Academic literature on the topic 'Effusion Cooling Modelling'
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Journal articles on the topic "Effusion Cooling Modelling"
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Mazzei, Lorenzo, Antonio Andreini, and Bruno Facchini. "Assessment of modelling strategies for film cooling." International Journal of Numerical Methods for Heat & Fluid Flow 27, no. 5 (May 2, 2017): 1118–27. http://dx.doi.org/10.1108/hff-03-2016-0086.
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Purpose Effusion cooling represents one the most innovative techniques for the thermal management of aero-engine combustors liners. The huge amount of micro-perforations implies a significant computational cost if cooling holes are included in computational fluid dynamics (CFD) simulations; therefore, many efforts are reported in literature to develop lower-order approaches aiming at limiting the number of mesh elements. This paper aims to report a numerical investigation for validating two approaches for modelling film cooling, distinguished according to the way coolant is injected (i.e. through either point or distributed mass sources). Design/methodology/approach The approaches are validated against experimental data in terms of adiabatic effectiveness and heat transfer coefficient distributions obtained for effusion cooled flat plates. Additional reynolds-averaged naver stokes (RANS) simulations were performed meshing also the perforation, so as to distinguish the contribution of injection modelling with respect to intrinsic limitations of turbulence model modelling. Findings Despite the simplified strategies for coolant injection, this work clearly shows the feasibility of obtaining a sufficiently accurate reproduction of coolant protection in conjunction with a significant saving in terms of computational cost. Practical/implications The proposed methodologies allow to take into account the presence of film cooling in simulations of devices characterized by a huge number of holes. Originality/value This activity represents the first thorough and quantitative comparison between two approaches for film cooling modelling, highlighting the advantages involved in their application.
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Murray, Alexander, Peter Ireland, Tsun Wong, Shaun Tang, and Anton Rawlinson. "High Resolution Experimental and Computational Methods for Modelling Multiple Row Effusion Cooling Performance." International Journal of Turbomachinery, Propulsion and Power 3, no. 1 (January 31, 2018): 4. http://dx.doi.org/10.3390/ijtpp3010004.
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MENDEZ, S., and F. NICOUD. "Large-eddy simulation of a bi-periodic turbulent flow with effusion." Journal of Fluid Mechanics 598 (February 25, 2008): 27–65. http://dx.doi.org/10.1017/s0022112007009664.
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Large-eddy simulations of a generic turbulent flow with discrete effusion are reported. The computational domain is periodic in both streamwise and spanwise directions and contains both the injection and the suction sides. The blowing ratio is close to 1.2 while the Reynolds number in the aperture is of order 2600. The numerical results for this fully developed bi-periodic turbulent flow with effusion are compared to available experimental data from a large-scale spatially evolving isothermal configuration. It is shown that many features are shared by the two flow configurations. The main difference is related to the mean streamwise velocity profile, which is more flat for the bi-periodic situation where the cumulative effect of an infinite number of upstream jets is accounted for. The necessity of considering both sides of the plate is also established by analysing the vortical structure of the flow and some differences with the classical jet-in-crossflow case are highlighted. Finally, the numerical results are analysed in terms of wall modelling for full-coverage film cooling. For the operating point considered, it is demonstrated that the streamwise momentum flux is dominated by non-viscous effects, although the area where only the viscous shear stress contributes is very large given the small porosity value (4%).
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Rogic, Nikola, Giuseppe Bilotta, Gaetana Ganci, James O. Thompson, Annalisa Cappello, Hazel Rymer, Michael S. Ramsey, and Fabrizio Ferrucci. "The Impact of Dynamic Emissivity–Temperature Trends on Spaceborne Data: Applications to the 2001 Mount Etna Eruption." Remote Sensing 14, no. 7 (March 29, 2022): 1641. http://dx.doi.org/10.3390/rs14071641.
