GAS TURBINE
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United States of America Patent
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Aug 29, 2017
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Aug 31, 2016
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Abstract
A gas turbine has a combustion chamber and a turbine nozzle guide vane ring. The combustion chamber includes an outer and inner combustion chamber walls with heat shield tiles. The guide vane ring has airfoils, and outer and inner platforms. The outer and/or inner platforms form a radial step towards a main flow path such that the upstream end of the outer platform is arranged radially outside and upstream of the downstream end of the heat shield tiles of the outer combustion chamber wall, and/or the upstream end of the inner platform is arranged radially inside and upstream of the downstream end of the heat shield tiles of the inner combustion chamber wall, so that the outer platform and the heat shield tiles of the outer combustion chamber wall and/or the inner platform and heat shield tiles of the inner combustion chamber wall overlap in the axial direction.
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