Turbine engine heat recuperator system

A gas turbine engine recuperator system (30) includes a heat recuperator (32) positioned in a gas turbine exhaust gas duct (28) for recovering heat from turbine exhaust gases (48) to preheat a compressor flow being supplied to the combustor (26). A continuous bleed flow (56) of the turbine exhaust gases is provided to bypass the heat recuperator (32). The continuous bleed flow (56) of the turbine exhaust gases is adjustable to reduce turbine exhaust gas pressure loss at a high engine operation level and to provide efficient heat recovery at low and/or medium engine operation levels.