NCMS Project #: 140874
Problem: Aero gas turbine engines operating in particulate-laden environments experience premature component damage due to fine particle agglomeration in turbine cooling passages leading to blockage and loss of cooling. Deposition on the external surfaces of the vane can also restrict engine mass flow and increase aerodynamic losses.
Benefit: When fully developed and adopted, protective gas turbine engine compressor coatings will make commercial aviation safer, more reliable, and less expensive. The same holds true for the power generation industry.
Solution/Approach: This phase initiative is strictly focused on AE 1107 C Nozzle Sand Ingestion Rig Testing. Testing on the AE1107C will be conducted with the Legacy and Block III designs as well as a modified Block III design.
Starting with the AE1107C Legacy design, rig shake-down tests will be performed to ensure that all target parameters can be reached safely (for facility integrity) and consistently (for testing repeatability). Upon successful completion of the rig shake-down testing, an AE1107C Legacy vane instrumented with thermocouples will be tested.
Impact on Warfighter:
- Increased time-on-wing and engine life
- Fuel savings
- Decreased maintenance
- Reduced environmental impact
- U.S. Navy, NAVAIR
- Ohio State University
- Cost savings
- Maintenance avoidance and reliability
- Maintenance management improvement
- Improved readiness
- Coatings/corrosion prevention