Abstract: The subject invention provides a gas turbine engine in which a cooling system is utilized to lower the temperature of light hydrocarbon liquid fuel before the fuel is injected into the combustors. Specifically, the fuel cooling system is deployed in the fuel delivery system upstream of the combustors to lower the temperature of the liquid fuel below the flash point temperature, preventing phase change and premature combustion. In the preferred embodiment, the cooling system is a closed loop system comprising a heat exchanger, a containment reservoir, and a refrigeration unit. Brine is circulated within the loop, such that cooled brine is passed into the heat exchanger to act as a heat sink for the light hydrocarbon flowing therethrough. Warm brine exiting the heat exchanger is directed into the refrigeration unit for cooling before being collected and stored in the containment reservoir. The cooled light hydrocarbon exits the heat exchanger and is injected into the gas turbine engine.