B - Operations – Transporting – 29 – C
Patent
B - Operations, Transporting
29
C
B29C 70/86 (2006.01) B29D 99/00 (2010.01) B29C 65/48 (2006.01) B29C 70/44 (2006.01)
Patent
CA 2196424
A fiberglass or other material skin is applied to a composite airfoil structure (2) in a mold assembly (22) having a partially compliant caul plate component which defines the shape of the lower surface of the airfoil. The caul plate component includes a first portion (34) which is essentially rigid and which covers the leading edge (16) of the airfoil. The rigid portion of the caul plate component provides improved conformation of the airfoil skin to the leading edge of the airfoil. The caul plate component also includes a compliant portion (36) which covers and defines the shape of the trailing edge of the lower surface of the airfoil. The stiffness of the caul plate component also has a variable stiffness zone (38) which interconnects the rigid and compliant portions thereof. The use of rigid and compliant portions on the caul plate provides for a controlled conformance of the skin to the leading edge of the airfoil, while allowing the skin to accurately conform to the remainder of the airfoil in spite of variations in the dimensions of internal operating components of the airfoil.
On applique une peau de fibre de verre ou d'un autre matériau sur une structure (2) composite à profil aérodynamique dans un ensemble moule (22) dont un composant est une plaque d'acier partiellement souple qui détermine la forme de la surface inférieure de la structure aérodynamique. Cette plaque comprend une première portion (34), essentiellement rigide, qui couvre le bord (16) d'attaque de la structure et procure une conformation perfectionnée de la peau de la structure aérodynamique au niveau du bord d'attaque de celle-ci. Ladite plaque comprend également une portion souple (36) qui couvre la forme du bord de fuite de la surface inférieure de la structure aérodynamique, et détermine cette forme. La portion rigide de la plaque possède également une zone (38) à rigidité variable reliant les portions rigides et souples de la plaque. L'utilisation des portions rigide et souple sur ladite plaque permet de régler la conformation de la peau au niveau du bord d'attaque de la structure aérodynamique tout en permettant à cette peau de se conformer précisément au reste de ladite structure malgré des variations dans les dimensions des composants fonctionnels internes de la structure.
Jones Corey D.
Kovalsky David A.
Reinfelder William C.
Norton Rose Or S.e.n.c.r.l. S.r.l./llp
United Technologies Corporation
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