Effect of Velocity and Temperature Distribution at the Hole Exit on Film Cooling of Turbine Blades

Garg, Vijay K.; Gaugler, Raymond E.

doi:10.1115/1.2841117

Cited by 62 publications

(37 citation statements)

References 35 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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“…Detailed numerical analyses of the film cooling physics on a flat plate with one row of holes were presented by Walters and Leylek [5] for cylindrical holes. Garg and Gaugler [6] showed the importance of film hole exit profiles. Complex 3-D numerical investigations of a real film-cooled blade were presented by Garg and Rigby [7] with a focus on the hole exit regions and the heat transfer.…”

Section: Introductionmentioning

confidence: 98%

Conjugate heat transfer analysis of film cooling flows

Jiang

Sugishita

et al. 2006

J. of Therm. Sci.

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The objective of this study is to evaluate the potential of various grids to satisfactorily simulate the development of a cooling film, using a coupled computation that takes into account the full geometry. Detailed computations of a single row of 30 degrees round holes on a flat plate are presented for blowing ratios of 0.764, 1.01 and 1.54. The simulation results are compared well with experimental data. The two-layer model gave more accurate results but consumed much more computational time than the standard wall functions. The k-ε turbulence model with wall functions with appropriate values of + y is suitable for practical use. The results show the importance of the conjugate calculation for accurately describing the influence of the heat transfer within the cooling film.K eywords: film cooling, conjugate heat transfer, blowing ratio. CLC number: TK124 Document code: A

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“…Terms for the viscous flux vector Go can be written similarly by interchanging 7/ and " and replacing F by G everywhere in Eqs, (3) and (4). The solution is obtained in terms of the absolute velocity components (u, v, w) …”

Section: Discussionmentioning

confidence: 99%

“…A periodic C grid with up to one million grid points was used. Following Garg and Gaugler [3], who provided results using the same grid for the B-L model, the grid used for the VKI rotor was 353 X 53 X 17, while for the C3X vane, it was 281 X 45 X 81, where the first number represents the number of grid points along the wraparound direction (for the C grid), the second in the blade-to-blade direction, and the third in the span direction. Normal to the blade surface is the dense viscous grid, with y + < 1 for the first point off the blade surface, following …”

Section: Computational Detailsmentioning

confidence: 99%

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Comparison of Two-Equation Turbulence Models for Prediction of Heat Transfer on Film-Cooled Turbine Blades

Garg¹,

Ameri²

1997

Numerical Heat Transfer, Part A: Applications

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A Ihree-dimensional Ntw~r-StoUs code IrJJS beell used to cotrI/IUU 1M heJlJ~., coef/iciml 011 two fiIm-eookd turbine b1DJks, 1IQ1IIe/y, 1M JIKI rotor with six rows of cooling holes, induJling three rows 011 1M shower Mad, and 1M C3X VIlM with niM rows of holes, induding five rows 011 1M shower heIJd. Pmlidions ofheJlJ tmnsfer coef/icielllat the bItule SUlfa« using three hf>o-equatioll turbuJmce motfels, specijieoJly, Cookley's q·w model, Chiell's t-e motfet, and WIIcar's k-o» model with Melller's modijieations, luwe been compand with 1M experimmtot t1IJJIl of Camei and Arts £11for 1M VKl rotor, and ofHyltoll el aI. 121for the C3X VIlM along with pretlidions using the Ba/dwin-Lo1ll/U (B-O model tIIkm from Gtug and Gaugler 131. II is foruul t1UIl for 1M CDS" considered here the twoequatioll motlds pretlid the btDde heJlJ~er somewhat better Ihtm 1M B-L model ex«pI immediote/y downstrttJm of the jiIm-cooling holes 011 1M suction SUIf-of 1M JIKI rotor, and over nwsI of 1M suaion surf-of 1M C3X VIlM. However, all hf>o-equatiOIl motfels require 40% more computer core than the B·L motfelfor solution, and while 1M q.w and t-e motfels need 40% mDre computer nine Ihtm 1M B-L motfet, the t-w model reqIIin3 at least 65% more nine becou.se of 1M slower tYlU of convergmt:e. II is loruul t1UIl 1M heJlJ tmnsfer coejJicielll uhibils a strollgspallwiseas wellas stretlmwise variationlor both b1DJks and all turbulence motfels.

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Effect of Velocity and Temperature Distribution at the Hole Exit on Film Cooling of Turbine Blades

Abstract: lop An existing three-dimensionalNavier-Stokes code (Arnone et aL, 1991)

Cited by 62 publications

References 35 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

Conjugate heat transfer analysis of film cooling flows

Comparison of Two-Equation Turbulence Models for Prediction of Heat Transfer on Film-Cooled Turbine Blades

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