ABSTRACT
The introduction of turbomachinery in the late 1940s and early 1950s as a means of propelling military and, later, civilian aircraft led to a large increase of research in fluid mechanics and heat transfer centered on the gas turbine engine. Durable, efficient, highperformance engines were needed for a large number of new aircraft performing a wide variety of missions. Also gas turbines became increasingly popular for ground power and marine applications. The designers of these new machines faced more and more challenges in terms of size, time between overhaul, and power output. Each new generation of engines needed to operate at the highest practical turbine inlet temperature for maximum thrust or power output and highest thermodynamic (fuel) efficiency.
