Effect of fuel to air ratio on Mach 0. 3 burner rig hot corrosion of ZrO/sub 2/-Y/sub 2/O/sub 3/ thermal barrier coatings

Technical Report · Thu Jul 01 04:00:00 EDT 1982

OSTI ID:5312834

Hodge, P E

A Mach 0.3 burner rig test program was conducted to determine how the fuel-to-air mass ratio affects the durability of ZrO/sub 2/-Y/sub 2/O/sub 3//Ni-16Cr-6A1-0.31Y thermal barrier coating system in combustion products containing 5 ppM Na and 2 ppM V based on Jet A fuel. Triplicate coated specimens were exposed to Mach 0.3 combustion gases at the fuel-to-air mass ratios of 0.039, 0.044, and 0.049. Exposure cycles consisted of subjecting the specimens to 1 h at temperature followed by 6 min out of the combustion gases with external forced air cooling on the specimens. Specimens were examined after twenty 1-hour cycles and were removed from test when the ceramic had spalled over approximately 1/4 of the hot zone on the leading edge. Test conditions were: 843/sup 0/C substrate temperature and 982/sup 0/, 1010/sup 0/, and 1038/sup 0/C ceramic surface temperature for the respective fuel-to-air mass ratios of 0.039, 0.044, and 0.049. Based on these tests, it was found that: as this fuel-to-air mass ratio is increased from 0.039 to 0.049; the durability of ZrO/sub 2/-6Y/sub 2/O/sub 3/, ZrO/sub 2/-8Y/sub 2/O/sub 3/, and ZrO/sub 2/-12Y/sub 2/O/sub 3/ coatings decreases, and this decrease in durability is attributed to the 25% increase in fuel impurity flux for the corresponding 25% increase in fuel; ZrO/sub 2/-8Y/sub 2/O/sub 3/ coatings were approximately 2X and 1.3X more durable than ZrO/sub 2/-12Y/sub 2/O/sub 3/ and ZrO/sub 2/-6Y/sub 2/O/sub 3/ coatings, respectively at the fuel-to-air mass ratio of 0.039; the number of cycles endured by ZrO/sub 2/-8Y/sub 2/O/sub 3/-coated specimen varied from an average of 53 to 200 for the respective fuel-to-air mass ratios of 0.049 and 0.039; and at a fuel-to-air mass ratio of 0.049, all ZrO/sub 2/-Y/sub 2/O/sub 3/ coated specimens failed in 40 to 60 h.

• Research Organization: National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
• DOE Contract Number: AI01-77ET10350
• OSTI ID: 5312834
• Report Number(s): DOE/NASA/10350-32; NASA-TM-82879; ON: DE82019790
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
360205 -- Ceramics
Cermets
& Refractories-- Corrosion & Erosion
42 ENGINEERING
421000* -- Engineering-- Combustion Systems
ALLOYS
CERAMICS
CHALCOGENIDES
CHEMICAL REACTIONS
COMBUSTION
COMBUSTORS
CORROSION RESISTANCE
CORROSION RESISTANT ALLOYS
CORROSIVE EFFECTS
DATA
EXHAUST GASES
EXPERIMENTAL DATA
FLOW RATE
FLUIDS
FUEL-AIR RATIO
FUELS
GASEOUS WASTES
GASES
HEAT RESISTANT MATERIALS
INFORMATION
JET ENGINE FUELS
MACH NUMBER
MATERIALS
NUMERICAL DATA
OXIDATION
OXIDES
OXYGEN COMPOUNDS
PERFORMANCE
THERMOCHEMICAL PROCESSES
TRANSITION ELEMENT COMPOUNDS
VELOCITY
WASTES
YTTRIUM COMPOUNDS
YTTRIUM OXIDES
ZIRCONIUM COMPOUNDS
ZIRCONIUM OXIDES