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Spaceborne detection and measurements of high-temperature thermal anomalies enable monitoring and forecasts of lava flow propagation. The accuracy of such thermal estimates relies on the knowledge of input parameters, such as emissivity, which notably affects computation of temperature, radiant heat flux, and subsequent analyses (e.g., effusion rate and lava flow distance to run) that rely on the accuracy of observations. To address the deficit of field and laboratory-based emissivity data for inverse and forward modelling, we measured the emissivity of ‘a’a lava samples from the 2001 Mt. Etna eruption, over the wide range of temperatures (773 to 1373 K) and wavelengths (2.17 to 21.0 µm). The results show that emissivity is not only wavelength dependent, but it also increases non-linearly with cooling, revealing considerably lower values than those typically assumed for basalts. This new evidence showed the largest and smallest increase in average emissivity during cooling in the MIR and TIR regions (~30% and ~8% respectively), whereas the shorter wavelengths of the SWIR region showed a moderate increase (~15%). These results applied to spaceborne data confirm that the variable emissivity-derived radiant heat flux is greater than the constant emissivity assumption. For the differences between the radiant heat flux in the case of variable and constant emissivity, we found the median value is 0.06, whereas the 25th and the 75th percentiles are 0.014 and 0.161, respectively. This new evidence has significant impacts on the modelling of lava flow simulations, causing a dissimilarity between the two emissivity approaches of ~16% in the final area and ~7% in the maximum thickness. The multicomponent emissivity input provides means for ‘best practice’ scenario when accurate data required. The novel approach developed here can be used to test an improved version of existing multi-platform, multi-payload volcano monitoring systems.
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M. Dragoni. "Physical modelling of lava flows." Annals of Geophysics 40, no. 5 (October 18, 1997). http://dx.doi.org/10.4401/ag-3856.
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Lava flows are not only a fascinating scientific problem, involving many branches of continuum mechanics and thermodynamics, but are natural events having a strong social impact. A reliable evaluation of volcanic hazard connected with lava flows depends on the availability of physical models allowing us to predict the evolution of these phenomena. In this regard, the rheological properties of lavas are of major importance in controlling the dynamics of lava flows. Lava is a multi-phase and chemically heterogeneous system. This entails a characteristic, non-Newtonian behaviour of lava flows, which is emphasized by the fact that the rheological parameters are strongly temperature dependent and are therefore affected by the progressive cooling of lava after effusion. Physical models of lava flows show us the complex relationships between the many quantities governing this process and in the near future they may allow us to predict the dynamics of lava flows and to take effective measures for the reduction of volcanic risk.
Dissertations / Theses on the topic "Effusion Cooling Modelling"
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Oguntade, Habeeb Idowu. "Modelling of gas turbine film and effusion cooling." Thesis, University of Leeds, 2012. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.581946.
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This thesis presents CFD predictions of gas turbine film and effusion cooling. The dearth of detailed experimental adiabatic effusion cooling data led to the validation of the computational procedures against the experimental adiabatic cooling effectiveness data for a single row of inclined round film cooling holes. This showed that the overall best agreement of the CFD predictions with experimental data was for the realizable k-e turbulence model with enhanced wall function. This was also shown to give good predictions of experimental results for trench outlet film cooling. This film cooling CFD work was extended .to demonstrate trench outlet lip geometries that could further improve the cooling effectiveness. The limitation of the CFD model was at higher blowing rates, M, when the film jet lifted off from the surface, where the CFD did not accurately predict the adiabatic cooling effectiveness close to the hole. For attached jets at lower M the agreement was good. The same CFD procedures were used for all the effusion cooling conjugate heat transfer (CHT) predictions. The hot metal wall effusion cooling experimental data base of Andrews and co-workers (1983-1995) was used to validate the CHT effusion cooling predictions. This database was for combustor flat wall cooling with mainly 90° injection holes. The overall effusion cooling effectiveness was measured and this required conjugate heat transfer CFD predictions. The adiabatic film cooling effectiveness was also predicted, by using a gas tracer in the cooling air and predicting its concentration at the effusion wall. For each effusion hole configuration, the coolant mass flow rate, G kg/srrr2bar, was varied from 0.1 to 1.5 and each G required a separate computation. The influence of the number of holes at a constant X!D of 4.6 and the hole size at fixed X were investigated. The agreement between the predictions and experimental data was good. Finally, the influence of the effusion coolant jets flow direction to the hot-gas crossflow on effusion cooling performance was investigated. This included 30° inclined opposed-flow jets effusion wall, which was predicted to be the best effusion jets flow pattern. The addition of the filleted shape trench outlet to effusion cooling was predicted to improve the cooling performance with reduced coolant mass flow rate, due to the improved adiabatic film cooling.
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Paccati, Simone. "Development of advanced numerical tools for the prediction of wall temperature and heat fluxes for aeroengine combustors." Doctoral thesis, 2021. http://hdl.handle.net/2158/1238641.
