US 12,331,684 B2
Strut microtube counterflow evaporator
Jon Erik Sobanski, Glastonbury, CT (US); and Jacob C. Snyder, East Haddam, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Nov. 7, 2023, as Appl. No. 18/503,279.
Prior Publication US 2025/0146440 A1, May 8, 2025
Int. Cl. F02C 7/10 (2006.01); F28D 7/16 (2006.01)
CPC F02C 7/10 (2013.01) [F28D 7/16 (2013.01); F05D 2260/221 (2013.01)] 18 Claims
OG exemplary drawing
 
1. An aircraft propulsion system comprising:
a core engine section defining a core flow path where an inlet airflow is compressed, mixed with fuel, and ignited to generate an exhaust gas flow;
an inner nacelle assembly surrounding the core engine section;
an outer nacelle assembly spaced radially apart from the inner nacelle assembly;
a condenser where water is extracted from the exhaust gas flow to generate a water flow; and
an evaporator system where thermal energy from the exhaust gas flow is utilized to generate a steam flow from at least a portion of the water flow from the condenser, the evaporator system including a strut heat exchanger extending radially between the inner nacelle assembly and the outer nacelle assembly, wherein within the strut heat exchanger a portion of the exhaust gas flow is placed in thermal communication with a portion of the water flow to generate the steam flow for injection into the core engine.