Enhanced APU operability
A fuel system for a gas turbine engine comprises an injector disposed to inject fuel and air into a combustor of the gas turbine engine. In a first embodiment, the fuel system further comprises an air separation module configured to supply oxygen-enriched air into the combustor via the injector for combustion. In a second embodiment, the fuel system further comprises a barbotage system and a heating element. The barbotage system is configured to feed hydrogen to the injector, and the heating element is configured to pre-heat the fuel.
1. A fuel system for a gas turbine engine comprising:
an injector disposed to inject fuel and air into a combustor of the gas turbine engine;
an air separation module configured to deliver oxygen-enriched air into the combustor via the injector for combustion;
a thermoelectric generator having an aircraft cabin as a heat source, and a tail cone as a heat sink; and
a heating element comprising a resistive heater powered by the thermoelectric generator and configured to pre-heat the fuel.
2. The fuel system of claim 1 , wherein the gas turbine engine is an auxiliary power unit.
3. The fuel system of claim 1 , wherein the heating element is a circulative heating element configured to heat the fuel in a fuel tank.
4. The fuel system of claim 1 , wherein the heating element is configured to heat fuel at a fuel inlet line to the injector.
5. The fuel system of claim 1 , wherein the heating element is a heat exchanger.