Composite turbine engine blade with structural reinforcement

Patent metadata

Field	Value
Publication number	US-9765634-B2
Application number	US-201313949703-A
Country	US
Kind code	B2
Filing date	Jul 24, 2013
Priority date	Jul 24, 2012
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

The invention relates to a turbine engine blade, particularly made of composite material, including:
on the one hand, an airfoil ( 10 ) which exhibits:
a leading edge ( 12 ), a trailing edge ( 14 ) opposite to the leading edge ( 12 ), intrados ( 16 ) and extrados ( 18 ) lateral walls which connect the leading edge ( 12 ) to the trailing edge ( 14 ), et
on the other hand, a structural reinforcement ( 20 ) including a base ( 24 ) extending into two fins ( 26, 28 ) and designed to be applied to the leading edge ( 12 ) and the lateral walls ( 16, 18 ) of the airfoil ( 10 ), characterized in that the fins ( 26, 28 ) of the structural reinforcement ( 20 ) and/or the lateral walls ( 16, 18 ) of the airfoil ( 10 ) are shaped to maintain an assembly space ( 30 ) with nonzero thickness between at least one of the fins ( 26, 28 ) and the airfoil ( 10 ) when the structural reinforcement ( 20 ) is in place on the airfoil ( 10 ), said assembly space ( 30 ) extending from a free end ( 27, 29 ) of said fin ( 26, 28 ) toward the base ( 24 ) of the structural reinforcement ( 20 ).

First claim

The invention claimed is:

1. A blade of a turbine engine, said blade being made of composite material and comprising:
an airfoil with:
a leading edge,
a trailing edge opposite to the leading edge,
intrados and extrados lateral walls which connect the leading edge to the trailing edge, and
a blade root and a blade tip, the blade root and the blade tip defining a longitudinal axis of the blade, said longitudinal axis extending along a principal direction of the blade; and

a structural reinforcement including a base extending into two fins and configured to be applied to the leading edge and the lateral walls of the airfoil,
wherein the fins of the structural reinforcement and/or the lateral walls of the airfoil are shaped to maintain an assembly space with nonzero thickness between at least one of the fins and the airfoil when the structural reinforcement is in place on the airfoil, said assembly space extending from a free end of said at least one of the fins toward the base of the structural reinforcement, and
wherein a transverse cross-section relative to the longitudinal axis of a portion of a surface defined by at least one of the lateral walls of the airfoil positioned facing the at least one of the fins is straight, and a transverse cross-section relative to the longitudinal axis of a portion of a surface defined by an inner wall of the at least one of the fins positioned facing the at least one of the lateral walls is curved.

2. The blade according to claim 1 , wherein said at least one of the fins is supported against the airfoil at a first contact zone, located at the free end of said at least one of the fins, and at a second contact zone, located facing the leading edge of the airfoil, the assembly space extending between the first contact zone and the second contact zone.

3. The blade according to claim 1 , wherein the assembly space extends between the free end of the at least one of the fins located in front of the lateral extrados wall and the base of the structural reinforcement.

4. The blade according to claim 1 , wherein the fins of the structural reinforcement and/or the lateral walls of the airfoil are shaped so as to maintain assembly spaces having nonzero thickness between said fins of the structural reinforcement and the airfoil when the structural reinforcement is in place on the airfoil, said assembly spaces extending from the free end of said fins toward the base of the structural reinforcement.

5. The blade according to claim 4 , further comprising at least one stop positioned in a cavity between the leading edge and the base.

6. The blade according to claim 1 , wherein the assembly space includes an adhesive.

7. The blade according to claim 6 , wherein the assembly space has a maximum thickness comprised between 100 microns and 300 microns.

8. A turbine engine fan comprising the blade according to claim 1 .

9. A blade of a turbine engine, said blade being made of composite material and comprising:
an airfoil with:
a leading edge,
a trailing edge opposite to the leading edge,
intrados and extrados lateral walls which connect the leading edge to the trailing edge, and
a blade root and a blade tip, the blade root and the blade tip defining a longitudinal axis of the blade, said longitudinal axis extending along a principal direction of the blade; and

a structural reinforcement consisting of a base and two fins extending from the base so that the structural reinforcement is V-shaped, said fins being configured to be applied to the leading edge and the lateral walls of the airfoil,
wherein the fins of the structural reinforcement and/or the lateral walls of the airfoil are shaped to maintain an assembly space with nonzero thickness between at least one of the fins and the airfoil when the structural reinforcement is in place on the airfoil, said assembly space extending from a free end of said at least one of the fins toward the base of the structural reinforcement,
wherein a transverse cross-section relative to the longitudinal axis of a portion of a surface defined by at least one of the lateral walls of the airfoil positioned facing the at least one of the fins is straight, and
wherein said at least one of the fins is supported against the airfoil at a first contact zone, located at the free end of said at least one of the fins, and at a second contact zone, located facing the leading edge of the airfoil, the assembly space extending between the first contact zone and the second contact zone.

10. The blade according to claim 9 , wherein the assembly space extends between the free end of the at least one of the fins located in front of the lateral extrados wall and the base of the structural reinforcement.

11. The blade according to claim 9 , wherein a transverse cross-section relative to the longitudinal axis of a portion of a surface defined by an inner wall of the at least one of the fins is straight.

12. The blade according to claim 9 , wherein the fins of the structural reinforcement and/or the lateral walls of the airfoil are shaped so as to maintain assembly spaces having nonzero thickness between said fins of the structural reinforcement and the airfoil when the structural reinforcement is in place on the airfoil, said assembly spaces extending from the free end of said fins toward the base of the structural reinforcement.

13. The blade according to claim 12 , further comprising at least one stop positioned in a cavity between the leading edge and the base.

14. The blade according to claim 9 , wherein the assembly space includes an adhesive.

15. The blade according to claim 14 , wherein the assembly space has a maximum thickness comprised between 100 microns and 300 microns.

16. A turbine engine fan comprising the blade according to claim 9 .

Assignees

• Snecma

Inventors

• Fameau Vincent
• Abadie Aude

Classifications

• F04D29/023

  especially adapted for elastic fluid pumps · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F04D29/324

  Blades · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title