CORE DRIVEN PLY SHAPE COMPOSITE FAN BLADE AND METHOD OF MAKING

• US 20110129348A1
• Filed: 11/30/2009
• Published: 06/02/2011
• Est. Priority Date: 11/30/2009
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Parkin, Michael, Alexander, Phillip, Huth, Brian P., Klinetob, Carl Brian
• Application Number:
  US12/627,629
• Publication Number:
  US 20110129348A1
• Time in Patent Office: Days
• US Class Current: 416/230
• CPC Class Codes: B29D 99/0025 Producing blades or the like, e.g. blades for turbines, propellers, or wings
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F05D 2300/431 Rubber
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced

Abstract

A method of forming a composite airfoil having a suction side and pressure side includes the steps of designing a mold, designing a woven core, designing a plurality of plies and assembling the designed mold, core and plies to create the composite airfoil. The hollow mold has an inner surface which defines the surface profile of the composite airfoil. The plurality of plies is designed to fit between the inner surface of the mold and an outer surface of the woven core. The plurality of plies is designed after the step of designing the woven core.

Claims

1. A method of forming a composite airfoil having a suction side, a pressure side, a tip and a root, the method comprising:

designing a hollow mold having an inner surface which defines a surface profile of the composite airfoil;

designing a woven core for placement in the mold;

designing a plurality of plies to fit between the inner surface of the mold and an outer surface of the woven core, wherein the plurality of plies are designed after the step of designing the woven core; and

assembling the designed woven core and plurality of plies in the mold to create the composite airfoil.

2. The method of claim 1 and further comprising:

building a parametric core model comprising;

sectioning a model of the airfoil into sections along a span-wise axis;

inserting a curve in each section that extends between a suction side and a pressure side of the airfoil model; and

defining a point on each curve based on a percentage P of a length of the curve, wherein the point represents an interface between the woven core and the plies, and wherein the point is used in the step of designing the woven core.

3. The method of claim 2 wherein the step of designing the plurality of plies comprises:

populating a space between the inner surface of the mold and the outer surface of the woven core with plies.

4. The method of claim 2 and further comprising:

adjusting the locations of the points on the curves to locally optimize ply drops.

5. The method of claim 4 wherein the step of adjusting the location of the points comprises:

adjusting the locations of the points on the curves so that there is a 20;

1 minimum ratio of ply drop distance to ply thickness for each ply.

6. The method of claim 2, wherein the step of defining a point on each curve based on a percentage P of a length of the curve comprises:

defining a point that is perpendicular to a mid-surface of the parametric core model and parallel to a root of the airfoil model.

7. The method of claim 1, wherein the woven core is a three-dimensional woven core.

8. The method of claim 2, and further comprising:

defining a second point on each curve based on a second percentage P2 of the length of the curve, wherein the points define an interface between the plies and a pressure side of the woven core and the second points define an interface between the plies and a suction side of the woven core.

9. The method of claim 1, wherein the plies are composite plies including a plurality of fibers and a resin.

10. A composite airfoil formed by the method of claim 1.

11. A method for designing a composite airfoil, the method comprising:

designing a mold having an inner surface that defines a surface profile of the airfoil;

defining a preliminary core surface of a woven core, wherein the preliminary core surface is offset from the inner surface of the mold by a specified percentage;

filling the space between the mold and the preliminary core surface with a plurality of plies; and

assembling the woven core and the plurality of plies in the mold and curing to form the composite airfoil.

12. The method of claim 11 wherein the method further comprises:

adjusting the preliminary core surface to both define an adjusted core surface and alter a shape of the plies; and

filling the space between the mold and the adjusted core surface with a plurality of adjusted plies.

13. The method of claim 12 wherein there is a 20:

1 minimum ratio of ply drop distance to ply thickness for each adjusted ply.

14. The method of claim 11 wherein the specified percentage is a specified percentage of thickness of the mold.

15. The method of claim 11 wherein the step of defining a preliminary core surface comprises:

defining thickness curves between a pressure side and a suction side of the mold; and

locating points along the thickness curves at specified percentages of a length of the respective thickness curve, wherein the points define the preliminary core surface.

16. A composite airfoil formed by the method of claim 11.

17. A method for forming a composite airfoil, the method comprising:

designing a mold having an inner surface that defines a surface profile of the airfoil;

designing a woven core having an outer surface for positioning in the mold, the step of designing a woven core comprising;

creating a model of the airfoil;

sectioning the airfoil model into section along a longitudinal axis of the airfoil;

inserting thickness curves in each section of the airfoil model, wherein the thickness curves extend from a pressure side to a suction side of the airfoil model; and

positioning points along the thickness curves of each section of the airfoil to define an outer surface of the woven core;

populating a space between the inner surface of the mold and the outer surface of the woven core with a plurality of laminate plies; and

curing the designed woven core and laminate plies in the mold to create the composite airfoil.

18. The method of claim 17 wherein the step of positioning points along the thickness curves comprises:

positioning a first point along one of the thickness curves at a first percentage P of a length of the thickness curve to define a pressure side of the outer surface of the woven core; and

positioning a second point along a same thickness curve as the first point at a second percentage P2 of the length of the thickness curve to define a suction side of the outer surface of the woven core.

19. The method of claim 17 and further comprising:

adjusting an outer surface of the woven core to create an adjusted outer surface of the woven core after the step of populating the space between the inner surface of the mold and the outer surface of the woven core with a plurality of laminate plies; and

re-populating the space between the inner surface of the mold and the adjusted outer surface of the woven core with a plurality of adjusted laminate plies after the step of adjusting the outer surface of the woven core.

20. A composite airfoil formed by the method of claim 17.