Patent ID: 9102416
Filing Date: 2015-08-11
Classification: A62C,B64D,F02C,F05D

Abstract:
1. A method of inerting a fuel tank in an aircraft having a main thrust generating engine and an auxiliary power unit, comprising the steps of: providing a dedicated turbine engine; combusting hydrocarbon fuel with oxygen in said dedicated turbine engine positioned in the aircraft, said dedicated turbine engine operating independent of the main thrust generating engine and said auxiliary power unit; operating said dedicated turbine engine at a stoichiometric ratio to generate engine exhaust comprising carbon dioxide and having an oxygen content below a predetermined threshold; cooling said engine exhaust with a first cooling air flow from a blower powered by said dedicated turbine engine; compressing said engine exhaust in a compressor powered by said dedicated turbine engine to generate compressed exhaust; cooling said compressed exhaust with a second cooling air flow from the blower; and directing said compressed exhaust into the fuel tank.