Relevant bibliographies by topics / Nimonic 90

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Nimonic 90'

Author: Grafiati
Published: 6 September 2023
Last updated: 7 September 2023

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Journal articles on the topic "Nimonic 90"

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Lou, D. C., O. M. Akselsen, J. K. Solberg, M. I. Onsoien, J. Berget, and N. Dahl. "Silicon-boronising of Nimonic 90 superalloy." Surface and Coatings Technology 200, no. 11 (March 2006): 3582–89. http://dx.doi.org/10.1016/j.surfcoat.2005.03.030.

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Singh Nain, S., R. Sai, P. Sihag, S. Vambol, and V. Vambol. "Use of machine learning algorithm for the better prediction of SR peculiarities of WEDM of Nimonic-90 superalloy." Archives of Materials Science and Engineering 1, no. 95 (January 1, 2019): 12–19. http://dx.doi.org/10.5604/01.3001.0013.1422.

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Sharma, Sahil, Umesh Kumar Vates, and Amit Bansal. "Optimization of machining characteristics for EDM of different nickel-based alloys by embodying of fuzzy, grey relational and Taguchi technique." World Journal of Engineering 18, no. 1 (October 19, 2020): 23–36. http://dx.doi.org/10.1108/wje-07-2020-0262.

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Purpose In the current exploration, the machinability of three different nickel-based super-alloy materials (Inconel 625, Inconel 718 and Nimonic 90) was experimentally investigated by using a die-sinking electrical discharge machining (EDM). The effect of changing important input process parameters such as pulse on time (Ton), off time (Toff), peak current (Ip) and tool rotation (TR) was investigated to get optimum machining characteristics such as material removal rate, roughness, electrode wear rate and overcut. Design/methodology/approach Experimentation has been performed by using Taguchi L9 orthogonal design. An integrated route of fuzzy and grey relational analysis approach with Taguchi’s philosophy has been intended for the simultaneous optimization of machining output parameters. Findings The most approbatory factors for machining setting have been attained as: (Ton = 100 µs, Toff = 25 µs, Ip = 14 A, TR = 725 rpm) for machining of Inconel 625 and Inconel 718; and (Ton = 100 µs, Toff = 75 µs, Ip = 14 A, TR = 925 rpm) for machining of the Nimonic 90 material. Peak current has been observed as an overall influencing factor to achieve better machining process. Microstructural study through SEM has also been carried out to figure out the surface morphology for the EDMed Ni-based super alloys. Originality/value The proposed machining variables and methodology has never been presented for Nimonic 90 alloy on die-sinking EDM.
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Marchionni, M., Hellmuth Klingelhöffer, Hans Joachim Kühn, T. Ranucci, and Kathrin Matzak. "Thermo-Mechanical Fatigue of the Nickel–Base Superalloy Nimonic 90." Key Engineering Materials 345-346 (August 2007): 347–50. http://dx.doi.org/10.4028/www.scientific.net/kem.345-346.347.

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The thermo-mechanical fatigue (TMF) behaviour of the Nimonic 90 Nickel base superalloy has been investigated within two laboratories. In-phase-tests (IP) where the maximum mechanical strain occurs at the maximum temperature (850°C), and 180°-out-of-phase-tests (180° OP) where the maximum mechanical strain coincides with the minimum temperature (400°C) have been applied. All tests were carried out at varying mechanical strain ranges with a constant strain ratio of Rε = - 1. A temperature rate of 5 K/s was used throughout the whole cycle without any additional cooling system during decreasing temperature. The fatigue life of 180° OP tests is longer compared to identical IP tests. The stress / mechanical strain hysteresis loops are completely different and some characteristic values are compared to each other. The fracture surfaces observed show that fatigue crack (or cracks) starts on the external surface and propagates inwards. The fractures of 180° OP tests are transgranular showing the presence of fatigue striations, while the fractures of IP tests are mixed transgranular and intergranular with no fatigue striations.
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Harrison, G. F., W. J. Evans, and M. R. Winstone. "Comparison of empirical and physical deformation maps for Nimonic 90." Materials Science and Technology 25, no. 2 (February 2009): 249–57. http://dx.doi.org/10.1179/174328408x369339.

