Turbine stage heat flux measurements

1982 ◽  
Author(s):  
M. DUNN ◽  
J. HOLT
Keyword(s):  
Heat Flux ◽  
Turbine Stage ◽  
Flux Measurements

Influence of Vane/Blade Spacing on the Heat Flux for a Transonic Turbine

2000 ◽  
Vol 122 (4) ◽  
pp. 684-691 ◽  
Author(s):  
M. G. Dunn ◽  
C. W. Haldeman ◽  
R. S. Abhari ◽  
M. L. McMillan
Keyword(s):  
Heat Flux ◽  
Reynolds Number ◽  
Nusselt Number ◽  
Heat Load ◽  
Two Dimensional ◽  
Turbine Stage ◽  
Flux Measurements ◽  
Analytical Research ◽  
Transonic Turbine ◽  
Measured Phase

An experimental and analytical research program determining the influence of vane/blade spacing on the vane and blade time-averaged and unsteady heat flux for a full-scale rotating turbine stage was performed. The turbine stage was operated at a transonic vane exit condition, with pressure and heat flux measurements obtained throughout the stage. This paper focuses on the midspan heat flux measurements for both the vane and blade at three vane/blade axial spacings: 20, 40, and 60 percent of vane axial chord. The time-averaged heat flux results for the vane and the blade are compared with predictions obtained using a two-dimensional, Reynolds-averaged multiblade row code, UNSFLO, developed by Giles (1984). The measured and predicted unsteady heat flux envelopes (as a function of vane/blade spacing) are also compared with predictions. For selected locations on the blade, a direct comparison between the measured phase-averaged surface pressure and the measured phase-averaged Nusselt number history is presented. At some locations along the surface the pressure and the heat flux are shown to be in phase, but at other locations they are not. The influence of vane/blade spacing on the blade heat load was found to be small, and much less than the differences caused by changes in the Reynolds number during the experimental matrix. [S0889-504X(00)00904-1]

Time-Averaged Heat-Flux Distributions and Comparison With Prediction for the Teledyne 702 HP Turbine Stage

1988 ◽  
Vol 110 (1) ◽  
pp. 51-56 ◽  
Author(s):  
M. G. Dunn ◽  
R. E. Chupp
Keyword(s):  
Thin Film ◽  
Heat Flux ◽  
Shock Tube ◽  
Flat Plate ◽  
Leading Edge ◽  
Turbine Stage ◽  
Heated Air ◽  
Edge Distribution ◽  
Flux Measurements ◽  
Good Agreement

Time-averaged heat-flux distributions are reported for the vane and blade of the Teledyne CAE 702 HP full-stage rotating turbine. A shock tube is used as a short-duration source of heated air to which the turbine is subjected and thin-film gages are used to obtain the heat-flux measurements. The thin-film gages were concentrated on the midspan region from the leading edge to near the trailing edge. The blade contained two contoured inserts wtih gages spaced very close together so that the leading edge distribution could be resolved. The NGV and blade results are compared with predictions obtained using a flat-plate technique, an eddy-diffusing model (STAN 5), and a k–ε model. The results of the comparison between data and prediction suggest that: (a) first, the vane data are bounded by the turbulent flat plate and the fully turbulent STAN 5 prediction. For the vane, the k–ε prediction is in relatively good agreement with the STAN 5 prediction and (b) secondly, the blade data are acceptably predicted by the k–ε prediction on both the pressure and the suction surfaces. The STAN 5 fully turbulent calculation for the blade falls above the data (essentially in agreement with the turbulent flat-plate calculation) and the STAN 5 fully laminar falls substantially below the data. With the exception of the pressure loadings and the geometry, the code inputs used for these predictions were identical to those previously used to predict the Garrett TFE 731-2 HP turbine and the Garrett LART HP turbine.

Influence of Vane/Blade Spacing on the Heat Flux for a Transonic Turbine

2000 ◽  
Author(s):  
M. G. Dunn ◽  
C. W. Haldeman ◽  
R. S. Abhari ◽  
M. L. McMillan
Keyword(s):  
Heat Flux ◽  
Reynolds Number ◽  
Nusselt Number ◽  
Heat Load ◽  
Turbine Stage ◽  
Blade Row ◽  
Flux Measurements ◽  
Analytical Research ◽  
Transonic Turbine ◽  
Measured Phase

An experimental and analytical research program determining the influence of vane/blade spacing on the vane and blade time-averaged and unsteady heat-flux for a full-scale rotating turbine stage was performed. The turbine stage was operated at a transonic vane exit condition, with pressure and heat-flux measurements obtained throughout the stage. This paper focuses on the midspan heat-flux measurements for both the vane and blade at three vane/blade axial spacings: 20%, 40%, and 60% of vane axial chord. The time-averaged heat-flux results for the vane and the blade are compared with predictions obtained using a 2-D, Reynolds-averaged multi-blade row code, UNSFLO, developed by Giles (1984). The measured and predicted unsteady heat-flux envelopes (as a function of vane/blade spacing) are also compared with predictions. For selected locations on the blade, a direct comparison between the measured phase-averaged surface pressure and the measured phase-averaged Nusselt number history is presented. At some locations along the surface the pressure and the heat flux are shown to be in phase, but at other locations they are not. The influence of vane/blade spacing on the blade heat load was found to be small, and much less than the differences caused by changes in the Reynolds number during the experimental matrix.

