Maurice Tutor

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Category > Management Posted 21 Mar 2018 My Price 7.00

performance of gas turbine

The performance of gas turbine engines may be improved by increasing the tolerance of the turbine blades to hot gases emerging from the combustor. One approach to achieving high operating temperatures involves application of a thermal barrier coating (TBC) to the exterior surface of a blade, while passing cooling air through the blade. Typically, the blade is made from a high-temperature superalloy, such as Inconel  while a ceramic, such as zirconia  is used as a TBC.

 

Consider conditions for which hot gases at T∞,o = 1700 K and cooling air at T∞,i = 400 K provide outer and inner surface convection coefficients of ho = 1000 W/m2 ∙ K and hi = 500 W/m2 ∙  K, respectively. If a 0.5-mm-thick zirconia TBC is attached to a 5-mmthick Inconel blade wall by means of a metallic bonding agent, which provides an interfacial thermal resistance of  can the Inconel be maintained at a temperature that is below its maximum allowable value of 1250 K? Radiation effects may be neglected, and the turbine blade may be approximated as a plane wall. Plot the temperature distribution with and without the TBC. Are there any limits to the thickness of the TBC?

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Maurice Tutor
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Status NEW Posted 21 Mar 2018 06:03 AM My Price 7.00

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