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Ahamed J, Fakrudeen Ali, and Pandivelan Chinnaiyan. "Studies on Finite Element Analysis in Hydroforming of Nimonic 90 Sheet." Mathematics 11, no. 11 (May 24, 2023): 2437. http://dx.doi.org/10.3390/math11112437.

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The primary goal of this study was to investigate the formability of Nimonic 90 sheet which performs well at high temperatures and pressures, making it ideal for applications in the aerospace, processing, and manufacturing industries. In this present study, finite element analysis (FEA) and optimization of process parameters for formability of Nimonic 90 in sheet hydroforming were investigated. The material’s mechanical properties were obtained by uniaxial tensile tests as per the standard ASTM E8/E8M. The sheet hydroforming process was first simulated to obtain maximum pressure (53.46 MPa) using the FEA and was then validated using an experiment. The maximum pressure obtained was 50.5 MPa in experimentation. Since fully experimental or simulation designs are impractical, the Box–Behnken design (BBD) was used to investigate various process parameters. Formability was measured by the forming limit diagram (FLD) and maximum deformation achieved without failure. Analysis of variance (ANOVA) results also revealed that pressure and thickness were the most effective parameters for achieving maximum deformation without failure. Response surface methodology (RSM) optimizer was used to predict optimized process parameter to achieve maximized response (deformation) without failure. Experimental validation was carried out for the optimized parameters. The percentage of error between experimental and simulation results for maximum deformation was less than 5%. The findings revealed that all the aspects in the presented regression model and FEM simulation were effective on response values.
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Alhodaib, Aiyeshah, Pragya Shandilya, Arun Kumar Rouniyar, and Himanshu Bisaria. "Experimental Investigation on Silicon Powder Mixed-EDM of Nimonic-90 Superalloy." Metals 11, no. 11 (October 20, 2021): 1673. http://dx.doi.org/10.3390/met11111673.

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Powder mixed electrical discharge machining (PM-EDM) is a technological advancement in electrical discharge machining (EDM) processes where fine powder is added to dielectric to improve the machining rate and surface quality. In this paper, machining of Nimonic-90 was carried out using fabricated PM-EDM, setup by adding silicon powder to kerosene oil. The influence of four input process parameters viz. powder concentration (PC), discharge current (IP), spark on duration (SON), and spark off duration (SOFF) has been investigated on surface roughness and recast layer thickness. L9 Taguchi orthogonal and grey relational analysis have been employed for experimental design and multi-response optimization, respectively. With the addition of silicon powder to kerosene oil, a significant decrease in surface roughness and recast layer thickness was noticed, as compared to pure kerosene. Spark on duration was the most significant parameter for both surface roughness and the recast layer thickness. The minimum surface roughness (3.107 µm) and the thinnest recast layer (14.926 μm) were obtained at optimum process parameters i.e., PC = 12 g/L, IP = 3 A, SON = 35 μs, and SOFF = 49 μs using grey relational analysis.
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Cagliyan, E., and F. Walter. "Metallurgical Failure Investigation of Overheated Brackets Made of Nimonic Alloy 90." Practical Metallography 52, no. 11 (November 16, 2015): 665–78. http://dx.doi.org/10.3139/147.110251.

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Özgün, Ö., H. Ö. Gülsoy, F. Findik, and R. Yilmaz. "Microstructure and mechanical properties of injection moulded Nimonic-90 superalloy parts." Powder Metallurgy 55, no. 5 (December 2012): 405–14. http://dx.doi.org/10.1179/1743290112y.0000000010.

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Goel, A. K., N. D. Sharma, R. K. Mohindra, P. K. Ghosh, and M. C. Bhatnagar. "Surface composition and microhardening in nitrogen and boron implanted nimonic-90 alloy." Thin Solid Films 213, no. 2 (June 1992): 192–96. http://dx.doi.org/10.1016/0040-6090(92)90282-g.

