Toughened Silcomp composites for gas turbine engine applications. Continuous fiber ceramic composites program: Phase I final report, April 1992--June 1994

Technical Report · Fri Jul 01 00:00:00 EDT 1994

OSTI ID:10194426

Corman, G S; Luthra, K L; Brun, M K; Meschter, P J

The two main factors driving the development of new industrial gas turbine engine systems are fuel efficiency and reduced emissions. One method of providing improvements in both areas is to reduce the cooling air requirements of the hot gas path components. For this reason ceramic components are becoming increasingly attractive for gas turbine applications because of their greater refractoriness and oxidation resistance. Among the ceramics being considered, continuous fiber ceramic composites (CFCCs) are leading candidates because they combine the high temperature stability of ceramics with the toughness and damage tolerance of composites. The purpose of this program, which is part of DOE`s CFCC initiative, is to evaluate the use of CFCC materials as gas turbine engine components, and to demonstrate the feasibility of producing such components from Toughened Silcomp composites. Toughened silcomp is a CFCC material made by a reactive melt infiltration process, and consists of continuous SiC reinforcing fibers, with an appropriate fiber coating, in a fully dense matrix of SiC and Si. Based on the material physical properties, the material/process improvements realized in Phase 1, and the preliminary design analyses from Task 1, they feel the feasibility of fabricating Toughened Silcomp with the requisite physical and mechanical properties for the intended applications has been demonstrated. Remaining work for Phase 2 is to further improve the system for enhanced oxidation resistance, incorporate additional process controls to enhance the reproducibility of the material, transition the fabrication process to the selected vendors for scale-up, develop a more complete material property data base, including long-term mechanical behavior, and fabricate and test preliminary ``representative part`` specimens.

• Research Organization: General Electric Co., Schenectady, NY (United States). Corporate Research and Development Center
• Sponsoring Organization: USDOE, Washington, DC (United States)
• DOE Contract Number: FC02-92CE41000
• OSTI ID: 10194426
• Report Number(s): DOE/CE/41000-2; ON: DE95002851; BR: ED3801000; TRN: AHC29429%%76
• Resource Relation: Other Information: PBD: Jul 1994
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
36 MATERIALS SCIENCE
GAS TURBINE ENGINES
HEAT RESISTANT MATERIALS
COMPOSITE MATERIALS
RESEARCH PROGRAMS
SILICON CARBIDES
SILICON ALLOYS
PROGRESS REPORT
CORROSION RESISTANCE
USES
FEASIBILITY STUDIES
FABRICATION
MECHANICAL PROPERTIES
330103
360600
TURBINE
OTHER MATERIALS