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US 8,789,377 B1Granted
Gas turbine engine with liquid metal cooling
AssigneeFlorida Turbine Technologies, Inc.
InventorsJoseph D Brostmeyer, John W Appleby, Jr.
Life of this patent
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Abstract
A gas turbine engine with a closed loop liquid metal cooling fluid system for cooling stator vanes within the turbine, in which the stator vanes include a liquid metal cooling passage lined with Tantalum or Molybdenum and a liquid metal cooling fluid of Bismuth or Lead or Zinc or Tin or alloy mixtures of these metals.
Claims3
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.
6 more elements
Dependencies are inferred from the claim text.