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Dissertations / Theses on the topic "Nimonic 90"

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"Machining of nimonic 90 using sustainable techniques and modelling for the specific cutting energy." Thesis, 2018. http://localhost:8080/iit/handle/2074/7718.

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Book chapters on the topic "Nimonic 90"

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Cagliyan, E., F. Walter, and E. Engert. "Metallurgical Failure Investigation of Overheated Brackets Made of Nimonic Alloy 90 | Metallurgische Schadensuntersuchung an überhitzten Befestigungselementen aus der Legierung Nimonic 90." In Schadensfallanalysen metallischer Bauteile 2, 253–67. 2nd ed. München: Carl Hanser Verlag GmbH & Co. KG, 2021. http://dx.doi.org/10.3139/9783446470538.024.

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Marchionni, M., Hellmuth Klingelhöffer, Hans Joachim Kühn, T. Ranucci, and Kathrin Matzak. "Thermo-Mechanical Fatigue of the Nickel–Base Superalloy Nimonic 90." In The Mechanical Behavior of Materials X, 347–50. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-440-5.347.

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Conference papers on the topic "Nimonic 90"

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Subbarao, Rayapati, and Nityanando Mahato. "Computational Analysis on the Use of Various Nimonic Alloys As Gas Turbine Blade Materials." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2398.

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Abstract Blade failure is triggering more problems to the gas turbine engines, while being used in airline and jet engines. In this paper, causes of blade failure with respect to various Nimonic alloys is investigated by performing structural and thermal analyses. Using Ansys, both these analyses on turbine blade are carried out, which is utilized for determining equivalent stresses, deformation and thermal stresses by applying different turbine inlet temperatures and pressures. Turbine blade model is prepared using Solid Works. The computational model is then imported to Ansys workbench. Before importing to the solver, the domain is meshed and boundary conditions are applied. Properties like coefficient of thermal expansion and thermal conductivity are given as material conditions. Ambient temperature, rotational speed, inlet pressure and temperature are considered as boundary conditions. For various configurations and alloy materials, deformation, strain and thermal stresses are plotted and analyzed. After thorough investigation, the turbine blade failure region is identified and the trend is compared for different input temperatures and pressures. At the root of the blade, the stresses and strains are found to be more. Of all the materials considered, Nimonic-90 has less deformation and thermal stresses. Nimonic-80A has more equivalent stress, strain and deformation. Out of the other two materials, Nimonic-263 is showing favourable properties than Nimonic-105. However, the values of stresses and strains are comparable. Thus the present work is beneficial in identifying suitable Nimonic alloy as gas turbine blade material in order to avoid the frequent turbine blade failures.
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Lortz, W., and Radu Pavel. "Process Mechanics – a Guide for Industry 4.0: Modelling Cutting of Nimonic 90 and Ti-6Al-4V." In ASME 2022 17th International Manufacturing Science and Engineering Conference. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/msec2022-85443.

