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A new aero-engine nose cone anti-icing system using a rotating heat pipe has been proposed to replace the current method of blowing hot compressor bleed air over the nose cone surface. Here, the heat is transferred from a hot source within the engine to the nose cone through a rotating heat pipe along the central fan shaft. A compact evaporator is used at the evaporator end due to space constraints in the engine. The system is modeled as a thermal resistance network where the thermo-fluid dynamics of each component determine the resistors. This paper reviews each of the component models and results, which show that the evaporator thermal resistance is one of the limiting factors for adequate transfer of heat for anti-icing.

An experimental investigation was conducted to characterize the operational transients of a small-scale 6-tube exhaust gas recirculation (EGR) cooling device, designed to simulate operating conditions of commercial devices, for a wide range of exhaust mass flow rates and different coolant temperatures. The transient pressure drop across the device and the thermal performance were measured for exhaust mass flow rates varying over a full range typically used in commercial devices. The coolant temperatures tested ranged from 25 °C to 55 °C. The temperature distribution on the outer shell surface of the small-scale EGR cooling device was also measured periodically using a thermal imaging camera to characterize the secondary side flow in the experiments. The results show that both the exhaust mass flow rate and the coolant temperature had a significant influence on the transient performance of the 6-tube EGR cooling device.