Patent ID: 6487862
Filing Date: 2002-12-03
Classification: F01D,F02C,Y02T

Abstract:
A jet engine comprising: a compressor and a turbine and a combustor connected between the compressor and the turbine, said combustor adapted for taking in air from said compressor and combusting fuel with compressed air from said compressor to provide an exhaust for driving said turbine, control means for starting and controlling the operation of the jet engine, said control means including a fuel supply system for supplying fuel under pressure to said combustor for combustion and an externally supported fuel ignitor in said combustor for igniting fuel supplied to said combustor, said control means further including an air nozzle adapted for injecting high velocity compressed air from an independent source into said compressor for inducing start-up rotation of said compressor and said turbine, and a pressure sensor in said combustor and adapted for discontinuing the flow of air from said nozzle and for discontinuing ignition from said fuel ignitor in said combustor when a predetermined minimum pressure for self-sustaining operation of said engine is attained, said control means including a self-correcting shutdown mechanism for igniting fuel in said combustor upon occurrence of flame-out when said fuel supply system is set in other than an off position after self-sustaining operation of the engine has been attained.