NDLI: Durability of Oxide/Oxide CMCs in Gas Turbine Combustors

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Roode, Mark Van Arun, K. Bhattacharya
Copyright Year	2012
Abstract	An integrated creep rupture strength degradation and water vapor degradation model for gas turbine oxide-based CMC (Ceramic Matrix Composite) combustor liners was expanded with heat transfer computations to establish maximum TRIT (Turbine Rotor Inlet Temperature) for gas turbines with 10:1 pressure ratio. Recession rates and average CMC operating temperatures were calculated for an existing baseline N720/A (N720/Al2O3) CMC combustor liner system, with and without protective Al2O3 FGI (Friable Graded Insulation) for 30,000-h liner service life. The potential for increasing TRIT by YAG (Y3Al5O12) substitution for the fiber, matrix and FGI constituents of the CMC system was explored, because of the known superior creep and water vapor degradation resistance of YAG compared to Al2O3. It was predicted that uncoated N720/A can be used as a combustor liner material up to a TRIT of ∼1200°C, offering no TRIT advantage over a conventional metal + TBC (Thermal Barrier Coating) combustor liner. A similar conclusion was previously reached for a SiC/SiC CMC liner with BSAS-type EBC (Barium Strontium Aluminum Silicate Environmental Barrier Coating). The existing N720/A + Al2O3 FGI combustor liner system can be used at a maximum TRIT of ∼1350°C, a TRIT increase over metal + TBC and uncoated N720/A of ∼150°C. Replacing the Al2O3 with YAG is predicted to increase the maximum allowable TRIT. Substitution of the fiber or matrix in N720/A increases TRIT by ∼100°C. A YAG FGI improves the TRIT of the 720/A + Al2O3 FGI by ∼50°C, enabling a TRIT of ∼1400°C, similar to that predicted for SiC/SiC CMCs with protective rare earth monosilicate EBCs.
Sponsorship	International Gas Turbine Institute
Starting Page	475
Ending Page	485
Page Count	11
File Format	PDF
ISBN	9780791844670
DOI	10.1115/GT2012-68974
Volume Number	Volume 1: Aircraft Engine; Ceramics; Coal, Biomass and Alternative Fuels; Controls, Diagnostics and Instrumentation
Conference Proceedings	ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
Language	English
Publisher Date	2012-06-11
Publisher Place	Copenhagen, Denmark
Access Restriction	Subscribed
Subject Keyword	Insulation Ceramic matrix composites Temperature Creep Aluminum Metals Rotors Rupture Service life (equipment) Durability Water vapor Coatings Pressure Fibers Strontium Gas turbines Computation Thermal barrier coatings Coating processes Combustion chambers Heat transfer Turbines Operating temperature
Content Type	Text
Resource Type	Article

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