Flow field survey in a transonic compressor rig

Abstract

As the Navy prepares to transition to F-35C Joint Strike Fighter the need to understand "pop stalls-- caused by steam leakage in catapult systems is of concern. â Pop stalls* caused by steam ingestion through the aircraft engine result in a loss of power and possible engine stall. The F-35C is a single engine aircraft and therefore the probability of a â pop stall* resulting in the loss of the aircraft is increased. Investigation of this phenomenon is currently being examined at the Turbopropulsion Laboratory by means of a transonic compressor rotor. The present study utilizes both three and five-hole probes to survey the flow field upstream and downstream of the rotor to examine compressor stability. A new compressor performance map was defined and a validation of previous steam ingestion was performed.