Accession Number : AD0882105
Title : Advanced Composite Engine Design Allowables Program.
Descriptive Note : Final technical rept. 1 Apr 69-15 Dec 70,
Corporate Author : PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN
Personal Author(s) : Boll,Kenneth G. ; Mangiapane,Joseph A.
Report Date : MAR 1971
Pagination or Media Count : 252
Abstract : This report covers the work performed in determining material properties of the advanced composite materials selected for fan blade development and intermediate case development for a supersonic gas turbine. Four composite systems were evaluated in support of fan blade development activities: BORON-Skybond 703, boron-P13N, HMG50-P13N, and BORSIC -6061 aluminum. The polyimide systems were investigated at temperatures from -65 F to 500 F and the BORSIC aluminum system from -65 F to 600 F. The investigation included determinations of both short-time and time-dependent properties. Three composite systems were evaluated in support of the intermediate case technology development: boron-P13N, HMS GRAPHITE-P13N, and HTS graphite-P13N. Properties for the first two systems were determined at 70 F, 450 F, and 600 F and for the third system at 70 F and 600 F. The properties determined were longitudinal flexure, longitudinal and transverse tension, interlaminar shear, and coefficient of thermal expansion. (Author, modified-PL)
Descriptors : (*GAS TURBINES, *COMPOSITE MATERIALS), FANS, GAS TURBINE BLADES, IMIDES, FLEXURAL STRENGTH, TENSILE PROPERTIES, SHEAR STRESSES, THERMAL EXPANSION, BORON COMPOUNDS, BORON ALLOYS, ALUMINUM ALLOYS, GRAPHITE, NONDESTRUCTIVE TESTING, FATIGUE(MECHANICS), COMPRESSIVE PROPERTIES, RADIOGRAPHY, LOADS(FORCES), TORSION, EROSION, METALLOGRAPHY, ULTRASONIC RADIATION, IMPACT SHOCK, DIFFUSION BONDING, MOLDING MATERIALS, CREEP
Subject Categories : Laminates and Composite Materials
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE