Propeller, engine cooling device comprising such a propeller, and mould for producing said propeller

Patent metadata

Field	Value
Publication number	US-9790954-B2
Application number	US-201013498179-A
Country	US
Kind code	B2
Filing date	Sep 28, 2010
Priority date	Sep 29, 2009
Publication date	Oct 17, 2017
Grant date	Oct 17, 2017

Abstract

A propeller ( 1 ) includes a hub ( 2 ), blades ( 3 ), and a shell ( 4 ) having two flanks ( 41, 42 ) connected by an elbow, the blades ( 3 ) extending from the hub ( 2 ) to the shell ( 4 ). The thickness (e 1 , e 2 ) of at least one part of at least one of the flanks ( 41, 42 ) of the shell ( 4 ) is reduced towards the free end of the flank.

First claim

The invention claimed is:

1. A propeller ( 1 ) comprising an outer shell ( 4 ), an inner hub ( 2 ), blades ( 3 ) extending radially between said hub ( 2 ) and said shell ( 4 ), and said shell ( 4 ) having two flanks ( 41 , 42 ) connected by an elbow piece and comprising a polymer material reinforced by a fibrous reinforcement and being integral, unitary, and one-piece, the blades ( 3 ) extending from the hub ( 2 ) to the shell ( 4 ), wherein one of the two flanks ( 41 , 42 ) has an outer surface and an inner surface each extending axially and being planar an entire length thereof and the other of the two flanks has an outer surface and an inner surface each extending radially and being planar an entire length thereof, wherein in a first half of a length, but not an entire length, of at least one of the two flanks ( 41 , 42 ) from the elbow piece to a free end a thickness (e 1 , e 2 ) of at least one of the two flanks ( 41 , 42 ) of the shell ( 4 ) is reduced gradually toward a free end of the two flanks ( 41 , 42 ) and wherein a remainder of the length from the first half of the length to the free end of the at least one of the two flanks ( 41 , 42 ) a thickness is substantially uniform, wherein the reduction in thickness (e 1 , e 2 ) in the shell ( 4 ) is at least 30% between a thickness of the shell ( 4 ) in a region of the elbow piece and the thickness of the shell ( 4 ) in a region of the free edge.

2. The propeller ( 1 ) as claimed in claim 1 , wherein a thickness (e 1 , e 2 ) of the two flanks ( 41 , 42 ) of the shell ( 4 ) is reduced gradually toward the free end of each of the two flanks ( 41 , 42 ).

3. The propeller ( 1 ) as claimed in claim 2 , wherein the shell ( 4 ) comprises a substantially cylindrical first flank ( 41 ), coaxial with an axis (X) of the hub ( 2 ) and defining a face with which ends of the blades ( 3 ) come into contact, and in that the second flank ( 42 ) extends radially from one edge of the first flank ( 41 ).

4. The propeller ( 1 ) as claimed in claim 1 , wherein the shell ( 4 ) comprises a substantially cylindrical first flank ( 41 ), coaxial with an axis (X) of the hub ( 2 ) and defining a face with which ends of the blades ( 3 ) come into contact, and in that the second flank ( 42 ) extends radially from one edge of the first flank ( 41 ).

5. An engine cooling device comprising at least one propeller ( 1 ) as claimed in claim 1 .

6. An injection mold of a propeller ( 1 ) comprising an outer shell ( 4 ), an inner hub ( 2 ), blades ( 3 ) extending radially between said hub ( 2 ) and said shell ( 4 ), said shell ( 4 ) having two flanks ( 41 , 42 ) connected by an elbow piece and comprising a polymer material reinforced by a fibrous reinforcement and being integral, unitary, and one-piece, the blades ( 3 ) extending from the hub ( 2 ) to the shell ( 4 ), wherein one of the two flanks ( 41 , 42 ) has an outer surface and inner surface each being planar and extending axially and the other of the two flanks has an inner surface and an outer surface being planar and extending radially, the injection mold comprising an area corresponding to the hub ( 2 ), an area corresponding to each of the blades ( 3 ) and an area corresponding to the shell ( 4 ), the area corresponding to the shell ( 4 ) having in a first half of a length, but not an entire length, of at least one of the two flanks ( 41 , 42 ) from the elbow piece to its free end a thickness (e 1 , e 2 ) is gradually reduced and wherein a remainder of the length from the first half of the length to the free end of the at least one of the two flanks ( 41 , 42 ) a thickness is substantially uniform, wherein a reduction in thickness (e 1 , e 2 ) in the shell ( 4 ) is from 30% to 50% between a thickness of the shell ( 4 ) in a region of the elbow piece and a thickness of the shell ( 4 ) in a region of the free end.

Assignees

• Turcas Sylvain
• Valeo Systemes Thermiques

Inventors

• Turcas Sylvain

Classifications

• B29L2031/08

  Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers · CPC title

• B29C45/0046

  Details relating to the filling pattern or flow paths or flow characteristics of moulding material in the mould cavity · CPC title

• F04D29/326 Primary

  comprising a rotating shroud · CPC title

• B29C45/0025

  Preventing defects on the moulded article, e.g. weld lines, shrinkage marks (preventing defects on the preformed parts or layers B29C45/14836) · CPC title