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Relevant bibliographies by topics / Structural analysis of an engine

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Academic literature on the topic 'Structural analysis of an engine'

Author: Grafiati

Published: 4 June 2021

Last updated: 10 February 2022

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Journal articles on the topic "Structural analysis of an engine"

1

Zhang, Hong Xin, Yu Qin Jiao, Tie Zhu Zhang, and Lian Jun Cheng. "Structural Principle of Hydraulic Engine." Applied Mechanics and Materials 709 (December 2014): 28–31. http://dx.doi.org/10.4028/www.scientific.net/amm.709.28.

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Hydraulic engines can be widely used in many fields, such as agricultural machinery, construction machinery, duty vehicle, and many other fixing or mobile devices. The development analysis and study on their structural principle, technical and operational characteristics will be undoubtedly very useful for putting forward new type hydraulic engines. The structural principle of Hydraulic Free Piston Engine, Hydraulic Confined Piston Engine was introduced. The structural principle of Half Crank Hydraulic Engine (HCHE), which inherits the merits of traditional engine, HFPE and HCPE, was put forward.

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Ji, Yan Ping, Ping Sun, and Si Bo Zhao. "Analysis of Temperature Field of High Speed Diesel Engine Parts and their Structural Optimization." Applied Mechanics and Materials 490-491 (January 2014): 1003–7. http://dx.doi.org/10.4028/www.scientific.net/amm.490-491.1003.

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The analysis of structure and performance of internal combustion engine is presented in this paper from the following two aspects: the thermal load of I. C. Engine and the thermal efficiency of diesel engines. Firstly, the thermal load of key parts of I. C. Engine as well as the evaluation parameters of which are introduced briefly. Furthermore, based on the factors influencing the heat transfer process of internal combustion engine, the current research situation of internal combustion engine work process and heat balance for combustion chamber components, and the whole engine using numerical simulation method is described, while the coupled study of internal combustion engine components is developing trends of internal combustion engine heat balance study in the future.

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Han, Moon-Sik, and Jae-Ung Cho. "Structural Analysis of Engine Mounting Bracket." Journal of manufacturing engineering & technology 21, no. 4 (August 15, 2012): 525–31. http://dx.doi.org/10.7735/ksmte.2012.21.4.525.

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Dave Marmik M, Dave Marmik M., and Kothari Kartik D. "Static Structure Analysis of Diesel Engine Camshaft." International Journal of Scientific Research 2, no. 5 (June 1, 2012): 208–9. http://dx.doi.org/10.15373/22778179/may2013/69.

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Cheng, Yuqiang, and Jianjun Wu. "Particle swarm algorithm-based damage-mitigating control law analysis and synthesis for liquid-propellant rocket engine." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 10 (October 31, 2018): 3810–18. http://dx.doi.org/10.1177/0954410018806080.

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The damage-mitigating control is a novel technique to ameliorate the reliability and safety of liquid-propellant rocket engines by achieving an optimized trade-off level between overall dynamic performance of the liquid-propellant rocket engine and structural durability of some selected critical damageable components under the condition of no impact on the achievement of the launch and flight mission. Thus, it is needed to be solved for the damage-mitigating control that the global optimization of the best trade-off between the damage of the critical damageable components and the performance of rocket engine. The major challenge should focus on: (i) to construct model of a certain rocket engine system dynamics, critical components structural dynamics, and damage dynamics; (ii) to optimize open loop feed-forward control law based on liquid-propellant rocket engine system dynamic model, structural and damage dynamics model, by using particle swarm optimization algorithm; (iii) to synthesize an intelligent damage-mitigating control system using the optimized open loop control law. In this paper, synthesis procedure of damage mitigation is introduced; structure and damage dynamic model of damageable components are formulated. The results of the simulation computation show that the synthesized control laws are implemented and achieve the effect of damage mitigating for the liquid-propellant rocket engine. It can provide important theoretical and practical value not only for improving the safety and reliability of the liquid-propellant rocket engine, but also for the complex thermo-flow-mechanical systems such as airplane engines, automobile engines, and fossil-fueled power plant because their service life is very critical too.

