| CPC H01M 8/04111 (2013.01) [H01M 4/8652 (2013.01); H01M 2004/8684 (2013.01); H01M 2008/1293 (2013.01); H01M 2250/20 (2013.01)] | 20 Claims |
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1. A propulsion system for an aircraft, the aircraft comprising an aircraft fuel supply, the propulsion system comprising:
a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from the aircraft fuel supply, wherein the combustion section includes, a swirler assembly, an inner liner and an outer liner, wherein the inner liner and the outer liner define a combustion chamber, and wherein the swirler assembly is disposed upstream from the combustion chamber; and
a fuel cell assembly comprising a plurality of fuel cell stacks arranged circumferentially about the outer liner or the inner liner, each fuel cell stack of the plurality of fuel cell stacks having a solid oxide fuel cell, the solid oxide fuel cell defining an outlet positioned to remove output products from the solid oxide fuel cell and provide the output products to the combustion chamber through the outer liner or the inner liner downstream from the swirler assembly, the solid oxide fuel cell comprising:
a cathode;
an electrolyte layer; and
an anode positioned opposite the electrolyte layer from the cathode, the anode comprising a cermet, the cermet comprising less than 25% by volume nickel.
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