Accession Number : AD0835373

Title :   COMPOSITE MATERIALS FOR TURBINE COMPRESSORS.

Descriptive Note : Final rept. 1 Jun 66-30 Nov 67,

Corporate Author : SOLAR TURBINES INTERNATIONAL SAN DIEGO CA

Personal Author(s) : Compton, W. A. ; Steward, K. P. ; Mnew, H.

Report Date : JUN 1968

Pagination or Media Count : 188

Abstract : A program to investigate metal-matrix composite materials for possible application in aircraft compressor blades has been carried out. The program was divided into three phases. Phase I included a review of the turbojet engine compressor requirements and the definition of relevant guidelines that could be used to further define the mechanical property requirements of compressor components. Phase II was concerned with the development and validation of the selected screening tests. Phase III covered the detailed evaluation of the above mentioned composites, and again included material characterization and tensile testing plus ballistic impact, axial and flexural fatigue, creep rupture, and salt corrosion tests. In addition to Al-B and Al-S/S, Ti-SiC was examined briefly as a possible candidate for operation in the temperature regimes up to 1000 F. (Author)

Descriptors :   *AXIAL FLOW COMPRESSOR BLADES), (*COMPOSITE MATERIALS, GAS TURBINES, STRESSES, AXIAL FLOW COMPRESSORS, STRAIN(MECHANICS), HEAT EXCHANGERS, PROPULSION SYSTEMS, ALUMINUM ALLOYS, BORON ALLOYS, IMPACT, TENSILE PROPERTIES, MODULUS OF ELASTICITY, THERMAL STABILITY, EROSION, FLEXURAL STRENGTH, CREEP, ELECTRON MICROSCOPY, RUPTURE, SALT SPRAY TESTS, TURBOJET ENGINES, RADIOGRAPHY, BALLISTICS.

Subject Categories : Laminates and Composite Materials
      Hydraulic and Pneumatic Equipment
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE