Preliminary Investigation of a Ceramic Lining for a Combustion Chamber for Gas-Turbine Use
Abstract
Combustion chamber liners for gas turbines and experimental set-ups were tested for failure. A ceramic-lined test chamber was operated at fuel/air ratios up to 0.050. Thermal-shock evaluation indicated that a ceramic lining, which expands after firing, would crack but would not fall apart during operation. Refractoriness of the lining and the resistance to mechanical shock were adequate. In general, shell temperature reductions of approximately 400 deg F were effected by the use of this lining at fuel/air ratios of 0.016 and 0.050. The mechanism of failure of the ceramic lining was induced by sudden heating and cooling during operation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 12, 1948
- Accession Number
- ADA800763
Entities
People
- A. R. Bobrowsky
- William H. Woodward
Organizations
- Glenn Research Center