Advanced composite combustor structural concepts program. Final Report
An analytical study was conducted to assess the feasibility of and benefits derived from the use of high temperature composite materials in aircraft turbine engine combustor liners. The study included a survey and screening of the properties of three candidate composite materials including tungsten reinforced superalloys, carbon-carbon and silicon carbide (SiC) fibers reinforcing a ceramic matrix of lithium aluminosilicate (LAS). The SiC-LAS material was selected as offering the greatest near term potential primarily on the basis of high temperature capability. A limited experimental investigation was conducted to quantify some of the more critical mechanical properties of the SiC-LAS composite having a multidirection 0/45/-45/90 deg fiber orientation favored for the combustor linear application. Rigorous cyclic thermal tests demonstrated that SiC-LAS was extremely resistant to the thermal fatigue mechanisms that usually limit the life of metallic combustor liners. A thermal design study led to the definition of a composite liner concept that incorporated film cooled SiC-LAS shingles mounted on a Hastelloy X shell. With coolant fluxes consistent with the most advanced metallic liner technology, the calculated hot surface temperatures of the shingles were within the apparent near term capability of the material. Structural analyses indicated that the stresses in the composite panels were low, primarily because of the low coefficient of expansion of the material and it was concluded that the dominant failure mode of the liner would be an as yet unidentified deterioration of the composite from prolonged exposure to high temperature. An economic study, based on a medium thrust size commercial aircraft engine, indicated that the SiC-LAS combustor liner would weigh 22.8N (11.27 lb) less and cost less to manufacture than advanced metallic liner concepts intended for use in the late 1980's.
- Research Organization:
- Pratt and Whitney Aircraft, East Hartford, CT (USA)
- OSTI ID:
- 6419160
- Report Number(s):
- N-87-20387; NASA-CR-174733; NAS-1.26:174733; PWA-5890-24
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
ALUMINIUM SILICATES
MECHANICAL PROPERTIES
COMBUSTION CHAMBERS
COMPOSITE MATERIALS
LITHIUM SILICATES
CARBON FIBERS
ECONOMIC ANALYSIS
FATIGUE
GAS TURBINE ENGINES
HASTELLOY X
LINERS
SILICON CARBIDES
STRESS ANALYSIS
THERMAL CONDUCTIVITY
THERMAL EXPANSION
TUNGSTEN ALLOYS
ALKALI METAL COMPOUNDS
ALLOYS
ALUMINIUM COMPOUNDS
CARBIDES
CARBON COMPOUNDS
CHROMIUM ALLOYS
COBALT ALLOYS
ECONOMICS
ENGINES
EXPANSION
FIBERS
HASTELLOYS
HEAT ENGINES
HEAT RESISTANT MATERIALS
HEAT RESISTING ALLOYS
INTERNAL COMBUSTION ENGINES
IRON ALLOYS
LITHIUM COMPOUNDS
MATERIALS
MOLYBDENUM ALLOYS
NICKEL ALLOYS
OXYGEN COMPOUNDS
PHYSICAL PROPERTIES
SILICATES
SILICON COMPOUNDS
THERMODYNAMIC PROPERTIES
360603* - Materials- Properties