Patent ID: 9267435
Filing Date: 2016-02-23
CPC Classification: F02C

Claim Text:
1. A turbofan gas turbine engine comprising: a core portion of the engine; an annular bypass duct wall coaxially surrounding and supporting the core portion, thereby to define an annular bypass air passage radially between the core portion and the bypass duct wall for directing a bypass air flow passing therethrough; and a support link having a plurality of rods extending across the annular bypass air passage to interconnect the core portion and the annular bypass duct wall, the plurality of rods being connected to the core portion by a cam-type apparatus, the cam-type apparatus having a plurality of eccentric rotating pins adjustable for centering the core portion with respect to the annular bypass duct wall and having a plurality of connecting bases circumferentially spaced apart and attached to the core portion, each of the plurality of eccentric rotating pins having a connecting section received in a hole of one of the plurality of rods and a base section received in a hole substantially radially extending through one of the plurality of connecting bases, the base section being eccentric to the connecting section at an eccentric distance, the base section being rotatable about a central axis thereof to adjust a position of the connecting section which is connected to one of the plurality of rods, the base section being lockable to lock the adjusted position of the connecting section and connected to the one of the plurality of rods.