US 11,982,232 B2
Aircraft heat exchangers
James F. Wiedenhoefer, Windsor, CT (US); Russell J. Bergman, South Windsor, CT (US); William P. Stillman, Westminster, CO (US); and Patrick M. Hart, Newington, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Jan. 23, 2023, as Appl. No. 18/100,130.
Application 18/100,130 is a continuation of application No. 17/124,551, filed on Dec. 17, 2020, granted, now 11,585,273.
Claims priority of provisional application 62/963,297, filed on Jan. 20, 2020.
Prior Publication US 2023/0160342 A1, May 25, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/18 (2006.01); B64D 33/10 (2006.01); F02K 3/02 (2006.01); F02K 3/105 (2006.01); F28D 7/00 (2006.01)
CPC F02C 7/185 (2013.01) [B64D 33/10 (2013.01); F02K 3/025 (2013.01); F02K 3/105 (2013.01); F28D 7/0075 (2013.01); F05D 2220/323 (2013.01); F05D 2260/213 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine engine heat exchanger comprising:
a manifold having a first face and a second face opposite the first face;
a plurality of first plates along the first face, each first plate having an interior passageway;
a plurality of second plates along the second face, each second plate having an interior passageway; and
a first flowpath passing through the interior passageways of the first plates, the manifold, and the interior passageways of the second plates,
wherein:
the manifold forms a transfer plenum into which respective first flowpath legs through the first plates merge and from which respective second flowpath legs through the second plates split,
the manifold forms an inlet plenum from which respective first flowpath legs through the first plates split; and
the manifold forms an outlet plenum into which respective first flowpath legs through the second plates merge.