Journal articles: 'Aeronautical engine'

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Lemco, Ian. "Wittgenstein's aeronautical investigation." Notes and Records of the Royal Society 61, no. 1 (December 22, 2006): 39–51. http://dx.doi.org/10.1098/rsnr.2006.0163.

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After a rigorous German education in the physical sciences, young Ludwig Wittgenstein entered Manchester University as an aeronautical engineering research student. There he devised and patented a novel aero-engine employing an airscrew propeller driven by blade tip-jets. Within the context of the growth of English aviation during the first half of the twentieth century (including the contributions of many Fellows of the Royal Society) and taking into account related aspects of his life, this paper examines an unfulfilled engineering aspiration. In enlarging upon what Wittgenstein might have accomplished during his stay at Manchester, it contrasts his invention with later comparable proven designs, albeit applied to hybrid rotorcraft. His engine employed centrifugal flow compression and arguably was a precursor of Sir Frank Whittle's gas turbine. In conclusion, reasons are given for Wittgenstein's departure from Manchester.

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Faruoli, Maria, Annarita Viggiano, Paolo Caso, and Vinicio Magi. "A Numerical Analysis of the Air-Cooling System of a Spark Ignition Aeronautical Engine." E3S Web of Conferences 197 (2020): 06003. http://dx.doi.org/10.1051/e3sconf/202019706003.

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It is well known that spark ignition internal combustion engines for aeronautical applications operate within a specific temperature range to avoid structural damages, detonations and loss of efficiency of the combustion process. An accurate assessment of the cooling system performance is a crucial aspect in order to guarantee broad operating conditions of the engine. In this framework, the use of a Conjugate Heat Transfer method is a proper choice, since it allows to estimate both the heat fluxes between the engine walls and the cooling air and the temperature distribution along the outer wall surfaces of the engine, and to perform parametric analyses by varying the engine operating conditions. In this work, the air-cooling system of a 4-cylinder spark ignition engine, designed by CMD Engine Company for aeronautical applications, is analysed in order to evaluate the amount of the air mass flow rate to guarantee the heat transfer under full load operating conditions. A preliminary validation of the model is performed by comparing the results with available experimental data. A parametric study is also performed to assess the influence of the controlling parameters on the cooling system efficiency. This study is carried out by varying the inlet air mass flow rate from 1.0 kg/s to 1.5 kg/s and the temperature of the inner wall surfaces of the engine combustion chambers from 390 K to 430 K.

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Férand, Mélissa, Thomas Livebardon, Stéphane Moreau, and Marlène Sanjosé. "Numerical Prediction of Far-Field Combustion Noise from Aeronautical Engines." Acoustics 1, no. 1 (February 19, 2019): 174–98. http://dx.doi.org/10.3390/acoustics1010012.

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A hybrid methodology combining a detailed Large Eddy Simulation of a combustion chamber sector, an analytical propagation model of the extracted acoustic and entropy waves at the combustor exit through the turbine stages, and a far-field acoustic propagation through a variable exhaust temperature field was shown to predict far-field combustion noise from helicopter and aircraft propulsion systems accurately for the first time. For the single-stream turboshaft engine, the validation was achieved from engine core to the turbine exit. Propagation to the far field was then performed through a modeled axisymmetric jet. Its temperature modified the acoustic propagation of combustion noise significantly and a simple analytical model based on the Snell–Descarte law was shown to predict the directivity for axisymmetric single jet exhaust accurately. Good agreement with measured far-field spectra for all turboshaft-engine regimes below 2 kHz stresses that combustion noise is most likely the dominant noise source at low frequencies in such engines. For the more complex dual-stream turbofan engine, two regime computations showed that direct noise is mostly generated by the unsteady flame dynamics and the indirect combustion noise by the temperature stratification induced by the dilution holes in the combustion chamber, as found previously in the turboshaft case. However, in the turboengine, direct noise was found dominant at the combustor exit for the low power case and equivalent contributions of both combustion noise sources for the high power case. The propagation to the far-field was achieved through the temperature field provided by a Reynolds-Averaged Navier–Stokes simulation. Good agreement with measured spectra was also found at low frequencies for the low power turboengine case. At high power, however, turboengine jet noise overcomes combustion noise at low frequencies.

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McCord, Charles G. "THE AERONAUTICAL ENGINE LABORATORY, NAVAL AIRCRAFT FACTORY, PHILADELPHIA, PENNA." Journal of the American Society for Naval Engineers 37, no. 2 (March 18, 2009): 275–305. http://dx.doi.org/10.1111/j.1559-3584.1925.tb02517.x.

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Fedele, Lorenzo, Luca Di Vito, and Fulvio Enzo Ramundo. "Increasing Efficiency in an Aeronautical Engine through Maintenance Evaluation and Upgrades: Analysis of the Reliability and Performance Improvements under Financial Issues." Energies 13, no. 12 (June 12, 2020): 3059. http://dx.doi.org/10.3390/en13123059.

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This paper defines a methodology for the evaluation of the technical and economic performance of aeronautical engines through the upgrades introduced during its life. The CFM56 is a high-bypass turbofan engine. The variants share a common design, but the details are different. The fan and booster evolved over the different iterations of the engine, as did the compressor, combustor, and turbine sections. Maintenance consists of the activities carried out during the life cycle of an engine to ensure safe, reliable, and economic operation. Maintenance costs represent 20–25% of an airline’s operating costs, of which 35–40% refer to the engine. The changes in the performance parameters indicate the state of the engine in the medium to long term: for example, it is possible to detect blade fouling or data on vibrations, and highlight changes in the characteristic behavior of an engine. This work investigates the behavior of the performance parameters in the period prior to an engine development event: a comparison is made with the monitoring of engine vibrations. In the conclusions, a final expressive graph makes us aware of the significant progress, over the years, achieved with the methodology here presented.

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Loyda, A., G. M. Hernández-Muñoz, L. A. Reyes-Osorio, P. Zambrano, and F. Montemayor-Ibarra. "Numerical Simulation of Rotary Forging Inconel 718 Superalloy Applied to Aeronautical Components." MRS Proceedings 1812 (2016): 101–7. http://dx.doi.org/10.1557/opl.2016.25.

