Patent ID: 11920539
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 6:
7. An aircraft, comprising:
a fuselage, a wing and a turbofan engine, the turbofan engine including a turbine section and an exhaust nozzle disposed downstream from the turbine section, wherein the exhaust nozzle comprises:
a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end, wherein each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root; and
wherein at least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip, and wherein the inner wall extends along the first segment, the second segment and the third segment, wherein the first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment; and
wherein the inner wall along the first segment has a radius that is variable with respect to the axial centerline from the root to a first inflection or termination point, the inner wall along the second segment maintains a constant radius from the first inflection or termination point to a second inflection or termination point, and the inner wall along the third segment has a decreasing radius from the second inflection or termination point to the tip.