A superalloy gas turbine component was originally designed to operate at temperatures up to 760°C and exhibited a stress rupture life of 900 h under this operating condition. An updated design calls for a thermal barrier coating to be added to the same component to allow engine operation under the same conditions, but with an increase in reliability. If an increase in rupture life to 1800 h is desired, what temperature differential between the inside and outside of the component must be achieved by the addition of the TBC?

Question

A superalloy gas turbine component was originally
designed to operate at temperatures up to 760°C and exhibited
a stress rupture life of 900 h under this operating condition. An
updated design calls for a thermal barrier coating to be added
to the same component to allow engine operation under the
same conditions, but with an increase in reliability. If an
increase in rupture life to 1800 h is desired, what temperature
differential between the inside and outside of the component
must be achieved by the addition of the TBC?

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