equal to π

at said trailing edge, and wherein d is proportional to the distance from the point of attachment of said blade structure and assumes a maximum of no more than 1.

8. The propeller configuration according to claim 1, which further comprises a pipe section surrounding said plurality of propeller blades.