Condenser for hydrogen steam injected turbine engine
A propulsion system for an aircraft includes a hydrogen fuel system supplying hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from an exhaust gas flow and includes a plurality of spiral passages disposed within a collector. The spiraling passages generate a transverse pressure gradient to direct water out of the exhaust gas flow toward the collector.
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 fuel and ignited to generate a high energy gas flow that is expanded through a turbine section;
a hydrogen fuel system configured to supply the 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 axial passages receiving the high energy gas flow along a condenser axis, a transition region that introduces a swirl into the high energy gas flow received from the plurality of axial passages, and a plurality of spiral passages, a collector is in communication with a water passage, wherein the plurality of axial passages, the transition region and the spiral passages are aligned sequentially along the condenser axis radially inward of an outer periphery of the collector, and the plurality of spiral passages are configured to receive the high energy gas flow and generate a transverse pressure gradient to direct the water out of the high energy gas flow radially outward 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.
2. The propulsion system as recited in claim 1 , wherein the condenser is configured to receive a cooling flow to cool the high energy gas flow.
3. The propulsion system as recited in claim 2 , wherein the condenser is configured to receive the cooling flow at a location along an outer periphery of the spiral passages.
4. The propulsion system as recited in claim 2 , wherein the plurality of spiral passages are defined between a plurality of curved layers extending axially and curving about the condenser axis.
5. The propulsion system as recited in claim 4 , wherein the plurality of curved layers include openings configured to exhaust the water collected from the high energy gas flow to the collector.
6. The propulsion system as recited in claim 2 , wherein the condenser includes a plurality of cooling flow passages that extend axially along a condenser axis and each of the plurality of spiral passages wrap around at least one of the plurality of cooling flow passages.
7. The propulsion system as recited in claim 6 , wherein each of the plurality of spiral passages include a condensate opening for communicating the water extracted from the high energy gas flow with the collector.
8. The propulsion system as recited in claim 7 , including an inlet manifold configured to direct the high energy gas flow into the plurality of spiral passages and the cooling flow into the plurality of cooling flow passages.
9. The propulsion system as recited in claim 1 , wherein the plurality of spiral passages include a hydrophilic coating.
10. The propulsion system as recited in claim 1 , wherein the plurality of spiral passages include a hydrophobic coating.
11. The propulsion system as recited in claim 1 , wherein the plurality of spiral passages include a textured surface.
12. The propulsion system as recited in claim 1 , including a water storage tank and the collector is configured to communicate the water extracted from the high energy gas flow to the water storage tank.
13. The propulsion system as recited in claim 1 , wherein a cooling flow is directed along the outer periphery of the condenser.
14. The propulsion system as recited in claim 1 , wherein a cooling flow and the high energy gas flow are directed through separate and adjacent ones of the plurality of spiral passages.
15. The propulsion system as recited in claim 1 , wherein the plurality of spiral passages includes an aft end where the high energy gas flow is exhausted axially from the plurality of spiral passages.
16. The propulsion system as recited in claim 1 , wherein the plurality of spiral passages extend axially from the transition region along the condenser axis.