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McKnight, R. L. "Structural Analysis Applications." Journal of Engineering for Gas Turbines and Power 111, no. 2 (April 1, 1989): 271–78. http://dx.doi.org/10.1115/1.3240248.

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The programs in the structural analysis area of the HOST program emphasized the generation of computer codes for performing three-dimensional inelastic analysis with more accuracy and less manpower. This paper presents the application of that technology to Aircraft Gas Turbine Engine (AGTE) components: combustors, turbine blades, and vanes. Previous limitations will be reviewed and the breakthrough technology highlighted. The synergism and spillover of the program will be demonstrated by reviewing applications to thermal barrier coatings analysis and the SSME HPFTP turbine blade. These applications show that this technology has increased the ability of the AGTE designer to be more innovative, productive, and accurate.

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Lalvani, J. Isaac Joshua Ramesh, E. Prakash, M. Parthasarathy, S. Jayaraj, and K. Annamalai. "Structural Analysis on Swirling Grooved SCC Piston." Advanced Materials Research 984-985 (July 2014): 452–55. http://dx.doi.org/10.4028/www.scientific.net/amr.984-985.452.

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This journal describes a study on the structural effects of DI diesel engine conventional piston and modified pistons. To enhance the combustion efficiency of the engine conventional piston has been modified as shallow depth piston bowl with swirling grooves on the piston crown. Three different widths (5.5mm, 6.5mm and 7.5mm) and constant depth (00 to 50) swirling grooves added on the shallow depth combustion chambered piston crown. The conventional piston and modified pistons has been modeled in CATIA software and structural analysis done in ANSYS 14. In structural analysis observed that deformation for the modified pistons are same and negligible as compared to the conventional piston.

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Du, Xian Feng, Zhi Jun Li, Feng Rong Bi, Jun Hong Zhang, Xia Wang, and Kang Shao. "Structural Topography Optimization of Engine Block to Minimize Vibration Based on Sensitivity Analysis." Advanced Materials Research 291-294 (July 2011): 318–26. http://dx.doi.org/10.4028/www.scientific.net/amr.291-294.318.

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This paper describes the structural optimization technique with FEM topography optimization technology, the design shape of engine components have been optimized based on the sensitivity analysis, and the purpose is to minimize the vibration of engine block. The process of structural optimization display that the vibration on FEM models of engine block as boundary conditions for subsequent topography optimization were used to be an output from dynamic response analysis, and the loads exerted on the FEM models are acquired from the multibody dynamics system, and topography optimization is performed to detect the effective design parameters of engine block shape to structural strength, to reduce the vibration velocity intensity. This paper presents today’s computer design capabilities in the simulation of the dynamic and vibration behaviour of engine and focuses on the relative merits of modification and full-scale structural optimization of engine, together with the creation of new low-vibration designs. The results verify the analysis, assessment and vibration optimization of the engine.

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Avdeev, S. V. "Mathematical model of turbofan engine weight estimation taking into account the engine configuration and size." VESTNIK of Samara University. Aerospace and Mechanical Engineering 20, no. 1 (April 20, 2021): 5–13. http://dx.doi.org/10.18287/2541-7533-2021-20-1-5-13.

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The paper presents a new correlation-regression model of estimating the turbofan engine weight considering the effect of the engines design schemes and dimensions. The purpose of this study was to improve the efficiency of the conceptual design process for aircraft gas turbine engines. Information on 183 modern turbofan engines was gathered using the available sources: publications, official websites, reference books etc. The statistic information included the values of the total engine air flow, the total turbine inlet gas temperature, the overall pressure ratio and the bypass ratio, as well as information on the structural layout of each engine. The engines and the related statistics were classified according to their structural layout and size. Size classification was based on the value of the compressor outlet air flow through the gas generator given by the parameters behind the compressor. Depending on the value of this criterion, the engines were divided into three groups: small-sized, medium-sized gas turbine engines, and large gas turbine engines. In terms of the structural layout, all engines were divided into three groups: turbofan engines without a mixing chamber, engines with a mixing chamber and afterburning turbofan engines. Statistical factors of the improved weight model were found for the respective groups of engines, considering their design and size. The coefficients of the developed model were determined by minimizing the standard deviations. Regression analysis was carried out to assess the quality of the developed model. The relative average error of approximation of the developed model was 8%, the correlation coefficient was 0,99, and the standard deviation was 10,2%. The model was found to be relevant and reliable according to Fisher's test. The obtained model can be used to assess the engine weight at the stage of conceptual design and for its optimization as part of an aircraft.

