Add to ORKGPredictions of the rate of heat transfer to the tip and shroud of a gas turbine rotor blade are presented. The simulations are performed with a multiblock computer code which solves the Reynolds Averaged Navier-Stokes equations. The effect of inlet boundary layer thickness as well as rotation rate on the tip and shroud heat transfer is examined. The predictions of the blade tip and shroud heat transfer are in reasonable agreement with the experimental measurements. Areas of large heat transfer rates are identified and physical reasoning for the phenomena presented
In today's modern gas turbine engines, the region between the rotor and the stationary shroud has th...
Comparisons are shown between predictions and experimental data for blade and endwall heat transfer....
Estimates of the heat transfer from the gas to stationary (vanes) or rotating blades poses a major u...
In gas turbines, the blades of axial turbine stages rotate in close proximity to a stationary periph...
ABSTRACT This work presents a numerical study that was done to investigate the heat transfer charact...
A combined experimental and computational study has been performed to investigate the detailed distr...
A combined experimental and computational program was conducted to examine the heat transfer distrib...
Results are shown for a three-dimensional Navier-Stokes analysis of both the flow and the surface he...
One of the most critical components of gas turbine engines, rotor blade tip and casing, is exposed t...
In current and advanced gas turbine engines, increased speeds, pressures and temperatures are used t...
This work is motivated by the need to accurately predict heat transfer in turbomachinery. For effici...
Higher operating temperatures increase the efficiency of aircraft gas turbine engines, but can also ...
Due to the increasingly high turbine inlet temperatures, heat transfer analysis is now, more than ev...
Improvements in methods for predicting heat transfer rates on the hot gas side of turbine airfoils a...
Steady simulations were performed to investigate tip leakage flow and heat transfer characteristics ...
In today's modern gas turbine engines, the region between the rotor and the stationary shroud has th...
Comparisons are shown between predictions and experimental data for blade and endwall heat transfer....
Estimates of the heat transfer from the gas to stationary (vanes) or rotating blades poses a major u...
In gas turbines, the blades of axial turbine stages rotate in close proximity to a stationary periph...
ABSTRACT This work presents a numerical study that was done to investigate the heat transfer charact...
A combined experimental and computational study has been performed to investigate the detailed distr...
A combined experimental and computational program was conducted to examine the heat transfer distrib...
Results are shown for a three-dimensional Navier-Stokes analysis of both the flow and the surface he...
One of the most critical components of gas turbine engines, rotor blade tip and casing, is exposed t...
In current and advanced gas turbine engines, increased speeds, pressures and temperatures are used t...
This work is motivated by the need to accurately predict heat transfer in turbomachinery. For effici...
Higher operating temperatures increase the efficiency of aircraft gas turbine engines, but can also ...
Due to the increasingly high turbine inlet temperatures, heat transfer analysis is now, more than ev...
Improvements in methods for predicting heat transfer rates on the hot gas side of turbine airfoils a...
Steady simulations were performed to investigate tip leakage flow and heat transfer characteristics ...
In today's modern gas turbine engines, the region between the rotor and the stationary shroud has th...
Comparisons are shown between predictions and experimental data for blade and endwall heat transfer....
Estimates of the heat transfer from the gas to stationary (vanes) or rotating blades poses a major u...