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Anti-icing apparatus and method for aero-engine nose cone
Anti-icing apparatus and method for aero-engine nose cone
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机译:航空发动机鼻锥的防冰装置和方法
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摘要
An aero-engine nose cone anti-icing system (10) using a rotating heat pipe (12) is provided to replace the current method of blowing hot compressor bleed air over the nose cone surface. Heat is transferred from a hot source (36) within the engine (22) to the nose cone (18) through a rotating heat pipe (12) along the central shaft (16). A condenser (20) and evaporator (14) are provided which are adapted to the heat transfer requirements and space constraints in the engine (22).
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