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ABSTRACTNowadays the aeronautical industry keeps strict quality standards in its dimensional specifications, mechanical properties and microstructural characteristics. Therefore, the involved manufacturing processes require keeping high standards. The nickel based superalloys are present in many components of the jet engines, being the Inconel 718MR superalloy the most common, making up to 50% of the jet engine. This is designed to resist high temperatures, corrosion and creep. The process of rotary forging is a manufacturing process that is currently under scientific and technological development in the aeronautical industry. An Avrami model coupled with a commercial FEM platform (DEFORMTM 3D) was developed to evaluate the average grain size, as a function of the working conditions at 980 °C and 1000 °C. The results provide a better understanding of the influence of temperature in the grain size evolution during the rotary forging process, compared with previous reports.

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Brouckaert, Jean-François, François Mirville, Kevin Phuah, and Peter Taferner. "Clean Sky research and demonstration programmes for next-generation aircraft engines." Aeronautical Journal 122, no. 1254 (July 9, 2018): 1163–75. http://dx.doi.org/10.1017/aer.2018.37.

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ABSTRACTThe Clean Sky Joint Undertaking is currently managing two large-scale research and innovation programmes under FP7 and Horizon 2020 to contribute to the strengthening of the European aeronautical sector ensuring global leadership and competitiveness. This paper describes the research and demonstration programmes in Clean Sky (2008–2017) and Clean Sky 2 (2014–2024) related to propulsion technologies for the next-generation aircraft. The bulk of this work is addressed in Clean Sky 1 under the “Sustainable And Green Engines” (SAGE) programme and under the “ENGINES” programme in Clean Sky 2. The High-Level Objectives are described for each engine architecture as well as the targets in terms of CO2 and noise reduction versus a year 2000 reference unless stated otherwise. An overview of the new engine concepts that would satisfy the ACARE objectives is presented, including the main technologies which are to be developed to ensure the successful demonstration of each of those new engine concepts.

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Nakano, Toshihiro, Michael Zeutzius, Hideo Miyanishi, Toshiaki Setoguchi, and Kenji Kaneko. "Studies on Pulse Jet Engine by Wind Tunnel Testing." International Journal of Rotating Machinery 7, no. 2 (2001): 79–85. http://dx.doi.org/10.1155/s1023621x01000070.

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Simple design and efficiency make pulse jet engines attractive for aeronautical short-term operation applications. An active control system extends the operating range and reduces the fuel consumption considerably so that this old technology might gain a new interest. The results on wind tunnel experiments have been reported together with the impact of combustion mode (pulse or steady) on system performance.

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Иванов, Антон, Anton Ivanov, Рушана Анамова, Rushana Anamova, Андрей Рипецкий, Andrey Ripetskiy, Александр Автушенко, Aleksandr Avtushenko, Александр Осипов, and Aleksandr Osipov. "Application methodology for additive technologies at the stages of prototyping airborne components and assemblies." Bulletin of Bryansk state technical university 2015, no. 2 (June 30, 2015): 8–16. http://dx.doi.org/10.12737/22847.

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In this article described application features for additive technologies in the aeronautical industry. Application methodology for additive technologies at the stages of prototyping airborne components and assemblies is developed. Proposed methodology is appraised for manufacturing dummy engine components.

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Palano, F., F. W. Panella, and V. Dattoma. "Characterization of aeronautical engine parts welded with capacitor discharge welding technology." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 224, no. 1 (October 8, 2009): 11–22. http://dx.doi.org/10.1243/09544100jaero607.

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11

Gonzalez Caranton, Alberth Renne, Vladimir Silva Leal, Camilo Bayona-Roa, Manuel Alejandro Mayorga Betancourt, Carolina Betancourt, Deiver Cortina, Nelson Jimenez Acuña, and Mauricio López. "Experimental Investigation of the Mechanical and Thermal Behavior of a PT6A-61A Engine Using Mixtures of JETA-1 and Biodiesel." Energies 14, no. 11 (June 4, 2021): 3282. http://dx.doi.org/10.3390/en14113282.

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Biofuels are important additives to conventional fuels in combustion engines of the transport sector, as they reduce atmospheric emissions and promote environmental-friendly production chains. The mechanical and thermal performance of a PT6A-61A engine on a test bench of the Colombian Air Force operating with blends of JETA-1 and Biodiesel up to 25% volume values of substitution is evaluated in this work. Experimental results show that blends are operationally reliable up to 15% volume content. In that range, the engine operation is not compromised in terms of response variables. Moreover, experimental properties of fuel blends show that the freezing point—which is the most critical variable, does not comply with aeronautical regulations. The system dynamics are subject to several variations in the test parameters, which mainly affected fuel flow, Inter-Turbine Temperature (ITT), and engine performance. A Principal Component Analysis (PCA) is performed over the experimental results to quantify possible disturbances on the bench measurements. This is based on the fact that the study is restrained to stationary test bench conditions.

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Cesari, G., F. W. Panella, and A. Pirinu. "Stress/strain state for critical components of a jet engine aeronautical compressor." Engineering Failure Analysis 116 (October 2020): 104745. http://dx.doi.org/10.1016/j.engfailanal.2020.104745.

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Beranoagirre, A., and Luis Norberto López de Lacalle. "Topography Prediction on Grinding of Emerging Aeronautical TiAl Intermetallic Alloys." Materials Science Forum 797 (June 2014): 84–89. http://dx.doi.org/10.4028/www.scientific.net/msf.797.84.

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Gamma-TiAl intermetallic materials are the focus of all leading aerospace / gas turbine manufacturers, as a replacement for some nickel-based superalloy components in parts of the engine subject to temperatures < 900°C. Although applicable for only a relatively narrow range of applications, titanium intermetallic materials are likely to play a significant role in the production of future aeroengines. This work presents the results from grinding tests on two types of Gamma TiAl alloys.

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Fąfara, Jean-Marc. "Overview of low emission combustors of aircraft turbine drive units." Combustion Engines 183, no. 4 (December 15, 2020): 45–49. http://dx.doi.org/10.19206/ce-2020-407.

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It is important to notice that aircraft turbine drive units are commonly used in the modern aviation. The piston engines are often reserved for small and/or sportive aircraft. The turbine drive units are also combustion engine. This paper presents the most popular combustors used in the aeronautical turbine engines. Firstly there are listed the requirements that a combustor has to achieve. Then are presented the combustor designs that permit to achieve the firstly presented requirements. In this work are presented the LPP, TAPS, RQL, graduated combustion zone, VGC, exhaust recirculation system combustors. For each combustor design is enlighten its principle of work, described the etymology of the given name to this design and shown a scheme. The work is closed by a briefly conclusion about the described combustor.

