Composite propeller blade for an aircraft

Patent metadata

Field	Value
Publication number	US-10414487-B2
Application number	US-201414903434-A
Country	US
Kind code	B2
Filing date	Jun 25, 2014
Priority date	Jul 8, 2013
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

An aircraft propeller blade including a streamlined structure constituted by at least one piece of fiber reinforcement obtained by three-dimensionally weaving yarns and densified by a matrix, together with a spar including an enlarged portion extending outside the fiber reinforcement and forming the root of the blade, and a shaping portion present in a housing arranged inside the fiber reinforcement. The fiber reinforcement includes a non-interlinked zone forming the housing inside the fiber reinforcement. The non-interlinked zone opens out into the bottom portion and into the rear edge of the fiber reinforcement so as to form an opening for inserting the shaping portion of the spar into the housing of the fiber reinforcement. The opening present in the rear edge of the fiber reinforcement extends over a height that is less than the height of the housing.

First claim

The invention claimed is:

1. An aircraft propeller blade comprising:
a fiber reinforcement obtained by three-dimensionally weaving yams and densified by a matrix; and
a spar including an enlarged portion extending outside the fiber reinforcement and forming a root of the aircraft propeller blade, and a shaping portion present in a housing arranged inside the fiber reinforcement,
the fiber reinforcement including
a non-interlinked zone forming said housing inside the fiber reinforcement, dimensions of the housing matching dimensions of the shaping portion of the spar, the non-interlinked zone opening out into a bottom portion of the fiber reinforcement and into a rear edge of the fiber reinforcement so as to form an opening for inserting the shaping portion of the spar into the housing of the fiber reinforcement, and
an interlinked zone,

wherein the opening in the rear edge of the fiber reinforcement extends between the bottom portion of the fiber reinforcement and a junction on the rear edge of the fiber reinforcement such that a height of the opening is less than a height of the housing so as to leave in said rear edge a retaining portion formed in the interlinked zone that comes at least partly into contact with the shaping portion of the spar,
wherein the interlinked zone on the rear edge of the fiber reinforcement extends between the junction and a tip of the fiber reinforcement,
wherein the non-interlinked zone is defined by an outline between the non-interlinked zone and the interlinked zone,
wherein the outline of the non-interlinked zone separates progressively from an outline of the housing starting from a predetermined point and going to the junction such that the retaining portion presents a width that decreases between a tip of the housing and the junction,
wherein a height between the predetermined point and the tip of the housing is 20% to 50% of the height of the housing, and
wherein the height of the opening is 20% to 50% of the height of the housing.

2. The aircraft propeller blade according to claim 1 , wherein the spar comprises a structural part of composite material and a part made of rigid cellular material adhesively bonded to a portion of an outline of the structural part.

3. An aeroengine having a plurality of aircraft propeller blades according to claim 1 .

4. An aircraft including at least one aeroengine according to claim 3 .

5. A method of fabricating an aircraft propeller blade, the method comprising:
making a fiber blank as a single piece by three-dimensionally weaving yarns, said fiber blank including an interlinked zone and a non-interlinked zone forming a housing inside the fiber blank, said non-interlinked zone opening out into a bottom portion of the fiber blank and into a rear edge of the fiber blank so as to form an opening;
making a spar including an enlarged portion extending outside the fiber blank and forming a root of the aircraft propeller blade, and a shaping portion, the shaping portion of the spar being present in the housing formed inside the fiber blank, dimensions of the shaping portion of the spar matching dimensions of a shaping portion of the housing;
shaping the fiber blank by inserting the shaping portion of the spar into the housing in the fiber blank via the opening in order to obtain a preform; and
densifying the preform with a matrix in order to obtain a streamlined structure constituted by said preform and densified by the matrix,
wherein the opening in the rear edge of the fiber blank extends between the bottom portion of the fiber blank and a junction on the rear edge of the fiber blank such that a height of the opening is less than a height of the housing so as to leave in said rear edge a retaining portion formed in the interlinked zone that comes at least partly into contact with the shaping portion of the spar,
wherein the interlinked zone on the rear edge of the fiber blank extends between the junction and a tip of the fiber blank,
wherein the non-interlinked zone is defined by an outline between the non-interlinked zone and the interlinked zone,
wherein the outline of the non-interlinked zone separates progressively from an outline of the housing starting from a predetermined point and going to the junction such that the retaining portion presents a width that decreases between a tip of the housing and the junction,
wherein a height between the predetermined point and the tip of the housing is 20% to 50% of the height of the housing, and
wherein the height of the opening is 20% to 50% of the height of the housing.

6. The method according to claim 5 , wherein the spar is made by fabricating a structural part of composite material and adhesively bonding a part made of rigid cellular material to a portion of an outline of said structural part.

Assignees

• Safran Aircraft Engines

Inventors

• Laurenceau Adrien
• Fabre Adrien Jacques Philippe
• Gimat Matthieu

Classifications

• B29B11/16

  comprising fillers or reinforcement {(non-woven fabrics per se D04H1/00, D04H3/00)} · CPC title

• B29L2031/082

  Blades, e.g. for helicopters · CPC title

• B29C70/24

  oriented in at least three directions forming a three-dimensional [3D] structure · CPC title

• D03D25/005

  Three-dimensional woven fabrics · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title