Aero-Thermal Performance Measurements and Analysis of a Two-Dimensional High Turning Rotor Blade

Arts, Tony; Duboue, J.-M.; Rollin, G.

doi:10.1115/97-gt-120

Cited by 11 publications

(9 citation statements)

References 5 publications

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“…Predicted rotor profile loss was consistent with current design practice. Arts et al (1997), Dunn et al (1994), and Blair (1994) among others, showed midspan rotor blade leading edge heat transfer rates nearly twice the highest values seen elsewhere on the blade. Civinskas et al (1990) showed heat transfer in this region was reduced using a large leading edge diameter, and aerodynamic losses were not significantly increased.…”

Section: Fig 1 Transonic Turbine Blade Cascadementioning

confidence: 85%

Blade Heat Transfer Measurements and Predictions in a Transonic Turbine Cascade

Giel¹,

Fossen

Boyle

et al. 1999

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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Detailed heat transfer measurementa and predictions are given for a turbine rotor with 136° of turning and an axial chord of 12.7 cm. Data were obtained for inlet Reynolds numbers of 0.5 and 1.0 × 106, for isentropic exit Mach numbers of 1.0 and 1.3, and for inlet turbulence intensities of 0.25% and 7.0%. Measurements were made in a linear cascade having a highly three-dimensional flow field resulting from thick inlet boundary layers. The purpose of the work is to provide benchmark quality data for three-dimensional CFD code and model verification. Data were obtained by a steady-state technique using a heated, isothermal blade. Heat fluxes were determined from a calibrated resistance layer in conjunction with a surface temperature measured by calibrated liquid crystals. The results show the effects of strong secondary vortical flows, laminar-to-turbulent transition, shock impingement, and increased inlet turbulence on the surface heat transfer.

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Section: Fig 1 Transonic Turbine Blade Cascadementioning

confidence: 85%

Blade Heat Transfer Measurements and Predictions in a Transonic Turbine Cascade

Giel¹,

Fossen

Boyle

et al. 1999

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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“…The stator cases chosen were from Arts et al (1990), and from Hylton et al (1983). The rotor cases presented were those of Arts et al (1997). These data show rotor surface heat transfer for a range of Mach numbers, Reynolds numbers, and rotor incidence angles.…”

Section: Data Comparisonsmentioning

confidence: 99%

Mach Number Effects on Turbine Blade Transition Length Prediction

Boyle

Simon

1998

Volume 1: Turbomachinery

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The effect of a Mach number correction on a model for predicting the length of transition was investigated. The transition length decreases as the turbulent spot production rate increases. Much of the data for predicting the spot production rate comes from low speed flow experiments. Recent data and analysis showed that the spot production rate is affected by Mach number. The degree of agreement between analysis and data for turbine blade heat transfer without film cooling is strongly dependent of accurately predicting the length of transition. Consequently, turbine blade heat transfer data sets were used to validate a transition length turbulence model. A method for modifying models for the length of transition to account for Mach number effects is presented. The modification was made to two transition length models. The modified models were incorporated into the two-dimensional Navier-Stokes code, RVCQ3D. Comparisons were made between predicted and measured midspan surface heat transfer for stator and rotor turbine blades. The results showed that accounting for Mach number effects significantly improved the agreement with the experimental data.

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“…The entire blade might be manufactured in ceramic for cascade testing (Arts et al [27]), or inserts could be fitted into metallic blades in the case of measurements on the rotor of a turbine stage (Dénos [28]). …”

Section: Measurement Technique Thin Film Gaugesmentioning

confidence: 99%

Experimental Heat Transfer Investigation in a Multisplitter LP Vane Architecture

Pinilla

Solano

Paniagua

et al. 2010

Volume 4: Heat Transfer, Parts a and B

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This paper reports the external convective heat transfer in an innovative low pressure vane with multisplitter configuration. Three small aerodynamic blades are positioned between each structural vane, providing a novel architecture for ultra-high by-pass ratio aero-engines, with increased LP vane radius and swan-neck diffuser to link the HP turbine. The measurements have been performed in the compression tube test rig of the von Karman Institute, using single layered thin film gauges. Time-averaged and time-resolved heat transfer distributions are presented for the three aerovanes and for the structural blade, at three pressure ratios tested at representative conditions of modern aeroengines, with M 2,is ranging from 0.87 to 1.07 and a Reynolds number of about 10 6 . This facility is specially suited to control the gas-to-wall temperature ratio. Accurate time-averaged heat transfer distributions around the aerovanes are assessed, that allow characterizing the boundary layer status for each position and pressure ratio. The heat transfer distribution around the structural blade is also obtained, depicting clear transition to turbulence, as well as particular flow features on the pressure side, like separation bubbles. Unsteady data analysis reveals the destabilizing effect of the rotor left-running shock on the aerovanes boundary layer, as well as the shift of transition onset for different blade passing events.

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Aero-Thermal Performance Measurements and Analysis of a Two-Dimensional High Turning Rotor Blade

Cited by 11 publications

References 5 publications

Blade Heat Transfer Measurements and Predictions in a Transonic Turbine Cascade

Blade Heat Transfer Measurements and Predictions in a Transonic Turbine Cascade

Mach Number Effects on Turbine Blade Transition Length Prediction

Experimental Heat Transfer Investigation in a Multisplitter LP Vane Architecture

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