US 12,188,413 B2
Gas turbine engine and a method of operating a heat exchanger assembly for a gas turbine engine
Peter D Smout, Solihull (GB); Vasileios Kyritsis, Derby (GB); Benjamin J Eastment, Bristol (GB); Paul S Mccabe, Derby (GB); Sebastiaan Bottenheim, Bristol (GB); and Jason Chetwynd-Chatwin, Bristol (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Dec. 16, 2022, as Appl. No. 18/083,174.
Claims priority of application No. 0220100081 (GR), filed on Jan. 27, 2022; and application No. 2203636 (GB), filed on Mar. 16, 2022.
Prior Publication US 2023/0235700 A1, Jul. 27, 2023
Int. Cl. F02C 7/141 (2006.01)
CPC F02C 7/141 (2013.01) [F05D 2220/323 (2013.01); F05D 2260/213 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising an engine core, a bypass duct and a heat exchanger assembly, the heat exchanger assembly comprising a heat exchanger and a heat exchanger duct having an inlet region, an inflection region and an outlet region, wherein
the inlet region is configured to receive a flow of air from the bypass duct, the inflection region is configured to transfer the flow of air from the inlet region to the outlet region, and the outlet region is configured to discharge the flow of air into the bypass duct,
a direction of a centreline of the heat exchanger duct has a tangential component with respect to a principal rotational axis of the gas turbine engine at one or more of the inlet region, the inflection region and the outlet region,
the heat exchanger is within the inflection region and configured to transfer heat generated by the gas turbine engine into the flow of air as it passes through the inflection region,
the heat exchanger assembly is radially outward of the engine core and radially inward of the bypass duct,
the heat exchanger is configured to transfer heat generated by the engine core into the flow of air as it passes through the inflection region,
the heat exchanger duct comprises an inlet region opening and an outlet region opening,
the inlet region is configured to receive the flow of air from the bypass duct of the gas turbine engine via the inlet region opening,
the outlet region is configured to discharge the flow of air into the bypass duct via the outlet region opening,
the inlet region opening is at a first circumferential position about the principal rotational axis, and
the outlet region opening is at a second circumferential position about the principal rotational axis different from the first circumferential position.