External Heat-Transfer Distribution on Film Cooled Turbine Vanes

Lander, Richard D.; Fish, R. W.; Suo, M.

doi:10.2514/3.59068

Cited by 23 publications

(11 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Takeishi et al (1992) used the mass transfer analogy with CO2 injectant, under both stationary and rotational conditions, to determine film effectiveness locally. Thinwalled airfoils of metal, with imbedded thermocouples and internal insulation have been used by Takeishi et al (1990), and in earlier tests of Lander et al (1972), to obtain film effectiveness distributions for various film cooling configurations.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer and Film Cooling Effectiveness in a Linear Airfoil Cascade

Abuaf

Bunker

Lee

1995

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

View full text Add to dashboard Cite

A warm (315 C) wind tunnel test facility equipped with a linear cascade of film cooled vane airfoils was used in the simultaneous determination of the local gas side heat transfer coefficients and the adiabatic film cooling effectiveness. The test rig can be operated in either a steady-state or a transient mode. The steady-state operation provides adiabatic film cooling effectiveness values while the transient mode generates data for the determination of the local heat transfer coefficients from the temperature-time variations and of the film effectiveness from the steady wall temperatures within the same aero-thermal environment. The linear cascade consists of five airfoils. The 14% cascade inlet free stream turbulence intensity is generated by a perforated plate, positioned upstream of the airfoil leading edge. For the first transient tests, five cylinders having roughly the same blockage as the initial 20% axial chord of the airfoils were used. The cylinder stagnation point heat transfer coefficients compare well with values calculated from correlations. Static pressure distributions measured over an instrumented airfoil agree with inviscid predictions. Heat transfer coefficients and adiabatic film cooling effectiveness results were obtained with a smooth airfoil having three separate film injection locations, two along the suction side, and the third one covering the leading edge showerhead region. Near the film injection locations, the heat transfer coefficients increase with the blowing film. At the termination of the film cooled airfoil tests, the film holes were plugged and heat transfer tests were conducted with non-film cooled airfoils. These results agree with boundary layer code predictions.

show abstract

Section: Introductionmentioning

confidence: 99%

Heat Transfer and Film Cooling Effectiveness in a Linear Airfoil Cascade

Abuaf

Bunker

Lee

1995

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

View full text Add to dashboard Cite

show abstract

“…Their data show relatively large coefficients near the injection slot; as the downstream distance from the slot increases, hH quickly declines approaching the coefficient obtained without injection. Measurements of heat transfer coefficients averaged across the test surface are reported in some studies of three-dimensional film cooling from a single row and multiple rows of circular holes (Metzger and Fletcher, 1971;Mayle and Camarata, 1975;Liess, 1975;Metzger, Kuenstler and Takeuchi, 1976;Lander, Fish and Suo, 1972;Ligrani and Breugelmans, 1981). Effects of parameters such as injection geometry, blowing rate, pressure gradient, and boundary layer transition on variation of spanwise-averaged coefficients in the mainflow direction were investigated in these studies.…”

Section: Introductionmentioning

confidence: 99%

Surface Injection Effect on Mass Transfer From a Cylinder in Crossflow: A Simulation of Film Cooling in the Leading Edge Region of a Turbine Blade

Karni

Goldstein

1990

Journal of Turbomachinery

View full text Add to dashboard Cite

A naphthalene sublimation technique is used to study the effect of surface injection on the mass (heat) transfer from a circular cylinder in crossflow. Using a heat/mass transfer analogy the results can be used to predict film cooling effects in the leading edge region of a turbine blade. Air injection through one row of circular holes is employed in the stagnation region of the cylinder. Streamwise and spanwise injection inclinations are studied separately, and the effects of blowing rate and injection location relative to the cylinder front stagnation line are investigated. Streamwise injection produces significant mass transfer increases downstream of the injection holes, but a relatively small increase is observed between holes, normal to the injection direction. The mass transfer distribution, measured with spanwise injection through holes located near the cylinder front stagnation line, is extremely sensitive to small changes in the injection hole location relative to stagnation. When the centers of the spanwise injection holes are located 5 deg or more from the stagnation line, the holes lie entirely on one side of the stagnation line and the injection affects the mass transfer only on that side of the cylinder, approaching the pattern observed with streamwise injection.

show abstract

“…The final dataset considered for this report was taken from the suction surface data reported by Lander (12) and Lander et al (13). This data was generated in a transient test using hot combustion gases to heat a cascade of turbine airfoils that was quickly shuttled into the hot stream.…”

Section: Selection Of Oatasetsmentioning

confidence: 99%

A Review and Analysis of Boundary Layer Transition Data for Turbine Application

Gaugler

1985

Volume 3: Heat Transfer; Electric Power

View full text Add to dashboard Cite

A Symposium on Transition in Turbines was held recently at the NASA Lewis Research Center. One recommendation of the working groups was the collection of existing transition data to provide standard cases against which models could be tested. This paper represents a preliminary response to that recommendation. A number of data sets from the open literature that include heat transfer data in apparently transitional boundary layers, with particular application to the turbine environment, were reviewed and analyzed to extract transition information from the heat transfer data. The data were analyzed using a version of the STAN5 two-dimensional boundary layer code. The transition starting and ending points were determined by adjusting parameters in STAN5 until the calculations matched the data. The results are presented as tables of the deduced transition location and length as functions of the test parameters. The data sets reviewed cover a wide range of flow conditions, from low speed, flat plate tests to full scale turbine airfoils operating at simulated turbine engine conditions. The results indicate that free stream turbulence and pressure gradient have strong, and opposite, effects on the location of the start of transition and on the length of the transition zone.

show abstract

External Heat-Transfer Distribution on Film Cooled Turbine Vanes

Cited by 23 publications

References 5 publications

Heat Transfer and Film Cooling Effectiveness in a Linear Airfoil Cascade

Heat Transfer and Film Cooling Effectiveness in a Linear Airfoil Cascade

Surface Injection Effect on Mass Transfer From a Cylinder in Crossflow: A Simulation of Film Cooling in the Leading Edge Region of a Turbine Blade

A Review and Analysis of Boundary Layer Transition Data for Turbine Application

Contact Info

Product

Resources

About