Publications
138 results found
Carnevale M, Montomoli F, D'Ammaro A, et al., 2012, UNCERTAINTY QUANTIFICATION: A STOCHASTIC METHOD FOR HEAT TRANSFER PREDICTION USING LES, ASME Turbo Expo 2012, Publisher: AMER SOC MECHANICAL ENGINEERS, Pages: 59-+
Montomoli F, Eastwood S, 2011, Implementation of synthetic turbulence inlet for turbomachinery LES, COMPUTERS & FLUIDS, Vol: 46, Pages: 369-374, ISSN: 0045-7930
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- Citations: 2
Salvadori S, Montomoli F, Martelli F, et al., 2011, Aerothermal Study of the Unsteady Flow Field in a Transonic Gas Turbine With Inlet Temperature Distortions, JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, Vol: 133, ISSN: 0889-504X
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- Citations: 29
Montomoli F, Massini M, Salvadori S, 2011, Geometrical uncertainty in turbomachinery: Tip gap and fillet radius, COMPUTERS & FLUIDS, Vol: 46, Pages: 362-368, ISSN: 0045-7930
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- Citations: 48
Montomoli F, Hodson HP, Lapworth L, 2011, RANS-URANS in axial compressor, a design methodology, PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART A-JOURNAL OF POWER AND ENERGY, Vol: 225, Pages: 363-374, ISSN: 0957-6509
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- Citations: 9
Montomoli F, Massini M, Adami P, et al., 2010, Effect of incidence angle with wake passing on a film cooled leading edge: A numerical study, INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN FLUIDS, Vol: 63, Pages: 1359-1374, ISSN: 0271-2091
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- Citations: 8
Montomoli F, Hodson H, Haselbach F, 2010, Effect of Roughness and Unsteadiness on the Performance of a New Low Pressure Turbine Blade at Low Reynolds Numbers, JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, Vol: 132, ISSN: 0889-504X
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- Citations: 25
Montomoli F, Massini M, Maceli N, et al., 2010, Interaction of Wheelspace Coolant and Main Flow in a New Aeroderivative Low Pressure Turbine, JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, Vol: 132, ISSN: 0889-504X
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- Citations: 2
Simone S, Montomoli F, Martelli F, et al., 2010, ANALYSIS ON THE EFFECT OF A NON-UNIFORM INLET PROFILE ON HEAT TRANSFER AND FLUID FLOW IN TURBINE STAGES, ASME Turbo Expo 2010, Publisher: AMER SOC MECHANICAL ENGINEERS, Pages: 2657-2670
Montomoli F, Massini M, Salvadori S, et al., 2010, GEOMETRICAL UNCERTAINTY AND FILM COOLING: FILLET RADII, ASME Turbo Expo 2010, Publisher: AMER SOC MECHANICAL ENGINEERS, Pages: 423-432
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- Citations: 1
Montomoli F, Adami P, Martelli F, 2009, A finite-volume method for the conjugate heat transfer in film cooling devices, PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART A-JOURNAL OF POWER AND ENERGY, Vol: 223, Pages: 191-200, ISSN: 0957-6509
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- Citations: 18
Montomoli F, Hodson H, Haselbach F, 2008, EFFECT OF ROUGHNESS AND UNSTEADINESS ON THE PERFORMANCE OF A NEW LPT BLADE AT LOW REYNOLDS NUMBERS, 53rd ASME Turbo Expo 2008, Publisher: AMER SOC MECHANICAL ENGINEERS, Pages: 1859-1870
Montomoli F, Massini M, Maceli N, et al., 2006, Interaction of wheelspace coolant and main flow in a new aeroderivative LPT, 51st ASME Turbo Expo, Publisher: AMER SOC MECHANICAL ENGINEERS, Pages: 1865-1873
Adami P, Montomoli F, Belardini E, et al., 2004, Interaction between wake and film cooling jets: Numerical analysis, Pages: 1053-1063
The present work presents the results obtained from the numerical investigation of the 3D unsteady flow field in a film-cooled turbine vane. The blade under research is the AGTB-B1 investigated in the cascade of the High Speed Cascade Wind Tunnel of the University of Armed Forces Munich. The unsteady flow consists of a wake which periodically interacts with the shower-head film cooling system of the blade nose. The paper discusses the aerodynamical interaction between the film-cooled blade and the periodic wake produced by a moving row of bars placed in a plane upstream the cascade. The predictive approach is based on a U-RANS CFD solver using a conventional two-equation closure. The unsteady CFD results are discussed against the experimental data available. Special emphasis is devoted to the unsteady interaction of the wake with the shower-head film-cooling system of the blade.
