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The dataset presented here regard the analysis reported in the research article entitled "Comparison of different plasma actuation strategies for aeroelastic control on a linear compressor cascade" De Giorgi et al. (2021) [1]. These data are related to the Computational Fluid Dynamics (CFD) assessment of different plasma actuation strategies for the aeroelastic control of an aero engine compressor cascade in subsonic flow conditions. The authors evaluated the accuracy of numerical computations using experimental results. Here, both experimental and raw data of the CFD simulations are presented.
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The article presents the data regarding the experimental characterization of combustion of liquid jet A1 with addition of urea-water emulsion. A liquid-fuel gas turbine derived burner operating in non-premixed mode under three different equivalence fuel/air ratios was used. The data were collected, with and without urea addition, with two high speed visualization systems which acquired the broadband and spatially and spectrally resolved chemiluminescence emissions. Chemiluminescence images of OH* were acquired using an intensified camera system with a narrow-band filter at approximately 310 nm CWL, while the chemiluminescence images of CH* were recorded with a 436 nm CWL. Measurements of exhaust temperature and NOx, CO and CO2 emissions have been also performed. The data presented here are related to the article entitled "COMBUSTION PERFORMANCE OF A LOW NOx GAS TURBINE COMBUSTOR USING UREA ADDITION INTO LIQUID FUEL" [1].
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The present dataset provides experimental measurements of the 3D liquid/gas interface shape during lateral water sloshing in a partially filled cylindrical container. The measurement technique used to acquire the data is the Reference Image Topography [1] based on a Synthetic Schlieren Free-Surface Reconstruction method [2]. A modified version of the processing algorithm has been used. This one transforms the coordinate system from Cartesian to polar so that the computational domain only includes the area where the fluid is present. Moreover, it uses the conservation of the fluid volume into the investigated area that permits to obtain the absolute height. This allows overcoming the strong limitation of the RIT method regarding the inability to detect changes of the mean surface height, at the condition that the complete and only liquid domain recorded in the images is used in the inversion algorithm. The complete details of the post-processing of the images is reported in the paper associated to this DIB [3]. The dataset includes the external excitation history and maps of the liquid/gas interface acquired during the experiment. These data are considered fundamental for the validation of CFD simulations of sloshing and of simplified theoretical models. A set of 12 test cases are reported in this DIB. A part of these test cases refers to steady state sloshing and a part to sloshing damping. In the last cases, also the 3D map of damping coefficients, calculated using the logarithmic decrement method, is provided.
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The design of aeroengine real-time control systems needs the implementation of machine learning based techniques. The lack of in-flight aeroengine performance data is a limit for the researchers interested in the development of these prediction algorithms. Dynamic aeroengine models can be used to overcome this lack. This data article presents data regarding the performance of a turbojet that were predicted by the dynamic engine model that was built using the Gas turbine Simulation Program (GSP) software. The data were also used to implement an Artificial Neural Network (ANN) that predicts the in-flight aeroengine performance, such as the Exhaust Gas Temperature (EGT). The Nonlinear AutoRegressive with eXogenous inputs (NARX) neural network was used. The neural network predictions have been also given as dataset of the present article. The data presented here are related to the article entitled "MultiGene Genetic Programming - Artificial Neural Networks approach for dynamic performance prediction of an aeroengine" [1].
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The data regard the analysis reported in the research article "Influence of actuation parameters of multi-DBD plasma actuators on the static and dynamic behavior of an airfoil in unsteady flow" [1]. The data are related to the study focused on the evaluation of the effects of an active flow control system on the performance of an airfoil in an unsteady flow, with particular focus on the influence of actuation parameters on the global performances.
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The data presented in this article were the basis for the study reported in the research articles entitled "Characterization of unsteady cavitating flow regimes around a hydrofoil, based on an extended Schnerr-Sauer model coupled with a nucleation model" (De Giorgi et al., 2018)[1]. The reference study presented a spatio-temporal characterization of different cavitating flow regimes using Computational Fluid Dynamics (CFD). The authors evaluated the accuracy of an extended Schnerr-Sauer cavitation model. The accuracy of the numerical model has been improved by means of the introduction of a Density Correction Model of the turbulent viscosity, and a simplified Population Balance Modeling (PBM).
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The data presented in this data article were on the basis of the study reported in the research articles entitled "A novel quasi-one-dimensional model for performance estimation of a Vaporizing Liquid Microthruster" (De Giorgi and Fontanarosa, 2018). The reference study presented a numerical analysis of the performance of the Vaporizing Liquid Microthruster (VLM) experimentally investigated in the data article entitled "Performance evaluation and flow visualization of a MEMS based Vaporizing Liquid Microthruster" (Cen and Xu, 2010). For the purpose, a novel quasi one-dimensional model was proposed, and results were compared with the numerical predictions provided by 2D and 3D CFD computations. Due to the scarcity of experimental data concerning the flow characterization inside a Vaporizing Liquid Microthruster, the present Data in Brief aims to provide the entire dataset coming from the numerical predictions for benchmark purposes and comparisons with different numerical approach.
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The article presents the data related to the flame acquisitions in a liquid-fuel gas turbine derived burner operating in non-premixed mode under three different equivalence fuel/air ratio, which corresponds to a richer, an intermediate, and an ultra-lean condition, near lean blowout (LBO). The data were collected with two high speed visualization systems which acquired in the visible (VIS) and in the infrared (NIR) spectral region. Furthermore chemiluminescence measurements, which have been performed with a photomultiplier (PMT), equipped with an OH* filter, and gas exhaust measurements were also given. For each acquisition the data were related to operating parameters as pressure, temperature and equivalent fuel/air ratio. The data are related to the research article "Image processing for the characterization of flame stability in a non-premixed liquid fuel burner near lean blowout" in Aerospace Science and Technology [1].
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Global rainbow thermometry (GRT) measures the mean size and temperature of an ensemble of spray droplets. The domain of validity of the Airy theory for this technique is established through comparison with Lorenz-Mie theory. The temperature derivation from the inflection points of the Airy rainbow pattern appears to be independent of the type of spray dispersion. Measurements in a water spray are reported. The mean diameter obtained from the rainbow pattern lies between the arithmetic and the Sauter mean diameters measured by phase Doppler anemometry. The temperature measurement by GRT is shown to be accurate within a few degrees Celsius.
