Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane

Du, Haifen; Mei, Ziyue; Zou, Jiayao; Jiang, Wenxue; Xie, Danmei

doi:10.3390/e21101007

Cited by 11 publications

(6 citation statements)

References 35 publications

(30 reference statements)

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“…In the previous analyses on the injection/main flow analyses, the global variables, for example of the pressure loss coefficient [ 19 , 35 ], the entropy production [ 36 ] and the adiabatic cooling effectiveness [ 37 ], are selected to quantify the aerodynamic efficiency and the cooling performance. However, they reflect the historic effect inside the passage and, thus lack the ability to provide more information about where the loss occurs [ 38 ] in the turbine passage.…”

Section: Entropy Generation Rate Based Loss Analysis Methodsmentioning

confidence: 99%

Interaction Mechanism and Loss Analysis of Mixing between Film Cooling Jet and Passage Vortex

Mao

Chen

et al. 2021

Entropy

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The interaction between the film-cooling jet and vortex structures in the turbine passage plays an important role in the endwall cooling design. In this study, a simplified topology of a blunt body with a half-cylinder is introduced to simulate the formation of the leading-edge horseshoe vortex, where similarity compared with that in the turbine cascade is satisfied. The shaped cooling hole is located in the passage. With this specially designed model, the interaction mechanism between the cooling jet and the passage vortex can therefore be separated from the crossflow and the pressure gradient, which also affect the cooling jet. The loss-analysis method based on the entropy generation rate is introduced, which locates where losses of the cooling capacity occur and reveals the underlying mechanism during the mixing process. Results show that the cooling performance is sensitive to the hole location. The injection/passage vortex interaction can help enhance the coolant lateral coverage, thus improving the cooling performance when the hole is located at the downwash region. The coolant is able to conserve its structure in that, during the interaction process, the kidney vortex with the positive rotating direction can survive with the negative-rotating passage vortex, and the mixture is suppressed. However, the larger-scale passage vortex eats the negative leg of the kidney vortices when the cooling hole is at the upwash region. As a result, the coolant is fully entrained into the main flow. Changes in the blowing ratio alter the overall cooling effectiveness but have a negligible effect on the interaction mechanism. The optimum blowing ratio increases when the hole is located at the downwash region.

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Section: Entropy Generation Rate Based Loss Analysis Methodsmentioning

confidence: 99%

Interaction Mechanism and Loss Analysis of Mixing between Film Cooling Jet and Passage Vortex

Mao

Chen

et al. 2021

Entropy

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“…The turbulent kinetic energy is determined by solving a semi empirical transport equation [7]. In a standard turbulence model, the length scale is assumed to be the length scale of kinetic energy dissipation:…”

Section: Heat Conduction Of Marine Gas Turbine Lubricating Oilmentioning

confidence: 99%

Real time numerical simulation of thermal conductivity of marine gas turbine lubricating oil under complex sea conditions

Wang

et al. 2021

THERM SCI

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Due to the influence of the marine environment, marine gas turbine lubricants are required to have good thermal conductivity. However, the current research on marine gas turbine lubricants mainly focuses on its corrosion resistance. Therefore, a real-time numerical simulation of thermal conductivity of marine gas turbine lubricating oil under complex sea conditions is proposed. In this paper, the turbulent kinetic energy equation and the loss transport equation are obtained by introducing the turbulent column and the k-e model. The Nusselt number in the k-e model can be regarded as the ratio of convective heat transfer between fluid and solid wall and internal heat transfer of fluid. According to the equations, the transient heat transfer model of vertical moving contact parts is established, and the heat transfer relationship between lubricating oil and plug group is obtained. The experimental results show that the area of low temperature in this scheme is larger than that in the traditional scheme, which means that the efficiency of impingement cooling is improved after the introduction of the pin structure in the impingement cooling design. The heat transfer process on the suction surface is stronger than that on the pressure surface, and the heat transfer coefficient of the blade increases continuously, reaching the local maximum value at about X/L = 0.65.

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“…The adiabatic film effectiveness (η ad ) was experimentally characterized in a previous campaign [2]. As demonstrated by previous works [3][4][5], the CFD analysis is a must-have tool for the design and the optimization phases of film cooled vanes and blades. However, CFD simulations are generally restricted to the situation where a set of constant input parameters are imposed, and a deterministic result is provided.…”

mentioning

confidence: 94%

Uncertainty Quantification of Film Cooling Performance of an Industrial Gas Turbine Vane

Gamannossi

Amerini

Mazzei

et al. 2019

Entropy

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Computational Fluid Dynamics (CFD) results are often presented in a deterministic way despite the uncertainties related to boundary conditions, numerical modelling, and discretization error. Uncertainty quantification is the field studying how these phenomena affect the numerical result. With these methods, the results obtained are directly comparable with the experimental ones, for which the uncertainty related to the measurement is always shown. This work presents an uncertainty quantification approach applied to CFD: the test case consists of an industrial prismatic gas turbine vane with standard film cooling shaped holes system on the suction side only. The vane was subject of a previous experimental test campaign which had the objective to evaluate the film cooling effectiveness through pressure-sensitive paint technique. CFD analyses are conducted coherently with the experiments: the analogy between heat and mass transfer is adopted to draw out the adiabatic film effectiveness, solving an additional transport equation to track the concentration of CO2 used as a coolant fluid. Both steady and unsteady simulations are carried out: the first one using a RANS approach with k-ω SST turbulence model the latter using a hybrid LES-RANS approach. Regarding uncertainty quantification, three geometrical input parameters are chosen: the hole dimension, the streamwise inclination angle of the holes, and the inlet fillet radius of the holes. Polynomial-chaos approach in conjunction with the probabilistic collocation method is used for the analysis: a first-order polynomial approximation was adopted which required eight evaluations only. RANS approach is used for the uncertainty quantification analysis in order to reduce the computational cost. Results show the confidence interval for the analysis as well as the probabilistic output. Moreover, a sensitivity analysis through Sobol’s indices was carried out which prove how these input parameters contribute to the film cooling effectiveness, in particular, when dealing with the additive manufacturing process.

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Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane

Cited by 11 publications

References 35 publications

Interaction Mechanism and Loss Analysis of Mixing between Film Cooling Jet and Passage Vortex

Interaction Mechanism and Loss Analysis of Mixing between Film Cooling Jet and Passage Vortex

Real time numerical simulation of thermal conductivity of marine gas turbine lubricating oil under complex sea conditions

Uncertainty Quantification of Film Cooling Performance of an Industrial Gas Turbine Vane

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