US 12,421,917 B2
Gas turbine engine with third stream
Randy M. Vondrell, Newport, KY (US); Alexander Kimberley Simpson, Cincinnati, OH (US); David Marion Ostdiek, Liberty Township, OH (US); and Craig William Higgins, Liberty Township, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Evendale, OH (US)
Filed on Dec. 10, 2024, as Appl. No. 18/975,350.
Application 18/975,350 is a continuation in part of application No. 18/888,873, filed on Sep. 18, 2024.
Application 18/975,350 is a continuation in part of application No. 18/740,613, filed on Jun. 12, 2024.
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.
Application 18/740,613 is a continuation in part of application No. 17/879,384, filed on Aug. 2, 2022, granted, now 12,031,504, issued on Jul. 9, 2024.
Prior Publication US 2025/0129756 A1, Apr. 24, 2025
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;
a secondary fan located downstream of the primary fan within the inlet duct, the gas turbine engine defining a thrust to power airflow ratio (TPAR) between 3.5 and 100 and a core bypass ratio (CBR) between 0.1 and 10, wherein the TPAR 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 CBR is a ratio of the airflow through the fan duct to the airflow through the core duct; and
a booster located downstream of the secondary fan and comprising a booster rotor blade and a booster cowl, the booster cowl separating an upstream portion of the fan duct into an upper fan duct having an upper fan duct inlet and a lower fan duct having a lower fan duct inlet, the upper fan duct inlet and lower fan duct inlet collectively forming the fan duct inlet, the gas turbine engine defining a booster bleed ratio (BBR), wherein the BBR is a ratio of an airflow through the lower fan duct inlet to the airflow through the core duct, and
wherein BBR is less than or equal to an upper range of 0.005625×TPAR+0.2375, and greater than or equal to a lower range of 0.001125×TPAR+0.00977.