The fuel system of claim 7, wherein the motive bypass valve is a commanded valve receiving inputs from sources external to the fuel system.ġ1. The fuel system of claim 8, wherein the motive bypass valve is one of pressure and thermally actuated.ġ0. The fuel system of claim 1, further comprising a motive bypass line on the motive fuel line in parallel with the first heat exchanger, the motive bypass line including a motive bypass valve operable to close when a threshold is crossed to redirect the second portion of the fuel within the motive fuel line around the first heat exchanger thereby bypassing the first heat exchanger.ĩ. The fuel system of claim 6, wherein a first portion of the fuel of the main fuel line is directed by the fuel metering unit to the combustor, the portion of the fuel of the main fuel line directed into the motive flow line is a second portion of the fuel, and the fuel metering unit selects a third portion of the fuel from the main fuel line and injects said third portion back into the main fluid line upstream of the high pressure pump.Ĩ. The fuel system of claim 1, wherein the fuel system further comprises a high pressure pump disposed in the main fuel line downstream of the second heat exchanger and upstream of the fuel metering unit.ħ. The fuel system of claim 1, wherein the fuel system further comprises a low pressure pump disposed in the main fuel line downstream of the ejector pump and upstream of the first heat exchanger.Ħ. The fuel system of claim 1, wherein a first portion of the fuel of the main fuel line is directed by the fuel metering unit to the combustor, and the portion of the fuel of the main fuel line directed into the motive flow line is a second portion of the fuel.ĥ. The fuel system of claim 2, wherein the second heat exchanger is a fuel-to-oil heat exchanger, the fuel-to-oil heat exchanger providing heat transfer communication between the main fuel line and an oil line of an oil system of the gas turbine engine, to transfer heat from oil in the oil line to the fuel in the main fuel line.Ĥ. The fuel system of claim 1, wherein the second heat exchanger provides heat transfer communication from a source of heat external to the main fuel line to the fuel in the main fuel line.ģ.
A fuel system for a gas turbine engine having a combustor that is fed fuel from a fuel tank, the fuel system comprising: a main fuel line providing fuel flow from the fuel tank to the combustor at least one pump pumping fuel from the fuel tank to the combustor via a fuel metering unit, the at least one pump including an ejector pump, the fuel metering unit directing a portion of the fuel into a motive flow line, the motive flow line providing return of the portion of the fuel to the ejector pump and a first heat exchanger and a second heat exchanger disposed in serial flow communication within the main fuel line between the at least one pump and the fuel metering unit, the second heat exchanger being downstream from the first heat exchanger, the first heat exchanger being a fuel-to-fuel heat exchanger providing heat transfer communication between the main fuel line and the motive flow line.Ģ. MODULAR EXHAUST GAS RECIRCULATION COOLING FOR INTERNAL COMBUSTION ENGINESġ. TURBINE ENGINE ANNULAR COMBUSTION CHAMBER WITH ALTERNATE FIXINGSĪDDITIVE-AGENT DIFFUSION PLATE IN EXHAUST PASSAGE, STRUCTURE OF ADDITIVE-AGENT DIFFUSION PLATE, AND EXHAUST SYSTEM INCLUDING ADDITIVE-AGENT DIFFUSION PLATE Secondary air supply system for internal combustion engineĬONTROLLING THE AERODYNAMIC DRAG OF A GAS TURBINE ENGINE DURING A SHUTDOWN STATEĮxhaust Aftertreatment System with Flow Distribution
Electricity produced by CO2, air and waterĮxhaust gas processing method and exhaust gas processing system