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18 pages, 8300 KB

Open AccessArticle

Numerical Modelling of the 3D Unsteady Flow of an Inlet Particle Separator for Turboshaft Engines

by Marco Castaldi, Ignacio Mayo, Jacques Demolis and Frank Eulitz

Int. J. Turbomach. Propuls. Power 2023, 8(4), 52; https://doi.org/10.3390/ijtpp8040052 - 4 Dec 2023

Cited by 5 | Viewed by 2555

Helicopter and turboprop engines are susceptible to the ingestion of debris and other foreign objects, especially during take-off, landing, and hover. To avoid deleterious effects, filters such as Inlet Particle Separators (IPS) can be installed. However, the performance and limitations of these systems have to be investigated before the actual equipment can be installed in the aircraft powerplant. In this paper, we propose different numerical methods with increasing resolution in order to provide an aerodynamic characterization of the IPS, i.e., from a simple semi-empirical model to 3D large eddy simulation. We validate these numerical tools that could aid IPS design using experimental data in terms of global parameters such as separation efficiency and pressure losses. For each of those tools, we underline weaknesses and potential benefits in industry practices. Unsteady flow analysis reveals that detached eddy simulation is the trade-off choice that allows designers to most effectively plan experimental campaigns and mitigate risks. Full article

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18 pages, 3269 KB

Open AccessArticle

Analytical Calculation Model of the TV3-117 Turboshaft Working Regimes Based on Experimental Data

by Razvan Marius Catana and Gabriel Dediu

Appl. Sci. 2023, 13(19), 10720; https://doi.org/10.3390/app131910720 - 26 Sep 2023

Cited by 24 | Viewed by 3192

Abstract

The paper presents a practical and relevant analytical calculation model for free turbine turboshaft working regimes and engine performance. The analytical calculation model is based on a post-processing method that analyzes a series of experimental data, specifically focusing on the percentage variations of the engine’s main parameters from the minimum to the takeoff working regime. The experimental data were acquired from three different types of engines: TV2-117A turboshaft, AI-20K turboprop, and Viper 632-41 turbojet. The analysis method aimed to identify, through calculations, certain similarity parameters that exhibit nearly constant variations or variations within tight limits. These parameters can then be used as approximate constants in the calculation model. By utilizing these constants related to similarity parameters, a mathematical connection between different engine regimes is established; more exactly, for the engine data from a known to unknown regime. In the current case, only the engine data from the takeoff regime are requested to be known, and in this way, the other working regimes of several engines can be calculated. Full article

(This article belongs to the Section Aerospace Science and Engineering)

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20 pages, 6528 KB

Open AccessArticle

Experimental Analysis on the Operating Line of Two Gas Turbine Engines by Testing with Different Exhaust Nozzle Geometries

by Razvan Marius Catana and Gabriel Petre Badea

Energies 2023, 16(15), 5627; https://doi.org/10.3390/en16155627 - 26 Jul 2023

Cited by 7 | Viewed by 2886

Abstract

This paper presents a special analysis study about the gas turbine operating line, and an overall description of a gas turbines project, based on experimental data from two particular applications, in order to convert two different types of aero engines into the same engine configuration. The experimental works were carried out with the aim of converting an Ivchenko AI-20K turboprop and a Rolls-Royce Viper 632-41 turbojet into free turbine turboshaft engines, to be used in marine propulsion, and also to obtain an experimental database to be used in other gas turbine applications. In order to carry out the experimental work, the engines were tested in turbojet configuration, to simulate the free turbine load by using jet nozzles with different geometries of the outlet cross-section. Following the engines’ tests, a series of measured data were obtained, through which it was possible to experimentally determine the operating line of some engine components such as the compressor, turbine, and exhaust jet nozzle. This paper is comprehensive and useful through its scientific and technical guidelines, the operation curves coming in handy in the thermodynamic analysis and testing methodology for researchers dealing with similar applications. Full article

(This article belongs to the Section I: Energy Fundamentals and Conversion)

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30 pages, 5733 KB

Open AccessArticle

Study of a Regional Turboprop Aircraft with Electrically Assisted Turboshaft

by Anaïs Luisa Habermann, Moritz Georg Kolb, Philipp Maas, Hagen Kellermann, Carsten Rischmüller, Fabian Peter and Arne Seitz

Aerospace 2023, 10(6), 529; https://doi.org/10.3390/aerospace10060529 - 2 Jun 2023

Cited by 15 | Viewed by 4954

Abstract

Hybrid-Electric Propulsion (HEP) could be part of the solution to decrease emissions associated with regional commercial aviation. This study presents results for the aircraft level fuel reduction potential of a regional turboprop concept with an HEP architecture and Entry-Into-Service (EIS) in 2035+. The configuration specifically tackles the elaborated challenges of introducing an additional electrical energy source to the configuration by employing a twofold electrical assistance to a turboshaft engine in combination with an innovative thermal management concept. Relevant components and disciplines were modeled and incorporated into an integrated aircraft design environment. The behavior and interaction of the HEP architecture with the aircraft was thoroughly investigated. A best-performing configuration was derived and compared with a conventional reference configuration following a State-of-the-Art (SoA) reference aircraft approach. For a typical mission with 200 nmi range, a block fuel reduction of 9.6% was found. However, the assumed battery performance characteristics limited the reduction potential and led to a fuel burn increase for the 600 nmi design mission. Furthermore, sourcing the non-propulsive subsystems directly from the on-board battery was detrimental. The innovative Thermal Management System (TMS) located in the propeller slipstream showed a synergistic effect with the investigated configuration. Full article

(This article belongs to the Section Aeronautics)

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