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Fatsis, Antonios. "Performance Enhancement of One and Two-Shaft Industrial Turboshaft Engines Topped With Wave Rotors." International Journal of Turbo & Jet-Engines 35, no. 2 (May 25, 2018): 137–47. http://dx.doi.org/10.1515/tjj-2016-0040.

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Abstract Wave rotors are rotating equipment designed to exchange energy between high and low enthalpy fluids by means of unsteady pressure waves. In turbomachinery, they can be used as topping devices to gas turbines aiming to improve performance. The integration of a wave rotor into a ground power unit is far more attractive than into an aeronautical application, since it is not accompanied by any inconvenience concerning the over-weight and extra dimensioning. Two are the most common types of ground industrial gas turbines: The one-shaft and the two-shaft engines. Cycle analysis for both types of gas turbine engines topped with a four-port wave rotor is calculated and their performance is compared to the performance of the baseline engine accordingly. It is concluded that important benefits are obtained in terms of specific work and specific fuel consumption, especially compared to baseline engines with low compressor pressure ratio and low turbine inlet temperature.

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Sulikowski, Paweł, and Ryszard Maronski. "Quasi-Periodic Control Technique for Minimizing Fuel Consumption During Record Vehicle Competition." Archive of Mechanical Engineering 60, no. 2 (June 1, 2013): 185–97. http://dx.doi.org/10.2478/meceng-2013-0012.

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The problem of the optimal driving technique during the fuel economy competition is reconsidered. The vehicle is regarded as a particle moving on a trace with a variable slope angle. The fuel consumption is minimized as the vehicle covers the given distance in a given time. It is assumed that the run consists of two recurrent phases: acceleration with a full available engine power and coasting down with the engine turned off. The most fuel-efficient technique for shifting gears during acceleration is found. The decision variables are: the vehicle velocities at which the gears should be shifted, on the one hand, and the vehicle velocities when the engine should be turned on and off, on the other hand. For the data of students’ vehicle representing the Faculty of Power and Aeronautical Engineering it has been found that such driving strategy is more effective in comparison with a constant speed strategy with the engine partly throttled, as well as a strategy resulting from optimal control theory when the engine is still active.

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Song, Shu Fang, and Zhen Zhou Lu. "Line Sampling Reliability Analysis for Low Cycle Fatigue Life of Aeronautical Engine Disc Structure." Key Engineering Materials 324-325 (November 2006): 875–78. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.875.

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In engineering reliability analysis, the limit state equation is generally implicit and nonlinear, and large number basic random variables and small failure probability are associated. For this kind of reliability analysis, a novel numerical simulation is presented based on the combination of Markov Chain Simulation and line sampling. In the presented method, Markov Chain Simulation is used to draw samples in the failure domain rapidly, and important direction for the line sampling is determined by these samples. Then the line sampling technique is employed to take samples according to the important direction, and failure probability can be evaluated by line sampling with high efficiency. Comparing to the finite differential method for obtaining the important direction, higher accuracy and higher robustness of the important direction are obtained by the presented method. The application in the reliability analysis of low cycle fatigue life of aeronautical engine turbine disc structure, which is applied by multiple cyclic loads, shows that the presented line sampling combining with the Markov Chain Simulation is efficient and feasible.

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Dubikovsky, Sergey, Peng Hao Wang, and Katherine Minarik. "Equipment Condition’s Effect on Student Perceived Workload and Efficiency of Problem Based Projects in an Aeronautical Engineering Technology Program." Research Journal of Education, no. 71 (January 27, 2021): 23–28. http://dx.doi.org/10.32861/rje.71.23.28.

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Aeronautical Engineering Technology (AET) of Purdue University’s School of Aviation and Transportation Technology offers its students a comprehensive and holistic approach to engineering in an applied fashion. Students’ learning outcome includes an application of technical knowledge and hands-on skills in areas of aerospace design, operations, and manufacturing. The curriculum of the program includes a course in which students must learn advanced maintenance concepts and practices including the overhaul of reciprocating engines. This study examined the relationship between engine operational vs. non-operational statuses, time spent to finish a task, and student perceived workloads regarding the maintenance procedures. The tests followed the Federal Aviation Administration (FAA) requirements for the practical test questions from the Airframe and Powerplant Certificate (A&P) Exam. Students were also required to fill out a task perceived load index developed and used by NASA.

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Jones, R. I. "The design challenge of high altitude long endurance (Hale) unmanned aircraft." Aeronautical Journal 103, no. 1024 (June 1999): 273–80. http://dx.doi.org/10.1017/s0001924000064812.

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Abstract The requirement for an aircraft to operate in the thin atmosphere at high altitudes for long periods provides a particular challenge to all areas of aeronautical engineering. This is reflected in a range of difficulties encountered when attempting to design aircraft for this type of operation. This paper first considers the reasons for adopting an unmanned solution for high altitude long endurance (Hale) aircraft. It then indicates how the demands of Hale operations lead to problems in applying the design approach taken for more common aircraft types. Some of the work performed at the College of Aeronautics (CoA), in attempting to address the problem areas for the design process and produce initial designs for a range of Hale unmanned aircraft (UMA) types, is then reviewed. The lack of data/methods to allow the prediction of Hale UMA structure mass, engine performance at high altitudes and aerodynamic parameters for low Reynolds number operation and high aspect ratio configurations are identified as particular problems. However, initial design, based on standard approaches, has been shown to be possible, provided caution is exercised.

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Holden, T. M., J. H. Root, D. C. Tennant, and D. Leggett. "Non-Invasive Temperature Measurements by Neutron Diffraction in Aero-Engine Components." Advances in X-ray Analysis 38 (1994): 9–20. http://dx.doi.org/10.1154/s0376030800017602.

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Abstract A requirement exists in the aeronautical industry for measuring temperature non-invasively in critical components, such as the turbine disc in an operating engine. Neutron diffraction, unique among nuclear techniques, offers the possibility of measuring both temperature and strain within an operating engine by virtue of the high penetration of neutrons through industrial materials. Static diffraction experiments on Waspaloy and Ti6A14V showed, by comparison with thermocouples, that both the diffraction peak position and the peak intensity can measure the tempeiaturc to within ±6 K aL 800 K. Measurements on a rotating Waspaloy disc, heated from its rim, showed that temperature gradients could be determined accurately by lattice parameter measurements. The large grain size in Waspaloy prevented accurate peak intensity measurements in this dynamic test. Finally, the structures within a small Pratt & Whitney engine in its equatorial plane were mapped by mounting the engine on an X-Y translator on the diffractometer and moving it through a grid of positions. Possible future directions in the field will be discussed.

