Temperature Rise Study on Aircraft Engine Fluid Distribution Tubes Subjected to Oil Burner

Abstract

There are lots of tubes in aircraft engine nacelle to transfer different kinds of fluid to other parts of the aircraft. These tubes is required to be tested by standard oil burner, which provides an environment of temperature about 2000 °F and heat flux about 11.9 W/m2. The purpose of this paper is to achieve a better understanding of the heat transfer process of tube fire test and make prediction on the temperature rise before samples were subjected to the test facility. The flow rate was studied by both theoretical and experimental method to determine its influence on temperature rise. Also, temperature rise of Jet A-1 fuel and lubricant RIPP 4050, which have different fluid characteristics, was used for comparison of the model. The result shows a good compliance between theoretical value and experimental measurements.