The Experts below are selected from a list of 198 Experts worldwide ranked by ideXlab platform
Louis A. Peluso - One of the best experts on this subject based on the ideXlab platform.
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Role of Environmental Deposits in Spallation of Thermal Barrier Coatings on Aeroengine and Land-Based Gas Turbine Hardware
Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls Diagnostics and Instrumentation; Education; General, 1996Co-Authors: Marcus P Borom, Curtis A. Johnson, Louis A. PelusoAbstract:Thermal barrier coating (TBC) spallation on power generation combustors was compared with TBC spallation observed both in military turboshaft Engines, and in commercial Turboprop Engines. In each case, irrespective of operating conditions or geographic location, spallation was linked to the presence and infiltration of high temperature molten phases of similar composition. Electron microprobe analysis found that, from all the possible oxides available in the external environment, only CaO, MgO, Al2O3 and SiO2 (CMAS) are incorporated in the molten phase that infiltrates the TBC microstructure. Iron and nickel oxides from turbine components and zirconia and yttria from the TBC were also found in varying amounts in the molten phase.Melting of environmental deposits in conjunction with infiltration was found to result in: densification of the TBC, an increase in its Young’s modulus and an increase in the room temperature compressive stress in the TBC. Delamination of the TBC during thermal cycling is, thereby, attributed to changes in the mechanical properties and associated changes in the stress state of the coating due to infiltration of the environmental deposit.Copyright © 1996 by ASME
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Role of environment deposits and operating surface temperature in spallation of air plasma sprayed thermal barrier coatings
Surface and Coatings Technology, 1996Co-Authors: Marcus P Borom, Curtis A. Johnson, Louis A. PelusoAbstract:Spallation of air plasma sprayed (APS) thermal barrier coatings (TBCs) was investigated on power generation combustors, military turboshaft Engines, and commercial Turboprop Engines. In each case, irrespective of operating conditions or geographic location, spallation was linked to the presence and infiltration of high temperature molten phases of similar composition. Electron microprobe analysis found that, from all the possible oxides available in the external environment, only CaO, MgO, Al2O3 and SiO2 (CMAS) are incorporated in the molten phase that infiltrates the TBC microstructure. Fe and Ni oxides from metallic components and zirconia and yttria from the TBC were also found in varying amounts in the molten phase. The melting and recrystallization behavior of CMAS deposits was carefully defined by differential thermal analysis.
Marcus P Borom - One of the best experts on this subject based on the ideXlab platform.
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Role of Environmental Deposits in Spallation of Thermal Barrier Coatings on Aeroengine and Land-Based Gas Turbine Hardware
Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls Diagnostics and Instrumentation; Education; General, 1996Co-Authors: Marcus P Borom, Curtis A. Johnson, Louis A. PelusoAbstract:Thermal barrier coating (TBC) spallation on power generation combustors was compared with TBC spallation observed both in military turboshaft Engines, and in commercial Turboprop Engines. In each case, irrespective of operating conditions or geographic location, spallation was linked to the presence and infiltration of high temperature molten phases of similar composition. Electron microprobe analysis found that, from all the possible oxides available in the external environment, only CaO, MgO, Al2O3 and SiO2 (CMAS) are incorporated in the molten phase that infiltrates the TBC microstructure. Iron and nickel oxides from turbine components and zirconia and yttria from the TBC were also found in varying amounts in the molten phase.Melting of environmental deposits in conjunction with infiltration was found to result in: densification of the TBC, an increase in its Young’s modulus and an increase in the room temperature compressive stress in the TBC. Delamination of the TBC during thermal cycling is, thereby, attributed to changes in the mechanical properties and associated changes in the stress state of the coating due to infiltration of the environmental deposit.Copyright © 1996 by ASME
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Role of environment deposits and operating surface temperature in spallation of air plasma sprayed thermal barrier coatings
Surface and Coatings Technology, 1996Co-Authors: Marcus P Borom, Curtis A. Johnson, Louis A. PelusoAbstract:Spallation of air plasma sprayed (APS) thermal barrier coatings (TBCs) was investigated on power generation combustors, military turboshaft Engines, and commercial Turboprop Engines. In each case, irrespective of operating conditions or geographic location, spallation was linked to the presence and infiltration of high temperature molten phases of similar composition. Electron microprobe analysis found that, from all the possible oxides available in the external environment, only CaO, MgO, Al2O3 and SiO2 (CMAS) are incorporated in the molten phase that infiltrates the TBC microstructure. Fe and Ni oxides from metallic components and zirconia and yttria from the TBC were also found in varying amounts in the molten phase. The melting and recrystallization behavior of CMAS deposits was carefully defined by differential thermal analysis.