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Mónico Muñoz, Luisa Fernanda, Juan José Sandoval Sotelo, and Andrés Felipe Rodríguez Chaparro. "Estudio Teórico de la Influencia del Uso de Mezclas de Biodiesel de Aceite de Palma con JET a-1 en Motores a Reacción." Ingeniería 22, no. 1 (February 21, 2017): 98. http://dx.doi.org/10.14483/udistrital.jour.reving.2017.1.a06.

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Context: like many others, today the aeronautical industry has been forced to implement methods to mitigate the damage produced to the environment due to the emission of polluting gases and in doing so, confront the problem of global warming. In this context, research on the use of alternative fuels is of paramount importance, in particular the study of engine performance when using blends of Colombian Biodiesel based on palm oil with Jet A1.Method: as a starting point, we made a review of the state of the art so as to select which engine to study and then the alternative fuels to be used. Simultaneously, Colombian biodiesel based on palm oil was selected, as it has been shown to be a fuel with good performance when it is blended in percentages of 10%, 20% and 50%. Each of the blends were tested in the laboratory to obtain their viscosity, density and calorific values. A spreadsheet program was developed to conduct the analysis, which contemplated the physical properties of mixtures and engine parameters, as well as emissions of nitrous oxides (NOx), atomization and combustion produced by the use of mixtures. The results were compared against those of the Gasturbine simulation softwareResults: CFM 56-5B was chosen as the appropriate engine for the study, because it is currently the most used in the Colombian aeronautical industry. On the other hand, none of the alternative fuel blends generates the same engine performance when using Jet A1. The blends E10 and E20 have a similar behavior, with the novelty of generating less amount of NOx emissions and improving the atomization of the fuel.Conclusions: When the engine’s performance with conventional fuel is comparing with Biodiesel mixtures, a decrease of the thrust is produced as the percentage of Biodiesel in the mixture increases. Because the mixtures of alternative fuel have a lower calorific value fuel consumption in these cases is always greater. However, when comparing the NOx levels produced, a decrease of this pollutant is observed when using Biodiesel blends. It is worth noting that it is of great interest for future work to evaluate other pollutant emissions and, in turn, the behavior of other types of Biodiesel in jet engines.Language: Spanish.

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Lhommeau, T., X. Perpiñà, C. Martin, R. Meuret, M. Mermet-Guyennet, and M. Karama. "Thermal fatigue effects on the temperature distribution inside IGBT modules for zone engine aeronautical applications." Microelectronics Reliability 47, no. 9-11 (September 2007): 1779–83. http://dx.doi.org/10.1016/j.microrel.2007.07.093.

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Bozza, F., M. Costa, and D. Siano. "Design issues concerning thermofluidynamic and acoustic aspects in a diesel engine suitable for aeronautical applications." International Journal of Vehicle Design 50, no. 1/2/3/4 (2009): 152. http://dx.doi.org/10.1504/ijvd.2009.025003.

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Ebus, Tobias, Markus Dietz, and Andreas Hupfer. "Experimental and numerical studies on small contra-rotating electrical ducted fan engines." CEAS Aeronautical Journal 12, no. 3 (May 29, 2021): 559–71. http://dx.doi.org/10.1007/s13272-021-00517-7.

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AbstractElectrical propulsion has been identified as one of the key fields of future research within the aerospace sector. The Institute of Aeronautical Engineering at the Universität der Bundeswehr München aims to contribute to the ongoing development of small-sized electrical ducted fan engines with a thrust in the range of 100 N. A special emphasis is placed on electrically powered contra-rotating fan stages. When compared to a conventional rotor–stator stage, contra-rotating fan stages allow for a more compact design, considering a given pressure ratio, or an increased pressure ratio at a constant fan diameter. Since numerous new aircraft concepts are presently being developed, a high demand for compact and powerful electrically driven engines arises. Electrically driven contra-rotating fan engines provide a high potential in terms of compactness, emissions and efficiency. Using electric motors offers the ability to overcome common issues, such as design and integration of a contra-rotating stage into a gas turbine. An innovative new engine design featuring such a contra-rotating stage is developed and tested at one of the Institute’s test benches for electrical propulsion. Key components are two brushless motors powering the fan stage, one for each rotor. Various operation points are investigated experimentally during an extensive test campaign. Experimental results are compared to results of numerical simulations computed by ANSYS CFX. Results indicate a good agreement between experiment and simulation. The engine is running very smooth throughout all tested operation points. Yet, intensive heating up of the electric motors and high-temperature zone are found to be an issue at higher rotation speeds.

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Xu, You Liang, Cheng Li Liu, and Zhen Zhou Lu. "Fuzzy-Random FOSM and its Application in Low Cycle Fatigue Life Reliability Analysis of an Aeronautical Engine Turbine Disk." Key Engineering Materials 324-325 (November 2006): 775–78. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.775.

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An approximate analytical method is presented to analyze reliability for the structure with fuzzy-random uncertainty in basic variables. On the basis of equivalent transformation from fuzzy possibility distribution (FPD) to random probability distribution (RPD), this contribution expands first order and second moment method (FOSM) for random reliability to that for fuzzy-random reliability. The expanded FOSM is illustrated by the way of the fuzzy-random low fatigue life reliability analysis about an aeronautical engine disk affected by fuzzy-random uncertainty. Comparison between the FOSM and the numerical simulation for the fuzzy-random reliability demonstrates the precision of the presented computational model.

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Tao, Jun, Tian Cang Zhang, Peng Tao Liu, Jing Li, and Yu Mang. "Numerical Computation of a Linear Friction Welding Process." Materials Science Forum 575-578 (April 2008): 811–15. http://dx.doi.org/10.4028/www.scientific.net/msf.575-578.811.

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Linear friction welding (LFW) has become a key manufacture and repair technology in the aeronautical engine manufacturing, especially in the blisk manufacturing. The kinematic equation during LFW was built, based on which the friction heat in the whole process was computed. With thermal- mechanical coupling technique, and considering the geometrical non-linearity, the material property non-linearity and the interface frictional non-linearity, a Finite Element Model (FEM) of temperature, stress and deformation fields were constructed. The distribution contour of temperature, plastic flow, stress and strain during LFW were plotted. The simulated temperature and axial shortening results were also validated by experimental data.

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Liu, Wei Wei, Yuan Yuan Cai, Feng Li, Xiao Yan Li, and Xu Sheng Wan. "A Study of Chatter Stability Domain in Different Phases of Milling Process of Thin-Wall Component." Advanced Materials Research 711 (June 2013): 137–42. http://dx.doi.org/10.4028/www.scientific.net/amr.711.137.

