Aerodynamic design and analysis of a gas producer turbine stator with film cooling injection

Liu, Jong-Shang; Utz, Robert; Bozzola, R.

doi:10.2514/6.1994-2928

Cited by 4 publications

(8 citation statements)

References 4 publications

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“…Both these extremes have merits and limitations. While the poor resolution of Liu et al (1994) perhaps prevented them from presenting any heat transfer results, they could consider the whole vane along with the hub and shroud endwalls containing 34 rows with hundreds of film cooling holes. On the other hand, Leylek and Zerkle analyzed just one row of holes on a flat plate (just one hole for computational purposes), while Weigand and Harasgama (1994) considered a total of nine holes in two rows on a rotating blade but with (unrealistic) injection in the tangential direction.…”

Section: Introductionmentioning

confidence: 99%

“…On the other hand, the computational effort is almost solely devoted to the real blade, though still stationary except for the analysis of Weigand and Harasgama (1994). Also, while the analysis of Liu et al (1994) forms one extreme in that no resolution of the mixing of coolant with the main flow was attempted, the analysis of Weigand and Harasgama (1994) and of Leylek and Zerkle (1994) represents the other extreme with the hole pipe and plenum chamber also discretized. Both these extremes have merits and limitations.…”

Section: Introductionmentioning

confidence: 99%

“…Their computations show a strong spanwise variation of the heat transfer coefficient on the blade surface, specially with shower-head cooling, while almost all experimental data is near mid-span or span-averaged. Liu et al (1994) implemented a bulk film cooling capability in a three-dimensional viscous code with the Baldwin-Lomax turbulence model to recognize the global effect of mass, momentum and energy addition without attempting to resolve the details of the cooling air jet and its mixing evolution with the main flow. Using this code, the first stage of a gas producer turbine was designed, and cases with and without cooling were compared.…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Leading Edge Film-Cooling Effects on Turbine Blade Heat Transfer

Garg

Gaugler

1996

Numerical Heat Transfer, Part A: Applications

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“…On the other hand, recent Computational effort is mostly devoted to the real blade, through still stationary except for the analysis of Weigand and Harasgama [8]. The computational effort is bounded at one end by the analysis of Liu et al [9], in which hundreds of Downloaded by [University of Lethbridge] at 12:29 14 June 2016 film-cooling holes were considered but without any resolution of the mixing of coolant with the main flow, and at the other by the analysis of Weigand and Harasgama (8] and of Leylek and Zerkle [10], wherein the hole pipe and plenum chamber were also discretized. Both these extremes have merits and limitations.…”

Section: Introductionmentioning

confidence: 98%

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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“…While the poor resolution of Liu et al [6] power-law) for the coolant velocity and temperature distribution at the hole exit were specified, in conformity with the observation of Leylek and Zerkle [7], since the hole-length to diameter ratio for the VKI rotor is greater than 3.0. Leylek and Zerkle [7] found that for high hole-length to diameter ratios (>/3.0) and high blowing ratios ( _>1.0), the velocity profile at the hole exit is akin to the l/7th power-law profile.…”

Section: Introductionmentioning

confidence: 99%