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

Claim 8:
9. The gas turbine engine mounted to the aircraft wing of claim 1, wherein the LP turbine further defines a first turbine rotor at an upstream-most end of the LP turbine and a last turbine rotor at the downstream-most end of the LP turbine, and further wherein the LP turbine defines a turbine burst area inward of the aircraft wing along a latitudinal direction, the turbine burst area extended from the axial centerline at a first angle along a plane of rotation of the first turbine rotor toward the upstream-most end, and at a second angle along a plane of rotation of the last turbine rotor toward the downstream-most end.