Effects of Rotation on Coolant Passage Heat Transfer. Volume 1. Coolant Passageswith Smooth Walls

摘要

An experimental program was conducted to investigate heat transfer and pressureloss characteristics of rotating multipass passages, for configurations and dimensions typical of modem turbine blades. This experimental program is one part of the NASA Hot Section Technology (HOST) Initiative, which has as its overall objective 'the development and verification of improved analysis methods that will form the basis for a design system that will produce turbine components with improved durability.' The objective of this program was the generation of a data base of heat transfer and pressure loss data required to develop heat transfer correlations and to assess computational fluid dynamic techniques for rotating coolant passages. The experimental work was broken down into two phases. Phase I consists of experiments conducted in a smooth wall large scale heat transfer model and is the subject of this report. In phase II the large scale model was modified to investigate the effects of skewed and normal passage turbulators. The results of phase II along with comparison to phase I will be presented in volume II of a NASA report. Heat transfer, Rotation, Turbomachinery.