Abstract
The replacement of their proprietary aluminum alloy turbine blades in a radio-controlled (RC), jet engine with thermal barrier coatings (TBC) on Inconel 718 to determine if there was an overall improvement to RC jet engine. TBC on Inconel 718 jet turbine blades were chosen as the potential replacement material systems because they are currently the most innovative process used in the commercial airline industry today for its strength and ability to reach extreme operating temperatures. If this process was applied to RC jet engines, it could potentially elevate engine running temperatures and increase efficiency. Creep tests were performed on uncoated and TBC samples of Inconel 718 that were subject to 700°C with stresses of 625 MPa and 694 MPa . These temperatures replicate the maximum values at which RC jet engines currently operate. In the current study, an initial feasibility study was preformed to evaluated. (DMM), were used to determine if any improvements have been attributed to the coating. Published creep maps were used to predict the creep mechanism for the creep test conditions. Based on the creep maps, the creep mechanism predicted is power law creep, which was proven with the samples exhibiting a cup and cone shearing failure. There was no significant improvement in creep performance between the coated sample and uncoated samples however if the stresses were lower it would change creep mechanism. There is a need for further study at lower stresses to confirm the benefits TBC on Inconel 718 as a replacement material in the RC jet turbine blade.