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In the thesis, a multiphysics loosely-coupled tool, called U-THERM3D, is assessed as a detailed investigation tool for high-fidelity prediction of combustion and near-wall processes in a LES CHT simulation framework, allowing a deep understanding of heat transfer modes influence with an affordable computational cost. The numerical analysis is carried out on a laboratory-scale combustor representative of a Rich-Quench-Lean concept, emphasizing the effect of radiative and wall heat losses on the highly sooting flame and the improvements in the wall temperature prediction with respect to a steady calculation.
In addition, a novel approach based on the application of 2D boundary sources to simulate the injection of coolant from effusion cooling holes is presented to overcome the issues related to the discretization of the effusion perforation, employing Reduced-Order Model techniques from a Machine Learning framework. For this scope, an in-house external code is combined with the CFD package within the U-THERM3D framework. The numerical tool is firstly validated on simplified geometries in RANS and SBES calculations and then applied on a non-reactive single sector planar rig representative of a real combustor geometry to test the robustness of the proposed strategy in presence of a more complex flow field. Nevertheless, several improvable aspects are highlighted, pointing the way for further enhancements.
Book chapters on the topic "Effusion Cooling Modelling"
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Jansson, L. S., and L. Davidson. "Numerical Study of Effusion Cooling in a Double-Row Discrete-Hole Configuration Using a Low-Re Reynolds Stress Transport Model." In Engineering Turbulence Modelling and Experiments, 731–40. Elsevier, 1996. http://dx.doi.org/10.1016/b978-0-444-82463-9.50076-9.
Full textConference papers on the topic "Effusion Cooling Modelling"
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Crouzy, Gaétan, Fabien Desarnaud, Emmanuel Laroche, and Pierre Millan. "Numerical modelling of a realistic annular effusion cooling system." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-4259.
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van de Noort, Michael, Alexander V. Murray, and Peter T. Ireland. "Low Order Heat & Mass Flow Network Modelling for Quasi-Transpiration Cooling Systems." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-81780.
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Abstract Quasi-transpiration cooling schemes such as Double-Wall Effusion Cooling allow the Nozzle Guide Vanes of High Pressure Turbines in modern aeroengines to experience high heat loads whilst maintaining acceptable temperatures. The combination of impingement, pin-fin and effusion cooling in such schemes produces a high convective cooling efficiency, but this is accompanied by large pressure losses that increase vulnerability to coolant migration toward low pressure regions. This can have severely detrimental effects on cooling performance as effusion holes around the Leading Edge can be starved of coolant, producing no local film cooling protection. This paper presents a Low Order Model (LOM) which rapidly produces pressure, temperature, mass and heat flow distributions throughout Double-Wall Effusion Cooling Schemes, developed from a previously presented Mass Flow Network LOM. These can be found for a variety of flow and geometric conditions, allowing fast analysis of cooling designs. Experiments were conducted using a steady-state facility, from which results were used to validate the new LOM to a satisfactory standard. Using specifically derived dimensionless groups for coolant migration, results from the LOM demonstrate the effect of heat transfer on it as well as the effects of coolant migration on the cooling performance, highlighting design guidelines to reduce such effects and to optimise the component life.
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Liu, Xiaoheng, Donghai Jin, and Xingmin Gui. "Throughflow Method for a Combustion Chamber With Effusion Cooling Modelling." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76195.
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The most progressive liner cooling technology for modern combustion chambers is represented by effusion cooling (or full-coverage film cooling), which is based on the use of several inclined small diameter cylindrical holes. However, as to simulation of the gas turbine combustion chamber, meshing of these discrete holes needs too much computer resource and demanding calculation time. The homogeneous boundary condition was attempted to apply in the throughflow method for the simulation of the full-scale combustion chamber. The verification of this uniform condition was performed through the model of two straight channels. Obtained results were compared with detailed LES simulations, highlighting well accordance and accurate flow structure around the plate. Furthermore, the modelling was used in the simulation of a loop combustion chamber with throughflow method on isothermal state. Performance characteristic and flow fields from this method were then contrasted with the details from the FLUENT simulation upon high geometric fidelity, and prove that the homogeneous boundary condition exerts a good prediction of the performance characteristics and flow field in the combustion chamber.
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Oguntade, Habeeb Idowu, Gordon E. Andrews, Alan Burns, Derek Ingham, and Mohammed Pourkashanian. "Predictions of Effusion Cooling With Conjugate Heat Transfer." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45417.
