Patent ID: 11859516
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine comprising:
a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath;
a primary fan driven by the turbomachine defining a primary fan tip radius R1 and a primary fan hub radius R2; and
a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3;
wherein a ratio of R1 to R3 is between 2 and 7.