US 12,410,763 B2
Gas turbine engine with third stream
Brandon Wayne Miller, Middletown, OH (US); Randy M. Vondrell, Newport, KY (US); David Marion Ostdiek, Liberty Township, OH (US); Craig William Higgins, Liberty Township, OH (US); and Alexander Kimberely Simpson, Cincinnati, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Evendale, OH (US)
Filed on Sep. 18, 2024, as Appl. No. 18/888,873.
Application 18/888,873 is a continuation in part of application No. 18/675,270, filed on May 28, 2024.
Application 18/675,270 is a continuation of application No. 17/879,384, filed on Aug. 2, 2022, granted, now 12,031,504, issued on Jul. 9, 2024.
Prior Publication US 2025/0012235 A1, Jan. 9, 2025
This patent is subject to a terminal disclaimer.
Int. Cl. F02K 3/065 (2006.01); F02C 3/06 (2006.01)
CPC F02K 3/065 (2013.01) [F02C 3/06 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A 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 an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct;
a primary fan driven by the turbomachine; and
a secondary fan in serial flow order with the primary fan and located downstream of the primary fan within the inlet duct,
the gas turbine engine defining a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10,
wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.