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This work involves CFD conjugate heat transfer modelling of the geometrical design influence on effusion cooling. Experimental data was modelled for the overall effusion film cooling effectiveness using Nimonic 75 walls with imbedded thermocouples. The Fluent CFD code was used to investigate the experimental configuration for a 10×10 square array of holes with a 90° injection angle. In the computational predictions, 10000ppm of methane tracer gas was added to the coolant and the concentration at the wall allowed the adiabatic cooling effectiveness of the effusion film cooling to be predicted separately from the overall wall cooling effectiveness. The predicted overall cooling effectiveness results show that the wall was locally at a uniform temperature, but the axial development of the cooling film does result in a gradual reduction of the wall temperature with axial distance. The predictions show that the heating of the coolant by the hot wall was equally split between the hole approach flow on the backside of the wall and inside the film cooling holes. This heating changed the conditions in the film cooling layer from those of the equivalent adiabatic wall. There was good agreement between the conjugate heat transfer predictions of the overall cooling effectiveness with the experimental data.
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Ammour, Dalila, and Gary J. Page. "Modelling Impingement-Effusion Flow Inside Double-Walled Combustor Tile." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64913.
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The prediction of temperature and heat transfer throughout the solid material of a gas-turbine combustor has driven interest in cooling technology which uses impingement/effusion (IE) cooling tiles on double-skinned combustor liners. The design of the IE tile system is simple but the aerodynamics are complex. The complexity of flow curvature, combined impingement and effusion cooling and heat transfer, poses a challenge to standard RANS CFD modelling. The IE combustor tile is numerically investigated using both URANS model with the SST-SAS model and Large Eddy Simulation (LES) in the Rolls-Royce in-house CFD code. The aim is to provide accurate CFD data and to test the viability of URANS approach to predict the impingement/effusion flow. Results of pressure, velocity and turbulence quantities are presented. It is found that the SST-SAS model, with high grid resolution, shows good agreement with LES. The current CFD results are used to resolve a substantial amount of very small impingement and effusion holes. The CFD results showed that every feature of the geometry has to be resolved by the numerical mesh, which makes the simulation impractical due to time consuming and high mesh resolution. These cooling holes can be omitted from the computational mesh and their effects captured on the flow via an impingement-effusion (IE) model which is based on defining the correct mass flow inside the holes as a function of the difference of pressure in the upstream and downstream regions of both impingement and effusion regions. The latter model takes the effect of pressure and velocity and it will be extended in future to take into account the heat transfer effects. The IE model is tested and validated for the 3-D combusor tile and results of pressure showed good agreement with the LES data.
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Paccati, S., L. Mazzei, A. Andreini, and B. Facchini. "Reduced-Order Models for Effusion Modelling in Gas Turbine Combustors." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59384.
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Abstract Effusion cooling represents the state-of-the-art for liner cooling technology in modern combustion chambers, combining a more uniform film protection of the wall and a significant heat sink effect by forced convection through a huge number of small holes. From a numerical point of view, a high computational cost is required in a conjugate CFD analysis of an entire combustor for a proper discretization of effusion holes in order to obtain accurate results in terms of liner temperature and effectiveness distributions. Consequently, simplified CFD approaches to model the various phenomena associated are required, especially during the design process. For this purpose, 2D boundary sources models are attractive, replacing the effusion hole with an inlet (hot side) and an outlet (cold side) patches to consider the related coolant injection. However, proper velocity profiles at the inlet patch together with the correct mass flow rate is mandatory to accurately predict the interaction and the mixing between coolant air and hot gases as well as temperature and effectiveness distributions on the liners. In this sense, reduced-order models techniques from the Machine Learning framework can be employed to derive a Surrogate Model (SM) for the prediction of these velocity profiles with a reduced computational cost, starting from a limited number of CFD simulations of a single effusion hole at different operating conditions. In this work, an application of these approaches will be presented to model the effusion system of a non-reactive single-sector linear combustor simulator equipped with a swirler and a multi-perforated plate, combining ANSYS Fluent with a MATLAB code. The employed Surrogate Model has been constructed on a training set of CFD simulations of the single effusion hole with operating conditions sampled in the model parameter space and subsequently assessed on a different validation set.