Measurement of Heat Flux and Pressure in a Turbine Stage

1981 ◽  
Author(s):  
M. G. Dunn ◽  
A. Hause
Keyword(s):  
Heat Flux ◽  
Reynolds Numbers ◽  
Wall Region ◽  
Pressure Measurements ◽  
Turbine Stage ◽  
Flux Measurements ◽  
Film Heat Transfer ◽  
End Wall ◽  
High Temperature High Pressure ◽  
Good Agreement

Selected portions of the first-stage stationary inlet nozzle, shroud, and rotor of the AiResearch TFE 731-2 turbine were instrumented with thin-film heat-transfer gages and heat-flux measurements were performed using a shock tunnel as a source of high-temperature, high-pressure gas. Experiments were performed over a range of Reynolds numbers, based on mid-annular stator chord, from 1.6 × 105 to 3.1 × 105 and corrected speeds from approximately 70 to 106 percent. The full-stage heat-flux results are compared to our previous measurements obtained with a stator only, in the absence of a rotor. The previous results are in good agreement with the full-stage data for the tip end-wall region, but they are significantly less than the full-stage results for the stator airfoil. Pressure measurements were obtained throughout the model and these results are shown to be in excellent agreement with the steady-state rig data supplied to us by AiResearch for this turbine. Heat-flux measurements are also presented for the stationary shroud as a function of rotor mid-annular chord. The shroud heat flux data are shown to be in excess of the rotor blade results. Rotor-tip heat flux measurements are likewise shown to be slightly greater than the shroud results.

Measurement of Heat Flux and Pressure in a Turbine Stage

1982 ◽  
Vol 104 (1) ◽  
pp. 215-223 ◽  
Author(s):  
M. G. Dunn ◽  
A. Hause
Keyword(s):  
Heat Flux ◽  
Reynolds Numbers ◽  
Wall Region ◽  
Pressure Measurements ◽  
Turbine Stage ◽  
Flux Measurements ◽  
Film Heat Transfer ◽  
End Wall ◽  
High Temperature High Pressure ◽  
Good Agreement

Selected portions of the first stage stationary inlet nozzle, shroud, and rotor of the AiResearch TFE 731-2 turbine were instrumented with thin-film heat-transfer gages and heat-flux measurements were performed using a shock tunnel as a source of high-temperature, high-pressure gas. Experiments were performed over a range of Reynolds numbers, based on mid-annular stator chord, from 1.6 × 105 to 3.1 × 105 and corrected speeds from approximately 70–106 percent. The full-stage heat-flux results are compared to our previous measurements obtained with a stator only, in the absence of a rotor. The previous results are in good agreement with the full-stage data for the tip end-wall region, but they are significantly less than the full-stage results for the stator airfoil. Pressure measurements were obtained throughout the model and these results are shown to be in excellent agreement with the steady-state rig data supplied to us by AiResearch for this turbine. Heat-flux measurements are also presented for the stationary shroud as a function of rotor mid-annular chord. The shroud heat-flux data are shown to be in excess of the rotor blade results. Rotor-tip heat-flux measurements are shown to be slightly greater than the shroud results.

QUANTIFYING ERRORS IN HEAT FLUX MEASUREMENTS USING A VERTICAL SEQUENCE OF THERMOCOUPLE SENSORS

2016 ◽  
Author(s):  
Gabriela Villegas ◽  
◽  
Jerry P. Fairley ◽  
Cary R. Lindsey ◽  
Megan M. Aunan ◽  
...  
Keyword(s):  
Heat Flux ◽  
Flux Measurements

Fast-Response transient heat flux measurements in a plasma wind tunnel

2021 ◽  
Vol 173 ◽  
pp. 121234
Author(s):  
Byrenn Birch ◽  
David Buttsworth ◽  
Stefan Löhle ◽  
Fabian Hufgard
Keyword(s):  
Heat Flux ◽  
Wind Tunnel ◽  
Fast Response ◽  
Flux Measurements ◽  
Transient Heat Flux

An analog period method for gap‐filling of latent heat flux measurements

2021 ◽  
Author(s):  
Lucas Emilio B. Hoeltgebaum ◽  
Nelson Luís Dias ◽  
Marcelo Azevedo Costa
Keyword(s):  
Heat Flux ◽  
Latent Heat ◽  
Latent Heat Flux ◽  
Gap Filling ◽  
Flux Measurements

Model-based optimization of equipment and control for heat flux measurements in a laboratory fermentor

1995 ◽  
Vol 11 (5) ◽  
pp. 525-532 ◽  
Author(s):  
Bastiaan H. A. van Kleeff ◽  
J. Gijs Kuenen ◽  
Ger Honderd ◽  
Sef J. Heijnen
Keyword(s):  
Heat Flux ◽  
Model Based ◽  
Flux Measurements ◽  
And Control ◽  
Laboratory Fermentor
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