Metal Matrix Composites for High Temperature Turbine Blades.
Abstract
The continued development and evaluation of the refractory wire reinforced FeCrAlY composites designed for application in advanced gas turbine engines is described. These investigations included determination of 1000-hour creep and stress rupture properties in the temperature range 1037 -1148C, generation of fiber/matrix reaction rate data, tensile tests on angle plied composites, burner rig tests and blade-oriented fabrication studies. Long term stress rupture and creep properties were in agreement with predictions based on earlier shorter time tests. Density compensated strengths of about 2.5:1 over current D.S. eutectics were demonstrated and relatively low creep rates observed. Parabolic growth rates for fiber/matrix reaction zones were identified and reaction rate constants determined. Tensile strengths at 648 and 760 C on angle plied composites indicated adequate strengths for a + or - 15 deg construction in terms of turbine blade root stresses. Preliminary burner rig tests indicated no significant problems for W/FeCrAlY composites exposed to this type of environment. Some blade oriented fabrication studies were also performed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1976
- Accession Number
- ADA030074
Entities
People
- William D. Brentnall