Patent ID: 7140188
Filing Date: 2006-11-28
Classification: F02C,F05D,F23R

Abstract:
1. A gas turbine engine comprising: a combustor; a compressor for supplying air to said combustor; a turbine driven by gas from said combustor; an air flow control system installed in an air intake path for introducing air to said compressor, said air intake path being located outside and upstream with respect to said compressor; intake air flow control means for controlling an intake air flow by operating said air flow control system according to a load of said engine so as to maintain an air-to-fuel ratio in said combustor within a proper range suited to suppress a discharge of an atmospheric pollutant: and an air intake duct connected to an inlet of said compressor so as to form said air intake path therein, said air intake duct extending in an axial direction with respect to a centerline of said air intake duct and being disposed substantially perpendicular to an axial direction of said compressor, said air flow control system being installed in said air intake duct.