B - Operations – Transporting – 29 – C
Patent
B - Operations, Transporting
29
C
B29C 69/00 (2006.01) B29D 99/00 (2010.01) B29C 33/30 (2006.01) B29C 33/72 (2006.01) B29C 53/56 (2006.01) B29C 70/34 (2006.01) B29C 70/48 (2006.01) B64C 1/00 (2006.01) F01D 5/28 (2006.01) F01D 9/02 (2006.01) B29D 31/00 (2006.01)
Patent
CA 2102239
A multi-vane structure (8) for incorporation in an aircraft gas turbine engine has vanes (9) of complex geometry made of braided fibers which are continuous about the cavities defined by the vanes. These complex geometry parts are prepared by providing a plurality of removable mandrels (14a, 14b), stacking the mandrels along a horizontal axis (18) in a cavity end (15b) to cavity end (16a) configuration, braiding (23) about the mandrels, cutting the mandrels adjacent the cavity end faces (17), side stacking the mandrels so the faces are placed in a parallel orientation and molding. Utilizing braided fibers instead of hand lay-up woven fibers eliminates seams and produces cavities having continuous fibers about the periphery thereof which substantially increases the strength and dimensional reproducibility of the part.
Forman Thomas P.
Fox Rance B.
Sabak George E.
Sands Timothy A.
Vallier Paul A.
Dow-United Technologies Composite Products Inc.
Kirby Eades Gale Baker
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