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Aeronautical thin-wall components are widely used in Aero-Engine, and the machining stability of the thin-wall components is a difficulty issue. In this paper, a single freedom dynamic model is set up to describe the dynamics of thin-wall milling process, and the stability of the dynamic model is analyzed with the discretization method. Then the modal parameters are gained in the different milling phases and the resonance region of spindle speed is proposed. Optimize the milling parameters with the chatter stability domain at different milling phases. The result shows that the cutting chatter can be restrained if getting the spindle speedcutting depth parameters considering the superposition area of chatter stability domains and avoiding the resonance region in the different milling phases. At last, the method is applied in Aero-Engine thin-wall blade milling, the metal remove rate increases greatly and the machining accuracy is improved greatly.

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Galinsky, Andrey A., Anton V. Ryabkov, Vladimir I. Berg, and Aslan F. Zakuraev. "To the question of thermal joining of composite Al-B materials." Journal of Composite Materials 53, no. 19 (March 27, 2019): 2715–25. http://dx.doi.org/10.1177/0021998319839130.

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This work deals with the application of new approaches to welding production of modern light, strong, and heat-resistant metal composite materials in aeronautical and space technology. The objective of this article is to substantiate introduction of modern technology for welding composites in production, namely the development of argon-arc welding technology and the choice of equipment when using composites of the Al-B system for manufacturing the flame tube of the combustion chamber of an aircraft engine. Based on the study of technical literature and scientific publications, a short analysis of the existing technological processes for welding heat-resistant glass-ceramic composites was carried out. The problems arising in the process of welding aluminum composites reinforced with boron and steel fibers are considered. A modern gas tungsten arc welding based on new technological processes is offered with an example of welding in manufacturing a combustion chamber of a modern gas turbine modified engine.

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Langston, Lee S. "Avian Avoidance and Aviation." Mechanical Engineering 136, no. 02 (February 1, 2014): 50–54. http://dx.doi.org/10.1115/1.2014-feb-4.

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This article presents an overview of the current state of dealing with jet engine bird ingestion. At Turbo Expo ‘13 in San Antonio, Dr. Aspi Wadia of GE Aviation and Dr. Lee S. Langston (author of this paper) co-chaired a three-hour panel, ‘Jet Engine Bird Ingestion – Current Issues and Ways Forward.’ The leadoff panelist was Capt. Paul Eschenfelder, a retired Delta Airlines pilot, now with Embry-Riddle Aeronautical University, who gave an overall review of recent bird strike accidents around the world. Panelist John Dalton, who is a Technical Fellow in Airplane Safety Engineering for Boeing, gave the airframe original equipment manufacturer (OEM) history and his views on the bird strike problem. The panel’s fourth member was Dr. Nicholas Carter who is the Director of Finance for the World Birdstrike Association (WBA). Carter explained the role of the WBA, which is the international body that represents all states and countries in issues related to bird hazards at airfields and airports.

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Farara, C. J. "John William Fozard, O. B. E.. 16 January 1928–17 July 1996." Biographical Memoirs of Fellows of the Royal Society 44 (January 1998): 193–204. http://dx.doi.org/10.1098/rsbm.1998.0013.

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The name of John Fozard will, in aeronautical circles, for ever be linked with the Harrier and vectored thrust jet V/STOL—that species of aeroplane endowed with the ability to take off and land either vertically or in a short distance by jet engine propulsive nozzles which may be rotated from pointing conventionally rearwards through any angle downwards to forwards of the vertical. He did not conceive the idea of the vectored thrust engine or of vertical take-off aircraft or even the basic layout of the uniquely successful Harrier jump jet. However, when put in charge of its development he not only led the team that turned a ‘demonstrator’ into an operational fighter to a demanding specification that could be built economically in large numbers to a fixed–price contract, but also embraced the concept of vectored thrust jet V/STOL with a religious zeal and set about preaching its gospel far and wide.

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31

Cater, John, and Ian Lemco. "Wittgenstein's combustion chamber." Notes and Records of the Royal Society 63, no. 1 (January 6, 2009): 95–104. http://dx.doi.org/10.1098/rsnr.2008.0031.

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Ludwig Wittgenstein, destined to be one of the most influential philosophers of the western world, entered Manchester University in 1908 as an aeronautical engineering research student. At Manchester he devised and patented a novel aero-engine that employed propeller-blade tip-jets. As a first practical step to the realization of this device, Wittgenstein constructed a variable-volume combustion chamber, but on departing for Cambridge he abandoned all further work on the project. The plans of this chamber survived and are presented in this paper. This article includes a detailed description of the drawings and an analysis of the probable function of the system.

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Nahum, Andrew. "Two-Stroke or Turbine? The Aeronautical Research Committee and British Aero Engine Development in World War II." Technology and Culture 38, no. 2 (April 1997): 312. http://dx.doi.org/10.2307/3107125.

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Liu, C. L., Z. Z. Lu, Y. L. Xu, and Z. F. Yue. "Reliability analysis for low cycle fatigue life of the aeronautical engine turbine disc structure under random environment." Materials Science and Engineering: A 395, no. 1-2 (March 2005): 218–25. http://dx.doi.org/10.1016/j.msea.2004.12.014.

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CICHOCKI, Maciej K., Dariusz SOKOŁOWSKI, and Zbigniew LEWANDOWSKI. "Influence of Mass Parameters Modification on Manoeuvrability of 9K33 „OSA” Set 9M33M3 Missile." Problems of Mechatronics Armament Aviation Safety Engineering 11, no. 3 (September 30, 2020): 9–18. http://dx.doi.org/10.5604/01.3001.0014.3704.

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This paper discusses analytical method for realization of preliminary missile stability design calculations. Action has been taken to estimate influence of replacing massive blocks of analogue electronics with compact solutions of digital electronics in missiles remaining in operation. On an example of a short-range 9M33M3 missile from 9K33 „OSA” set and its previously analysed aerodynamic characteristics, the analysis of the centre of gravity location impact was carried out to determine maximum loads occurring in the two most interesting phases of flight: after booster engine burnout and directly after cruise engine burnout. The suggestion for modification suggestion of flight parameters’ optimization is presented which defines stability and its critical impact of these parameters on aeronautical engineering. For the tested missile, the methodology suggestions for the modification is discussed with the comparison of serially produced copies to define the ability of improving the flight parameters. The paper includes visualizations and quantity analysis of: maximal loads on the fuselage, minimal turn radius, and control wing inclination angle as missile’s angle of attack function.