Montomoli F, Della Gatta S, Adami P, et al., 2004, Conjugate heat transfer modelling in film cooled blades, Pages: 147-156
A reliable and accurate prediction of temperature field in hot components plays a key role in design process of modern gas turbines. The first stages of turbine and the combustor basket are usually subjected to high heat transfer rates and hot gas temperatures exceed the melting point of the employed alloys. The accurate knowledge of temperature distribution could extend the life of critical components through an accurate design of coolant systems. The present work concerns the upgrade of the finite volume CFD (Computational Fluid Dynamic) solver HybFlow, (see Adami et al.[1]) to simulate heat transfer in gas turbine cooling devices. In particular, the conjugate simulation of flow field heat transfer and metal heat conduction has been considered. To this aim, the original solver has been coupled to a routine solving the Fourier equation in solid domain. This modification allows the "conjugate heat transfer" investigation of heat transfer in fluid flow and solid domain simultaneously. The code has been validated through two different test-case applications. The first is a laminar flow over a flat plate, while the second is a film-cooled plate. Finally, a complete 3D film cooled NGV (Nozzle Guide Vane) has been investigated as an example for a more complex application. The simulation couples the thermal field inside the metal and the flow field in the vane, in the two plenum channels and in the six rows of cooling channels as well.
Magi A, Adami P, Montomoli F, et al., 2004, Experimental and numerical investigation of stationary ribbed ducts, Pages: 157-165
Goal of this work is to define the main issues and guidelines for an accurate heat transfer CFD simulation of internal ribbed ducts. To this aim, two different ribbed ducts (AR=1,3) have been experimentally investigated to obtain a data set useful to validate numerical analyses. Experimental HTC contour maps have been obtained using unsteady TLC technique. CFD activity deals with numerical simulation using both a commercial (Star-CD™) and an "in house" solver (HybFlow). Four different variants of the well-known two-equation turbulence models have been considered. Low cost heat transfer predictions of internal ducts are highly demanded by industry despite the uncommon complexity of modern internal coolant system. Accordingly, the main aim of the work is to provide some indications for the numerical modelling and to evaluate the accuracy level of predicted heat transfer when commercial or research packages are employed along with different grid resolution levels. Overall results are in good agreement with experimental data even if some local discrepancies are present.
Adami P, Chana KS, Martelli F, et al., 2003, Numerical predictions of film cooled NGV blades, Pages: 639-649
Film-cooling is commonly used in modern gas turbines to increase inlet temperatures without compromising the mechanical strength of the hot components. The main objective of the study reported here is the critical evaluation of the capability of CFD, to predict film-cooling on three-dimensional engine realistic turbine aerofoil geometries. To achieve this aim two different film-cooling systems for NGV aerofoils are predicted and compared against experiments. The application concerns the following turbine vanes: the AGTB-B1 blade investigated by the "Institut fur Strahlantriebe of the Universitat der Bundeswehr Munchen (Germany)"; the MT1 HP NGV investigated by QinetiQ (ex DERA, UK). In the first test case the application mainly focuses on the interaction between the main flow and the coolant jets on the leading edge of the cooled aerofoil. In the second case, vane heat transfer rate is predicted with the film-cooling system made of six rows of cylindrical holes in single and staggered configuration.
Adami P, Martelli F, Montomoli F, et al., 2002, Numerical investigation of internal crossflow film cooling, Pages: 51-63
A full-3D unstructured solver is applied for the investigation of the physics involved in the flow of modern film cooling devices. The numerical simulation is based on a TVD upwind finite volume method that exploits the implicit time-marching approach. A conventional two equations eddy viscosity closure is considered for the turbulent flow field without wall-functions. The present application aims to investigate and discuss the flow field physics as obtained from a numerical RANS (Reynolds Averaged Navier-Stokes) simulation comparing different cooling duct systems devices. The CFD outcome is discussed against experiments considering the discharge coefficient as a means to quantify the accuracy of the numerical simulation. Particular attention is focused on the geometrical discretization, on the grid characteristics and on the capabilities of CFD for an efficient and realistic modelling of the flow field. The basic features of the film cooling technique are addressed considering the experimental test configurations investigated by Karlsruhe University for cylindrical, fanshaped and laid back fan shaped configurations with cross/parallel flows arrangement.
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