HIGH TEMPERATURE GAS TURBINE ENGINE

Abstract: a gas turbine engine is provided, including: a turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order, the turbine section comprising a turbine case and a turbine stage, the turbine stage comprising a plurality of turbine stator vanes, the stage being a stage count number, n, downstream from the combustion section, the turbine stator vanes comprising a first vane assembly comprising a nozzle formed of a first material defining a first coefficient of thermal expansion; and a hanger positioned outward of the nozzle along a radial direction and coupling the nozzle to the turbine case, the hanger formed of a second material defining a second coefficient of thermal expansion, the gas turbine engine defining a nozzle efficiency offset, neo, greater than 1 and less than or equal to 5, wherein neo is expressed as:

Inventor(s): Jeffrey Donald Clements, Mark Willard Marusko

CPC Classification: F01D9/04 (NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids ; non-positive displacement pumps ))

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