SYSTEMS, METHODS, AND APPARATUSES OF GAS TURBINE COOLING

Abstract: aspects of the present disclosure relate generally to systems, methods, and devices for cooling a gas-powered turbine. the system includes a plurality of gas-powered turbine components, such as a combustion chamber having an interior portion. an internal cooling circuit with a heat shield is disposed at least partly in the interior portion of the combustion chamber. the heat shield is positioned axially and/or along a lengthwise axis of the combustion chamber, while omitting radial portions extending outward towards an outer surface of the gas-powered turbine. additionally, the heat shield is positioned upstream from and/or outside of a hot gas path formed downstream of the combustion chamber away from moving/rotating components. the heat shield is an additive manufacturing heat shield formed of an additive manufacturing process (e.g., 3d printing).

Inventor(s): Carl Jonas RYDLAND, Carlo DE BERNARDI

CPC Classification: F02C7/12 (GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines ; jet-propulsion plants ; construction of compressors or fans ; generating combustion products of high pressure or high velocity ; using gas turbines in compression refrigeration plants ))

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