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Xie, Qiang, Cun Yun Pan, Hu Chen, Zheng Zhou Zhang, and Lei Zhang. "Structural Modal Analysis of a New Twin-Rotor Piston Engine." Applied Mechanics and Materials 390 (August 2013): 256–60. http://dx.doi.org/10.4028/www.scientific.net/amm.390.256.

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With the finite analysis software ANSYS, the key parts and the whole structure of a new twin-rotor piston engine is analyzed, and then the structural modal parameters are obtained by using finite element method in the cases of free modality. Furthermore, the natural vibration characteristics of the twin-rotor piston engine are analyzed, as well as the influence of structural parameters on vibration transfer and radiation noise. The research is expected to lay a foundation for the vibration reduction design of the twin-rotor piston engine.

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Dissertations / Theses on the topic "Structural analysis of an engine"

1

Vogel, Ryan N. "Structural-Acoustic Analysis and Optimization of Embedded Exhaust-Washed Structures." Wright State University / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=wright1374833633.

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Ercan, Taylan. "Thermodynamic And Structural Design And Analysis Of A Novel Turbo Rotary Engine." Master's thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/12606482/index.pdf.

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A novel turbo rotary engine, operating according to a novel thermodynamic cycle, having an efficient compression phase, a limited temperature combustion phase followed by a long power extraction phase is designed. Thermodynamic and structural design and analysis of this novel engine is carried out and two prototypes are manufactured according to these analysis. High performance figures such as torque, power and low specific fuel consumption are calculated. Also the component tests of the manufactured prototypes are completed and their results are demonstrated.

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Boiani, Davide. "Finite element structural and thermal analysis of JT9D turbofan engine first stage turbine blade." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2017. http://amslaurea.unibo.it/12566/.

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The objective of this work was to conduct a preliminary finite element static structural and transient thermal analyses of a first stage turbine blade which was previously assembled on a Pratt & Whitney JT9D-7A turbofan engine. This turbine blade was obtained from a collector of aircraft scrap parts. After an extensive theoretical background on airbreathing jet engines and materials used for such components, the process behind the creation of a 3D model was explained. The laser scanning technique and a piezoeletric digitizer were employed to recreate the blade inside a 3D modelling software. The model was then imported into the finite element analysis software ANSYS; the analyses were performed, and the most interesting results were evaluated. The structural and thermal results were found to be congruous with the literature on similar applications of components with the same material, and appear to be a realistic representation of the blade behaviour inside the first stage turbine environment.

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Aran, Gokhan. "Aerothermodynamic Analysis And Design Of A Rolling Piston Engine." Master's thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608449/index.pdf.

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A rolling piston engine, operating according to a novel thermodynamic cycle is designed. Thermodynamic and structural analysis of this novel engine is carried out and thermodynamic and structural variables of the engine were calculated. The losses in the engine, friction and leakage were calculated and their effects on the engine were demonstrated.

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Deshpande, Aditya S. "The use of geometric uncertainty data in aero engine structural analysis and design." Thesis, University of Southampton, 2013. https://eprints.soton.ac.uk/361705/.