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Abstract The chip formation models developed to date give no exact representation of the physics phenomena occurring during the complex machine cutting process. Despite the large number of investigations and simulations, there is still limited clarity of the real chip formation process. The models try to solve the plastic flow through force or stress simulation, without proper regard to adequate process mechanics. Due to these circumstances, practical evidence is missing. Analyzing this situation very carefully, some scientists founded the Industry 4.0 initiative to create scientific space with new opportunities. Whereas second and third industrial revolutions have been focused on organization and automation — Industry 4.0 is focused on technology, data integration and artificial intelligence (AI). However, before teaching a computer AI, the adequate process mechanics should be systematically developed and understood. This paper presents the complex process mechanics of chip formation with non-linear conditions in the metal microstructure, with two different friction zones, with self-hardening or temperatures effects. These entire phenomena can’t be solved separately because they have an interdependent relationship. The developed mathematical equations for strain and stress lead to square grid deformation in the chip formation zone, and this grid deformation does not disappear after completing the process, so that the theoretical development can be compared with practical results. This will be presented for two different materials Nimonic 90 and Ti-6Al-4V. For Nimonic 90 a built-up-edge (BUE) will be identified, and this is based on the stream-line inflow-angle. Quite contrary is the chip formation process for Ti-6Al-4V. A diffusion process in the interface chip-tool take place resulting in a self-blockade with segmented chip. In addition, the developed temperatures during cutting could be estimated and will be presented for the two different creep-resistant alloys. Finally, a high agreement between the theoretical and experimental results could be documented.
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Jawahar, M., Ch Sridhar Reddy, and Ch Srinivas. "Multi objective prediction and optimization of process parameters in the NPMEDM of Nimonic 90 by using Taguchi-grey relational analysis." In INTERNATIONAL CONFERENCE ON RESEARCH IN SCIENCES, ENGINEERING & TECHNOLOGY. AIP Publishing, 2022. http://dx.doi.org/10.1063/5.0081935.

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Muthu Shanmugam, Esakki, and Raghu V. Prakash. "The Effect of Creep-Fatigue Interactions on Thermo-Mechanical Fatigue Life and Reliability Estimates for a Typical Gas Turbine Engine Component." In ASME 2019 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/imece2019-11174.

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Abstract The low cycle fatigue-creep damage is the main parameter for the failures of gas turbine components under high temperature and cyclic loading. In this work, different combinations of Creep-Fatigue damage are introduced and checked for its impact on the Turbine life and its reliability. Linear and Non-Linear Creep-Fatigue combinations were considered as part of this work. The Turbine rotor under present study is made out of Nimonic-90 nickel base alloy forging. Weibull distribution method was used to study the reliability. It was found that, the reliability reduces from 99% to 25% when creep damage component is increased from 20% to 40% for a fixed Turbine life. The damage factor was found more in above linear Creep-Fatigue curve and less in below linear Creep-Fatigue curve.
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Rajeevalochanam, Prathapanayaka, S. N. Agnimitra Sunkara, Balamurugan Mayandi, Bala Venkata Ganesh Banda, Veera Sesha Kumar Chappati, and Kishor Kumar. "Design of Highly Loaded Turbine Stage for Small Gas Turbine Engine." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56178.

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Aero-thermodynamic and mechanical design of a single stage axial turbine stage has been carried out for small gas turbine engine in Propulsion Division, CSIR-NAL. From the engine design configuration extract, it is envisaged that the single stage axial gas turbine operating close to 50500 rpm and at an elevated temperature of 1095K would meet the power requirement of mixed flow compressor of 385kW. This paper presents the aero-thermodynamic, mechanical design and analysis of a single stage highly loaded axial turbine stage with a stage loading coefficient of 1.45 and a flow coefficient of 0.67. The mean-line and detailed 3D aero-thermodynamic design is carried out using commercially available dedicated turbomachinery design codes Axial® and Axcent™ of Concepts NREC. The number of blades of the rotor and stator are 50 & 19 respectively. The turbine stage has undergone a series of design improvements. The final configuration of single stage turbine is analyzed using commercially available RANS CFD software ANSYS-CFX™ and NUMECAFINE™/Turbo flow solver. The design is carried out by aiming 88% total-to-total efficiency. Detailed 3D-RANS CFD analysis of the turbine shows that, the design requirements of turbine are achieved with enhanced efficiency of 90%. Mechanical design & analysis of the turbine stage is carried out using ANSYS-Mechanical™ software. Nimonic-90 material is selected for fabrication. Detailed non-linear steady thermal-structural analysis is carried out for both stator assembly and rotor BLISK. Burst margin of rotor disk is estimated to be around 63% at design speed.
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Oguntade, Habeeb Idowu, Gordon E. Andrews, Alan Burns, Derek Ingham, and Mohammed Pourkashanian. "Predictions of Effusion Cooling With Conjugate Heat Transfer." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45417.

