US 12,031,478 B2
Air bottoming cycle driven propulsor
Stephen H. Taylor, East Hartford, CT (US); Alan Retersdorf, Avon, CT (US); and Oliver V. Atassi, Longmeadow, MA (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Sep. 23, 2022, as Appl. No. 17/951,991.
Application 17/951,991 is a continuation in part of application No. 17/724,904, filed on Apr. 20, 2022, granted, now 11,702,981.
Prior Publication US 2024/0117764 A1, Apr. 11, 2024
Int. Cl. F02C 6/08 (2006.01); F02C 3/10 (2006.01); F02C 7/18 (2006.01); F02C 7/32 (2006.01); F02C 7/36 (2006.01); F02C 9/18 (2006.01)
CPC F02C 6/08 (2013.01) [F02C 3/10 (2013.01); F02C 7/18 (2013.01); F02C 7/32 (2013.01); F02C 7/36 (2013.01); F02C 9/18 (2013.01); F05D 2220/323 (2013.01); F05D 2220/36 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft propulsion system comprising:
a core engine including a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that is expanded through a turbine section for powering a primary propulsor;
a tap at a location upstream of the combustor section where a bleed airflow is drawn;
a heat exchanger where the bleed airflow is heated by the gas flow;
a power turbine through which heated bleed airflow is expanded to generate a work output; and
a secondary propulsor driven by the work output generated by the power turbine.