Gas turbine engine lubrication system

A lubrication system for a gas turbine engine comprising:

• a first tubular rotor shaft including an outer surface and an inner surface disposed coaxially about a centerline axis, a first portion, and an outer seat spaced axially from said first portion;
• a second tubular rotor shaft disposed coaxially about said centerline axis and spaced radially inwardly from said first shaft and including a first portion disposed adjacent to said first shaft first portion, and an inner seat aligned axially with said first outer seat;
• a differential first bearing disposed in said first outer and inner seats;
• an annular first scoop extending axially from said first shaft outer surface at said first portion thereof;
• a plurality of circumferentially spaced apart first holes extending axially through said first shaft radially below said first scoop and in flow communication therewith;
• an annular second scoop extending axially from said first inner seat of said second shaft;
• a plurality of circumferentially spaced apart second holes extending axially through said first inner seat from radially below said second scoop and in flow communication therewith;
• a first shell extending axially between said second scoop in said first shaft inner surface from radially above said first holes in flow communication therewith;
• and
• means for injecting oil under said first scoop for flow by centrifugal force from rotation of said first shaft through said first holes and along said first shell into said second scoop for flow through said second holes to lubricate said first bearing.