Accession Number : ADA325412
Title : Thermal Management Research Studies. Volume 2. Rotating Hear Pipe.
Descriptive Note : Final rept. Mar 91-Aug 96,
Corporate Author : UNIVERSAL ENERGY SYSTEMS INC DAYTON OH
Personal Author(s) : Ponnappan, Rengasamy
PDF Url : ADA325412
Report Date : 17 SEP 1996
Pagination or Media Count : 217
Abstract : This document presents a comprehensive account of the high speed rotating heat pipe (RHP) research performed in support of the more electric airplane technology development. A literature review revealed that there are no studies done on RHP at rotational speeds above 12,000 rpm. New trends in advanced IPU (Integrated Power Unit) and IS/G (Integral Starter/Generator) type of systems require very high speeds up to 60,000 rpm in order to be directly coupled to the gas turbine engines used in aircraft. RHP technology may be a viable method for the thermal management of these power systems. RHP test articles have been designed, fabricated and tested successfully in the high speed test rig developed especially for this purpose. Water and methanol filled RHPs made of stainless steel were tested up to 30,000 rpm for the first time. Some deficiencies in the existing analytical modeling of the RHP performance were identified and improvement directions were initiated. Several unique design and testing scenarios, such as critical speed, and dynamic balancing aspects, non-contact temperature measurement, induction heating, oil jet cooling, etc. are presented. Air jet cooling of the RHP condenser looks attractive for low heat transport capacity applications as opposed to the oil jet cooling which requires rotary shaft seals.
Descriptors : *AIRCRAFT ENGINES, *THERMAL ANALYSIS, *HEAT PIPES, *LIQUID COOLING, GAS TURBINES, POWER SUPPLIES, ELECTRIC POWER, TEMPERATURE CONTROL, ELECTRIC GENERATORS, CONDUCTION(HEAT TRANSFER), THERMAL DEGRADATION, INDUCTION HEATING, AIR COOLED, RADIANT COOLING, THERMOELECTRIC COOLING, THERMAL INSTABILITY, MOTOR STARTERS, ROTARY SEALS.
Subject Categories : Thermodynamics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE