| 摘要 |
PURPOSE: A cooling device and cooling tube are provided to consecutively cool fuel through heat transmission with air of low temperatures because a cooling tube for cooling the fuel is exposed to the air of low temperature cooled in advance. CONSTITUTION: A cooling device for a high altitude test of a gas turbine engine comprises an air guiding unit(110), a fuel cooling unit(120), a fuel supply unit(121), spay unit(130), and a fuel discharging unit(122). The air guiding unit guides air of low temperatures. The fuel cooling unit is installed in an air flow path of the air guiding unit, thereby cooling fuel by heat transmission with the air of low temperatures. The fuel supply unit supplies the fuel to the fuel cooling unit. The spray unit connected to one end part of the fuel supply unit and fuel cooling unit sprays the fuel to the fuel cooling unit. The fuel discharging unit discharges the cooled fuel.
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