Influence of different film cooling arrangements on endwall cooling

Li, Xueying; Ren, Jing; Jiang, Hongde

doi:10.1016/j.ijheatmasstransfer.2016.06.047

Cited by 42 publications

(6 citation statements)

References 29 publications

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“…Currently, the Uni-FIB PSP (UF470-750) from ISSI Inc. is used in the experiments. LED light with a wavelength of 470nm excites the PSP and the emitted light is recorded by a CCD camera with a filer to shield the excitation light [26]. Four different kinds of images are recorded during the experiments: image with mainflow and N 2 /CO 2 , image with mainflow and air, image without mainflow and coolant (reference image), and background image (to remove noise).…”

Section: Pressure Sensitive Paint and Adiabatic Effectivenessmentioning

confidence: 99%

“…The light intensity ratio is converted to pressure ratio using a calibration curve shown in Fig. 7 which was obtained using a calibration device similar to Li et al [26]. The pressure was normalized with the room pressure (P 0 ), while the intensity data were normalized with three different reference conditions recorded at room pressure and at the same temperature of the correspondent curve (I 0 ).…”

Section: Pressure Sensitive Paint and Adiabatic Effectivenessmentioning

confidence: 99%

“…The typical uncertainty of adiabatic film cooling effectiveness measurements varies with different coolant gas, i.e. CO 2 .The uncertainty is estimated to be 6% for η higher than 0.3, and 11% for η around 0.1 [26]. All the uncertainty analysis is based on 95% confidence.…”

Section: Pressure Sensitive Paint and Adiabatic Effectivenessmentioning

confidence: 99%

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Experimental investigation of wall thickness and hole shape variation effects on full-coverage film cooling performance for a gas turbine vane

Ren

et al. 2018

Applied Thermal Engineering

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The effects of wall thickness and hole shape variation on a full-coverage film cooled turbine vane are investigated in a stationary and linear cascade utilizing the pressure sensitive paint technique. The varied wall thickness produces hole lengthto-diameter ratio (L/D) in a range from L/D=2 to 5, and holes tested include simple angle hole, compound angle hole, and fan-shaped hole. Five rows of holes are provided on the pressure side while three rows of holes are provided on the suction side, with six rows of cylindrical holes drilled on the leading edge to construct showerhead film cooling. The tested blowing ratios for the showerhead, pressure side, and suction side range from 0.25 to 1.5, with a density ratio of 1.5. The freestream Reynolds number is 1.35×10 5 , based on the axial chord length and the inlet velocity, with a freestream turbulence intensity level of 3.5% at the cascade inlet. The results indicate that the wall thickness variation produces significant influence on the pressure side film cooling effectiveness, while only marginal effect on the showerhead and suction side film cooling. Also observed is that the fan-shaped hole generates the highest film cooling effectiveness on pressure or suction side. Also discussed is the surface curvature effect, combining with effects of wall thickness and hole shape variations, on the film cooling effectiveness in comparison to the flat-plate data.

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Section: Pressure Sensitive Paint and Adiabatic Effectivenessmentioning

confidence: 99%

Section: Pressure Sensitive Paint and Adiabatic Effectivenessmentioning

confidence: 99%

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Experimental investigation of wall thickness and hole shape variation effects on full-coverage film cooling performance for a gas turbine vane

Ren

et al. 2018

Applied Thermal Engineering

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“…All the heat transfer coefficient experiments were performed in the low speed wind tunnel shown in Fig.2. Heat transfer coefficients measurements on the turbine vane endwall in this tunnel have been reported by Li et al [22][23][24]. The test section has an inlet cross section of 0.24×0.16m 2 , and the mainstream velocity is set to 25m/s measured by a five-hole probe.…”

Section: Low Speed Wind Tunnelmentioning

confidence: 99%

Length to diameter ratio effect on heat transfer performance of simple and compound angle holes in thin-wall airfoil cooling

