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Aslanidou, Ioanna
Publications (10 of 12) Show all publications
Kavvalos, M., Xin, Z., Schnell, R., Aslanidou, I., Kalfas, A. & Kyprianidis, K. (2019). A Modelling Approach of Variable Geometry for Low Pressure Ratio Fans. In: International Symposium on Air Breathing Engines, ISABE 2019, Canberra, Australia, 23 - 27 September 2019 Paper No. ISABE-2019-24382: . Paper presented at International Symposium on Air Breathing Engines, ISABE 2019, Canberra, Australia, 23 - 27 September 2019 Paper No. ISABE-2019-24382.
Open this publication in new window or tab >>A Modelling Approach of Variable Geometry for Low Pressure Ratio Fans
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2019 (English)In: International Symposium on Air Breathing Engines, ISABE 2019, Canberra, Australia, 23 - 27 September 2019 Paper No. ISABE-2019-24382, 2019Conference paper, Published paper (Refereed)
Abstract [en]

This paper presents the development and application of a modelling approach of variable geometry conceptsfor low pressure ratio fans; namely Variable Area Nozzle and Variable Pitch Fan. An enhanced approachfor Outlet Guide Vane pressure loss predictions and an aerothermodynamic analysis of variable pitchconcept are developed and integrated into a multi-disciplinary conceptual engine design framework. Astreamline curvature algorithm is deployed for the derivation of the off-design fan performance map,alleviating scaling issues from higher pressure ratio fan designs. Correction deltas are derived through thevariable pitch analysis for calculating the re-shaped off-design fan performance map. The aforementionedvariable geometry concepts are evaluated in terms of surge margin at engine and aircraft level for a lowpressure ratio aft-fan of a hybrid-electric configuration. Performance assessments carried out suggest thata +8° closing of fan blade cascades leads to a 33% surge margin improvement (with reference being thesurge margin without variable geometry) compared to a 25% improvement achieved by +20% opening thenozzle area at end of runway take-off conditions. Although weight and complexity implications of variablegeometry are not considered, the integrated modelling approach is shown to be able to assess and comparesuch novel engine technologies for low pressure ratio fans in terms of operability.

Keywords
Low Pressure Ratio Fan; Variable Area Nozzle; Variable Pitch Fan; Conceptual Design; Engine Performance;
National Category
Aerospace Engineering
Research subject
Energy- and Environmental Engineering
Identifiers
urn:nbn:se:mdh:diva-46288 (URN)
Conference
International Symposium on Air Breathing Engines, ISABE 2019, Canberra, Australia, 23 - 27 September 2019 Paper No. ISABE-2019-24382
Available from: 2019-12-11 Created: 2019-12-11 Last updated: 2019-12-13Bibliographically approved
Zaccaria, V., Rahman, M., Aslanidou, I. & Kyprianidis, K. (2019). A review of information fusion methodsfor gas turbine diagnostics. Paper presented at International Gas Turbine Congress IGTC2019. Sustainability, 11(22), Article ID 6202.
Open this publication in new window or tab >>A review of information fusion methodsfor gas turbine diagnostics
2019 (English)In: Sustainability, ISSN 2071-1050, E-ISSN 2071-1050, Vol. 11, no 22, article id 6202Article, review/survey (Refereed) Published
Abstract [en]

The correct and early detection of incipient faults or severe degradation phenomena in gas turbine systems is essential for safe and cost-effective operations. A multitude of monitoring and diagnostic systems were developed and tested in the last few decades. The current computational capability of modern digital systems was exploited for both accurate physics-based methods and artificial intelligence or machine learning methods. However, progress is rather limited and none of the methods explored so far seem to be superior to others. One solution to enhance diagnostic systems exploiting the advantages of various techniques is to fuse the information coming from different tools, for example, through statistical methods. Information fusion techniques such as Bayesian networks, fuzzy logic, or probabilistic neural networks can be used to implement a decision support system. This paper presents a comprehensive review of information and decision fusion methods applied to gas turbine diagnostics and the use of probabilistic reasoning to enhance diagnostic accuracy. The different solutions presented in the literature are compared, and major challenges for practical implementation on an industrial gas turbine are discussed. Detecting and isolating faults in a system is a complex problem with many uncertainties, including the integrity of available information. The capability of different information fusion techniques to deal with uncertainty are also compared and discussed. Based on the lessons learned, new perspectives for diagnostics and a decision support system are proposed. 

