Patent ID: 9222415
Filing Date: 2015-12-29
Classification: F02C,F05D,Y02T

Abstract:
1. A gas turbine engine fuel system comprising: a fuel pump for providing a fuel flow; a gas turbine engine comprising: a compressor for compressing inlet air; a combustor for mixing the fuel flow with compressed inlet air and producing exhaust gas; and a turbine for receiving exhaust gas from the combustor; a coil disposed within exhaust gas leaving the turbine so as to be heated, the coil configured to receive a motive flow of fluid; and a heat exchanger in fluid communication with the motive flow of fluid from the coil and the fuel flow from the fuel pump so as to transfer heat from the motive flow of fluid to the fuel flow; wherein the fuel pump comprises: an inlet line for receiving fuel, the inlet line including a temperature sensor; an outlet line in fluid communication with the combustor; a bypass line in fluid communication with the heat exchanger, the bypass line including a bypass valve; and a return line in fluid communication with the heat exchanger, the return line including a check valve.