Advanced Ceramic Turbine Seal System, Phases II and III.
Abstract
'Final' design of the advanced engine graded ZrO2-NiCr turbine seal which includes thermal and structural analysis has been completed. Thermal fatigue, erosion and rub tolerance rig testing exceeded performance requirements with improved quality ceramic seals. Mechanical design of the 'final' advanced engine graded ZrO2-NiCr turbine seal has been completed. This design is compatible with an advanced engine seal design. Thermal and structural analysis of the 'final' advanced engine graded ZrO2-NiCr turbine seal predicted acceptable temperature and stress levels utilizing approximately equal to 0.75% W(ae) cooling air. Thermal fatigue, erosion and rub tests of the graded ZrO2-NiCr advanced engine turbine seal with improved quality ceramic seals have exceeded performance requirements with a thermal fatigue life greater than 500 cycles, erosion life greater than 1600 hours for 10 mils ceramic erosion and rub tolerance which produces 10 mils of ceramic wear with less than 1 mil blade wear. X-ray inspection and superficial hardness are effective non-destructive techniques for controlling the quality of the graded ZrO2-NiCr turbine seal. Structural ceramic (SiC) turbine seal exhibited extremely poor rub tolerance and posed a very difficult compliant attachment problem to prevent high stresses (point loading) throughout the total engine cycle. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 29, 1976
- Accession Number
- ADA033196
Entities
Organizations
- Pratt & Whitney