Experimental and numerical study of the anti-crossflows impingement cooling structure

Chi, Zhongran; Kan, Rui; Ren, Jing; Jiang, Hongde

doi:10.1016/j.ijheatmasstransfer.2013.04.052

Cited by 74 publications

(7 citation statements)

References 19 publications

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“…First, the numerical results of impingement cooling structures were compared with experimental data acquired by transient liquid crystal measurements as presented in [22] (at room pressure and temperature). The hole diameter D, streamwise interval of jets P x , spanwise interval of jets P y , impingement distance H, and averaged Reynolds number Re of they jets were changed in different cases, as shown in Fig.…”

Section: A Experimental Validation Of Numerical Modelmentioning

confidence: 99%

“…The airfoil and the prototype cooling Fig. 10 Experimental validation of impingement cooling simulation using SST model [22]. structure of the vane are almost the same as those of General Electric Company's energy-efficient engine first-stage vane, except for a redesigned internal cooling structure at the trailing edge (TE), as shown in Fig.…”

Section: B Prototype Geometry Of the Hpt First-stage Vanementioning

confidence: 99%

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Semi-Inverse Design Optimization Method for Film-Cooling Arrangement of High-Pressure Turbine Vanes

Chi

Liu

Zang

2016

Journal of Propulsion and Power

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A semi-inverse design optimization method for the film-cooling arrangement of high-pressure turbine first-stage vanes is initiated based on a combinatorial optimization algorithm, a one-dimensional heat conduction model, and computational fluid dynamics methods, in which inlet temperature distortion, radiation, and inlet swirl are all considered simultaneously. This semi-inverse design optimization method can optimize the total coolant amount of the film-cooling structure while ensuring an acceptable metal temperature distribution, which finally provides a scattered and nonuniform arrangement of the film-cooling holes and a minimal coolant amount. The optimization methodology is tested on the General Electric energy-efficient engine first-stage vane under a high thermal load, and the optimization result is verified by the conjugate heat transfer computational fluid dynamics simulations. As for the optimized cooling structure, a significant improvement of cooling performance is observed while the total coolant amount is slightly reduced compared with the prototype. It is also found that neglecting each of the three factors (inlet temperature distortion, radiation, and inlet swirl) could result in a significantly different film-cooling arrangement while maintaining the overall cooling performance, which highlights the capability of the semi-inverse design optimization method at various design conditions. Nomenclature A = area of outer surface BR = blowing ratio c p = specific heat at constant pressure DR = density ratio d = thickness h = convective heat transfer coefficient k = turbulence kinetic energy/number of sample points on pressure side and suction side M = total coolant mass flow m = mass flow N = population size (of genetic algorithm) n = number of candidate holes p = pressure p = total pressure q = wall heat flux T = temperature T = total temperature Tu = turbulence intensity x = bit of the design variable α = swirl angle η = film-cooling effectiveness λ = heat conductivity ω = turbulent specific dissipation rate/rotation speed Subscripts ave = area-averaged C = child (of genetic algorithm) c = coolant/with cooling/coolant side c1 = coolant inlet 1 c2 = coolant inlet 2 f = film cooling g = hot gas in cascade passage/gas side i = vane cascade inlet max = maximum value o = rotor cascade outlet P = parent (of genetic algorithm) rad = radiative w = wall (metal beneath thermal barrier coating layer)

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Section: A Experimental Validation Of Numerical Modelmentioning

confidence: 99%

Section: B Prototype Geometry Of the Hpt First-stage Vanementioning

confidence: 99%

Semi-Inverse Design Optimization Method for Film-Cooling Arrangement of High-Pressure Turbine Vanes

Chi

Liu

Zang

2016

Journal of Propulsion and Power

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“…Blade cooling technology mainly includes internal cooling and film cooling [3]. In internal cooling, various heat transfer augmentation methods, including jet impingement [4], U shaped turning bend [5], and rough structures [6] are usually applied, and recently the closed cycle-based steam cooling technology [7] has been developed, greatly promoting the improvement of cooling performance. Han [8] of Texas the local flow structures and enhanced heat transfer by 40%.…”

Section: Introductionmentioning

confidence: 99%

Effects of Channel Outlet Configuration and Dimple/Protrusion Arrangement on the Blade Trailing Edge Cooling Performance

2019

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The trailing edge regions of high-temperature gas turbine blades are subjected to extremely high thermal loads and are affected by the external wake flow during operation, thus creating great challenges in internal cooling design. With the development of cooling technology, the dimple and protrusion have attracted wide attention for its excellent performance in heat transfer enhancement and flow resistance reduction. Based on the typical internal cooling structure of the turbine blade trailing edge, trapezoidal cooling channels with lateral extraction slots are modeled in this paper. Five channel outlet configurations, i.e., no second passage (OC1), radially inward flow second passage (OC2), radially outward flow second passage (OC3), top region outflow (OC4), both sides extractions (OC5), and three dimple/protrusion arrangements (all dimple, all protrusion, dimple–protrusion staggered arrangement) are considered. Numerical investigations are carried out, within the Re range of 10,000–100,000, to analyze the flow structures, heat transfer distributions, average heat transfer and friction characteristics and overall thermal performances in detail. The results show that the OC4 and OC5 cases have high heat transfer levels in general, while the heat transfer deterioration occurs in the OC1, OC2, and OC3 cases. For different dimple/protrusion arrangements, the protrusion case produces the best overall thermal performance. In conclusion, for the design of trailing edge cooling structures with lateral slots, the outlet configurations of top region outflow and both sides extractions, and the all protrusion arrangement, are recommended.

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“…This type of porous media approach has been used in several other fields including the modelling of catalytic converters, heat exchangers, concrete flow and fuel injectors (see [6 -12]). There have also been multiple studies on impingement flows such as flow through perforated plates [13], flow through impingement cooling holes employed as film cooling in turbine blades [14][15][16], combustor liners [17][18] and TCC systems [4,19].…”

Section: Introductionmentioning

confidence: 99%

Improved Modeling Capabilities of the Airflow Within Turbine Case Cooling Systems Using Smart Porous Media

Walker

Irving

2018

Journal of Engineering for Gas Turbines and Power

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Impingement cooling is commonly employed in gas turbines to control the turbine tip clearance. During the design phase, computational fluid dynamics (CFD) is an effective way of evaluating such systems but for most turbine case cooling (TCC) systems resolving the small scale and large number of cooling holes is impractical at the preliminary design phase. This paper presents an alternative approach for predicting aerodynamic performance of TCC systems using a “smart” porous media (PM) to replace regions of cooling holes. Numerically CFD defined correlations have been developed, which account for geometry and local flow field, to define the PM loss coefficient. These are coded as a user-defined function allowing the loss to vary, within the calculation, as a function of the predicted flow and hence produce a spatial variation of mass flow matching that of the cooling holes. The methodology has been tested on various geometrical configurations representative of current TCC systems and compared to full cooling hole models. The method was shown to achieve good overall agreement while significantly reducing both the mesh count and the computational time to a practical level.

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Experimental and numerical study of the anti-crossflows impingement cooling structure

Cited by 74 publications

References 19 publications

Semi-Inverse Design Optimization Method for Film-Cooling Arrangement of High-Pressure Turbine Vanes

Semi-Inverse Design Optimization Method for Film-Cooling Arrangement of High-Pressure Turbine Vanes

Effects of Channel Outlet Configuration and Dimple/Protrusion Arrangement on the Blade Trailing Edge Cooling Performance

Improved Modeling Capabilities of the Airflow Within Turbine Case Cooling Systems Using Smart Porous Media

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