Skip to main content
Advances in Aerodynamics

Table 4 High temperature rise combustor design requirements

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

Parameters

Design status

Slow state

Total inlet temperature (K)

850

492.9

Oil–gas ratio

0.0430

0.0106

Combustion efficiency

 > 99%

 > 98%

Total pressure loss

 < 6%

 < 7%

Overall temperature distribution factor

 < 0.20

-

Radial temperature distribution factor

 < 0.12

-

Back to article page