Effect of coolant temperature and mass flow on film cooling of turbine blades

Garg, Vijay K.; Gaugler, Raymond E.

doi:10.1016/0017-9310(96)00040-3

Cited by 41 publications

(20 citation statements)

References 8 publications

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“…Garg and Gaugler [13][14][15][16][17] compared their predictions to experimental results obtained on the C3X vane, the VKI rotor blade and the ACE rotor blade. It should be noted that neither of the blades was rotating.…”

Section: Introductionmentioning

confidence: 94%

Experimental study of rotation effect on film cooling over the flat wall with a single hole

Tao

Yang

Ding

et al. 2008

Experimental Thermal and Fluid Science

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Section: Introductionmentioning

confidence: 94%

Experimental study of rotation effect on film cooling over the flat wall with a single hole

Tao

Yang

Ding

et al. 2008

Experimental Thermal and Fluid Science

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“…Comparison of the spanwise‐averaged heat transfer coefficient on the vane with experimental data shows qualitative agreement in certain regions, and the disagreement is attributed to mesh characteristics. In a series of papers, Garg and Gaugler13–15 used the Baldwin‐Lomax model to obtain predictions of flow and heat transfer over a film‐cooled C3X vane (data provided by Hylton et al16) and a VKI rotor (for which measurements are reported by Camci and Arts17). The computational model consisted of a series of holes in the spanwise directions (covering, for example, 20% of the span), and the calculations were reasonably well resolved (nearly 0.5 million grid points).…”

Section: Algebraic Modelsmentioning

confidence: 99%

“…Garg and coworkers have systematically studied the effects of turbulence models28 and the hole physics29,30,13,14. In Garg28, an ACE rotor with five rows containing 93 film cooling holes were simulated.…”

Section: Two‐equation Turbulence Modelsmentioning

confidence: 99%

Flow and Heat Transfer Predictions for Film Cooling

Acharya¹,

Tyagi²,

Hoda³

2001

Annals of the New York Academy of Sciences

108

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Film cooling flows are characterized by a row of jets injected at an angle from the blade surface or endwalls into the heated crossflow. The resulting flowfield is quite complex, and accurate predictions of the flow and heat transfer have been difficult to obtain, particularly in the near field of the injected jet. The flowfield is characterized by a spectrum of vortical structures including the dominant kidney vortex, the horse‐shoe vortex, the wake vortices and the shear layer vortices. These anisotropic and unsteady structures are not well represented by empirical or ad‐hoc turbulence models, and lead to inaccurate predictions in the near field of the jet. In this paper, a variety of modeling approaches have been reviewed, and the limitations of these approaches are identified. Recent emergence of Direct Numerical Simulation (DNS) and Large Eddy Simulation (LES) tools allow the resolution of the coherent structure dynamics, and it is shown in this paper, that such approaches provide improved predictions over that obtained with turbulence models.

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“…Several further studies in this field have been summarized by Garg and Gaugler (1993, 1994. A number of parametric studies have been performed by Garg and co-workers to determine the effect of several parameters, such as the effect of coolant velocity and temperature distributions at the hole exit (Garg and Gaugler, 1997b), the effect of blade rotation and of the direction of coolant injection from the shower-head holes (Garg, 1997), the effect of spanwise pitch of shower-head holes (Garg and Gaugler, 1996), the effect of coolant to mainstream mass flow and temperature ratio (Garg and Gaugler, 1997a), and the effect of turbulence modeling (Garg and Abhari, 1997;Garg and Amen, 1997;Garg, 1998Garg, , 1999. Four turbulence models, the Baldwin-Lomax model, Coakley's q-ø model, Chien's k-e model, and Wilcox's k-ru models have been analyzed, and results compared with the experimental data for heat transfer from rotating as well as stationary blades.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer on a Film-Cooled Rotating Blade

Garg

1999

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

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A multi-block, three-dimensional Navier-Stokes code has been used to compute heat transfer coefficient on the blade, hub and shroud for a rotating high-pressure turbine blade with 172 film-cooling holes in eight rows. Film cooling effectiveness is also computed on the adiabatic blade. Wilcox’s k-ω model is used for modeling the turbulence. Of the eight rows of holes, three are staggered on the shower-head with compound-angled holes. With so many holes on the blade it was somewhat of a challenge to get a good quality grid on and around the blade and in the tip clearance region. The final multi-block grid consists of 4784 elementary blocks which were merged into 276 super blocks. The viscous grid has over 2.2 million cells. Each hole exit, in its true oval shape, has 80 cells within it so that coolant velocity, temperature, k and ω distributions can be specified at these hole exits. It is found that for the given parameters, heat transfer coefficient on the cooled, isothermal blade is highest in the leading edge region and in the tip region. Also, the effectiveness over the cooled, adiabatic blade is the lowest in these regions. Results for an uncooled blade are also shown, providing a direct comparison with those for the cooled blade. Also, the heat transfer coefficient is much higher on the shroud as compared to that on the hub for both the cooled and the uncooled cases.

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Effect of coolant temperature and mass flow on film cooling of turbine blades

Cited by 41 publications

References 8 publications

Experimental study of rotation effect on film cooling over the flat wall with a single hole

Experimental study of rotation effect on film cooling over the flat wall with a single hole

Flow and Heat Transfer Predictions for Film Cooling

Heat Transfer on a Film-Cooled Rotating Blade

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