US 11,920,515 B2
Condenser for hydrogen steam injected turbine engine
Abbas A. Alahyari, Glastonbury, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on May 13, 2022, as Appl. No. 17/744,379.
Prior Publication US 2023/0366351 A1, Nov. 16, 2023
Int. Cl. F02C 7/141 (2006.01)
CPC F02C 7/141 (2013.01) [F05D 2220/323 (2013.01); F05D 2220/60 (2013.01); F05D 2260/213 (2013.01); F05D 2260/2214 (2013.01); F05D 2260/60 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A propulsion system for an aircraft comprising:
a core engine including a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen based fuel and ignited to generate a high energy gas flow that is expanded through a turbine section;
a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path;
a condenser arranged along the core flow path and configured to extract water from the high energy gas flow, the condenser including a plurality of rotating passages disposed in a collector, wherein the passages are configured to rotate about a condenser axis to generate a transverse pressure gradient to direct water out of the high energy gas flow toward the collector; and
an evaporator arranged along the core flow path and configured to receive a portion of the water extracted by the condenser to generate a steam flow, wherein the steam flow is injected into the core flow path upstream of the turbine section.