Film Cooling System Numerical Design: Adiabatic and Conjugate Analysis

Andreini, Antonio; Carcasci, Carlo; Gori, Stefano; Surace, Marco

doi:10.1115/ht2005-72042

Cited by 8 publications

(4 citation statements)

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“…They predicted that film effectiveness obtained from the conjugate model is in better agreement with the experimental data compared to the adiabatic model. Andreini et al [12] carried out several calculations to infer the trends of adiabatic and conjugate heat transfer performance in terms of heat transfer coefficient, overall and adiabatic effectiveness. They concluded that the reduction of metal temperature upstream of each cooling hole increased as the blowing rate grew.…”

Section: Introductionmentioning

confidence: 99%

Computational Analysis of Conjugate Heat Transfer and Particulate Deposition on a High Pressure Turbine Vane

Fletcher

2011

Journal of Turbomachinery

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Numerical computations were conducted to simulate flash deposition experiments on gas turbine disk samples with internal impingement and film cooling using a computational fluid dynamics (CFD) code (FLUENT). The standard k-ω turbulence model and Reynolds-averaged Navier–Stokes were employed to compute the flow field and heat transfer. The boundary conditions were specified to be in agreement with the conditions measured in experiments performed in the BYU turbine accelerated deposition facility (TADF). A Lagrangian particle method was utilized to predict the ash particulate deposition. User-defined subroutines were linked with FLUENT to build the deposition model. The model includes particle sticking/rebounding and particle detachment, which are applied to the interaction of particles with the impinged wall surface to describe the particle behavior. Conjugate heat transfer calculations were performed to determine the temperature distribution and heat transfer coefficient in the region close to the film cooling hole and in the regions further downstream of a row of film cooling holes. Computational and experimental results were compared to understand the effect of film hole spacing, hole size, and TBC on surface heat transfer. Calculated capture efficiencies compare well with experimental results.

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Section: Introductionmentioning

confidence: 99%

Computational Analysis of Conjugate Heat Transfer and Particulate Deposition on a High Pressure Turbine Vane

Fletcher

2011

Journal of Turbomachinery

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“…a given number of rows). A this purpose Andreini et al [133] propose to specify the effectiveness superposition length for each row of cooling holes.…”

Section: Gas Side Convectionmentioning

confidence: 99%

A 3D Coupled Approach for the Thermal Design of Aero-Engine Combustor Liners

Mazzei

Andreini

Facchini

et al. 2016

Volume 5B: Heat Transfer

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The adoption of lean burn combustion to limit NOx emissions of modern aero-engines imposes a drastic reduction of air dedicated to cooling combustor dome and liners. In the latest years many aero-engine manufacturers are hence implementing effusion cooling, which provides uniform protection on the hot side of the liner and significant heat removal within the perforation. With an industrial perspective, the development of such components is usually carried out with different strategies depending on the level of accuracy required in the design phase involved (i.e preliminary or detailed). In the collaboration between GE Avio and University of Florence, the preliminary design of these devices is carried out with Therm1D, an in-house thermal flow-network solver based on the 1D correlative approach proposed by Lefebvre. This strategy, however, is not capable of taking into account the complexity of the three-dimensional nature of the flow field and the interaction between swirling flow and liner cooling, making necessary the use of Computational Fluid Dynamics (CFD) in the most advanced phases of the design process. Nevertheless, notwithstanding the increasing popularity of CFD, even a RANS simulation of a single sector of an annular combustor still presents a challenge, when the cooling system is taken into account. This issue becomes more critical in case of modern effusion cooled combustors, which may contain thousands of holes for each sector. With the aim of of increasing the fidelity of the prediction, keeping in mind the industrial needs for limited computational efforts, a new tool has been developed: Therm3D. This approach involves the CFD simulation of the combustor flametube by modelling effusion cooling with point mass sources, whereas the fluid dynamic prediction of the remaining part is fulfilled exploiting the equivalent flow-network solver implemented in Therm1D, which provides the estimation of flow split and cold side heat loads. The solution is coupled with two separate calculations aimed at solving flame radiation and heat conduction within the metal. This paper describes the main findings of the application of Therm3D to a lean annular combustor. The results obtained have been compared to experimental data and the above mentioned numerical tools employed during the design process.

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“…This class of model is the most sophisticated turbulence model available in the Reynolds Averaged Navier Stokes (RANS) strategy and is used in the present work. Andreini et al [11] and Plesniak [12] predicted film cooling using k−ε, k ω, and the Reynolds Stress Turbulence Model (RSM). They reported that the RSM model did not result in a significant improvement over the eddy viscosity model, which agrees with the findings of Walters and Leylek [13] and Azzi and Lakehal [10].…”

Section: Introductionmentioning

confidence: 99%

Reynolds Stress Transport Modeling of Film Cooling at the Leading Edge of a Symmetrical Turbine Blade Model

Nemdili

Azzi

Theodoridis

et al. 2008

Heat Transfer Engineering

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This paper investigates the performance of the SSG (Speziale, Sarkar, and Gatski) Reynolds Stress Model for the prediction of film cooling at the leading edge of a symmetrical turbine blade model using the CFX 5.7.1 package from ANSYS, Inc. Using a finite-volume method, the performance of the selected turbulence model is compared to that of the standard k−ε model. The test case blade model is symmetric and has one injection row of discrete cylindrical holes on each side near the leading edge. Numerical simulations are conducted for three different blowing ratios; film cooling effectiveness contours on the blade surface and lateral averaged adiabatic film cooling effectiveness are presented and compared with available measurements. The computations with the standard k−ε model reproduce the well-known underpredicted lateral spreading of the jet, and, consequently, lower values of the lateral averaged adiabatic film cooling effectiveness has been obtained. On the other hand, the second order Reynolds Stress Model yields reasonably good agreement with measurement data. In addition to validation data, several longitudinal and transversal contours and vector planes are reproduced and clearly underscore the anisotropic turbulent field occurring in the present shower head film cooling configuration.

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Film Cooling System Numerical Design: Adiabatic and Conjugate Analysis

Cited by 8 publications

References 0 publications

Computational Analysis of Conjugate Heat Transfer and Particulate Deposition on a High Pressure Turbine Vane

Computational Analysis of Conjugate Heat Transfer and Particulate Deposition on a High Pressure Turbine Vane

A 3D Coupled Approach for the Thermal Design of Aero-Engine Combustor Liners

Reynolds Stress Transport Modeling of Film Cooling at the Leading Edge of a Symmetrical Turbine Blade Model

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