Turbine engine vane with asymmetrical profile

Patent metadata

Field	Value
Publication number	US-9784112-B2
Application number	US-201414511624-A
Country	US
Kind code	B2
Filing date	Oct 10, 2014
Priority date	Oct 11, 2013
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%.

First claim

The invention claimed is:

1. A turbine engine vane comprising:
a main body made of composite material,
a leading edge,
a trailing edge, and
at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, wherein each profile of the junction surface portion of the structural reinforcement has a camber less than 30% and at least one cracking.

2. The vane according to claim 1 , wherein a junction surface portion of the main body to which the junction surface portion of the structural reinforcement is connected, is complementary to the junction surface portion of the structural reinforcement and has a profile identical to the profile of the latter.

3. The vane according to claim 1 , wherein the main body comprises an intrados and an extrados, and wherein the structural reinforcement comprises an intrados continuously following the intrados of the main body and an extrados continuously following the extrados of the main body, the intrados and the extrados of the structural reinforcement having respective profiles of different lengths.

4. The vane according to claim 1 , comprising a camber line cutting the profile of the structural reinforcement into two different area regions.

5. The vane according to claim 1 , wherein each profile of the junction portion of the structural reinforcement comprises less than two points of inflection.

6. The vane according to claim 1 , wherein the cracking is an apex introducing a change of direction of angle of between 45° and 90°.

7. A turbine engine comprising at least one vane according to claim 1 .

Assignees

• Snecma
• Safran

Inventors

• Briend Maxime
• Pautard Sebastien

Classifications

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F01D25/005

  Selecting particular materials · CPC title

• F05D2240/303

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

• F01D5/288

  Protective coatings for blades · 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