Patent ID: 8966756
Filing Date: 2015-03-03
Classification: F01D,F05D,Y10T

Abstract:
1. A method of assembling gas turbine engine front architecture comprising the steps of: positioning inner and outer fairings relative to one another; arranging multiple vanes circumferentially between the inner and the outer fairings, the arranging step includes inserting the vanes into first and second slots respectively provided in the outer and inner fairings, each vane includes an airfoil having outer and inner perimeters respectively received in the first and second slots, the arranging step includes providing gaps between the outer and the inner perimeters and the outer and inner fairings at their respective first and second slots, wherein the inner perimeters are suspended relative to the inner fairing and the outer perimeters are suspended relative to the outer fairing; applying a liquid sealant around a perimeter of each end of the vanes at the both of the respective inner and outer fairings, the applying step includes laying the liquid sealant about both the inner and outer perimeters within their respective gaps, the applying step is performed subsequent to the arranging step and the gaps are maintained during the applying step; and bonding and supporting the ends of vanes relative to the one of the fairings with the liquid sealant, wherein there is no direct contact between the vanes and the inner and outer fairings, wherein the liquid sealant provides the only mechanical connection and support of the vanes relative to both the inner and outer fairings.