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This work involves CFD conjugate heat transfer modelling of the geometrical design influence on effusion cooling. Experimental data was modelled for the overall effusion film cooling effectiveness using Nimonic 75 walls with imbedded thermocouples. The Fluent CFD code was used to investigate the experimental configuration for a 10×10 square array of holes with a 90° injection angle. In the computational predictions, 10000ppm of methane tracer gas was added to the coolant and the concentration at the wall allowed the adiabatic cooling effectiveness of the effusion film cooling to be predicted separately from the overall wall cooling effectiveness. The predicted overall cooling effectiveness results show that the wall was locally at a uniform temperature, but the axial development of the cooling film does result in a gradual reduction of the wall temperature with axial distance. The predictions show that the heating of the coolant by the hot wall was equally split between the hole approach flow on the backside of the wall and inside the film cooling holes. This heating changed the conditions in the film cooling layer from those of the equivalent adiabatic wall. There was good agreement between the conjugate heat transfer predictions of the overall cooling effectiveness with the experimental data.
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Soltan Mohammad Lou, Bita, Mohammad Pourgol-Mohammad, and Mojtaba Yazdani. "Life Assessment of Gas Turbine Blades Under Creep Failure Mechanism Considering Humidity." In ASME 2018 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/imece2018-87883.

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Gas turbines are the most important components in thermal power plants, and these components such as turbine has been studied carefully. Gas turbine components operate predominantly under elevated temperature and high stress, and consequently gradual deformation becomes temporally inevitable. In turbine blades, creep is common failure mechanism, and it is an important factor for design assessment. The gas turbine blade is a component operating at high elevated temperatures, requiring a cooling systems to reduce the temperature. Common power enhancement approach is to spray water into compressor, and it is how humidity becomes an important factor in creep failure mechanism. The humidity variability results in temperature level change during the turbine operation, potentially affecting the blades creep life. In this paper, first different creep life prediction models were classified, and then a new model is proposed for creep life considering humidity based on Arrhenius equation. In our study, failure criterion is rupture. As a case study, the creep life of Nimonic-90 alloy turbine blade was predicted using proposed method and compared with FEA results which collected by literature surveys. Proposed model is capable of predicting creep life with only knowing dry temperature (WAR = 0), and there is no need to measure blade temperature variation during operation. The influence of humidity (%WAR) were studied on turbine blades creep life, and results show that creep life of turbine blade increase with increasing humidity percentage.
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Oguntade, H. I., G. E. Andrews, A. D. Burns, D. B. Ingham, and M. Pourkashanian. "Conjugate Heat Transfer Predictions of Effusion Cooling With Shaped Trench Outlet." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25257.

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The influence of the application of a filleted shape trench hole outlet on the overall cooling effectiveness of a flat hot effusion Nimonic 75 metal wall with a 770K hot gas crossflow was investigated using conjugate heat transfer (CHT) CFD and the Ansys Fluent code. The baseline effusion wall had ten rows of holes with an X/D of 4.65 and a wall thickness of 6.35mm with normal injection holes. This was modelled and showed good agreement with the experimental results for overall cooling effectiveness. The aim of the work was to use these validated CHT CFD procedures to investigate improved hole outlet designs with 30° inclined effusion of X/D = 4.65 with improved hole outlet designs using various trench designs. The predictions involved the use of a gas tracer in the cooling air to simultaneously separate the predicted adiabatic film cooling effectiveness from the overall cooling effectiveness. The shaped trench outlet effusion wall designs were predicted to have a superior performance compared with the 90° effusion wall cooling design. This was due to the improved adiabatic film cooling. An increase in the trailing edge vertical wall depth of the trenched effusion wall design from 0.5D to 0.75D increased the overall and adiabatic cooling effectiveness. The filleted shaped trench outlet effusion wall only required a small amount of cooling air to achieve a satisfactory cooling performance. It was predicted that this new effusion wall design could enable a significant reduction in the coolant mass flow for cooled metal surfaces in in future high performance gas turbines.
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