National Category
Energy Engineering
Identifiers
urn:nbn:se:mdh:diva-45906 (URN)10.3390/su11226202 (DOI)000503277900016 ()2-s2.0-85075901692 (Scopus ID)
Conference
International Gas Turbine Congress IGTC2019
Available from: 2019-11-04 Created: 2019-11-04 Last updated: 2020-01-09Bibliographically approved
Pontika, E. C., Kalfas, A. I. & Aslanidou, I. (2019). Aeroengines: Multi-platform application for aero engine simulation and compressor map operating point prediction. In: Proceedings of the ASME Turbo Expo: . Paper presented at ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition, GT 2019, 17 June 2019 through 21 June 2019. American Society of Mechanical Engineers (ASME)
Open this publication in new window or tab >>Aeroengines: Multi-platform application for aero engine simulation and compressor map operating point prediction
2019 (English)In: Proceedings of the ASME Turbo Expo, American Society of Mechanical Engineers (ASME) , 2019Conference paper, Published paper (Refereed)
Abstract [en]

This paper presents the development of AeroEngineS (Aircraft Engine Simulation), a multi-platform app with graphical user interface for aero engine simulation and compressor map operating point prediction. Gas turbine performance simulation is a crucial part of the design process. It provides information about the required operating conditions of all the components and the overall performance of the engine so that engineers can determine whether the current engine configuration meets the performance requirements. Some gas turbine simulation programs have been developed in the last decades, however, there was a lack of an open-source, lightweight, user-friendly, but still very accurate, application which would be easily accessible from all platforms. AeroEngineS can be used as a user-friendly preliminary design tool, since, during this design phase, details about the geometry are not known yet. The main aim is to calculate simply and quickly the basic parameters of the thermodynamic cycle and the performance, in order to determine which design is able to meet the required specifications. AeroEngineS constitutes a free and simple app which can primarily serve educational purposes as it is easily accessible by students from any platform to assist them in aero engine technology courses. Secondarily, it has the potential to be used even by engineers as a quick tool accessible from all devices. The app consists of two basic stand-alone functions. The first function is aero engine simulation at Design Point which solves thermodynamic calculations. The second function is compressor map operating point prediction using a novel method of combining scaling techniques and Artificial Neural Networks.

Place, publisher, year, edition, pages
American Society of Mechanical Engineers (ASME), 2019
Keywords
Application programs, Compressors, Forecasting, Gas turbines, Graphical user interfaces, Neural networks, Simulation platform, Thermodynamic properties, Aero-engine technologies, Engine configuration, Gas turbine performance, Multi-platform applications, Operating condition, Performance requirements, Thermodynamic calculations, Thermodynamic cycle, Aircraft engines
National Category
Energy Engineering
Identifiers
urn:nbn:se:mdh:diva-46218 (URN)10.1115/GT2019-91961 (DOI)000502167600048 ()2-s2.0-85075513908 (Scopus ID)9780791858677 (ISBN)
Conference
ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition, GT 2019, 17 June 2019 through 21 June 2019
Available from: 2019-12-02 Created: 2019-12-02 Last updated: 2020-01-02Bibliographically approved
Papagianni, A., Kavvalos, M., Aslanidou, I., Kyprianidis, K. & Kalfas, A. (2019). Conceptual Design of a Hybrid Gas Turbine - Solid Oxide Fuel Cell System for Civil Aviation. In: : . Paper presented at International Symposium on Air Breathing Engines, ISABE 2019, Canberra, Australia, 23 - 28 September 2019 Paper No. ISABE-2019-24214.
Open this publication in new window or tab >>Conceptual Design of a Hybrid Gas Turbine - Solid Oxide Fuel Cell System for Civil Aviation
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2019 (English)Conference paper, Published paper (Refereed)
Abstract [en]

