Patent ID: 11970979
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A turbine engine, comprising:
an engine core comprising a compressor, a combustor, and a turbine in axial flow arrangement;
a flow path extending through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core;
a component comprising an outer surface with at least one attenuation structure protruding into the flow path; and
a rotatable set of airfoils in one of the compressor or the turbine, whereby rotation of the set of airfoils forms the working airflow having a shockwave propagating onto the outer surface of the component and at least partially attenuated by the at least one attenuation structure;
wherein the at least one attenuation structure comprises at least one of a set of raised ridges in the outer surface or a set of raised panels in the outer surface, the at least one of the set of raised ridges or the set of raised panels arranged to form a set of honeycomb structures.