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Murray, Alexander Vesale, Peter Thomas Ireland, Tsun Holt Wong, Shaun Wei Tang, and Anthony John Rawlinson. "High Resolution Experimental and Computational Methods for Modelling Multiple Row Effusion Cooling Performance." In European Conference on Turbomachinery Fluid Dynamics and hermodynamics. European Turbomachinery Society, 2017. http://dx.doi.org/10.29008/etc2017-130.
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Bohn, Dieter, and Robert Krewinkel. "Conjugate Simulation of the Effects of Oxide Formation in Effusion Cooling Holes on Cooling Effectiveness." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59081.
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Within Collaborative Research Center 561 “Thermally Highly Loaded, Porous and Cooled Multi-Layer Systems for Combined Cycle Power Plants” at RWTH Aachen University an effusion-cooled multi-layer plate configuration with seven staggered effusion cooling holes is investigated numerically by application of a 3-D in-house fluid flow and heat transfer solver, CHTflow. The effusion-cooling is realized by finest drilled holes with a diameter of 0.2 mm that are shaped in the region of the thermal barrier coating. Oxidation studies within SFB 561 have shown that a corrosion layer of several oxides with a thickness of appoximately 20μm grows from the CMSX-4 substrate into the cooling hole. The goal of this work is to investigate the effect this has on the cooling effectiveness, which has to be quantified prior to application of this novel cooling technology in real gas turbines. In order to do this, the influence on the aerodynamics of the flow in the hole, on the hot gas flow and the cooling effectiveness on the surface and in the substrate layer are discussed. The adverse effects of corrosion on the mechanical strength are not a part of this study. A hot gas Mach-number of 0.25 and blowing ratios of approximately 0.28 and 0.48 are considered. The numerical grid contains the coolant supply (plenum), the solid body for the conjugate calculations and the main flow area on the plate. It is shown that the oxidation layer does significantly affect the flow field in the cooling holes and on the plate, but the cooling effectiveness differs only slightly from the reference case. This seems to justify modelling the holes without taking account of the oxidation.
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Mazzei, L., A. Picchi, A. Andreini, B. Facchini, and I. Vitale. "Unsteady CFD Investigation of Effusion Cooling Process in a Lean Burn Aero-Engine Combustor." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56603.
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The use of lean burning flames stabilized by highly swirling flows represents the most effective technology to limit NOx emissions in modern aeroengine combustors. In these devices up to 70% of compressed air is admitted in the combustor through the injection system, which is usually designed to give strong swirling components to air flow. Complex fluidynamics is observed with large flow recirculations due to vortex breakdown and precessing vortex core, that may result in a not trivial interaction with liner cooling flows close to combustor walls. This interaction and its effects on the local cooling performance make the design of the cooling systems very challenging and time-consuming, considering design and commission of new test rigs for detailed analysis. Keeping in mind costs and complexities related to the investigation of swirl flow/wall cooling interaction by experimental approach, CFD can be considered an accurate and reliable alternative to understand the associated phenomena. The widely known overcomes of RANS formulation (e.g. underestimation of mixing and inability to properly describe swirling flows) and the more and more impressive increase in computational resources, pushed hybrid RANS-LES models as valuable and affordable approaches to accurately solve the main turbulent flow structures. This work describes the main findings of a CFD analysis intended to accurately investigate the flow field and wall heat transfer as a result of the mutual interaction between a highly swirling flow generated by a lean burn nozzle and a slot-effusion liner cooling system. In order to overcome some limitations of RANS approach, the simulations were performed with SST-SAS, a hybrid RANS-LES model. Moreover, the significant computational effort due to the presence of more than 600 effusion holes was limited exploiting two different modelling strategies: a homogeneous model based on the application of uniform boundary conditions on both aspiration and injection sides, and another solution that provides a coolant injection through point mass sources within a single cell. CFD findings were compared to experimental results coming from an investigation carried out on a three sector linear rig. The comparison pointed out that advanced modelling strategies, i.e. based on discrete mass sources, are able to reproduce the effects of mainstream-coolant interactions on convective heat loads. Validated the approach through a benchmark against time-averaged quantities, the transient data acquired were examined in order to better understand the unsteady behaviour of the thermal load through a statistical analysis, providing useful information with a design perspective.
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Mazzei, L., A. Andreini, B. Facchini, and L. Bellocci. "A 3D Coupled Approach for the Thermal Design of Aero-Engine Combustor Liners." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56605.
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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.