Design and Component Test of Engine Air Inlet Particle Separator for the Cv-7A Aircraft

摘要

An inlet protection system for the CV-7A aircraft's T64-GE-8 engine is described. Separator design, special manufacturing problems, and component test results are presented and discussed. Additional background information describing previous work from which the CV-7A separator design evolved is included where applicable. Component efficiency tests indicate that separator collection efficiencies exceed contract requirements. Pressure loss measurements, taken coincident with the efficiency test, indicate a pressure drop greater than design limits. Engine testing, not included in the modified contract work scope, would be required to accurately define the result of increased pressure loss on installed engine performance. (Author)