US 12,264,627 B2
Heat exchanger for a gas turbine engine
Eyitayo James Owoeye, Houston, TX (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Mar. 2, 2022, as Appl. No. 17/684,772.
Prior Publication US 2023/0279811 A1, Sep. 7, 2023
Int. Cl. F02C 7/18 (2006.01); F01D 25/12 (2006.01); F28D 1/04 (2006.01); F28D 1/053 (2006.01); F28D 7/06 (2006.01); F28D 7/16 (2006.01)
CPC F02C 7/185 (2013.01) [F01D 25/125 (2013.01); F28D 1/0417 (2013.01); F28D 1/05366 (2013.01); F28D 7/06 (2013.01); F28D 7/16 (2013.01); F05D 2250/312 (2013.01); F05D 2250/313 (2013.01); F05D 2260/213 (2013.01); F05D 2260/2212 (2013.01); F05D 2260/2214 (2013.01); F05D 2260/232 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A turbine engine, comprising:
a compressor section, a combustion section, and a turbine section in a serial flow arrangement; and
a heat exchanger comprising:
a core having a unit cell defining a first primary channel, a second primary channel, a first secondary channel in flow communication with the first primary channel, and a second secondary channel in flow communication with the second primary channel, the first secondary channel traverses through the second primary channel and the second secondary channel traverses through the first primary channel, wherein the first primary channel and the first secondary channel are directly fluidly connected at a first junction and the second primary channel and the second secondary channel are directly fluidly connected at a second junction, and wherein the first primary channel and the first secondary channel collectively form a trifurcating flow arrangement at the first junction and the second primary channel and the second secondary channel collectively form a trifurcating flow arrangement at the second junction.