GAS TURBINE ENGINE WITH HEAT PIPE FOR THERMAL ENERGY DISSIPATION
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United States of America Patent
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Jul 22, 2016
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Jul 22, 2016
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A gas turbine engine includes a core nacelle and a core engine disposed in the core nacelle. The core engine includes at least a compressor section, a combustor section, and a turbine section, which define a core flowpath. A bypass duct is radially outwards of the core nacelle. A component is disposed in the core engine. A cooling cavity is disposed outside of the bypass duct. A heat pipe contains a working medium sealed therein. The heat pipe includes a first section configured to accept thermal energy and a second section configured to dissipate the thermal energy in the cooling cavity. A tap from at least one of the compressor section or the bypass duct is configured to provide bleed air to the cooling cavity and dissipate the thermal energy from the second section.
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