Cooling Data for Turbine Engines in Helicopters
Efficient design of a turbine engine installation requires data on the ways the engine rejects heat, the temperature limits of various parts of the engine, and the changes in heat rejection from service, as well as a method of using these data. A uniform, practical method of data presentation and use is needed. Cooling margins developed by these methods would be subject to full scale testing for verification. A tested method of data presentation and use is described herein.