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A gas turbine disc has three critical regions for which lifing calculations are essential: the assembly holes or weld areas, the hub region, and the blade-disc attachment area. Typically, a firtree joint is used to attach the blades to the turbine disc instead of a dove-tail joint, which is commonly used for compressor discs. A firtree joint involves contact between two surfaces at more than one location which makes the joint more difficult to design. Large loads generated due to the centrifugal action of the disc and associated blades are distributed over multiple areas of contact within the joint. All of the contacts in a firtree joint are required to be engaged simultaneously when the blades are loaded. However, slight variations in the manufacture of these components can have an impact on this loading. It is observed that small changes in the geometric entities representing contact between the two bodies can result in variations in the stress distribution near contact edges and the notch regions. Even though manufacturing processes have advanced considerably in the last few decades, the variations in geometry due to these processes cannot be completely eliminated. Hence, it is necessary to design such components in the presence of uncertainties in order to minimise the variation observed in their performance. In this work, the variations in geometry due to the manufacturing processes used to produce firtree joints between a gas turbine blade and the disc are evaluated. These variations are represented in two different ways using measurement data of firtree joints obtained from a coordinate measuring machine (CMM): (i) the variation for the pressure angle in the firtree joint is extracted from a simple curve fit and (ii) using the same measurement data, the unevenness of the pressure surfaces is represented using a Fourier series after filtering noise components. A parametric computer aided design (CAD) model which represents the manufacturing variability is implemented using Siemens NX. Non-smooth surfaces are also numerically generated by assuming the surface profile to be a random process. Two- and three-dimensional elastic stress analysis is carried out on the firtree joint using the finite element code, Abaqus and the variations observed in the notch stresses with changing pressure angle are extracted. A surrogate assisted multiobjective optimisation is performed on the firtree joint based on the robustness principles. Kriging based models are used to build a surrogate for notch stresses and the non-dominated sorting genetic algorithm-II (NSGA-II) is implemented to perform a multiobjective optimisation in order to minimise the mean and standard deviation of the notch stresses. An iterative search algorithm that updates the Kriging models with equally spaced infill points from the predicted Pareto front is adopted. Finally, a new design of the firtree joint is obtained which has better performance with respect to the variation in the notch stresses due to manufacturing uncertainties.

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Gruenert, Thomas. "Analysis of crankshaft-crankcase interaction for the prediction of the dynamic structural response and noise radiation of IC-engine structures." Thesis, Loughborough University, 2000. https://dspace.lboro.ac.uk/2134/27786.

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This thesis presents research work which is concerned with the development of analytical and numerical methods for the dynamic analysis of the crankshaft-crankcase assembly. The effects of interaction of crankshaft and crankcase on the dynamic response of an IC engine block structure are studied. These methods are especially attractive for the simulation of the steady state response of rotating systems with many degrees of freedom which are forced by multiple periodic excitations. A major novelty of the methods is the ability to model the system non-linearities successfully as frequency dependent properties.

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Sarwade, Rohit Foster Winfred A. "Life prediction analysis of a subscale rocket engine combustor using a fluid-thermal-structural model." Auburn, Ala., 2006. http://repo.lib.auburn.edu/2006%20Spring/master's/SARWADE_ROHIT_49.pdf.

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Gozutok, Tanzer. "Life Assessment Of A Stationary Jet Engine Component With A Three-dimensional Structural Model." Master's thesis, METU, 2004. http://etd.lib.metu.edu.tr/upload/2/12604894/index.pdf.

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In this thesis, fatigue life of a stationary component of F110-GE-100 jet engine is assessed. Three-dimensional finite element model of the component itself and the neighboring components are modeled by using a finite element package program, ANSYS, in order to perform thermal, stress and fracture mechanics analyses. Coupled-field (thermal-stress) analysis is performed to identify fracture-critical locations and to describe the stress histories of the components. After determining the critical location, fracture mechanics calculations are performed by modeling a crack of various lengths at the critical locations with FRANC3D in order to calculate mode I and II stress intensity factors and geometry factors beta. Combining the outputs of coupled-field and fracture mechanics analyses, fatigue lives and creep rupture times are calculated with a crack growth life prediction program, AFGROW. A linear damage summation method is used to assess the fatigue life of the component of interest.