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Gany, Alon, and Aviad Gofer. "Study of a Novel Air-augmented Waterjet Boost Concept." Journal of Ship Production and Design 30, no. 01 (February 1, 2014): 1–6. http://dx.doi.org/10.5957/jspd.2014.30.1.1.

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This research presents analysis, experiment, and prediction of the performance of a unique marine propulsion concept, the air-augmented waterjet, having a revolutionary potential for significant thrust augmentation and boost capability of waterjet systems. So far, this concept has not been realized in any operational vessel. The air-augmented waterjet propulsion concept is similar to an after-burner in the aeronautical turbojet engine. The thrust augmentation results from the injection of air bubbles into the water flow, converting their expansion work òpdV into additional kinetic energy of the exhaust jet without affecting the pump operation. It can enable substantially augmenting boost capability, overcoming hump resistance, and increasing maximum attainable vessel speed while avoiding cavitation problems. Static tests at the Technion's water tank, using a jetski waterjet engine of a nominal power of 50 kW, have been conducted with and without air injection over a range of motor revolutions per minute (rpm). The addition of air increased the thrust by 20% to 50% depending on the airflow rate and engine rpm. Air expansion work increased the exhaust jet kinetic energy at an efficiency of 70% approximately. Based on the static experiments, prediction of the system behavior for different vessel speeds and engine power levels has been made, revealing a higher relative thrust augmentation for the same pump power and airflow rate at higher vessel speeds. The air-augmented waterjet concept may add a new dimension to marine propulsion as well as upgrade existing vessels.

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Li, Yi, Yang Zhang, and Junqiang Bai. "Numerical Simulation of the Aerodynamic Influence of Aircrafts During Aerial Refueling with Engine Jet." International Journal of Aeronautical and Space Sciences 21, no. 1 (September 9, 2019): 15–24. http://dx.doi.org/10.1007/s42405-019-00212-2.

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Abstract Aerial refueling technology has been widely applied in various fields and it is one of the hotspots but difficulties for the aeronautical technologies. DLR-F6 WBNP model is used as a tanker and a fighter model is used as a receiver. The flow field of Probe–Drogue refueling and Flying Boom refueling is numerically simulated using the Reynolds-averaged Navier–Stokes equations, and the effects of the jet flow and the aerodynamic characteristics of the receiver are taken into consideration. The results indicate that the effect of downwash of the tanker reduces the lift coefficient and decreases the pitching moment coefficient of the receiver. The jet flow of tanker increases the dynamic pressure while decreases the local angle of attack, which increases the pressure difference between the upper and lower surfaces of receiver. Compared with the results without jet, the jet flow can increase the lift and the drag of the receiver and reduces the pitching moment, and even cause the change of rolling moment direction. Therefore, engine jet is an important factor when simulating aerial refueling.

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Szender, Marcin. "SCALED HIGH ANGLE RESEARCH VEHICLE SHARV) PROGRAM." Aviation 8, no. 1 (March 31, 2004): 13–17. http://dx.doi.org/10.3846/16487788.2004.9635864.

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A flight test research program employing a remotely piloted vehicle (RPV) within high angle of attack range has commenced at the Faculty of Power and Aeronautical Engineering of Warsaw University of Technology, Poland. The initial flights of the scaled model of the “Bielik” aircraft were made with the aim to correlate RPV and full‐scale flight stall and departure and spin controllability considering the effects of dynamic scaling laws and Reynolds number. The remotely controlled research aircraft, which is powered by a turbine jet engine and equipped with a flight data recording system, proved to be good source of stability and control data at relatively low cost and without additional risk. The research remotely piloted vehicle and results of its initial flights are presented in this paper.

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Renzi, Cristina. "A genetic algorithm-based integrated design environment for the preliminary design and optimization of aeronautical piston engine components." International Journal of Advanced Manufacturing Technology 86, no. 9-12 (February 13, 2016): 3365–81. http://dx.doi.org/10.1007/s00170-016-8433-7.

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Song, Shu Fang, and Zhen Zhou Lu. "Improved Line Sampling Reliability Analysis Method and its Application." Key Engineering Materials 353-358 (September 2007): 1001–4. http://dx.doi.org/10.4028/www.scientific.net/kem.353-358.1001.

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For reliability analysis of implicit limit state function, an improved line sampling method is presented on the basis of sample simulation in failure region. In the presented method, Markov Chain is employed to simulate the samples located at failure region, and the important direction of line sampling is obtained from these simulated samples. Simultaneously, the simulated samples can be used as the samples for line sampling to evaluate the failure probability. Since the Markov Chain samples are recycled for both determination of the important direction and calculation of the failure probability, the computational cost of the line sampling is reduced greatly. The practical application in reliability analysis for low cycle fatigue life of an aeronautical engine turbine disc structure under 0-takeoff-0 cycle load shows that the presented method is rational and feasible.

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40

Capelotti, P. J. "A preliminary archaeological survey of a Tupolev TB-3 (ANT-6) aircraft on Ostrov Rudol'fa, Zemlya Frantsa-Iosifa, Russia." Polar Record 43, no. 2 (March 28, 2007): 173–77. http://dx.doi.org/10.1017/s0032247407256177.

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The partially snow-covered wreck of specially-modified Arctic variant of the Tupolev TB-3 four-engine bomber was located at Buhkta Teplits [Teplits Bay], Ostrov Rudol'fa [Rudolf Island] in Zemlya Frantsa-Iosifa [Franz Josef Land]. From data gathered, the wreck was subsequently identified as TB-3 (ANT-6) No. 210. This aircraft was piloted by Boris Chukhnovsky during a failed search for another TB-3 (ANT-6), No. 209, which had been lost in August 1937 during an attempt to fly from Moscow over the north pole to the United States. The Teplits TB-3 (ANT-6) wreck represents both the primary aeronautical archaeology of the triumphs and disasters of the Soviet Union's air expeditions to the pole in 1937–1938 and, at 81°47.5'N, is the northernmost aircraft wreck yet identified.

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Li, Lei, Qi Chang, Changcong Zhou, Wenxuan Wang, and Zheng Zhang. "Sensitivity Analysis-Based Optimization: A Case Study with the MTBF of an Aeronautical Hydraulic Pipeline System." International Journal of Computational Methods 17, no. 05 (August 27, 2019): 1940019. http://dx.doi.org/10.1142/s021987621940019x.

