US 11,674,442 B2
Gas turbine engine and method of operating
Lawrence Bernard Kool, Clifton Park, NY (US); Brandon Flowers Powell, Mason, OH (US); and Narendra Digamber Joshi, Guilderland, NY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Mar. 16, 2021, as Appl. No. 17/203,052.
Claims priority of provisional application 62/990,174, filed on Mar. 16, 2020.
Prior Publication US 2021/0285376 A1, Sep. 16, 2021
Int. Cl. F02C 7/22 (2006.01); F02C 7/16 (2006.01)
CPC F02C 7/22 (2013.01) [F02C 7/16 (2013.01); F05D 2220/323 (2013.01); F05D 2260/213 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A gas turbine engine, the gas turbine engine comprising:
a compressor, a combustor, and a turbine in serial flow relationship;
a heat exchanger having an inlet, an outlet, and an internal surface coated with a catalyst, the heat exchanger being located upstream of the compressor;
a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger;
a source of oxygen in fluid communication with the inlet of the heat exchanger;
a distribution system for receiving reformed hydrocarbon fuel from the heat exchanger; and
a hyperburner or augmentor, wherein the hyperburner or augmentor includes a hyperburner fuel nozzle, and wherein the distribution system is configured to selectively deliver liquid hydrocarbon fuel or reformed hydrocarbon fuel to the fuel nozzle.