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Zelko, Lukáš. "Píst zážehového motoru pro 3-D tisk." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2019. http://www.nusl.cz/ntk/nusl-400468.

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The goal of the thesis was to design a piston manufactured by conventional method and subsequently adjusted one for additive manufacturing. Beside the designs, thermo-structural model was created for both pistons, considering maximal loading of the engine. Analysis evaluation showed the possibility of further application of the new technology in comparison to current one, within automotive industry.

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Berrington, Rosalind. "Analytical methods for the analysis of bolted flanged joints in aero-engine structures." Thesis, University of Oxford, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.496825.

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Books on the topic "Structural analysis of an engine"

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Chamis, C. C. Computational engine structural analysis. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1986.

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Chamis, C. C. Computational structural mechanics for engine structures. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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Greuter, Ernst. Engine failure analysis: Internal combustion engine failures and their causes. Warrendale, Pa: SAE International, 2012.

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Chamis, C. C. Advanced methods for 3-D inelastic structural analysis for hot engine structures. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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Chamis, C. C. Advanced methods for 3-D inelastic structural analysis for hot engine structures. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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Chamis, C. C. Advanced methods for 3-D inelastic structural analysis for hot engine structures. [Washington, DC]: National Aeronautics and Space Administration, 1989.

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Foley, Michael J. Space shuttle main engine structural analysis and data reduction/evaluation.: Final report. Huntsville, AL: Lockheed Missiles & Space Co., Inc., Huntsville Engineering Center, 1989.

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Abdul-Aziz, Ali. Structural evaluation of a space main engine (SSME) high pressure fuel turbopump turbine blade. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

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Abdul-Aziz, Ali. Structural evaluation of a space main engine (SSME) high pressure fuel turbopump turbine blade. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

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Pian, Theodore H. H. Advanced stress analysis methods applicable to turbine engine structures. [Washington, DC]: National Aeronautics and Space Administration, 1991.

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Book chapters on the topic "Structural analysis of an engine"

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Chamis, C. C. "Engine Probabilistic Structural Analysis Methods Reliability/Certification." In Nonlinear Stochastic Mechanics, 115–29. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84789-9_10.

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Balmes, Etienne, Mathieu Corus, Stéphane Baumhauer, Pierrick Jean, and Jean-Pierre Lombard. "Constrained viscoelastic damping, test/analysis correlation on an aircraft engine." In Structural Dynamics, Volume 3, 1177–85. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-9834-7_103.

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Muller, Stéphane, and Yves Mauriot. "Smirnov Stationarity Criterion Applied to Rocket Engine Test Data Analysis." In Structural Dynamics, Volume 3, 771–78. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-9834-7_67.

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Biswas, Swati, Jivan Kumar, V. N. Satishkumar, and S. N. Narendra Babu. "Failure Analysis of a Squirrel Cage Bearing of a Gas Turbine Engine." In Advances in Structural Integrity, 117–25. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-7197-3_10.

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Peng, Gang, Chao Li, Huaqiang Zheng, Yanhong Ma, and Jie Hong. "Quantitative Analysis Method of Whole Aero-Engine Structural Design Based on Structural Efficiency." In Mechanisms and Machine Science, 3–17. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-99272-3_1.

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Dresevic, Bodin, Aleksandar Uzelac, Bogdan Radakovic, and Nikola Todic. "Book Layout Analysis: TOC Structure Extraction Engine." In Lecture Notes in Computer Science, 164–71. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-03761-0_17.

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Neher, J., P. Böhm, and N. Naranca. "Merging Disciplines and Models for Large Engine Structural Analyses." In Proceedings, 275–93. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-20828-8_16.

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Tim Huff, P. E. "Analysis Techniques for the Structural Engineer." In A Practical Course in Advanced Structural Design, 3–36. First edition. | Boca Raton, FL : CRC Press, 2021.: CRC Press, 2021. http://dx.doi.org/10.1201/9781003158998-2.

