Tribological Limitations in Gas Turbine Engines
This page summarizes the results of a workshop held on 15-17 September 1999 in Albany, NY, cosponsored by NASA Glenn Research Center, ASME (Tribology Division) and industry (Industrial Tribology Institute and Mohawk Innovative Technology, Inc.).
Gas Turbine Engines are subject to numerous limitations
-- physical, engineering, environmental, cost
- Mass Flow Considerations
- Materials (temperatures, strength, oxidation)
- Efficient Operating Range (off-design performance)
- Combustion Constraints
- Tribological Limitations
These technical areas received substantial R&D resources over that last five decades. However, resources dwindle as 'catastrophic failure/fire drill' problems are solved & supporting technology matures.
Tribological Component Limitations
- Bearings - High DN (2.5-3.0 MDN), Speed & Size
- Lubricants - Temperature (400°F)
- Seals - Leakage, Surface Velocity, Temperature, Life
- Gears - Tooth Loading & Surface Velocity
- Splines - Wear & Friction
- Dampers - Temperature (400°F)
- Bushings - Polymer Based (600°F)
Each component has its own technology barrier 'wall' to overcome
Oil-Free Bearing Potential Benefits
Oil-Free Foil Bearings Eliminate Oil Systems
15% Engine Weight Reduction
For a 50 Passenger Regional Jet this equates to an 8% Direct Operating Cost Reduction
Reports
- Tribological Limitations in Gas Turbine Engines: A Workshop to Identify the Challenges and Set Future Directions,
NASA/TM-2000-210059, May 01, 2000
Responsible NASA Official: Dr. Christopher DellaCorte
Curator: Michelle L. Beagle
Last Update: April 7, 2008
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