Patent ID: 11859546
Assignee: GE AVIO S.R.L.
Field: Mechanical elements (Mechanical engineering)
Classification: CPC F | IPC F

Claim 15:
16. A gearbox for a gas turbine engine, the gearbox comprising:
a rotor rotatable about a rotational axis in a rotational direction, the rotor having a radial direction and expelling oil radially outward when the rotor rotates;
an outer casing positioned radially outward of the rotor; and
a gutter positioned radially outward of the rotor in the radial direction of the rotor between the outer casing and the rotor, the gutter positioned to collect oil expelled by the rotor when the rotor rotates and including a plurality of gutter openings around a circumference of the gutter, each gutter opening of the plurality of gutter openings allowing oil to flow out of the gutter and into a cavity formed between the gutter and the outer casing,
wherein the rotor is positioned eccentrically with respect to at least one of the outer casing and the gutter and the at least one of the outer casing and the gutter has an eccentric surface,
wherein the rotor has a radius (Rr),
wherein the eccentric surface has (i) a maximum distance from the rotational axis to the eccentric surface (Dsmax), (ii) a minimum distance from the rotational axis to the eccentric surface (Dsmin), and (iii) an eccentricity ratio (ε) from two thousandths to seventy-six hundredths, the eccentricity ratio (ε) being the ratio of an eccentricity distance (e) to a centered clearance (C), and
wherein the eccentricity distance (e) is given by the following formula: e=(Dgmax−Dgmin)/2, and centered clearance (C) is given by the following formula: C=(Dgmax+Dgmin)/2−Rr.