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

Claim 11:
12. A method of operating a turbine engine having an engine core comprising a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow path through the engine core, the method comprising:
generating a shockwave in the working airflow that propagates onto an outer surface of a component within the turbine engine, the outer surface comprising at least one attenuation structure protruding into the flow path; and
directing the shockwave over the at least one attenuation structure to at least partially attenuate the shockwave;
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.