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Heat Pipe Combustor Cooling
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The general approach which has been taken toward cooling aircraft turbine combustor liners is to utilize a portion of incoming combustor air for film-cooling. In this paper an alternate cooling method is considered, which is referred to as Heat Pipe Combustor Cooling. The conventional film-cooled combustor liner is replaced by a thin, metallic heat pipe liner. Incident heat is transported upstream, and then into to an adjacent compressor discharge air stream. After first acting as a heat sink to cool the liner, the compressor discharge air stream enters the combustor and serves as a supplementary combustion air supply/combustion gas diluent. This dual-use capability effectively doubles the available air supply for liner cooling, extending the turbine inlet temperature range for which metallic construction of the combustor liner is feasible.
American Society of Mechanical Engineers
Title: Heat Pipe Combustor Cooling
Description:
The general approach which has been taken toward cooling aircraft turbine combustor liners is to utilize a portion of incoming combustor air for film-cooling.
In this paper an alternate cooling method is considered, which is referred to as Heat Pipe Combustor Cooling.
The conventional film-cooled combustor liner is replaced by a thin, metallic heat pipe liner.
Incident heat is transported upstream, and then into to an adjacent compressor discharge air stream.
After first acting as a heat sink to cool the liner, the compressor discharge air stream enters the combustor and serves as a supplementary combustion air supply/combustion gas diluent.
This dual-use capability effectively doubles the available air supply for liner cooling, extending the turbine inlet temperature range for which metallic construction of the combustor liner is feasible.
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