Patent ID: 8336317
Filing Date: 2012-12-25
Classification: F01D,F02C,Y02T

Abstract:
1. A turbine engine, comprising a final centrifugal compressor stage associated with an annular diffuser for supplying air to an annular combustion chamber; a high-pressure turbine wheel; an upstream flange mounted upstream from said high-pressure turbine wheel; injection means configured for injecting air onto the high-pressure turbine wheel through orifices of said upstream flange, said injection means being supplied with the air by the annular diffuser, and said final centrifugal compressor stage comprising an impeller which is connected by a rotating wall to the upstream flange; a labyrinth seal mounted between the injection means and the upstream flange; and at least one longitudinal duct disposed between the labyrinth seal and the injection means, such that the at least one longitudinal duct is located radially outside the labyrinth seal and located radially inside the injection means, wherein said at least one longitudinal duct is fed with air taken up from the final centrifugal compressor stage and has downstream air outlet orifices for injecting air onto the high-pressure turbine wheel through said orifices of said upstream flange.