A conceptual design of a hybrid Gas Turbine - Solid Oxide Fuel Cell (SOFC) system is presented for civil aviation applications. The system operates using hydrogen as fuel, for the aircraft’s propulsion, while at the same time produces electrical energy in the fuel cell. Hydrogen is produced during flight by reformation of methane. The motivation of the study is to investigate hydrogen’s use for aviation purposes, so the hybrid system’s operation characteristics need to be examined. A configuration is designed, where a SOFC and the burner is modeled as one and simulated, in a modern multidisciplinary programming environment, in order to analyze the thermodynamic characteristics of the hybrid system. The fuel cell sets into motion when the aircraft reaches top of climb. During operation, liquefied natural gas is converted to hydrogen in the fuel cell and part of it is used to produce electrical energy while the rest for combustion. To determine the efficiency of the system, its performance was simulated using two scenarios, one for longhaul flights and one for short-haul flights. Comparing the results, for long-haul flights, the hybrid system presents a reduction in fuel consumption and an increase in thermal efficiency. For flights of a short range, the existing conditions in the fuel cell inlet were found to be prohibitive for it’s operation and the use of the hybrid system ineffective. For the system’s efficiency, the larger the pressure in the SOFC’s inlet the better. However, SOFC’s pressure limits restrict the pressure range and the cell’s use only during flight. Concluding, according to the study’s results, the hybrid system can operate in flight conditions, making the use of hydrogen in civil aviation possible. As a result, a 12% and 35% benefit is achieved, in fuel saving and thermal efficiency respectively.

Keywords
Hybrid system; Solid Oxide Fuel Cell; Hydrogen; Fuel saving; thermal efficiency
National Category
Aerospace Engineering
Research subject
Energy- and Environmental Engineering
Identifiers
urn:nbn:se:mdh:diva-46257 (URN)
Conference
International Symposium on Air Breathing Engines, ISABE 2019, Canberra, Australia, 23 - 28 September 2019 Paper No. ISABE-2019-24214
Available from: 2019-12-08 Created: 2019-12-08 Last updated: 2019-12-13Bibliographically approved
Aslanidou, I. & Rosic, B. (2018). Effect of the Combustor Wall on the Aerothermal Field of a Nozzle Guide Vane. Journal of turbomachinery, 140(5), Article ID 051010.
Open this publication in new window or tab >>Effect of the Combustor Wall on the Aerothermal Field of a Nozzle Guide Vane
2018 (English)In: Journal of turbomachinery, ISSN 0889-504X, E-ISSN 1528-8900, Vol. 140, no 5, article id 051010Article in journal (Refereed) Published
Abstract [en]

In gas turbines with can combustors the trailing edge of the combustor transition duct wall is found upstream of ev- ery second vane. This paper presents an experimental and numerical investigation of the effect of the combustor wall trailing edge on the aerothermal performance of the nozzle guide vane. In the measurements carried out in a high speed experimental facility, the wake of this wall is shown to in- crease the aerodynamic loss of the vane. On the other hand, the wall alters secondary flow structures and has a protective effect on the heat transfer in the leading edge-endwall junc- tion, a critical region for component life. The different clock- ing positions of the vane relative to the combustor wall are tested experimentally and are shown to alter the aerothermal field. The experimental methods and processing techniques adopted in this work are used to highlight the differences be- tween the different cases studied. 

National Category
Fluid Mechanics and Acoustics
Identifiers
urn:nbn:se:mdh:diva-37506 (URN)10.1115/1.4038907 (DOI)000430492900010 ()2-s2.0-85046548519 (Scopus ID)
Available from: 2017-12-19 Created: 2017-12-19 Last updated: 2018-05-24Bibliographically approved
Zaccaria, V., Stenfelt, M., Aslanidou, I. & Kyprianidis, K. (2018). Fleet monitoring and diagnostics framework based on digital twin of aero-engines. In: Proceedings of the ASME Turbo Expo: . Paper presented at ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018, 11 June 2018 through 15 June 2018. American Society of Mechanical Engineers (ASME), 6
Open this publication in new window or tab >>Fleet monitoring and diagnostics framework based on digital twin of aero-engines
2018 (English)In: Proceedings of the ASME Turbo Expo, American Society of Mechanical Engineers (ASME) , 2018, Vol. 6Conference paper, Published paper (Refereed)
Abstract [en]

Monitoring aircraft performance in a fleet is fundamental to ensure optimal operation and promptly detect anomalies that can increase fuel consumption or compromise flight safety. Accurate failure detection and life prediction methods also result in reduced maintenance costs. The major challenges in fleet monitoring are the great amount of collected data that need to be processed and the variability between engines of the fleet, which requires adaptive models. In this paper, a framework for monitoring, diagnostics, and health management of a fleet of aircrafts is proposed. The framework consists of a multi-level approach: starting from thresholds exceedance monitoring, problematic engines are isolated, on which a fault detection system is then applied. Different methods for fault isolation, identification, and quantification are presented and compared, and the related challenges and opportunities are discussed. This conceptual strategy is tested on fleet data generated through a performance model of a turbofan engine, considering engine-to-engine and flight-to-flight variations and uncertainties in sensor measurements. Limitations of physics-based methods and machine learning techniques are investigated and the needs for fleet diagnostics are highlighted. 

