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Approved for public release, distribution unlimited / A single-stage transonic research compressor and test rig are to be used to obtain data on the effect of inlet flow distortion on compressor (and therefore engine) stall. Auxiliary injection was examined as a technique for generating distortion in inlet stagnation pressure, or temperature, or to simulate the more complex effects of engine steam ingestion from a catapult launch. Engineering analyses were developed and programmed in EES to relate inlet conditions to the compressor characteristics, for both pressure and temperature distortion. An injection duct area of 8% was selected to limit the required heater power. A CFD analysis was carried out to predict the compressor inlet flow field and hence position the injection duct exit. It was found that a broad range of distortion parameters could be generated by simply ducting (and heating) atmospheric air (or steam) through an auxiliary inlet throttle valve.

Approved for public release, distribution unlimited / 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. / US Navy (USN) author.

Approved for public release, distribution unlimited / During launch of aircraft off of a carrier deck, steam leakage is sometimes ingested into the aircraft's engine and may cause a compressor stall or 'pop-stall'. As the US Navy prepares to field the single engine F-35C Joint Strike Fighter, it becomes necessary to investigate the phenomenon known as 'pop-stall'. In the present study, steady-state as well as transient measurements prior to and during a steam induced rotating stall were taken. Changes to the honeycomb altered the performance characteristics of the Transonic Compressor Rig and needed to be remapped in order to determine a new stall line as well as a peak performance criterion. Data was taken at 90 percent design speed as well as during a 70 percent steam induced stall with the aide of 9 Kulites at varying positions along the case wall. Data was reduced and analyzed through the use of a data acquisition and data reduction system. / US Navy (USN) author.