Gas turbine propulsion unit with devices for branching off compressor air for cooling of hot parts

Claim 1

A gas turbine propulsion unit, comprising: compressor means; combustion chamber means; turbine means; and heat exchange path means for branching off compressor air for cooling hot parts of the turbine means; said heat exchange path means being in heat exchange relationship with heated structural parts of the propulsion unit, which parts substantially retain their heat content even upon an initiation of increase in loading on the propulsion unit, to maintain substantially constant the temperature of the branched off cooling compressor air upon changes in loading of the propulsion unit to avoid sudden changes in the temperature of the cooling air fed to the hot parts of the turbine, said heat exchange path including a gas-permeable means which provides a heat sink for the retained heat from said structural parts of the engine, which gas-porous-permeable means is in said heat exchange path and in contact with the compressor air bled off to assist in maintaining substantially constant the temperature of said branched-off cooling air.