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Posavljak, Strain. "Practical Problems of Modal Analysis of Aero Engine Blades." In Experimental Analysis of Nano and Engineering Materials and Structures, 65–66. Dordrecht: Springer Netherlands, 2007. http://dx.doi.org/10.1007/978-1-4020-6239-1_31.

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Nagy, Szilvia, and Levente Solecki. "Wavelet Analysis and Structural Entropy Based Intelligent Classification Method for Combustion Engine Cylinder Surfaces." In Studies in Computational Intelligence, 127–38. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-030-01632-6_9.

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Conference papers on the topic "Structural analysis of an engine"

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ALLIOT, P., F. DESNOT, and R. GAZAVE. "Vulcain engine dynamic analysis." In 31st Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1044.

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Deaton, Joshua, and Ramana Grandhi. "Thermal-Structural Analysis of Engine Exhaust-Washed Structures." In 13th AIAA/ISSMO Multidisciplinary Analysis Optimization Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-9236.

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Chamis, C. C., and R. H. Johns. "Computational Engine Structural Analysis." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-70.

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A significant research activity at the NASA Lewis Research Center is the computational simulation of complex multidisciplinary engine structural problems. This simulation is performed using computational engine structural analysis (CESA) which consists of integrated multidisciplinary computer codes in conjunction with computer post-processing for “problem-specific” application. A variety of the computational simulations of specific cases are described in some detail in this paper. These case studies include (1) aeroelastic behavior of bladed rotors, (2) high velocity impact of fan blades, (3) blade-loss transient response, (4) rotor/stator/squeeze-film/bearing interaction, (5) blade-fragment/rotor-burst containment, and (6) structural behavior of advanced swept turboprops. These representative case studies were selected to demonstrate the breadth of the problems analyzed and the role of the computer including post-processing and graphical display of voluminous output data.

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VANDENBRINK, D., and D. HOPKINS. "Optimization and analysis of gas turbine engine blades." In 28th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-827.

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Chamis, C. C., and D. A. Hopkins. "Probabilistic Structural Analysis Methods of Hot Engine Structures." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-122.

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Development of probabilistic structural analysis methods for hot engine structures is a major activity at Lewis Research Center. It consists of three program elements: (1) composite load spectra methodology, (2) probabilistic structural analysis methodology, and (3) probabilistic structural analysis application. Recent progress includes: (1) quantification of the effects of uncertainties for several variables on High Pressure Fuel Turbopump (HPFT) turbine blade temperature, pressure, and torque of the Space Shuttle Main Engine (SSME), (2) the evaluation of the cumulative distribution function for various structural response variables based on assumed uncertainties in primitive structural variables, and (3) evaluation of the failure probability. Collectively, the results demonstrate that the structural durability of hot engine structural components can be effectively evaluated in a formal probabilistic/reliability framework.

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Petrick, LeRoy, and Peter D. Gunness. "Analysis of Motorcycle Structural–Resonance–Induced Fatigue Problems." In Small Engine Technology Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1999. http://dx.doi.org/10.4271/1999-01-3279.

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PANDEY, AJAY. "Thermoviscoplastic analysis of engine cowl leading edge subjected tooscillating shock-shock interaction." In 33rd Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-2537.

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Christensen, Eric, Greg Frady, Katherine Mims, and Andrew Brown. "Structural dynamic analysis of the X-34 rocket engine." In 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2012.

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Chen, Gong. "Analysis of Compression-Ignition Engine Design Concerning Engine Structural Loading Capacity." In ASME 2004 Internal Combustion Engine Division Fall Technical Conference. ASMEDC, 2004. http://dx.doi.org/10.1115/icef2004-0869.

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Present-day high-power compression-ignition engines are required in design not only to achieve a targeted high fuel efficiency, but also to meet regulated exhaust emissions standards. This paper investigates the effects of the in-cylinder combustion related design parameters, including cylinder compression ratio, fuel injection-start timing, and the amount of cylinder air charge, on engine performances and emissions as the engine structure-loading allowance is specified. Thereby the determination of those parameters to optimize the engine overall performances without exceeding the allowances in engine mechanical and thermal loading can be achieved. An enhanced understanding of those design parameters associated with the engine structural loading parameters, such as the cylinder peak firing pressure and exhaust temperature, is studied. The analytical prediction of the trade-off between those parameters with peak firing pressure contained is modeled and developed.

