US 12,065,989 B2
Gas turbine engine with third stream
David Marion Ostdiek, Liberty Township, OH (US); and William Joseph Solomon, Montgomery, OH (US)
Assigned to General Electric Company, Cincinnati, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Oct. 31, 2022, as Appl. No. 17/977,292.
Application 17/977,292 is a continuation in part of application No. 17/717,462, filed on Apr. 11, 2022.
Prior Publication US 2023/0323837 A1, Oct. 12, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. B64C 11/48 (2006.01); F02K 3/06 (2006.01); B64C 11/00 (2006.01); B64C 11/18 (2006.01); F01D 9/02 (2006.01); F01D 17/10 (2006.01); F01D 17/14 (2006.01); F02C 7/36 (2006.01); F02K 3/065 (2006.01); F02K 3/072 (2006.01); F04D 19/02 (2006.01); F04D 29/34 (2006.01); F04D 29/38 (2006.01)
CPC F02K 3/06 (2013.01) [B64C 11/001 (2013.01); B64C 11/18 (2013.01); B64C 11/48 (2013.01); F01D 9/02 (2013.01); F01D 17/105 (2013.01); F01D 17/14 (2013.01); F02C 7/36 (2013.01); F02K 3/065 (2013.01); F02K 3/072 (2013.01); F04D 19/02 (2013.01); F04D 29/34 (2013.01); F04D 29/388 (2013.01); F05D 2200/14 (2013.01); F05D 2200/211 (2013.01); F05D 2220/323 (2013.01)] 19 Claims
OG exemplary drawing
 
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 comprising an inlet splitter defining in part an inlet to a working gas flowpath and a fan duct splitter defining in part an inlet to a fan duct flowpath;
a primary fan driven by the turbomachine defining a primary fan tip radius R1 between 2 feet and 14 feet, a primary fan hub radius R2, and a primary fan specific thrust rating TP; 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, a secondary fan hub radius R4, and a secondary fan specific thrust rating TS,
wherein the gas turbine engine defines an Effective Bypass Area (EBA), and wherein a ratio of R1 to R3 equals

OG Complex Work Unit Math
and
wherein EFP is between 0.15 and 33, wherein RqRPrim.-Fan is a ratio of R2 to R1, wherein RqRSec.-Fan is a ratio of R4 to R3, wherein the primary fan specific thrust rating TP is between 0.08 and 0.59, wherein the secondary fan specific thrust rating TS is between 0.21 and 0.6, and wherein the Effective Bypass Area (EBA) is between 0.2% and 15%.