Ring gear mounting arrangement with oil scavenge scheme

A gas turbine engine comprising:

• a fan supported on a fan shaft by at least one roller bearing and having a plurality of fan blades;
• a bypass ratio greater than about ten (10);
• an epicyclic gear system connected to the fan shaft, the epicyclic gear system having a gear reduction ratio of greater than 2.5, a plurality of intermediate gears, and a ring gear with an aperture that is, wherein the ring gear includes a first portion separated from a second portion, the first portion and the second portion each include a radially extending flange that extends radially outward away from a corresponding set of opposed angled teeth;
• a torque frame as least partially supporting the gear system with respect to a housing to facilitate segregation of vibrations;
• and
• an annular channel axially aligned with the aperture and located radially outward from the aperture.