Film cooling effectiveness distribution of cylindrical hole injections at different locations on a vane endwall

Li, Xueying; Ren, Jing; Jiang, Hongde

doi:10.1016/j.ijheatmasstransfer.2015.06.026

Cited by 34 publications

(3 citation statements)

References 30 publications

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“…Chowdhury et al 23 measured the endwall film cooling effectiveness under different discrete hole arrangements. Li et al 24 studied the film cooling distribution with six rows of cylindrical holes placed at different axial locations. Both of them considered that there were remarkable effects of the mass flow ratio and the density ratio on the film cooling performance.…”

Section: Introductionmentioning

confidence: 99%

Turbine vane endwall aerothermal and film cooling performance considering realistic swirling inflow conditions

Zhang

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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The turbine vane inlet downstream of the lean premixed combustor presents nonuniform distributions of velocity and temperature. For obtaining swirling inflow profiles close to reality, the simulated non-reacting combustor is designed firstly. Applying these profiles as inflow boundary conditions, the effects of realistic swirling inflow on the turbine vane endwall aerothermal characteristics and film cooling performance are numerically investigated through solving the three-dimensional Reynolds-Averaged Navier-Stokes equations coupled with the shear stress transfer ([Formula: see text]) turbulence model. Two swirling orientations (anticlockwise and clockwise) and five swirling core pitch-wise positions (aligned with vane 1 to vane 2) are considered in the current work. The results indicate that the residual vortices in the vane passage are strengthened and move with the swirling core along the pitch-wise direction. The migration of the horseshoe vortex is controlled by this movement. The shrinkage or expansion of the separation line of the horseshoe vortex can be observed under the anticlockwise and clockwise swirling inflow conditions respectively. The anticlockwise swirling inflow results in a larger aerodynamic loss by a 10%–35% increase of the laterally [Formula: see text]. The high Nu region near the pressure side surface enlarges and the area-averaged Nu at [Formula: see text] increases from 2337.9 to 2878.3. For the cases with clockwise swirling inflow, the area of the hot ring is enlarged and the Nu downstream of the row 3 film holes is decreased. As for the film cooling performance, the endwall coverage area shrinks and the phantom cooling area enlarges when the anticlockwise swirling core is aligned with vane 2. The endwall loses the protection from the row 3 film holes and the cooling failure ([Formula: see text]) occurs at [Formula: see text] when the swirling core is aligned with the vane passage. This is an extremely bad phenomenon that should be avoided. Among all cases, the highest endwall area-averaged [Formula: see text] (0.122) is obtained when the clockwise swirling core is aligned with vane 1. The largest endwall coverage area is achieved when the clockwise swirling core is aligned with vane 2.

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Section: Introductionmentioning

confidence: 99%

Turbine vane endwall aerothermal and film cooling performance considering realistic swirling inflow conditions

Zhang

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…The results analyzed the mechanisms of two cooling methods at different blowing ratios. Li et al [23][24][25][26] conducted extensive experimental research on film cooling of endwall by the PSP technique. The experiment measured the flow field and heat transfer distribution of different film cooling configurations with and without jet impingement.…”

Section: Introductionmentioning

confidence: 99%

Research on the flow field and film cooling effectiveness of the endwall with swirling film cooling

Zhang

Zheng

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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In order to obtain the effect of endwall secondary flow on the swirling film cooling, a geometric model of cascade is established to research the endwall swirling film cooling and swirling flow induced by prismatic jet impingement configurations. Numerical simulation is applied to investigate three jet flow configurations on the endwall film cooling performance at the compound angles of film hole γ = 0° and 30° and blowing ratios M = 0.5–2.0. The influence of complex vortex structures near endwall for jet flow is analyzed in detail; the strong transverse cross flow near the endwall is the main reason affecting the film cooling effectiveness. The variation laws of endwall film cooling effectiveness with the compound angle of film hole, jet flow configuration, and the blowing ratio are obtained. As the blowing ratio increases, the spanwise average film cooling effectiveness increases first and then decreases. While the blowing ratio is M =1.0, the endwall film cooling effectiveness is the best. Increasing the compound angle of the film hole leads to a decrease in the endwall cooling effectiveness. The spanwise average cooling effectiveness of γ = 30° decreases by 35% compared to the γ = 0°.

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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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Film cooling effectiveness distribution of cylindrical hole injections at different locations on a vane endwall

Cited by 34 publications

References 30 publications

Turbine vane endwall aerothermal and film cooling performance considering realistic swirling inflow conditions

Turbine vane endwall aerothermal and film cooling performance considering realistic swirling inflow conditions

Research on the flow field and film cooling effectiveness of the endwall with swirling film cooling

Effects of Upstream Endwall Film Cooling on a Vane Cascade Flowfield

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