CPC F23R 3/40 (2013.01) [F23R 3/28 (2013.01)] | 16 Claims |
9. An integrated reformer and combustor assembly for a turbomachine, the turbomachine defining an axial direction and a radial direction, the integrated reformer and combustor assembly comprising: a combustor a defining a combustion chamber and an opening at an upstream end of the combustion chamber, the combustor configured to receive a flow of aviation fuel through the opening when incorporated into the turbomachine; and a reformer stack extended around the combustion chamber and configured to provide output products to the combustion chamber, the reformer stack comprising a plurality of reformers aligned in the radial direction, wherein the reformer stack is positioned at a downstream section of the combustion chamber along the axial direction, wherein the propulsion system defines a downstream distance in the axial direction between the opening of the combustor and an upstream end of the reformer stack, and wherein the downstream distance is at least 30% of a length of the combustion chamber in the axial direction.
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