Blade having an integrated composite spar

Patent metadata

Field	Value
Publication number	US-9616629-B2
Application number	US-201313732884-A
Country	US
Kind code	B2
Filing date	Jan 2, 2013
Priority date	Jul 2, 2010
Publication date	Apr 11, 2017
Grant date	Apr 11, 2017

Abstract

A blade including a structure with aerodynamic profile including two opposite skins obtained by three-dimensional weaving of a fibrous reinforcement densified by a matrix, and a longeron including a fibrous reinforcement obtained by three-dimensional weaving and densified by a matrix, the longeron including a first part extending outside the structure with aerodynamic profile and designed to be connected to a drive hub in rotation of the blade and a second part arranged inside the structure with aerodynamic profile between the two skins. The second part of the longeron has a thickness substantially similar to that of the skins of the structure with aerodynamic profile. In addition, the fibrous reinforcement of the second part of the longeron has the same weaving armor as that of the reinforcement of the skins of the structure with aerodynamic profile.

First claim

The invention claimed is:

1. A blade comprising:
a structure with aerodynamic profile comprising first and second opposite skins obtained by three-dimensional weaving of a fibrous reinforcement densified by a matrix,
a longeron comprising a fibrous reinforcement obtained by three-dimensional weaving and densified by a matrix, said longeron comprising a first part extending outside said structure with aerodynamic profile and designed to be connected to a drive hub in rotation of the blade and a second part arranged inside the structure with aerodynamic profile between the first and second skins,
the second part of said longeron comprising one or two portions each having a thickness substantially similar to that of the first and second skins of the structure with aerodynamic profile, and
the fibrous reinforcement of the second part of the longeron having a same weaving armour as that of the reinforcement of the first and second skins of the structure with aerodynamic profile.

2. The blade according to claim 1 , wherein the first part of the longeron extends underneath the second part of the longeron in increasing thickness.

3. The blade according to claim 1 , wherein a variation in thickness between the thickness of the first and second skins and the thickness of the second part of the longeron is less than 40%.

4. The blade according to claim 1 , wherein the second part of the longeron comprises first and second symmetrical portions, the first symmetrical portion arranged opposite to the first skin of the structure with aerodynamic profile and the second symmetrical portion arranged opposite to the second skin, each respective symmetrical portion having a thickness substantially similar to that of the respective skin adjacent to the structure with aerodynamic profile.

5. The blade according to claim 4 , wherein at least one moulded piece made of rigid cellular material is arranged between the first and second symmetrical portions.

6. The blade according to claim 1 , wherein the second part of the longeron comprises two legs spaced apart from each other by a central recess and each having a thickness substantially similar to that of the first and second skins of the structure with aerodynamic profile.

7. The blade according to claim 6 , wherein at least one moulded piece made of rigid cellular material is arranged in the central recess.

8. The blade according to claim 1 , wherein the structure with aerodynamic profile comprises a reinforcement made with first fibres and densified by a first matrix and the longeron comprises a reinforcement made with seconds fibres and densified by a second matrix, at least one of the first and second fibres and the first and second matrices being different in kind.

9. The blade according to claim 1 , wherein the structure with aerodynamic profile and the longeron comprise a reinforcement of carbon fibres densified by a carbon matrix.

10. A manufacturing process of a blade comprising:
manufacturing a first fibrous preform of a structure with aerodynamic profile by three-dimensional weaving of threads, said first preform comprising first and second skins delimiting therebetween an internal space,
manufacturing a second fibrous preform of a longeron by three-dimensional weaving of threads, said second preform comprising a first portion and a second portion, the second portion having a thickness substantially equal to that of the first and second skins of the first preform and armour identical to that of said first and second skins,
forming of the first fibrous preform to produce a preform of structure with aerodynamic profile, said forming comprising arranging of the second portion of the second preform in the internal space between the first and second skins of the first fibrous preform, and
densification of the first and second preforms by a matrix to produce the blade comprising a structure with aerodynamic profile and a longeron, each having a fibrous reinforcement densified by the matrix.

11. The process according to claim 10 , wherein, during the manufacturing of the second fibrous preform of the longeron, the second portion of said second fibrous preform is divided into first and second symmetrical parts in the direction of the thickness of said second portion, the first symmetrical part and the second symmetrical part each having a thickness substantially similar to that of the first skin and the second skin of the first fibrous preform, respectively, the first symmetrical part and the first skin designed to be opposite each other and the second symmetrical part and the second skin designed to be opposite each other during the forming of the first fibrous preform.

12. The process according to claim 11 , wherein, during the forming of the first fibrous preform, at least one moulded piece made of rigid cellular material is arranged between the first and second symmetrical parts of said second portion.

13. The process according to claim 10 , wherein, during the manufacturing of the second fibrous preform of the longeron, a central recess is made in the second portion of said second fibrous preform, said recess delimiting two parts spaced apart from each other by the central recess and each having a thickness substantially similar to that of the first and second skins of the structure with aerodynamic profile.

14. The process according to claim 13 , wherein, during the forming of the first fibrous preform, at least one moulded piece made of rigid cellular material is arranged in the central recess.

15. The process according to claim 10 , wherein the first portion of the second fibrous preform further comprises a thickened part extended by a part of decreasing thickness towards the second portion of the second preform and said thickened part and part of decreasing thickness form respectively, after the densification, a foot and a blade stilt.

16. A manufacturing process of a blade comprising:
making a first fibrous preform of a structure with aerodynamic profile by three-dimensional weaving of threads, said first preform comprising first and second skins delimiting therebetween an internal space,
making a second fibrous preform of a longeron by three-dimensional weaving of threads, said second preform comprising a first portion and a second portion, the second portion having a thickness substantially equal to that of the first and second skins of the first preform and armour identical to that of said first and second skins,
densification of the second fibrous preform by a first matrix,
forming the first fibrous preform to obtain a preform of structure with aerodynamic profile, said forming comprising arranging of the second portion of the second densified preform in the internal space between the first and second skins of the first fibrous preform, and
densification of the first preform by a second matrix of a kind different to that of the first matrix to obtain the blade comprising a structure with aerodynamic profile and a longeron, each having a fibrous reinforcement densified by the matrix.

17. A turboprop equipped with a blade or propeller blade according to claim 1 .

18. An aircraft equipped with at least one turboprop according to claim 17 .

Assignees

• Snecma

Inventors

• Fabre Adrien Jacques Philippe
• Horn Nicolas
• Marsal David
• Perrollaz Jean-Marc Claude

Classifications

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• Y02T50/433

  Cross-Sectional Technologies · mapped topic

• F05D2300/224

  Carbon, e.g. graphite · CPC title