A deaeration rotor (90) for an aircraft engine lubrication system (30) comprises: an internal ring (92) about an axis (A) having a radially outer internal ring surface (92d) defining an inner boundary of an inner passage (P) of the deaeration rotor (90); a...

An internal combustion engine comprising: - a crankcase (12), - an oil sump (16), - at least one balancing shaft (20) rotatably mounted in a balancing tunnel (22) formed in the crankcase (12), wherein the balancing tunnel (22) has a first end portion (22a)...