Place, publisher, year, edition, pages
American Society of Mechanical Engineers (ASME), 2018
Keywords
Aircraft engines, Engines, Fault detection, Learning systems, Turbofan engines, Turbomachinery, Uncertainty analysis, Aircraft performance, Fault detection systems, Life prediction methods, Machine learning techniques, Monitoring and diagnostics, Physics-based methods, Reduced maintenance costs, Sensor measurements, Fleet operations
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:mdh:diva-41129 (URN)10.1115/GT2018-76414 (DOI)000456908700036 ()2-s2.0-85053863979 (Scopus ID)9780791851128 (ISBN)
Conference
ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018, 11 June 2018 through 15 June 2018
Available from: 2018-10-08 Created: 2018-10-08 Last updated: 2019-10-01Bibliographically approved
Aslanidou, I., Zaccaria, V., Pontika, E., Zimmerman, N., Kalfas, A. I. & Kyprianidis, K. (2018). Teaching gas turbine technology to undergraduate students in Sweden. In: Proceedings of the ASME Turbo Expo: . Paper presented at ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018, 11 June 2018 through 15 June 2018; Code 138886. American Society of Mechanical Engineers (ASME), 6
Open this publication in new window or tab >>Teaching gas turbine technology to undergraduate students in Sweden
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2018 (English)In: Proceedings of the ASME Turbo Expo, American Society of Mechanical Engineers (ASME) , 2018, Vol. 6Conference paper, Published paper (Refereed)
Abstract [en]

This paper addresses the teaching of gas turbine technology in a third-year undergraduate course in Sweden and the challenges encountered. The improvements noted in the reaction of the students and the achievement of the learning outcomes is discussed. The course, aimed at students with a broad academic education on energy, is focused on gas turbines, covering topics from cycle studies and performance calculations to detailed design of turbomachinery components. It also includes economic aspects during the operation of heat and power generation systems and addresses combined cycles as well as hybrid energy systems with fuel cells. The course structure comprises lectures from academics and industrial experts, study visits, and a comprehensive assignment. With the inclusion of all of these aspects in the course, the students find it rewarding despite the significant challenges encountered. An important contribution to the education of the students is giving them the chance, stimulation, and support to complete an assignment on gas turbine design. Particular attention is given on striking a balance between helping them find the solution to the design problem and encouraging them to think on their own. Feedback received from the students highlighted some of the challenges and has given directions for improvements in the structure of the course, particularly with regards to the course assignment. This year, an application developed for a mobile phone in the Aristotle University of Thessaloniki for the calculation of engine performance will be introduced in the course. The app will have a supporting role during discussions and presentations in the classroom and help the students better understand gas turbine operation. This is also expected to reduce the workload of the students for the assignment and spike their interest.

Place, publisher, year, edition, pages
American Society of Mechanical Engineers (ASME), 2018
Keywords
Curricula, E-learning, Fuel cells, Gas turbines, Gases, Machine design, Structural design, Teaching, Engine performance, Gas turbine design, Gas Turbine Technologies, Hybrid energy system, Performance calculation, Turbomachinery components, Undergraduate Courses, Undergraduate students, Students
National Category
Energy Engineering
Identifiers
urn:nbn:se:mdh:diva-41126 (URN)10.1115/GT2018-77074 (DOI)000456908700049 ()2-s2.0-85053912750 (Scopus ID)9780791851128 (ISBN)
Conference
ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018, 11 June 2018 through 15 June 2018; Code 138886
Available from: 2018-10-08 Created: 2018-10-08 Last updated: 2019-02-14Bibliographically approved
Aslanidou, I., Zaccaria, V., Rahman, M., Oostveen, M., Olsson, T. & Kyprianidis, K. (2018). Towards an Integrated Approach for Micro Gas Turbine Fleet Monitoring, Control and Diagnostics. In: : . Paper presented at Global Power and Propulsion Forum 2018, Zurich, Switzerland.
Open this publication in new window or tab >>Towards an Integrated Approach for Micro Gas Turbine Fleet Monitoring, Control and Diagnostics
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2018 (English)Conference paper, Published paper (Refereed)
Abstract [en]

Real-time engine condition monitoring and fault diagnostics results in reduced operating and maintenance costs and increased component and engine life. Prediction of faults can change the maintenance model of a system from a fixed maintenance interval to a condition based maintenance interval, further decreasing the total cost of ownership of a system. Technologies developed for engine health monitoring and advanced diagnostic capabilities are generally developed for larger gas turbines, and generally focus on a single system; no solutions are publicly available for engine fleets. This paper presents a concept for fleet monitoring finely tuned to the specific needs of micro gas turbines. The proposed framework includes a physics-based model and a data-driven model with machine learning capabilities for predicting system behaviour, combined with a diagnostic tool for anomaly detection and classification. The integrated system will develop advanced diagnostics and condition monitoring for gas turbines with a power output under 100 kW.

