Patent ID: 8979484
Filing Date: 2015-03-17
Classification: F01D,F05D

Abstract:
1. A casing for an aircraft turbofan bypass engine comprising: an outer ring and an inner hub defining an annular space therebetween, the inner hub configured for connection to at least one spool bearing, the outer ring configured for connection to at least one engine mount; a plurality of hollow radial struts arranged in a circumferential array mounting the inner hub to the outer ring; and an annular splitter box disposed between the inner hub and outer ring and configured to be connected with an upstream annular splitter tip structure to divide an air flow through the annular space into a core air flow and a bypass air flow, the splitter box defined by an inner wall and an outer wall, the outer ring and the outer wall of the splitter box in combination forming a bypass duct for the bypass air flow, the inner wall of the splitter box and the inner hub in combination forming a core fluid path for the core air flow, the splitter box further having an intermediate wall positioned radially between the inner and outer walls and extending downstream conically inward from said outer wall, the splitter box having openings in each of said inner, outer and intermediate walls for receiving said struts passing therethrough, each of said splitter box walls terminating at a downstream end configured for connection to a downstream engine case, the struts being mounted to said splitter box with a respective peripheral weld or braze between the intermediate wall and the struts at the openings of the intermediate wall.