Curtis A. Johnson - One of the best experts on this subject based on the ideXlab platform.
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Role of Environmental Deposits in Spallation of Thermal Barrier Coatings on Aeroengine and Land-Based Gas Turbine Hardware
Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls Diagnostics and Instrumentation; Education; General, 1996Co-Authors: Marcus P Borom, Curtis A. Johnson, Louis A. PelusoAbstract:Thermal barrier coating (TBC) spallation on power generation combustors was compared with TBC spallation observed both in military turboshaft Engines, and in commercial Turboprop Engines. In each case, irrespective of operating conditions or geographic location, spallation was linked to the presence and infiltration of high temperature molten phases of similar composition. Electron microprobe analysis found that, from all the possible oxides available in the external environment, only CaO, MgO, Al2O3 and SiO2 (CMAS) are incorporated in the molten phase that infiltrates the TBC microstructure. Iron and nickel oxides from turbine components and zirconia and yttria from the TBC were also found in varying amounts in the molten phase.Melting of environmental deposits in conjunction with infiltration was found to result in: densification of the TBC, an increase in its Young’s modulus and an increase in the room temperature compressive stress in the TBC. Delamination of the TBC during thermal cycling is, thereby, attributed to changes in the mechanical properties and associated changes in the stress state of the coating due to infiltration of the environmental deposit.Copyright © 1996 by ASME
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Role of environment deposits and operating surface temperature in spallation of air plasma sprayed thermal barrier coatings
Surface and Coatings Technology, 1996Co-Authors: Marcus P Borom, Curtis A. Johnson, Louis A. PelusoAbstract:Spallation of air plasma sprayed (APS) thermal barrier coatings (TBCs) was investigated on power generation combustors, military turboshaft Engines, and commercial Turboprop Engines. In each case, irrespective of operating conditions or geographic location, spallation was linked to the presence and infiltration of high temperature molten phases of similar composition. Electron microprobe analysis found that, from all the possible oxides available in the external environment, only CaO, MgO, Al2O3 and SiO2 (CMAS) are incorporated in the molten phase that infiltrates the TBC microstructure. Fe and Ni oxides from metallic components and zirconia and yttria from the TBC were also found in varying amounts in the molten phase. The melting and recrystallization behavior of CMAS deposits was carefully defined by differential thermal analysis.
Rudnik Ralf - One of the best experts on this subject based on the ideXlab platform.
