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Quinary, low-conductivity thermal barrier coatings for turbine engine components
Thermal barrier coatings, which may be used in gas turbine engines, comprise or consist of a tantala-niobia-zirconia mixture that is stabilized with two or more stabilizers. An exemplary thermal barrier coating comprises or consists of, by mole percent: about 2% to about 30% YO1.5; about 8% to about 30% YbO1.5 or GdO1.5 or combination thereof; about 6% to about 30% TaO2.5; about 0.1% to about 10% NbO2.5; about 0% to about 10% HfO2; and a balance of ZrO2.
Quinary, low-conductivity thermal barrier coatings for turbine engine components
Thermal barrier coatings, which may be used in gas turbine engines, comprise or consist of a tantala-niobia-zirconia mixture that is stabilized with two or more stabilizers. An exemplary thermal barrier coating comprises or consists of, by mole percent: about 2% to about 30% YO1.5; about 8% to about 30% YbO1.5 or GdO1.5 or combination thereof; about 6% to about 30% TaO2.5; about 0.1% to about 10% NbO2.5; about 0% to about 10% HfO2; and a balance of ZrO2.
Quinary, low-conductivity thermal barrier coatings for turbine engine components
JORGENSEN DAVID JOHN (author) / BAKER WIL (author) / TOLPYGO VLADIMIR K (author)
2020-10-20
Patent
Electronic Resource
English
QUINARY, LOW-CONDUCTIVITY THERMAL BARRIER COATINGS FOR TURBINE ENGINE COMPONENTS
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