US 12,215,622 B1
Partial exhaust condensation intercooling
Neil J. Terwilliger, Cheshire, CT (US); and Lance L. Smith, West Hartford, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Aug. 29, 2023, as Appl. No. 18/457,458.
Int. Cl. F02C 7/141 (2006.01); F02C 3/06 (2006.01); F02C 7/143 (2006.01); F02C 7/16 (2006.01)
CPC F02C 7/1435 (2013.01) [F02C 3/06 (2013.01); F02C 7/16 (2013.01); F05D 2220/323 (2013.01); F05D 2260/212 (2013.01); F05D 2260/609 (2013.01)] 18 Claims
OG exemplary drawing
 
1. An aircraft propulsion system comprising:
a compressor section where an inlet airflow is compressed to generate a compressed airflow;
a combustor section where the compressed airflow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path;
a turbine section through which the exhaust gas flow expands to generate a mechanical power output, wherein the exhaust gas flow is split into at least a first exhaust gas flow and a second exhaust gas flow, wherein the second exhaust gas flow is of a flow volume that is less than that of the first exhaust gas flow; and
a condenser where water is extracted from the second exhaust gas flow to generate an extracted water flow; and
a first heat exchanger where at least a portion of the extracted water flow is utilized for cooling a core flow along the core flow path.