US 12,331,679 B2
Air recuperated engine with air reinjection
Stephen H. Taylor, East Hartford, CT (US); Alan Retersdorf, Avon, CT (US); Oliver V. Atassi, Longmeadow, MA (US); and Nathan A Snape, Tolland, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Aug. 15, 2024, as Appl. No. 18/805,867.
Application 18/805,867 is a continuation of application No. 17/951,972, filed on Sep. 23, 2022, granted, now 12,078,102.
Prior Publication US 2024/0401523 A1, Dec. 5, 2024
Int. Cl. F02C 6/08 (2006.01); F02C 3/13 (2006.01); F02C 6/10 (2006.01); F02C 6/18 (2006.01); F02C 7/08 (2006.01); F02C 7/10 (2006.01); F02C 7/12 (2006.01); F02C 7/16 (2006.01); F02C 7/18 (2006.01); F02C 7/32 (2006.01); F02C 9/18 (2006.01); F02C 9/52 (2006.01); F02G 5/00 (2006.01); F02K 3/02 (2006.01); F02K 3/077 (2006.01); F02K 3/10 (2006.01)
CPC F02C 6/08 (2013.01) [F02C 3/13 (2013.01); F02C 6/10 (2013.01); F02C 6/18 (2013.01); F02C 7/08 (2013.01); F02C 7/10 (2013.01); F02C 7/12 (2013.01); F02C 7/16 (2013.01); F02C 7/18 (2013.01); F02C 7/32 (2013.01); F02C 9/18 (2013.01); F02C 9/52 (2013.01); F02G 5/00 (2013.01); F02K 3/02 (2013.01); F02K 3/077 (2013.01); F02K 3/10 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A gas turbine engine assembly 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 an exhaust gas flow that is expanded through a turbine section, wherein the turbine section is coupled to drive the compressor section through an engine drive shaft;
a tap at a location up stream of the combustor section for drawing a bleed airflow;
an exhaust heat exchanger configured to transfer thermal energy from the exhaust gas flow into the bleed airflow to generate a heated bleed airflow;
an injection location in communication with a portion of the turbine section for communicating the heated bleed airflow from the exhaust heat exchanger into the turbine section separate and independent from the exhaust gas flow generated in the combustor section, wherein the heated bleed airflow is expanded against a surface of a turbine blade to drive the turbine section; and
wherein the turbine section includes a low pressure turbine section with a first low pressure turbine and a second low pressure turbine and the injection location is disposed aft of the first low pressure turbine.