Ren

et al. 2018

International Journal of Heat and Mass Transfer

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Heat transfer coefficients on a flat plate surface downstream a row of simple and compound angle cylindrical holes are investigated using high-resolution thermographic liquid crystal technique. A variation of flow parameters including blowing ratio, and geometry parameters including compound angle and length-to-diameter ratio are examined. Blowing ratios (M) ranging from 0.3 to 2, length to diameter ratios (L/D) from 0.5 to 5, and two compound angle (β: 0°, 45°) are employed composing a test matrix of 70 test cases. Detailed local, spanwise averaged, and area averaged heat transfer coefficients hf/h0 are presented to illustrate the effect of length-to-diameter ratio and compound angle. The film cooling performance is also evaluated using NHFR method and Δφ method by combining adiabatic film effectiveness and heat transfer coefficient data. Results indicate that Δφ method has superiority in evaluating film cooling performance due to its direct reflection of temperature reduction by film protection.

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“…Thomas and Povey [5], Friedrichs et al [6], and Salvadori et al [7] report the aerodynamic losses at the exit of cascade passage due to the film-cooling flow from discrete holes in the endwall. The adverse effects of the secondary flows and configuration of film-cooling holes on the endwall coolant coverage and effectiveness are investigated by Bogard and Thole [8], Mahmood et al [9] and Li et al [10,11].…”

Section: Introductionmentioning

confidence: 99%

Effects of Upstream Endwall Film Cooling on a Vane Cascade Flowfield

Mahmood

Arnachellan

2018

Journal of Propulsion and Power

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The effects of film-cooling on the endwall region flow and aerodynamic losses are investigated experimentally as the film-flow is delivered from the slots in the endwall upstream of a linear vane cascade. Four slots inclined at 30° deliver the film-jet parallel to the main flow at four blowing ratios between 1.1 and 2.3 and at a temperature ratio of 1.0. The slots are employed in two configurations pitchwise-all four slots open (case-1) and two middle slots open (case-2). The inlet Reynolds number to the cascade is 2.0E+05. Measurements of the blade surface pressure, axial vorticities, yaw angles, and total pressure loss distributions along the cascade are reported with and without (Baseline) the film-cooling flow. The results show the film-flow changes the orientations, distributions,and strength of the endwall secondary flows and boundary layer. The case-1 of film-cooling provides more massflux and momentum than the case-2 affecting the passage vortex legs. The overall total pressure losses at the cascade exit are always lower for the film-cooling cases than for the Baseline. The overall losses are also lower at the low blowing ratios, but higher at the high blowing ratios for the film-cooling case-1 than for the case-2. NomenclatureC, C ax , P, S = true blade-chord, axial blade-chord, pitch, span C P,Blade = blade surface static pressure coefficient C pt,loss , C Pt,Loss = total pressure loss coefficient M = passage mass flow rate MFR, M in = mass fraction ratio, inlet blowing ratio P b,x = pressure on blade surface P s,r , P t,r = (static pressure, total pressure) at reference plane P t,x , P t,box = local total pressure at exit, total pressure in plenum box PS, SS, TE = pressure-side, suction-side, trailing edge Re = inlet Reynolds number based on actual-chord U = freestream velocity (X, Y, Z) = local Cartesian coordinates (X G , Y G , Z G ) = global Cartesian coordinates Lower Case u, v, w = velocity components along (X, Y, Z) s = blade surface coordinate Greek δ = boundary layer thickness Δ = change in related quantity ω = vorticity ρ = density

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Influence of different film cooling arrangements on endwall cooling

Cited by 42 publications

References 29 publications

Experimental investigation of wall thickness and hole shape variation effects on full-coverage film cooling performance for a gas turbine vane

Experimental investigation of wall thickness and hole shape variation effects on full-coverage film cooling performance for a gas turbine vane

Length to diameter ratio effect on heat transfer performance of simple and compound angle holes in thin-wall airfoil cooling

Effects of Upstream Endwall Film Cooling on a Vane Cascade Flowfield

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