Three-Dimensional Navier-Stokes Prediction of Heat Transfer With Film Cooling

Fougères, J. M.; Helder, R.

doi:10.1115/94-gt-014

Cited by 9 publications

(5 citation statements)

References 16 publications

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“…To give the boundary condition at the injection hole outlet, the flow in the holes inside the vane tends to be calculated with the multi-block technique in addition to the flow along the vane. Fougeres and Heider (1994) calculated the flow along a vane including two injection rows on the suction and pressure surface, respectively. The domain was holepitch thick.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Loss Increase due to Individual Film Cooling Injections From Gas Turbine Nozzle Surface

Kubo

Otomo

Fukuyama

et al. 1998

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

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A CFD investigation was conducted on the total pressure loss variation for a linear nozzle guide vane cascade of a gas turbine, due to the individual film injections from the leading edge shower head, the suction surface, the pressure surface and the trailing edge slot. The results were compared with those of low speed wind tunnel experiments. A 2-D Navier-Stokes procedure for a 2-D slot injection, which approximated a row of discrete film holes, was performed to clarify the applicable limitation in the pressure loss prediction during an aerodynamic design stage, instead of a costly 3-D procedure for the row of discrete holes. In mass flow rate ratios of injection to main flow from 0% to 1%, the losses computed by the 2-D procedure agreed well with the experimental losses except for the pressure side injection cases. However, as the mass flow rate ratio was increased to 2.5%, the agreement became insufficient. The same tendency was observed in additional 3-D computations more closely modeling the injection hole shapes. The summations of both experimental and computed loss increases due to individual row injections were compared with both experimental and computed loss increases due to all-row injection with the mass flow rate ratio ranging from 0% to 7%. Each summation agreed well with each all-row injection result. Agreement between experimental and calculated results was acceptable. Therefore, the loss due to all-row injections in the design stage can be obtained by the correlations of 2-D calculated losses from individual row injections. To improve more precisely the summation prediction for the losses due to the present all-row injections, extensive research on the prediction for the losses due to the pressure side injection should be carried out.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic Loss Increase due to Individual Film Cooling Injections From Gas Turbine Nozzle Surface

Kubo

Otomo

Fukuyama

et al. 1998

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

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show abstract

“…Moreover, in many gas turbine applications, much higher Mach numbers and coolant to mainstream density ratios are encountered than those used in the experiments of Hay et al (1994). Fougeres and Heider (1994) solved the unsteady threedimensional Navier-Stokes equations, completed by a mixinglength turbulence model, using a finite volume technique. They presented two applications of the multi-domain code; one for a single row of hot jets injected into a flat plate turbulent boundary layer, and another for a plane nozzle guide vane with two rows of staggered holes on the pressure as well as suction side of the vane.…”

Section: Introductionmentioning

confidence: 99%

Leading Edge Film-Cooling Effects on Turbine Blade Heat Transfer

Garg

Gaugler

1996

Numerical Heat Transfer, Part A: Applications

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An existing three-dimensional Navier-Stokes code (Amone et al., 1991), modified to include film cooling considerations (Gang and Gaugler, 1994), has been used to study the effect of spanwise pitch of shower-head holes and coolant to mainstream mass flow ratio on the adiabatic effectiveness and heat transfer coefficient on a film-cooled turbine vane. The mainstream is akin to that under real engine conditions with stagnation temperature = 1900 K and stagnation pressure = 3 MPa. It is found that with the coolant to mainstream mass flow ratio fixed, reducing P, the spanwise pitch for shower-head holes, from 7.5 d to 3.0 d, where d is the hole diameter, increases the average effectiveness considerably over the blade surface. However, when P/d = 7.5, increasing the coolant mass flow increases the effectiveness on the pressure surface but reduces it on the suction surface due to coolant jet lift-off. For P/d = 4.5 or 3.0, such an anomaly does not occur within the range of coolant to mainstream mass flow ratios analyzed. In all cases, adiabatic effectiveness and heat transfer coefficient are highly three-dimensional.

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“…The influence of radial temperature distortion on 77 f and the influence of gridding on the coolant flow distribution were discussed. Fougeres and Heider (1994) performed a simulation of film cooling on flat plate and actual vane geometry. They used an overlapping mesh system to represent the film holes and placed 2 rows of holes on both suction and pressure surfaces.…”

Section: Blade Surface Film Cooling Studiesmentioning

confidence: 99%

Prediction of Vane Surface Film Cooling Effectiveness Using Compressible Navier-Stokes Procedure and k-ε Turbulence Model With Wall Function

Fukuyama

Otomo

Sato³

et al. 1995

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

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A numerical prediction has been performed on the film cooling effectiveness and the total pressure loss of the actual turbine vane geometry. The Navier-Stokes code used in this study is an implicit, cell-centered, finite volume code with k-ε turbulence models. The convection term was stabilized by the variable order up-winding scheme. The film cooling injection has been simulated by adding the prescribed flux terms at the vane surface. The k and ε near wall distribution functions were developed based on the experimental and the DNS results in the literature. The wall functions for k and ε can be used with the selected low Reynolds number version of k-ε turbulence model irrespective of the distance between the wall and the first grid point. This combination would result in lower computational costs, since, near wall grid number can be reduced significantly. Based on the study, the Navier-Stokes predictions were performed on the actual turbine vane geometry. Also, the comparisons were made with the experimental total pressure loss distribution behind the vane row and the mid-span film-cooling effectiveness distribution for single and double row injection cases.

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Three-Dimensional Navier-Stokes Prediction of Heat Transfer With Film Cooling

Cited by 9 publications

References 16 publications

Aerodynamic Loss Increase due to Individual Film Cooling Injections From Gas Turbine Nozzle Surface

Aerodynamic Loss Increase due to Individual Film Cooling Injections From Gas Turbine Nozzle Surface

Leading Edge Film-Cooling Effects on Turbine Blade Heat Transfer

Prediction of Vane Surface Film Cooling Effectiveness Using Compressible Navier-Stokes Procedure and k-ε Turbulence Model With Wall Function

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