Patent ID: 8789377
Filing Date: 2014-07-29
Classification: F02C,F05D

Abstract:
1. An industrial size gas turbine engine comprising: a compressor; a turbine rotatably connected to the compressor; a combustor to receive compressed air from the compressor and produce a hot gas flow that enters the turbine; a first stage turbine stator vane of the industrial size gas turbine engine made from a base material of either a ferrous alloy, a nickel alloy or a cobalt alloy; a closed loop liquid metal cooling circuit passing through the first stage turbine stator vane to provide cooling; a heat exchanger to transfer heat from the first stage turbine stator vane and into the compressed air entering the combustor; the closed loop liquid metal cooling circuit within the first stage turbine stator vane having a liner made substantially of Molybdenum or Tantalum to prevent contact of the liquid metal with the base material of the first stage turbine stator vane; and, the liquid metal cooling fluid includes Bismuth or Lead.