Conjugate Heat Transfer Simulation of a Radially Cooled Gas Turbine Vane

Facchini, Bruno; Magi, Andrea; Av, Greco

doi:10.1115/gt2004-54213

Cited by 42 publications

(16 citation statements)

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“…Because no transition model was used, the simulated external HTC (EHTC) at the leading edge stagnation point and laminar region had low precision. Facchini [8] made another 3D conjugate heat transfer simulation of C3X, however there was an obvious difference of HTC between simulation results and experimental data. Sheng [9] researched 3D conjugate flow and heat transfer www.intechopen.com method of turbine.…”

Section: Introductionmentioning

confidence: 99%

Conjugate Flow and Heat Transfer of Turbine Cascades

Zeng¹,

Xiong-jie²

2011

Heat Transfer - Theoretical Analysis, Experimental Investigations and Industrial Systems

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Section: Introductionmentioning

confidence: 99%

Conjugate Flow and Heat Transfer of Turbine Cascades

Zeng¹,

Xiong-jie²

2011

Heat Transfer - Theoretical Analysis, Experimental Investigations and Industrial Systems

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“…In Figure 5 Blade LE and blade tail solids employ temperature dependent proprieties (following [104]). Concerning the thermal barrier solid, a low constant thermal conductivity value (0.03 W m…”

Section: Full 3d Cht Analysismentioning

confidence: 99%

Film Cooling Modelling for Gas Turbine Nozzles and Blades: Validation and Application

Andrei

Innocenti

Andreini

et al. 2015

Volume 5B: Heat Transfer

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The use of Computational Fluid Dynamics (CFD) for modern turbine blade design requires the accurate representation of the effect of film cooling. However, including complete cooling hole discretization in the computational domain requires a substantial meshing effort and leads to a drastic increase in the computing time. For this reason, many efforts have been made to develop lower order approaches aiming at reducing the number of mesh elements and therefore computational resources. The simplest approach models the set of holes as a uniform coolant injection, but it does not allow an accurate assessment of the interaction between hot gas and coolant. Therefore higher order models have been developed, such as those based on localized mass sources in the region of hole discharge. It is here proposed an innovative injection film cooling model (FCM), embedded in a CFD code, to represent the effect of cooling holes by adding local source terms at the hole exit in a delimited portion of the domain, avoiding the meshing process of perforations. The goal is to provide a reliable and accurate tool to simulate film-cooled turbine blades and nozzles without having to explicitly mesh the holes. The validation campaign of the proposed model is composed of two phases. During the first one, results obtained with the film cooling model are compared to experimental data and to numerical results obtained with the full meshing of the cooling holes on a series of test cases, ranging from single row to multi row flat plate, at varying coolant conditions (in terms of blowing and density ratio). Though details of the flow structure downstream of the holes cannot be perfectly captured, this method allows an accurate prediction of the overall flow and performance modifications induced by the presence of the cooling holes, with a strong agreement to complete hole discretization results. In the second phase, a complete film-cooled vane test case has been studied, in order to consider a real injection system and flow conditions. In this case, film cooling model predictions are compared to an in-house developed correlative approach and full CHT 3D-CFD results. Finally, a comparison between film cooling model predictions and experimental data was performed on an actual nozzle of a GE Oil & Gas heavy-duty gas turbine as well, in order to prove the feasibility of the procedure. The presented film cooling model proved to be a feasible and reliable tool to evaluate adiabatic effectiveness, simplifying the design phase avoiding the meshing process of perforations. Also, refining the mesh near the hole exit, FCM results well approximate the solution coming from a full CHT calculation.

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“…The RANS CFD tools have been providing a reasonable degree of accuracy for prediction of the thermal and blade loading in turbine blade rows. With a conjugate heat transfer (CHT) methodology, the RANS CFD tools are routinely used in aero and thermal design processes [3,4]. These trends have been accelerating with recent advance in computational performance.…”

Section: Introductionmentioning

confidence: 99%

Effects of Inlet Turbulence Conditions and Near-wall Treatment Methods on Heat Transfer Prediction over Gas Turbine Vanes

Bak¹,

Lee²,

Kang³

2016

International Journal of Aeronautical and Space Sciences

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This paper investigates the effects of inlet turbulence conditions and near-wall treatment methods on the heat transfer prediction of gas turbine vanes within the range of engine relevant turbulence conditions. The two near-wall treatment methods, the wall-function and low-Reynolds number method, were combined with the SST and ωRSM turbulence model. Additionally, the RNG k-ε, SSG RSM, and SST+γ-Reθ transition model were adopted for the purpose of comparison. All computations were conducted using a commercial CFD code, CFX, considering a three-dimensional, steady, compressible flow. The conjugate heat transfer method was applied to all simulation cases with internally cooled NASA turbine vanes. The CFD results at mid-span were compared with the measured data under different inlet turbulence conditions. In the SST solutions, on the pressure side, both the wall-function and low-Reynolds number method exhibited a reasonable agreement with the measured data. On the suction side, however, both wall-function and low-Reynolds number method failed to predict the variations of heat transfer coefficient and temperature caused by boundary layer flow transition. In the ωRSM results, the wall-function showed reasonable predictions for both the heat transfer coefficient and temperature variations including flow transition onset on suction side, but, low-Reynolds methods did not properly capture the variation of the heat transfer coefficient. The SST+γ-Reθ transition model showed variation of the heat transfer coefficient on the transition regions, but did not capture the proper transition onset location, and was found to be much more sensitive to the inlet turbulence length scale. Overall, the Reynolds stress model and wall function configuration showed the reasonable predictions in presented cases. showed the reasonable predictions in presented cases.

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Conjugate Heat Transfer Simulation of a Radially Cooled Gas Turbine Vane

Cited by 42 publications

References 0 publications

Conjugate Flow and Heat Transfer of Turbine Cascades

Conjugate Flow and Heat Transfer of Turbine Cascades

Film Cooling Modelling for Gas Turbine Nozzles and Blades: Validation and Application

Effects of Inlet Turbulence Conditions and Near-wall Treatment Methods on Heat Transfer Prediction over Gas Turbine Vanes

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