Invention Grant
US08234870B2 Additive injection system for improving thermal stability of jet fuel 有权
用于改善喷气燃料热稳定性的添加剂注射系统

Additive injection system for improving thermal stability of jet fuel
Abstract:
A gas turbine engine fuel system includes a fuel tank for storing fuel, a heat exchanger through which the fuel from the fuel tank can pass, a fuel pump located downstream from the heat exchanger for pumping the fuel, a fuel metering unit for metering the fuel pumped by the fuel pump, an additive tank for storing a fuel additive, an additive delivery subsystem for mixing the fuel additive with the fuel at or before the heat exchanger to generate a fuel and fuel additive mixture, and a combustor located downstream of the fuel metering unit where the fuel and fuel additive mixture is delivered for combustion. The fuel additive comprises a fuel stabilizer for reducing fuel coking.
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