A gas turbine engine with a lubrication system, the gas turbine engine comprising: a ball bearing assembly (108, 110); a rotor circumscribing a rotational axis and journaled within the ball bearing assembly (108, 110), wherein the ball bearing assembly (108, 110) further comprises: an inner race (114a, 114b) attached to the rotor; a ball bearing (112a, 112b) adjacent to and located radially outward of the inner race (114a, 114b); an outer race (116a, 116b) adjacent to and located radially outward of the ball bearing (112a, 112b); and a retaining clip (118a, 118b) adjacent to the outer race (116a, 116b) and configured to retain the ball bearing assembly (108, 110) in place; and a lubrication system (104; 204) located radially outward from a rotational axis and radially outward and adjacent to the ball bearing assembly (108, 110), the lubrication system (104; 204) comprising: a lubrication channel (124; 224) having an inlet and an outlet (126; 226); and a dispersion cone (128; 228) adjacent to the outlet (126; 226) of the lubrication channel (124; 224), wherein the dispersion cone (128; 228) is adjacent to an exterior surface of the ball bearing assembly (108, 110) and configured to evenly coat the ball bearing assembly (108, 110) with a lubricant; and wherein the dispersion cone (128; 228) further comprises a dispersion enhancement feature, characterized in that the dispersion enhancement feature is at least one airfoil shaped spar. a ball bearing assembly (108, 110); a rotor circumscribing a rotational axis and journaled within the ball bearing assembly (108, 110), wherein the ball bearing assembly (108, 110) further comprises: an inner race (114a, 114b) attached to the rotor; a ball bearing (112a, 112b) adjacent to and located radially outward of the inner race (114a, 114b); an outer race (116a, 116b) adjacent to and located radially outward of the ball bearing (112a, 112b); and a retaining clip (118a, 118b) adjacent to the outer race (116a, 116b) and configured to retain the ball bearing assembly (108, 110) in place; and an inner race (114a, 114b) attached to the rotor; a ball bearing (112a, 112b) adjacent to and located radially outward of the inner race (114a, 114b); an outer race (116a, 116b) adjacent to and located radially outward of the ball bearing (112a, 112b); and a retaining clip (118a, 118b) adjacent to the outer race (116a, 116b) and configured to retain the ball bearing assembly (108, 110) in place; and a lubrication system (104; 204) located radially outward from a rotational axis and radially outward and adjacent to the ball bearing assembly (108, 110), the lubrication system (104; 204) comprising: a lubrication channel (124; 224) having an inlet and an outlet (126; 226); and a dispersion cone (128; 228) adjacent to the outlet (126; 226) of the lubrication channel (124; 224), a lubrication channel (124; 224) having an inlet and an outlet (126; 226); and a dispersion cone (128; 228) adjacent to the outlet (126; 226) of the lubrication channel (124; 224), wherein the dispersion cone (128; 228) is adjacent to an exterior surface of the ball bearing assembly (108, 110) and configured to evenly coat the ball bearing assembly (108, 110) with a lubricant; and wherein the dispersion cone (128; 228) further comprises a dispersion enhancement feature, characterized in that the dispersion enhancement feature is at least one airfoil shaped spar.