Patent ID: 11898518
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 0:
1. A direct drive gas turbine engine mounted to an aircraft wing having a leading edge and a trailing edge, the direct drive gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction, the gas turbine engine comprising:
a fan assembly comprising a plurality of fan blades rotatably coupled to a fan rotor, the fan blades defining a maximum fan diameter and a fan pressure ratio; and
a low pressure (LP) turbine defining a core flowpath therethrough generally along the longitudinal direction, wherein the core flowpath defines a maximum outer flowpath diameter relative to the axial centerline, wherein the maximum outer flowpath diameter is defined at two or more rotating stages at a downstream-most end of the LP turbine, and wherein the gas turbine engine defines a fan to turbine diameter ratio of the maximum fan diameter to the maximum outer flowpath diameter less than or equal to 1.8, and wherein the fan to turbine diameter ratio over the fan pressure ratio is 0.90 or greater,
wherein a containment shield extends over the LP turbine from a first turbine rotor through a last turbine rotor along the longitudinal direction between the leading edge and the trailing edge of the aircraft wing,
wherein the containment shield is coupled to an outer casing of the engine extended generally along the longitudinal direction, wherein the containment shield extends at least partially along the circumferential direction from a top dead center reference line along the circumferential direction, and
wherein the containment shield extends 60 degrees or less from the top dead center reference line along the circumferential direction.