In aerospace engineering, the operation of a turbine nozzle is crucial as it impacts the performance of the turbine and the overall engine. The nozzle operates by expanding gases to provide thrust or power extraction.
The concept of pressure ratio is important here. It is defined as the ratio of the pressure at the nozzle entry to the pressure at the nozzle exit. The design condition for a nozzle is typically optimized for a specific pressure ratio, known as the design pressure ratio. Operating beyond this ratio has specific implications:
In this context, when the turbine nozzle operates at a higher pressure ratio than the design value, it is termed as operating under a supercritical condition.