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The complex layout and harsh working environment often encountered in aeronautical hydraulic pipeline system (AHPS) result in the requirement of a large number of constraints that are mainly utilized to avoid the damage caused by engine vibration and wing flutter. As a result, improvement of the mean time between failures (MTBF) of the AHPS considering all constraint locations is a costly process, and the management of such large-scale design variables is also frustrating. In this paper, a sensitivity analysis-based optimization is proposed. Firstly, the MTBF of AHPS under stochastic vibration is first deduced according to the first-passage theory-based dynamic strength reliability formula, and the corresponding optimization model is established. Secondly, a multiplicative-dimensional reduction method (M-DRM) based global sensitivity analysis (GSA) method is employed to screen out the constraint location coordinates that have little or no impact on MTBF. Lastly, the MTBF optimization is performed by considering only the remaining significant location coordinates as the design variables. The results show that the proposed sensitivity analysis-based optimization strategy shows advantages in efficiency and effect.

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Cavalier, Jean Claude, Isabelle Berdoyes, and Eric Bouillon. "Composites in Aerospace Industry." Advances in Science and Technology 50 (October 2006): 153–62. http://dx.doi.org/10.4028/www.scientific.net/ast.50.153.

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Since more than twenty five years, composite materials have been with continuously increasing spatial and aeronautical applications requirements. The thermostructural composites materials are of utmost importance for satisfying the needs of mechanical and thermal characteristics at very high temperature and in severe environments. This paper deals with a large variety of applications concerning the aerospace and nuclear applications like nozzles and hot gas valves for Solid Rocket Motor (SRM), brake disks for planes, aerospace turbine engine exhaust nozzles, thermal protection system for reentry vehicles, but also Divert and Attitude Control System (DACS) for interceptors, heat exchangers for hypersonic propulsion systems, plasma facing components for nuclear fusion applications and special components for nuclear fission applications. We will see that Carbon/Carbon and Ceramic Matrix Composites are leading candidate materials for these hightemperature structural applications. This lecture will identify the current state-of-the-art and new technological developments. A description of the main steps of the manufacturing processes will be made.

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43

Rodríguez, Adrián, Asier Fernández, Luís López de Lacalle, and Leonardo Sastoque Pinilla. "Flexible Abrasive Tools for the Deburring and Finishing of Holes in Superalloys." Journal of Manufacturing and Materials Processing 2, no. 4 (December 6, 2018): 82. http://dx.doi.org/10.3390/jmmp2040082.

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Many manufacturing sectors require high surface finishing. After machining operations such as milling or drilling, undesirable burrs or insufficient edge finishing may be generated. For decades, many finishing processes have been on a handmade basis; this fact is accentuated when dealing with complex geometries especially for high value-added parts. In recent years, there has been a tendency towards trying to automate these kinds of processes as far as possible, with repeatability and time/money savings being the main purposes. Based on this idea, the aim of this work was to check new tools and strategies for finishing aeronautical parts, especially critical engine parts made from Inconel 718, a very ductile nickel alloy. Automating the edge finishing of chamfered holes is a complicated but very important goal. In this paper, flexible abrasive tools were used for this purpose. A complete study of different abrasive possibilities was carried out, mainly focusing on roughness analysis and the final edge results obtained.

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Frija, Mounir, Raouf Fathallah, and Lasaad Ben Fkih. "Modeling of the Superficial Laser Shock Peening Treatment Process: Application on a Titanium Aircraft Turbine Engine Blade." Applied Mechanics and Materials 62 (June 2011): 85–94. http://dx.doi.org/10.4028/www.scientific.net/amm.62.85.

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This paper presents a numerical simulation of the Laser Shock Peening (LSP) process using Finite Element Method (FEM). The majority of the controlling parameters of the process have been taken into account. The LSP loading has been characterized by using a repetitive time Gaussian increment pressure applied uniformly at the impacted zone. The used behavior law of the treated material is supposed Johnson Cook elastic-viscous-plastic coupled with damage. The proposed model leads to obtain the surface modifications (i) the in-depth residual stresses profile, (ii) the induced plastic strains profile, (iii) the geometrical surface modification of the impacted zone and (iv) the superficial damage which can be induced in few cases, where the operating conditions are not well chosen and optimized. An aeronautical application of LSP has been carried out on aircraft turbine engine blade made by Ti-6Al-4V super alloy. This mechanical treatment is applied in order to increase the durability of titanium fan blades and decrease their sensitivity to foreign object damage (FOD). The resulting surface compressive residual stress significantly improves the high-cycle-fatigue properties of the component and greatly increases resistance to blade failure. Finally, we studied the feasibility of the influence of LSP treatment on the phenomenon of crack propagation by introducing a superficial crack defect on the edge of the studied blade structure. This is physically consistent and leads to optimize the operating conditions in order to limit the damage risks.

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Boggero, Luca, Sabrina Corpino, Andrea De Martin, Giuseppe Evangelista, Marco Fioriti, and Massimo Sorli. "A Virtual Test Bench of a Parallel Hybrid Propulsion System for UAVs." Aerospace 6, no. 7 (July 2, 2019): 77. http://dx.doi.org/10.3390/aerospace6070077.

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The article proposes the design of a test bench simulator to test a parallel hybrid propulsion architecture for aeronautical applications. The virtual test bench simulates, in a scaled version, the real test bench, designed for a power of about 0.4 MW. After presenting the architecture of the real propulsion system, the virtual test bench is described. The real system is basically composed by a paralleled electric motor and thermal engine which provide mechanical power to the propeller. Saving cost and volume the test bench is composed by electric motors simulates the behaviors of the real propulsion system despite their differences. The dynamic relationships expressing the transmission of torque between the components, and the method of down-sizing the power delivered are highlighted. Particular attention is given to the real inertia actions that must be simulated on the virtual test bench. An application of the proposed methodology is then presented through the simulation of the take-off phase, and the torque time histories, angular velocities and powers generated on the virtual test bench are used to verify the corresponding time histories expected in the real system.

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Chen, Shao-Hsien, and Yu-Lun Ho. "Application of response surface methodology (RSM) to the prediction of the service life of cutters used in milling super-alloy Waspaloy." HKIE Transactions 27, no. 3 (2020): 103–12. http://dx.doi.org/10.33430/v27n3thie-2017-0053.

