Patent ID: 9181813
Filing Date: 2015-11-10
Classification: F01D,F23R

Abstract:
1. A gas turbine engine compressed air flow control arrangement, comprising: a combustion gas structure comprising an acceleration geometry configured to receive combustion gas from a can combustor and accelerate the combustion gas to a speed appropriate for delivery onto a first row of turbine blades, the combustion gas structure defining a straight combustion flow path and disposed in a plenum that receives compressed air from a compressor; a film cooling hole disposed through the combustion gas structure at a location within or downstream of the acceleration geometry; a sleeve surrounding at least a portion of the combustion gas structure comprising the film cooling hole and defining a volume between the combustion gas structure and the sleeve; and an adjustable flow control system comprising a valve disposed in a cooling air flow path between the plenum and the volume, the valve configured to adjust a flow volume through the cooling air flow path.