Abstract: In gas turbines, combustor inlets are characterized by significant levels of unsteady circumferential distortion due to compressor wakes and secondary flows, together with additional radial nonuniformity induced by the ...

Abstract: The compression system in modern turbofan engines is split into stages linked by transition ducts. Downstream of the low-pressure system, a handling bleed is often required and, in conjunction with structural vanes, can ...

Abstract: Abstract. This paper presents a study of aerospace gas turbine combustor operability performance to capture the lean boundaries of ignition at sub idle conditions. Presented in previous literature, the characteristic time ...