초록 ▼

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 combustor

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. In other embodiments, the fuel cooling system may be either open or closed loop and may comprise other types of heat exchangers, such as water cooled or gas cooled heat exchangers.

대표청구항 ▼

[ What is claimed is:] [1.] A method for supplying fuel to gas turbine engine, the method comprising the following steps:a. providing a fuel at first temperature;b. passing said fuel through a cooling system wherein said fuel is cooled to a second temperature lower than the first temperature and bel

[ What is claimed is:] [1.] A method for supplying fuel to gas turbine engine, the method comprising the following steps:a. providing a fuel at first temperature;b. passing said fuel through a cooling system wherein said fuel is cooled to a second temperature lower than the first temperature and below flash point temperature of said fuel; andc. injecting said cooled fuel into a gas turbine engine.