Add to ORKGImprovement of the prediction of external (gas-to-blade) heat transfer coefficients in gas turbine engines was undertaken. The effects of improved eddy diffusivity of heat modeling in the turbulence model was specifically investigated. A two-dimensional boundary STAN5, was selected and modified by incorporating several different turbulent Prandtl number models. Results indicated that slight effects were attributable to the modified turbulence model. Boundary layer character appeared to be much more significant
Higher operating temperatures increase the efficiency of aircraft gas turbine engines, but can also ...
A modified form of the Lam-Bremhorst low-Reynolds number kappa-epsilon turbulence model was develope...
Significant progress was made in advancing the idea of establishing a unified approach for predictin...
The second phase of a continuing investigation to improve the prediction of turbine blade heat trans...
A program sponsored by NASA for the investigation of the heat transfer in the transition region of t...
A research effort was underway to study the use of two equation low Reynolds number turbulence model...
This viewgraph presentation summarizes some CFD experience at GE Aircraft Engines for flows in the p...
Estimates of the heat transfer from the gas to stationary (vanes) or rotating blades poses a major u...
The taxonomy of flow phenomena affecting turbine blade heat transfer has been widely researched and ...
A symposium on transition in turbines was held at the NASA Lewis Research Center. One recommendation...
Comparisons with experimental heat transfer and surface pressures were made for seven turbine vane a...
The results of aerodynamic and heat transfer experimental investigations performed in a high Reynold...
Results are shown for a three-dimensional Navier-Stokes analysis of both the flow and the surface he...
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1990.In...
Comparisons are shown between predictions and experimental data for blade and endwall heat transfer....
Higher operating temperatures increase the efficiency of aircraft gas turbine engines, but can also ...
A modified form of the Lam-Bremhorst low-Reynolds number kappa-epsilon turbulence model was develope...
Significant progress was made in advancing the idea of establishing a unified approach for predictin...
The second phase of a continuing investigation to improve the prediction of turbine blade heat trans...
A program sponsored by NASA for the investigation of the heat transfer in the transition region of t...
A research effort was underway to study the use of two equation low Reynolds number turbulence model...
This viewgraph presentation summarizes some CFD experience at GE Aircraft Engines for flows in the p...
Estimates of the heat transfer from the gas to stationary (vanes) or rotating blades poses a major u...
The taxonomy of flow phenomena affecting turbine blade heat transfer has been widely researched and ...
A symposium on transition in turbines was held at the NASA Lewis Research Center. One recommendation...
Comparisons with experimental heat transfer and surface pressures were made for seven turbine vane a...
The results of aerodynamic and heat transfer experimental investigations performed in a high Reynold...
Results are shown for a three-dimensional Navier-Stokes analysis of both the flow and the surface he...
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1990.In...
Comparisons are shown between predictions and experimental data for blade and endwall heat transfer....
Higher operating temperatures increase the efficiency of aircraft gas turbine engines, but can also ...
A modified form of the Lam-Bremhorst low-Reynolds number kappa-epsilon turbulence model was develope...
Significant progress was made in advancing the idea of establishing a unified approach for predictin...