Published: Jan 1995
| ||Format||Pages||Price|| |
|PDF ()||14||$25||  ADD TO CART|
|Complete Source PDF (4.5M)||14||$65||  ADD TO CART|
The burn characteristics of titanium alloy systems have limited their usefulness in environments that are typical during normal aircraft gas turbine engine operation. The density advantages of replacing nickel base superalloys would result in superior performance, fuel burn, and pay load. A novel approach to increasing burn resistance was based on reducing the alloy liquidus temperature below the temperature where catastrophic oxidation occurs. Beryllium was chosen as an alloying agent to titanium base alloys because of its ability to depress the liquidus temperature. Emphasis was made to evaluate burn characteristics in a compressor type environment. To improve burn resistance over baseline alloys a beryllium content between 10 and 18 atomic percent is required.
titanium, aircraft gas turbine engines, liquidus temperature, beryllium, laser ignition
Senior Materials Engineer, Materials and Mechanics Engineering, Pratt & Whitney, West Palm Beach, FL