National Category
Aerospace Engineering
Research subject
Energy- and Environmental Engineering
Identifiers
urn:nbn:se:mdh:diva-43169 (URN)
Conference
Global Power and Propulsion Forum 2018, Zurich, Switzerland
Available from: 2019-04-21 Created: 2019-04-21 Last updated: 2019-06-03Bibliographically approved
Aslanidou, I. & Rosic, B. (2017). Aerothermal Performance of Shielded Vane Design. Journal of turbomachinery, 139(11), Article ID 111003.
Open this publication in new window or tab >>Aerothermal Performance of Shielded Vane Design
2017 (English)In: Journal of turbomachinery, ISSN 0889-504X, E-ISSN 1528-8900, Vol. 139, no 11, article id 111003Article in journal (Refereed) Published
Abstract [en]

This paper presents an experimental investigation of the concept of using the combustor transition duct wall to shield the nozzle guide vane leading edge. The new vane is tested in a high-speed experimental facility, demonstrating the improved aerodynamic and thermal performance of the shielded vane. The new design is shown to have a lower average total pressure loss than the original vane, and the heat transfer on the vane surface is overall reduced. The peak heat transfer on the vane leading edge–endwall junction is moved further upstream, to a region that can be effectively cooled as shown in previously published numerical studies. Experimental results under engine-representative inlet conditions showed that the better performance of the shielded vane is maintained under a variety of inlet conditions.

National Category
Fluid Mechanics and Acoustics
Identifiers
urn:nbn:se:mdh:diva-37505 (URN)10.1115/1.4037126 (DOI)000412232000003 ()2-s2.0-85025165063 (Scopus ID)
Available from: 2017-12-19 Created: 2017-12-19 Last updated: 2018-07-25Bibliographically approved
Zaccaria, V., Dik, A., Bitén, N., Aslanidou, I. & Kyprianidis, K. (2017). Conceptual Design of a 3-Shaft Turbofan Engine with Reduced Fuel Consumption for 2025. In: Elsevier (Ed.), Energy Procedia: . Paper presented at 9th International Conference on Applied Energy, ICAE2017, 21-24 August 2017, Cardiff, UK.
Open this publication in new window or tab >>Conceptual Design of a 3-Shaft Turbofan Engine with Reduced Fuel Consumption for 2025
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2017 (English)In: Energy Procedia / [ed] Elsevier, 2017Conference paper, Published paper (Refereed)
Abstract [en]

In the past decade, aircraft fuel burn has been continually decreased, mainly by improving thermal and propulsion efficiencies with consequent decrement in specific fuel consumption. In view of future emission specifications, the requirements for SFC in the forthcoming years are expected to become more stringent. In this paper, a preliminary design of a turbofan engine for entry in service in 2025 was performed. The design of a baseline 2010 EIS engine was improved according to 2025 specifications. A thermodynamic analysis was carried out to select optimal jet velocity ratio, pressure ratio, and temperatures with the goal of minimizing specific fuel consumption. A gas path layout was generated and an aerodynamic analysis was performed to optimize the engine stage by stage design. The optimization resulted in a 3-shaft turbofan jet engine with a 21% increase in fan diameter, a 2.2% increment in engine length, and a fuel burn improvement of 11% compared to the baseline engine, mainly due to an increment in propulsive efficiency. A sensitivity analysis was also conducted to highlight what the focus of technology development should be.

National Category
Energy Engineering
Identifiers
urn:nbn:se:mdh:diva-37465 (URN)10.1016/j.egypro.2017.12.556 (DOI)000452901601136 ()2-s2.0-85041554792 (Scopus ID)
Conference
9th International Conference on Applied Energy, ICAE2017, 21-24 August 2017, Cardiff, UK
Available from: 2017-12-15 Created: 2017-12-15 Last updated: 2019-10-01Bibliographically approved
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