Aerothermal Analysis of a Turbine Casing Impingement Cooling System

Table 1

Geometric parameter.

Manifold diameter “𝐷”	m
Nozzle diameter “𝑑”	m
Manifold thickness “𝑡”	m
Holes number “𝑛”	—
Holes spacing “Sx”	m
Nozzle to wall distance “ℎ”	m