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ALLIOT, P., A. HUCK, and P. EDLINGER. "Low cycle fatigue analysis of the combustion chamber of the Vulcain engine gas generator." In 31st Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1045.

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Reports on the topic "Structural analysis of an engine"

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Heymsfield, Ernie, and Jeb Tingle. State of the practice in pavement structural design/analysis codes relevant to airfield pavement design. Engineer Research and Development Center (U.S.), May 2021. http://dx.doi.org/10.21079/11681/40542.

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An airfield pavement structure is designed to support aircraft live loads for a specified pavement design life. Computer codes are available to assist the engineer in designing an airfield pavement structure. Pavement structural design is generally a function of five criteria: the pavement structural configuration, materials, the applied loading, ambient conditions, and how pavement failure is defined. The two typical types of pavement structures, rigid and flexible, provide load support in fundamentally different ways and develop different stress distributions at the pavement – base interface. Airfield pavement structural design is unique due to the large concentrated dynamic loads that a pavement structure endures to support aircraft movements. Aircraft live loads that accompany aircraft movements are characterized in terms of the load magnitude, load area (tire-pavement contact surface), aircraft speed, movement frequency, landing gear configuration, and wheel coverage. The typical methods used for pavement structural design can be categorized into three approaches: empirical methods, analytical (closed-form) solutions, and numerical (finite element analysis) approaches. This article examines computational approaches used for airfield pavement structural design to summarize the state-of-the-practice and to identify opportunities for future advancements. United States and non-U.S. airfield pavement structural codes are reviewed in this article considering their computational methodology and intrinsic qualities.

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Collins, Peyton. Retirement for Cause/Engine Structural Integrity Program; Advanced Capability Motion Controller. Fort Belvoir, VA: Defense Technical Information Center, October 1998. http://dx.doi.org/10.21236/ada363487.

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Nguyen, P. M. Sodium loop framework structural analysis. Office of Scientific and Technical Information (OSTI), June 1995. http://dx.doi.org/10.2172/96909.

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Western, J. D-Zero Cryobridge Structural Analysis. Office of Scientific and Technical Information (OSTI), February 1990. http://dx.doi.org/10.2172/1031853.

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Ta, Khoi D. Application of MATLAB-Based Automated Turbine Engine Analysis. Fort Belvoir, VA: Defense Technical Information Center, September 2005. http://dx.doi.org/10.21236/ada438894.

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Sofu, Tanju. Diesel Engine Underhood Thermal Analysis - Final CRADA Report. Office of Scientific and Technical Information (OSTI), September 2007. http://dx.doi.org/10.2172/1334501.

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Vang, Leng, Curtis Smith, and Steven Prescott. Implementation of a Bayesian Engine for Uncertainty Analysis. Office of Scientific and Technical Information (OSTI), August 2014. http://dx.doi.org/10.2172/1166049.

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Lakhina, Anukool, Konstantina Papagiannaki, Mark Crovella, Christophe Diot, Eric D. Kolaczyk, and Nina Taft. Structural Analysis of Network Traffic Flows. Fort Belvoir, VA: Defense Technical Information Center, November 2003. http://dx.doi.org/10.21236/ada439086.

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Misiak, T. ESF GROUND SUPPORT - STRUCTURAL STEEL ANALYSIS. Office of Scientific and Technical Information (OSTI), June 1996. http://dx.doi.org/10.2172/891529.

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Zarghamee, Mehdi, Atis A. Iiepins, Said Bolourchi, Michael Mudlock, Daniel W. Eggers, Wassim I. Naguib, Omer O. Erbay, et al. Component, connection and subsystem structural analysis. Gaithersburg, MD: National Institute of Standards and Technology, 2005. http://dx.doi.org/10.6028/nist.ncstar.1-6c.

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