Abstract The introduction of Lean Burn concept as basic Low-N O x scheme for future aero-
engines is heavily affecting the aero-thermal design of combustors. A great amount of air is …

Cooling performance is experimentally and numerically investigated in an effusion-cooled,
swirl-stabilized three-sector gas turbine combustor at realistic reacting flows. The …

This paper presents experimental investigations in an effusion cooled single sector gas
turbine combustor under close-to-reality boundary conditions, ie elevated pressure and …

A three-sector annular combustor test rig is built to carry out experimental investigation on
the liner effusion cooling performance using steady state infrared radiation thermography …

Conjugate heat transfer characteristics of the effusion cooling applied on the swirl-stabilized
combustor liner is experimentally and numerically investigated in a three-nozzle gas turbine …

Thermal protection is an essential technology for gas turbine hot components to cope with
the unprecedented thermal loads, and to ensure their enduring and efficient operation. A 3D …

Mixing processes between main flow and effusion cooling air are investigated in an effusion
cooled, swirl-stabilized pressurized single sector gas turbine combustor using advanced …

Thermochemical interaction–represented by CO mole fraction and gas phase temperature
measurements–between flame and cooling air is investigated in a close-to-reality effusion …

Detailed effusion cooling feature on both inner and outer liner of a scaled annular combustor
equipped with three axial swirlers has been investigated experimentally under both non …

The adoption of lean burn combustion to limit NOx emissions of modern aero-engines
imposes a drastic reduction of air dedicated to cooling combustor dome and liners. In the …