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Nickel-based materials are widely used in making engine parts, compressor rotors and energy production. Nickel-based materials are resistant to corrosive conditions, and have a high strength in extreme temperatures. They also feature satisfactory mechanical properties in extreme heat. The use of these nickel-based super-alloys is on the rise every day as they have been widely used in military and civilian aeronautical industries in recent years. For this reason, it was the intention of this study to do optimised cutting experiments on Waspaloy in order to identify the significant factors which have impact on the tool life of cutting tools using the response surface methodology (RSM) in regression analysis. Several factors were found in the results that had significant impact on the machining tools’ life, including machining speed, depth, and feed rate. Finally, a regression analysis was adopted to establish a formula for calculating the service life of cutting tools. It was found that the minimum wear was achieved with the cutting speed at V = 33.21 m/min, cutting depth at dp = 0.0367 mm and feed per tooth at Ft = 0.367 mm/tooth.

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Pasha, Mudasar B. A., and Mohammed Kaleemulla. "Processing and Characterization of Aluminum Metal Matrix Composites: An Overview." REVIEWS ON ADVANCED MATERIALS SCIENCE 56, no. 1 (May 1, 2018): 79–90. http://dx.doi.org/10.1515/rams-2018-0039.

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Abstract An increased interest is observed in recent years in the processing of aluminum metal matrix composites (AMMCs) due to their remarkable properties such as light in weight, very high strength, environmental resistance, corrosion resistance, and low thermal coefficient of expansion compared to conventional metal and alloys. This leads to superior compressive strength, for fuel cell applications, low density and low cost for automotive and small engine applications. Homogeneous distribution of the reinforcement phase in turns improves hardness and ultimate tensile strength for lightweight applications, especially aeronautical and high-speed train industries. Uniform distribution of reinforcement directly influences properties and quality of the composite material. And develop a conventional low-cost method of producing metal matrix composites to obtain a homogenous dispersion of reinforcing materials. In this review article, processing and characterization of aluminum metal matrix composites have been reviewed. The Point of convergence is given to the new fabrication techniques, their physical and mechanical characterization. Substantially this review article censoriously reviews the present and past state of understanding of the processing of aluminum metal matrix composites with different reinforcement. The resulting failure mechanisms are discussed. Instructions are given to clarify open questions related to the fabrications of aluminum metal matrix composites.

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Cardone, Massimo, Bonaventura Gargiulo, and Enrico Fornaro. "Modelling and Experimental Validation of a Hybrid Electric Propulsion System for Light Aircraft and Unmanned Aerial Vehicles." Energies 14, no. 13 (July 1, 2021): 3969. http://dx.doi.org/10.3390/en14133969.

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This article presents a numerical model of an aeronautical hybrid electric propulsion system (HEPS) based on an energy method. This model is designed for HEPS with a total power of 100 kW in a parallel configuration intended for ultralight aircraft and unmanned aerial vehicles (UAV). The model involves the interaction between the internal combustion engine (ICE), the electric motor (EM), the lithium battery and the aircraft propeller. This paper also describes an experimental setup that can reproduce some flight phases, or entire missions, for the reference aircraft class. The experimental data, obtained by reproducing two different take-offs, were used for model validation. The model can also simulate anomalous operating conditions. Therefore, the tests chosen for the model validation are characterized by the EM flux weakening (“de-fluxing”). This model is particularly suitable for preliminary stages of design when it is necessary to characterize the hybrid system architecture. Moreover, this model helps with the choice of the main components (e.g., ICE, EM, and transmission gear ratio). The results of the investigation conducted for different battery voltages and EM transmission ratios are shown for the same mission. Despite the highly simplified model, the average margin of error between the experimental and simulated results was generally under 5%.

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Alvarez, Pedro, Lexuri Vázquez, Noelia Ruiz, Pedro Rodríguez, Ana Magaña, Andrea Niklas, and Fernando Santos. "Comparison of Hot Cracking Susceptibility of TIG and Laser Beam Welded Alloy 718 by Varestraint Testing." Metals 9, no. 9 (September 5, 2019): 985. http://dx.doi.org/10.3390/met9090985.

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Reduced hot cracking susceptibility is essential to ensure the flawless manufacturing of nickel superalloys typically employed in welded aircraft engine structures. The hot cracking of precipitation strengthened alloy 718 mainly depends on chemical composition and microstructure resulting from the thermal story. Alloy 718 is usually welded in a solution annealed state. However, even with this thermal treatment, cracks can be induced during standard industrial manufacturing conditions, leading to costly and time-consuming reworking. In this work, the cracking susceptibility of wrought and investment casting alloy 718 is studied by the Varestraint test. The test is performed while applying different welding conditions, i.e., continuous tungsten inert gas (TIG), low frequency pulsed TIG, continuous laser beam welding (LBW) and pulsed LBW. Welding parameters are selected for each welding technology in order to meet the welding quality criteria requested for targeted aeronautical applications, that is, full penetration, minimum cross-sectional welding width and reduced overhang and underfill. Results show that the hot cracking susceptibility of LBW samples determined by the Varestraint test is enhanced due to extended center line hot cracking, resulting in a fish-bone like cracking pattern. On the contrary, the minor effect of material source (wrought or casting), grain size and pulsation is observed. In fact, casting samples with a 30 times coarser grain size have shown better performance than wrought material.

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Passilly, Bruno, and Lara Molenda. "HOT HARDNESS MEASUREMENTS ON MATERIALS UP TO 600 °C DURING THE FIRST HOUR OF USING." Acta Polytechnica CTU Proceedings 27 (June 11, 2020): 160–63. http://dx.doi.org/10.14311/app.2020.27.0160.

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In the aeronautical field, materials are used in severe environmental conditions (temperature, atmosphere, exposure time ...), particularly for engine applications. In order to characterize the use of these materials in the evaluation of their properties, it is necessary to carry out tests in conditions close to their operating environment. Hot hardness is a simple method which can be applied on many different materials such as oxidized layers, coatings, composite materials, brazing cords, additive manufacturing materials. ONERA is developing micromechanical characterization means to carry out Vickers microhardness tests from room temperature up to 600 °C. In principle, a pyramidal punch is applied on the surface of a material and the applied load is continuously measured during indenter’s moving in the material. The material is tested locally under conditions close to the actual conditions of employment. The goal of this research is to improve microindentation in order to achieve temperature test campaigns up to 600 °C under a controlled atmosphere of argon and to validate a method to produce a series of results during the first hour of using up to 600 °C. Stainless material is studied to compare the evolution of its hot hardness properties versus different parameters such as load, holding time at the maximum load, atmosphere, and thermal duration. A discussion about these measurements and the technical limits of hot hardness technology is presented.

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Journal articles on the topic 'Aeronautical engine'

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