Optimization of aero-engine combustion chambers with the assistance of Hierarchical-Kriging surrogate model based on POD downscaling method

Advances in Aerodynamics

Table 5 Design variables

Variable symbols	Variable name	Range of changes
\({T}_{t}\)/K	Total inlet temperature	427.55 – 1070.33
\({P}_{t}\)/kPa	Total inlet pressure	500 – 3200
\({S}_{t}\)/kg_*s⁻¹	Total inlet flow	19.01 – 82.398
\({R}_{og}\)	Oil–gas ratio	0.0106 – 0.0430
\({N}_{m}\)/PCS	Number of main combustion holes	2 – 4
\({D}_{m}\)/mm	Size of main combustion holes	12.1 – 16.8
\({N}_{c}\)/PCS	Number of cooling holes per row	10 – 20
\({D}_{c}\)/mm	Cooling hole size	0.5 – 1.5