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Aerospace
Special Issues
Life Cycle Modeling of Aircraft Propulsion Systems
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Life Cycle Modeling of Aircraft Propulsion Systems

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (31 May 2021) | Viewed by 13245

Special Issue Editor

Prof. Dr. Stephan Staudacher

E-Mail Website
Guest Editor
Institute for Aircraft Propulsion Systems, University of Stuttgart, Pfaffenwaldring 6, 70569 Stuttgart, Germany
Interests: aircraft propulsion systems

Special Issue Information

Dear Colleagues,

Life cycle modeling of aircraft propulsion systems is a key ability in the fields of aircraft propulsion system design, engine selection, fleet management, flight mission and maintenance planning, development of engine repair technologies, as well as spare part logistics. As one manifestation of whole system modeling, it involves abilities such as engine performance and controls, performance and structural deterioration modeling, modeling the effect of ingested fluid and solid particles, as well as modeling the aging of engine structures. A key aspect is the complex interaction of the deterioration mechanisms that leads to specific patterns of propulsion system deterioration. Consequently, it requires scientific methods with a wide range of spatial and time resolution.

Prof. Dr. Stephan Staudacher
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • life cycle modeling
  • deterioration modeling
  • erosion modeling
  • fouling modeling
  • particle ingestion
  • fluid ingestion
  • corrosion modeling
  • tip clearance loss
  • fleet management

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Published Papers (3 papers)

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Research

24 pages, 4309 KiB  
Article
Monte Carlo Predictions of Aero-Engine Performance Degradation Due to Particle Ingestion
by Matthew Ellis, Nicholas Bojdo, Antonio Filippone and Rory Clarkson
Aerospace 2021, 8(6), 146; https://doi.org/10.3390/aerospace8060146 - 25 May 2021
Cited by 17 | Viewed by 4940
Abstract
Aero-engines, which encounter clouds of airborne particulate, experience reduced performance due to the deposition of particles on their high-pressure turbine nozzle guide vanes. The rate of this degradation depends on particle properties, engine operating state and the duration of exposure to the particle [...] Read more.
Aero-engines, which encounter clouds of airborne particulate, experience reduced performance due to the deposition of particles on their high-pressure turbine nozzle guide vanes. The rate of this degradation depends on particle properties, engine operating state and the duration of exposure to the particle cloud, variables that are often unknown or poorly constrained, leading to uncertainty in model predictions. A novel method coupling one-dimensional gas turbine performance analysis with generalised predictions of particle deposition is developed and applied through the use of Monte Carlo simulations to better predict high-pressure turbine degradation. This enables a statistical analysis of deterioration from which mean performance losses and confidence intervals can be defined, allowing reductions in engine life and increased operational risk to be quantified. The method is demonstrated by replicating two particle cloud encounter events for the Rolls-Royce RB211-524C engine and is used to predict empirical particle properties by correlating measured engine performance data with Monte Carlo model inputs. Potential improvements in the confidence of these predictions due to more tightly constrained input and validation data are also demonstrated. Finally, the potential combination of the Monte Carlo coupled degradation model with in-service engine performance data and particle properties determined through remote or in situ sensing is outlined and its role in a digital twin to enable a predictive approach to operational capability is discussed. Full article
(This article belongs to the Special Issue Life Cycle Modeling of Aircraft Propulsion Systems)
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15 pages, 2800 KiB  
Article
Two-Phase Flow Phenomena in Gas Turbine Compressors with a Focus on Experimental Investigation of Trailing Edge Disintegration
by Adrian Schlottke and Bernhard Weigand
Aerospace 2021, 8(4), 91; https://doi.org/10.3390/aerospace8040091 - 26 Mar 2021
Cited by 2 | Viewed by 2804
Abstract
Two-phase flow in gas turbine compressors occurs, for example, at heavy rain flight condition or at high-fogging in stationary gas turbines. The liquid dynamic processes are independent of the application. An overview on the processes and their approach in literature is given. The [...] Read more.
Two-phase flow in gas turbine compressors occurs, for example, at heavy rain flight condition or at high-fogging in stationary gas turbines. The liquid dynamic processes are independent of the application. An overview on the processes and their approach in literature is given. The focus of this study lies on the experimental investigation of the trailing edge disintegration. In the experiments, shadowgraphy is used to observe the disintegration of a single liquid rivulet with constant liquid mass flow rate at the edge of a thin plate at different air flow velocities. A two side view enables calculating droplet characteristics with high accuracy. The results show the asymptotic behavior of the ejected mean droplet diameters and the disintegration period. Furthermore, it gives a detailed insight into the droplet diameter distribution and the spreading of the droplets perpendicular to the air flow. Full article
(This article belongs to the Special Issue Life Cycle Modeling of Aircraft Propulsion Systems)
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17 pages, 17254 KiB  
Article
Dust Ingestion in a Rotorcraft Engine Compressor: Experimental and Numerical Study of the Fouling Rate
by Alessandro Vulpio, Alessio Suman, Nicola Casari and Michele Pinelli
Aerospace 2021, 8(3), 81; https://doi.org/10.3390/aerospace8030081 - 18 Mar 2021
Cited by 16 | Viewed by 4028
Abstract
Helicopters often operate in dusty sites, ingesting huge amounts of contaminants during landing, take-off, hover-taxi, and ground operations. In specific locations, the downwash of the rotor may spread soil particles from the ground into the environment and, once ingested by the engine, may [...] Read more.
Helicopters often operate in dusty sites, ingesting huge amounts of contaminants during landing, take-off, hover-taxi, and ground operations. In specific locations, the downwash of the rotor may spread soil particles from the ground into the environment and, once ingested by the engine, may stick to the compressor airfoils. In the present work, the Allison 250 C18 engine’s multistage axial-flow compressor is employed to study the fouling rate on rotor blades and stator vanes from both numerical and experimental standpoints. The compressor is operated in a typical ground-idle operation, in terms of the rotational regime and contaminant concentration, in laboratory-controlled conditions. The mass of deposits is collected from the airfoil surfaces at the end of the test and compared to that estimated through the numerical model. The experimental test shows that the airfoils collect almost 1.6% of the engine’s total mass ingested during a ground-idle operation. The capability of numerical methods to predict the fouling rate on the rotating and stationary airfoils of a multistage compressor is tested through the implementation of literature based deposition models. Sticking models show a good agreement in terms of the relative results; nevertheless, an overestimation of the deposited mass predicted is observed. Full article
(This article belongs to the Special Issue Life Cycle Modeling of Aircraft Propulsion Systems)
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