Date of Award

January 2015

Degree Type

Thesis

Degree Name

Master of Science in Aeronautics and Astronautics

Department

Aeronautics and Astronautics

First Advisor

Stephen D Heister

Committee Member 1

Timothée L Pourpoint

Committee Member 2

Carson D Slabaugh

Abstract

A series of experiments has been performed at ambient pressure using optically accessible test articles to study the dynamic response of a liquid injector subjected to a steep-fronted transverse pressure wave. The pressure differential across the injectors was varied between 1 and 5 psig. High speed video images revealed the highly complex and multi-dimensional nature of the flow response. Results also suggest that the diameter of the plenum immediately upstream of the injector influences dynamic response; a narrower plenum dampens it. A one-dimensional, lumped parameter model was also developed to predict injector response. Results were compared with empirical data, and the model was found to show promise in predicting backflow distance at the high end of tested pressure differentials. Its ability to predict injector recovery time remains inconclusive. The cause of deviation in the model’s predictions is believed to be the boundary layer effects along the injector channel wall. Further studies at elevated pressures will provide useful insights for improving the model.

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