US 12,031,481 B2
Air bottoming cycle air cycle system source
Alan Retersdorf, Avon, CT (US); Stephen H. Taylor, East Hartford, CT (US); and Oliver V. Atassi, Longmeadow, MA (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Sep. 1, 2023, as Appl. No. 18/459,716.
Application 18/459,716 is a continuation of application No. 17/951,936, filed on Sep. 23, 2022, granted, now 11,773,778.
Prior Publication US 2024/0102418 A1, Mar. 28, 2024
Int. Cl. F02C 6/18 (2006.01); F02C 7/32 (2006.01); F02C 9/18 (2006.01)
CPC F02C 6/18 (2013.01) [F02C 7/32 (2013.01); F02C 9/18 (2013.01); F05D 2220/62 (2013.01); F05D 2260/10 (2013.01); F05D 2260/213 (2013.01); F05D 2260/232 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A turbine engine assembly comprising:
a core engine including a core flow path where a core airflow is compressed in a main compressor section, communicated to a combustor section, mixed with fuel, and ignited to generate an exhaust gas flow that is expanded through a turbine section, wherein the turbine section is coupled to drive the main compressor section through an engine drive shaft;
a tap at a location upstream of the combustor section where a bleed airflow is drawn;
an auxiliary compressor section where a first portion of the bleed airflow is pressurized to generate a first compressed airflow;
a bleed air heat exchanger where a second portion of the bleed airflow directly from the tap is preheated;
an exhaust heat exchanger where the preheated second portion of the bleed airflow is heated by the exhaust gas flow;
a power turbine coupled to drive the auxiliary compressor section and driven by heated bleed airflow from the exhaust heat exchanger; and
an accessory system receiving pressurized airflow from the auxiliary compressor section.