公开(公告)号：US20240401491A1

公开(公告)日：2024-12-05

申请号：US18678000

申请日：2024-05-30

Applicant: General Electric Company

Inventor： Syed Khalid ,  David Marion Ostdiek ,  Jeffrey S. Spruill ,  Daniel Lawrence Tweedt ,  William Joseph Solomon ,  Brandon Wayne Miller ,  Randy M. Vondrell ,  Kevin Edward Hinderliter

IPC: F01D9/04 ,  F01D5/14

Abstract: A gas turbine engine is provided, comprising: a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; and a fan section having a fan drivingly coupled to the turbomachine and an airflow surface rotatable with the fan and exposed to a fan airflow provided to and through the fan during operation of the gas turbine engine, the airflow surface defining a plurality of boundary layer openings configured to ingest a boundary layer of the fan airflow over the airflow surface during operation of the gas turbine engine.