Patent ID: 9068506
Filing Date: 2015-06-30
Classification: F01D,F02C,F05D

Abstract:
1. A turbine engine heat recuperator system comprising: a heat recuperator including first and second fluid passages configured for heat exchanges between fluid flowing through the respective first and second passages, the first passage of the heat recuperator being connected to and forming part of a compressor air passage to allow a compressor air flow to pass through the first passage of the heat recuperator and to then enter a combustor, the heat recuperator being disposed in an engine exhaust duct to allow exhaust gases discharged from a turbine to pass through the second passage of the heat recuperator and to then be discharged from the exhaust duct; a diffuser disposed between the turbine and the heat recuperator, the diffuser forming part of the exhaust duct to allow the exhaust gases to flow therethrough, the diffuser having a boundary wall defining a plurality of holes for continuously bleeding a boundary layer of the exhaust gases flowing through the diffuser; a valve device for adjusting a continuous bleed flow of the exhaust gases bled from the holes of the boundary wall of the diffuser; and a secondary passage for directing the adjusted continuous bleed flow of the exhaust gasses into the exhaust duct downstream of the heat recuperator, to thereby bypass the heat recuperator.