AUTOMATED LAMINATE COMPOSITE SOLID PLY GENERATION

• US 20160250812A1
• Filed: 10/01/2014
• Published: 09/01/2016
• Est. Priority Date: 10/14/2013
• 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: Roach, James T., Hepworth, Ammon, Chang, Hoyt Y., Luczak, Blake J.
• Application Number:
  US15/028,557
• Publication Number:
  US 20160250812A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B29C 70/345 using matched moulds
• CPC Class Codes: B29C 70/386 Automated tape laying [ATL]
• CPC Class Codes: B29C 70/48 and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM] , e.g. by vacuum
• CPC Class Codes: B29D 99/0025 Producing blades or the like, e.g. blades for turbines, propellers, or wings
• CPC Class Codes: B29K 2075/00 Use of PU, i.e. polyureas or polyurethanes or derivatives thereof, as moulding material
• CPC Class Codes: B29K 2105/0872 Prepregs
• CPC Class Codes: B29L 2031/082 Blades, e.g. for helicopters
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments

Abstract

A method for creating a laminate design geometry for a composite component according to an exemplary aspect of the present disclosure includes, among other things, defining a spatial volume of a solid defined between a plurality of external surface boundaries, defining an offset boundary spaced by an offset value from one of the plurality of external surface boundaries to define a region in which a ply is to be received, defining a partitioning boundary dividing the region into a ply portion and a resin portion; and repeating the steps of defining an offset boundary and defining a partitioning boundary by defining an offset boundary from any one of the plurality of external surface boundaries and the offset boundary in a previous iteration of defining an offset boundary.

Claims

1. Method for creating a laminate design geometry for a composite component, the method comprising:

a) defining a spatial volume of a solid defined between a plurality of external surface boundaries;

b) defining an offset boundary spaced by an offset value from one of said plurality of external surface boundaries to define a region in which a ply is to be received;

c) defining a partitioning boundary dividing said region into a ply portion and a resin portion; and

d) repeating steps b) and c) by defining an offset boundary from any one of said plurality of external surface boundaries and said offset boundary in a previous iteration of step b).

2. The method of claim 1, wherein a number of iterations of step d) is based upon a distance between each said region defined in step b) being less than said offset value.

3. The method of claim 1, wherein said ply portion is represented by a first material and said resin portion is represented by a second material different from said first material.

4. The method of claim 1, wherein said offset value is a thickness of said ply.

5. The method of claim 1, wherein a cross section of said spatial volume is defined by at least three external surface boundaries.

6. The method of claim 1, wherein each of said external surface boundaries extends between two inflection points at a cross section of said spatial volume.

7. The method of claim 1, wherein said partition boundary perpendicularly intersects said offset boundary at an intersection of the respective offset boundary and one of said plurality of external surface boundaries or another offset boundary.

8. The method of claim 1, further comprising accessing a ply table defining at least one ply attribute.

9. The method of claim 1, further comprising laying up a plurality of plies of a laminate according to said laminate design geometry.

10. The method of claim 1, further comprising defining a mid-surface boundary extending from said partitioning boundary, wherein a length of said ply corresponds to said mid-surface boundary.

11. Method for fabricating a composite component according to a laminate design geometry, the method comprising:

laying up a plurality of plies of a laminate according to a predetermined laminate design geometry,

wherein said predetermined laminate design geometry includes data representing a plurality of regions in which a ply of said plurality of plies is to be received, each of said regions being defined by an offset boundary spaced by an offset value from an external surface boundary or another offset boundary, and each of said regions being divided into a ply portion and a resin portion by a partition boundary.

12. The method of claim 11, further comprising injecting an amount of resin in said resin portion.

13. The method of claim 11, further comprising generating a data set representing said predetermined laminate design geometry.

14. A composite component, comprising:

a plurality of plies and a resin arranged according to a predetermined laminate design geometry,

wherein said predetermined laminate design geometry includes data representing a plurality of regions in which a ply of said plurality of plies is to be received, each of said regions being defined by an offset boundary spaced by an offset value from an external surface boundary or another offset boundary, and each of said regions being divided into a ply portion and a resin portion by a partition boundary.

15. The composite component of claim 14, wherein said ply portion is a first material and said resin portion is a second material different from said first material.

16. The composite component of claim 15, wherein said first material includes a composite structure and said second material includes a resin.

17. The composite component of claim 14, wherein said offset value is a thickness of said ply.

18. The composite component of claim 14, wherein a cross section of said predetermined laminate design geometry is defined by at least three external surface boundaries.

19. The composite component of claim 14, further comprising an overwrap extending from at least two of said regions.

20. The composite component of claim 14, wherein said predetermined laminate design geometry represents an airfoil.