Composite Compressor Blade for an Axial-Flow Turbomachine

• US 20160258297A1
• Filed: 02/25/2016
• Published: 09/08/2016
• Est. Priority Date: 03/05/2015
• Status: Active Grant

• Current Assignee: Techspace Aero SA (Safran SA)
• Original Assignee: Techspace Aero SA (Safran SA)
• Inventors: Cortequisse, Jean-Franois
• Granted Patent: US 10,280,758 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 5/147 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 Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/023 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/542 Bladed diffusers fixing blades to stators F01D9/042
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2230/22 by sintering
• CPC Class Codes: F05D 2230/31 Layer deposition
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2240/121 related to the leading edge of a stator vane
• CPC Class Codes: F05D 2240/301 Cross-sectional characteristics
• CPC Class Codes: F05D 2240/303 related to the leading edge of a rotor blade
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2300/133 Titanium
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The present application relates to a composite airfoil for a low-pressure compressor of an axial-flow turbomachine. The airfoil includes a platform and an aerodynamic airfoil having a leading edge and a trailing edge. The airfoil extends into the primary flow of the turbomachine. The airfoil includes a body extending from the leading edge to the trailing edge and a reinforcement of the leading edge of the airfoil. The reinforcement includes a reinforcing sheet, which extends from the leading edge to the trailing edge, and which is arranged in the thickness of the body in such a way as to reinforce it. In addition, the reinforcement includes a shell forming the leading edge and which is integral with the sheet. The sheet is a titanium sheet, and the body includes a composite material having an organic matrix charged with fibres. This configuration improves the rigidity and the resistance to corrosion while lightening the airfoil.

Claims

1. A composite airfoil for an axial-flow turbomachine intended to project radially into a flow of the turbomachine, the airfoil comprising:

a leading edge;

a trailing edge;

a composite body arranged between the leading edge and the trailing edge; and

a reinforcement forming the leading edge of the airfoil;

wherein the reinforcement of the leading edge comprises;

a reinforcing sheet of essentially constant thickness, the reinforcing sheet extending from the leading edge to the trailing edge and being arranged in the thickness of the body so as to cross the body, the reinforcing sheet including an edge of reduced thickness forming the trailing edge of the airfoil.

2. The composite airfoil of claim 1, wherein the body comprises:

an outer sharp trailing edge which is in contact of the constant thickness sheet.

3. The composite airfoil of claim 1, wherein the airfoil comprises:

an intrados surface and an extrados surface which extend from the leading edge to the trailing edge, the sheet sweeping the majority of the intrados surface and the majority of the extrados surface.

4. The composite airfoil of claim 1, wherein the reinforcement comprises:

a upstream portion forming the leading edge of the airfoil, the sheet and the upstream portion being joined, the sheet and the upstream portion being integrally formed.

5. The composite airfoil of claim 3, wherein the upstream portion forms a constant thickness layer.

6. The composite airfoil of claim 1, wherein the sheet comprises:

a granular material, the reinforcement being made by additive manufacturing with powder.

7. The composite airfoil of claim 1, wherein the body is made of a polymer material charged with fibres.

8. The composite airfoil of claim 1, wherein the reinforcement forms an insert arranged at least partially in the body, the sheet separating the body into two parts, the reinforcement comprising:

apertures formed in the sheet.

9. The composite airfoil of claim 1, wherein the body covers the majority of the surfaces of each face of the sheet.

10. The composite airfoil of claim 1, wherein the sheet divides the body, and the sheet extends on the whole of the radial height of the leading edge and on the whole of the radial height of the trailing edge of the airfoil.

11. The composite airfoil of claim 1, wherein the body exhibits a radial stack of aerodynamic profiles having mean camber lines, at least one or each mean camber line being arranged in the thickness of the sheet.

12. The composite airfoil of claim 1, further comprising:

a fixing platform delimiting the reinforcement radially, the fixing platform and the reinforcement being integrally formed.

13. The composite airfoil of claim 12, wherein the fixing platform comprises:

a plate with a surrounding edge such as to delimit a space within the fixing platform.

14. The composite airfoil of claim 1, further comprising:

a locking tab extending the sheet radially, the locking tab comprising;

locking member configured to fix an inner stator shroud.

15. The composite airfoil of claim 1, wherein the composite airfoil forms a stator vane.

16. The composite airfoil of claim 1, wherein the composite airfoil forms a rotor blade.

17. An axial flow compressor of a turbomachine, the axial flow compressor including at least one airfoil intended to project radially into an annular flow of the compressor, the airfoil comprising:

a leading edge;

a compressor airfoil trailing edge;

a body arranged between the leading edge and the trailing edge; and

a reinforcement forming the leading edge of the airfoil;

wherein the reinforcement of the leading edge comprises;

a reinforcing sheet forming the compressor airfoil trailing edge, the reinforcing sheet extending from the leading edge to the trailing edge and being arranged in the thickness of the body so as to cross the body.

18. The axial flow compressor of claim 17, wherein the sheet comprises:

a compressor airfoil curvature.

19. A gas turbine engine, comprising:

at least one airfoil intended to project into a flow of the gas turbine engine, the airfoil comprising;

a leading edge;

a trailing edge;

a body arranged between the leading edge and the trailing edge; and

a reinforcement forming the leading edge of the airfoil;

wherein the reinforcement of the leading edge comprises;

a reinforcing sheet which extends from the leading edge to the trailing edge and which is arranged within the thickness of the body, the reinforcing sheet including a trailing area with a constant thickness portion and with a portion thinner than the constant thickness portion forming the trailing edge.

20. The gas turbine engine of claim 19, wherein the thickness of the thinner portion progressively reduces from the thickness of the constant thickness portion.