Patent ID: 8966755
Filing Date: 2015-03-03
Classification: F01D,F05D,Y10T

Abstract:
1. A method of assembling a gas turbine engine front architecture comprising the steps of: securing inner and outer fairings within a fixture relative to one another; securing multiple vanes between the inner and outer fairing within the fixture, wherein securing the multiple vanes includes positioning each of the multiple vanes within an opening of the inner fairing and an opening of the outer fairings such that no part of the multiple vanes are in direct engagement with the inner fairing and the outer fairing; applying a curable material at an interface between each of the multiple vanes and the inner and outer fairings; curing the curable material while maintaining a relative position between the multiple vanes and the inner and outer fairings, wherein the curable material remains flexible once cured; and releasing the multiple vanes and the inner and outer fairings from the fixture.