MATERIALS, MANUFACTURING AND TEST DEVELOPMENT OF A COMPOSITE FAN BLADE LEADING EDGE SUBCOMPONENT FOR IMPROVED IMPACT RESISTANCE

摘要

Application of polymer matrix composite materials for jet engine fan blades is becomingrnattractive as an alternative to metallic blades; particularly for large engines where significantrnweight savings are recognized on moving to a composite structure. However, the weight benefitrnof the composite is offset by a reduction of aerodynamic efficiency resulting from a necessaryrnincrease in blade thickness; relative to the titanium blades. Blade dimensions are largely drivenrnby resistance to damage on bird strike. Further development of the composite material isrnnecessary to allow composite blade designs to approximate the dimensions of a metallic fanrnblade. The reduction in thickness over the state of the art composite blades is expected torntranslate into structural weight reduction, improved aerodynamic efficiency, and thereforernreduced fuel consumption. This paper presents test article design, subcomponent blade leadingrnedge fabrication, test method development, and initial results from ballistic impact of a gelatinrnprojectile on the leading edge of composite fan blades. The simplified test article geometry wasrndeveloped to realistically simulate a blade leading edge while decreasing fabrication complexity.rnImpact data is presented on baseline composite blades and toughened blades; where arnconsiderable improvement to impact resistance was recorded.