US 11,719,441 B2
Systems and methods for providing output products to a combustion chamber of a gas turbine engine
Honggang Wang, Clifton Park, NY (US); and Michael Anthony Benjamin, Cincinnati, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jan. 4, 2022, as Appl. No. 17/568,341.
Prior Publication US 2023/0213197 A1, Jul. 6, 2023
Int. Cl. F23R 3/40 (2006.01); F23R 3/28 (2006.01)
CPC F23R 3/40 (2013.01) [F23R 3/28 (2013.01)] 16 Claims
OG exemplary drawing
 
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.