Pages that link to "Item:Q646588"
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The following pages link to Numerical simulation on the effect of jet nozzle position on impingement cooling of gas turbine blade leading edge (Q646588):
Displaying 6 items.
- Numerical predictions of augmented heat transfer of an internal blade tip-wall by hemispherical dimples (Q608730) (← links)
- Numerical study of film cooled rotor leading edge with tip clearance in 1-1/2 turbine stage (Q929845) (← links)
- Development of a numerical correlation for the discharge coefficient of round inclined holes with low crossflow (Q1648331) (← links)
- Effects of nozzle arrangement on uniformity of multiple impinging jets heat transfer in a fast cooling simulation device (Q1649648) (← links)
- Calculation of the flow around a high-pressure turbine blade with cooling-jet injection from slots at the leading edge (Q1975851) (← links)
- Effect of incidence angle with wake passing on a film cooled leading edge: A numerical study (Q3579860) (← links)