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Nacelle Strake Design for Short Takeoff and Landing Configuration with Turboprop Engines
'American Institute of Aeronautics and Astronautics (AIAA)', 2018Co-Authors: Keller Dennis, Hasan, Yasim Julian, Rudnik RalfAbstract:The scope of this Paper is to investigate the Integration effects of Turboprop Engines on a high-lift wing with an internally blown plain flap system with Reynolds-averaged Navier–Stokes computations. It is shown that the resulting nacelle vortices can significantly reduce the high-lift performance at zero thrust conditions. To limit the negative impact, an inboard nacelle strake was designed with the aim of maximizing the lift coefficient of the landing configuration at zero thrust. To reach this goal, a sensitivity study on basic geometric strake parameters was carried out. The best nacelle strake is able to improve the maximum lift coefficient by ΔCL,max � 0.17 and the maximum angle of attack by 3 deg. The study also reveals the further potential of improvement due to an additional outboard strake. First simulations with outboard strake lead to a further improvement of ΔCL; max � 0.13 and 4 deg in the maximum angle of attack. It is also shown that the installation of an inboard strake does not negatively impact the high-lift performance at a moderate thrust level
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Integration Aspects of Lift Augmentation Systems on the Aerodynamics of a High-Lift Configuration
2015Co-Authors: Keller Dennis, Rudnik RalfAbstract:The scope of this report is to illustrate the installation effects of circulation control and Turboprop Engines on the stability characteristics of the reference aircraft’s landing configuration in lateral motion and in failure cases. Therfore, RANS simulations of the full configuration at different side slip angles and with asymmetric boundary conditions of the circulation control system and the propellers were performed. It is shown that the lateral stability of the investigated configuration is influenced by both aspects. While thrust generally leads to a reduced stability, activated circulation control tends to amplify the aircraft’s behavior. As a result, the configuration is unstable under certain conditions. The simulation of the one engine inoperative case demonstrated yawing moments up to twice as high as the actual yawing moments due to the asymmetric thrust. Furthermore, the report highlights the impact of the design update on the aerodynamic behavior in longitudinal motion, where an increase of maximum angle of attack and maximum lift could be achieved. Additional configuration enhancements were realized due to the design and integration of a nacelle strake
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Numerical Investigations of Aerodynamic Properties of a Propeller Blown Circulation Control System on a High Wing Aircraft
2015Co-Authors: Keller Dennis, Rudnik RalfAbstract:The contribution gives an overview over the wide range of CFD simulations, which were performed in the course of the German collaborative research center 880 in order to investigate the aerodynamic properties of a complete aircraft landing configuration with a circulation control high-lift system and Turboprop Engines. The main purpose is to highlight the integration aspects of lift augmentation technologies into the design of a short take-off and landing aircraft concept. Therefore, the influence of engine nacelles and thrust on the stall behavior and the following improvements due to the use of a nacelle strake are discussed. Furthermore, static longitudinal and lateral stability as well as the dynamic longitudinal stability are investigated. While circulation control itself has a rather small impact, the impact of engine thrust in conjunction with circulation control is considerable. Additionally, the one engine inoperative case was simulated. For some flow and engine conditions, the resulting yawing moments are more than twice as high as the actual yawing moments due to asymmetric thrust and thus are higher than expected
Beneš Petr - One of the best experts on this subject based on the ideXlab platform.
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Aircraft Turboprop Engine Vibration Monitoring Module
Západočeská univerzita v Plzni, 2020Co-Authors: Dulík Tomáš, Pospíšilík Martin, Opluštil Vladimír, Beneš PetrAbstract:The paper describes electronic vibration monitoring module (EVM) that can be used as standalone diagnostic system or as a part of a complex modular concept of engine electronic control (EEC/FADEC) with aircraft health monitoring system. We present a new generation of EVM for modern small Turboprop Engines and their vibration diagnostics which has been developed by Unis, a.s. in cooperation with Brno University of Technology and Tomas Bata University in Zlin
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Aircraft Turboprop engine vibration monitoring module
IEEE Computer Society, 2020Co-Authors: Dulík Tomáš, Pospíšilík Martin, Opluštil Vladimír, Beneš PetrAbstract:The paper describes electronic vibration monitoring module (EVM) that can be used as standalone diagnostic system or as a part of a complex modular concept of engine electronic control (EEC/FADEC) with aircraft health monitoring system. We present a new generation of EVM for modern small Turboprop Engines and their vibration diagnostics which has been developed by Unis, a.s. in cooperation with Brno University of Technology and Tomas Bata University in Zlin. © 2020 University of West Bohemia
