Temat: mechanical simulation - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Thermal-mechanical coupled simulation
Autorzy:: Nguyen, H. P.
Derewońko, A.
Niezgoda, T.
Powiązania:: https://bibliotekanauki.pl/articles/244229.pdf
Data publikacji:: 2015
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: thermo-mechanical coupled
simulation
plastic deformation
Opis:: Optimal design of engineering structures and technological processes requires taking into account various factors affecting the state of strain and stresses in the structure. Coupled thermo-mechanical analysis enables, among others, determination of undesirable changes in a body shape resulting from the implementation method of the initially-boundary conditions, for example, time-varying load and physical properties of the material depending on the temperature. They are also used to determine residual stresses remaining after manufacturing to prevent revalued stiffness and rigidity of the designed construction. In this study, coupled thermo-mechanical analysis illustrated by metal machining operation is presented. The commercial code MSC.Marc has been used to develop a coupled thermo-mechanical finite element model of plane-stress orthogonal metal cutting operations. Metal cutting is one of the most important and common manufacturing processes in the car industry. A thermal mechanical transient analysis is performed to convert mechanical work into heat by plastic deformation of the workpiece material and friction during metal machining operation. The finite element mesh distortion, due to large deformations, requires a remesh technique. The influence of parameters of the 2D and 3D finite element mesh adaptation on plastic deformation and temperature generated in the cutting processing is considered.
Źródło:: Journal of KONES; 2015, 22, 3; 161-168
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Modelling of vane and rotor blade rows in simulations of gas turbine performance
Autorzy:: Sznajder, Janusz
Powiązania:: https://bibliotekanauki.pl/articles/244955.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
mechanical engineering
engine parts
simulation
modelling
Opis:: A method of modelling of nozzle and rotor blade rows of gas turbine dedicated to simulations of gas turbine performance is proposed. The method is applicable especially in early design stage when many of geometric parameters are yet subject to change. The method is based on analytical formulas derived from considerations of flow theory and from cascade experiments. It involves determination of parameters of gas flow on the mean radius of blade rows. The blade row gas exit angle, determined in turbine design point is a basis for determination of details of blade contour behind the throat position. Throat area is then fixed based on required maximum mass flow in critical conditions. Blade leading edge radius is determined based on flow inlet angle to the blade row in the design point. The accuracy of analytical formulas applied for definition of blade contour details for assumed gas exit angle was verified by comparing the results of analytical formulas with CFD simulations for an airfoil cascade. Losses of enthalpy due to non-isentropic gas flow are evaluated using the analytical model of Craig and Cox, based on cascade experiments. Effects of blade cooling flows on losses of total pressure of the gas are determined based on analytical formulas applicable to film cooling with cooling streams blowing from discrete point along blade surface, including leading and trailing edges. The losses of total pressure due to film cooling of blades are incorporated into the Craig and Cox model as additional factor modifying gas flow velocities.
Źródło:: Journal of KONES; 2019, 26, 1; 183-190
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: A numerical model for calculation of piston rings wetted area in a combustion engine
Autorzy:: Guzik, M.
Koszałka, G.
Niewczas, A.
Powiązania:: https://bibliotekanauki.pl/articles/246518.pdf
Data publikacji:: 2012
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: combustion engine
ring pack
lubrication
simulation
wear
mechanical losses
Opis:: Assumptions made while modelling the oil film between the ring and the cylinder liner in IC engines, especially concerning the boundaries of the wetted area of the ring face surface, were discussed and the assumptions adopted for the developed model were presented in this study. It was assumed that the model should take into account partially flooded lubrication, which meant that the boundaries of the ring wetted area had to be determined. Based on the adopted assumptions, a model for calculation of the oil film thickness between the cylinder and moving rings, and thickness of the oil film left on the cylinder by the ring pack was developed. A computer application operating in the Windows operation system was developed to carry out numerical calculations. The results of initial numerical calculations were also presented. The proposed model can be utilized to determine the effects of the ring pack geometry, especially the geometry of the ring surface, on parameters of lubrication. These parameters, including the oil film thickness, distribution of pressure in oil film or tangential force, are crucial for friction and wear of cooperating surfaces, oil consumption, and flow of gas from the combustion chamber to the crankcase, thus playing a role in the durability, fuel consumption and emission of an engine.
Źródło:: Journal of KONES; 2012, 19, 3; 156-164
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Simulations of hot-gas flow in internally cooled cascade of turbine vanes
Autorzy:: Sznajder, Janusz
Powiązania:: https://bibliotekanauki.pl/articles/242679.pdf
Data publikacji:: 2019
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: aircraft engines
mechanical engineering
engine parts
simulation and modelling
Opis:: An experiment in cooling of gas turbine nozzle guide vanes was modelled numerically with a conjugate viscousflow and solid-material heat conduction solver. The nozzle vanes were arranged in a cascade and operated in highpressure, hot-temperature conditions, typical for first turbine stage in a flow of controlled-intensity, artificiallygenerated turbulence. The vane cooling was internal, accomplished by 10 channels in each vane with cooling-air flow. Numerical simulations of the experiment were conducted applying two turbulence models of the k-omega family: k-omega-SST and Transition SST implemented in the ANSYS Fluent solver. Boundary conditions for the simulations were set based on conditions of experiment: total pressures and total temperature on inlet to cascade, static pressure on the outlet of the cascade and heat flux on the surface of cooling channels. The values of heat flux on the surface of cooling channels were evaluated based on Nusselt numbers obtained from experiment and varied in time until steadystate conditions were obtained. Two test cases, one with subcritical outlet flow, and another one, with supercritical outlet flow were simulated. The result of experiment – distributions of pressure, surface temperature, and heat transfer coefficients on the vane external surface were compared to results of numerical simulations. Sensitivity of the vane surface temperatures and heat transfer coefficients to turbulence models and to boundary-condition values of parameters of turbulence models: turbulence energy and specific dissipation of turbulence energy was also studied.
Źródło:: Journal of KONES; 2019, 26, 2; 151-158
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Numerical simulations of mechanical peening of titanium alloy
Autorzy:: Kosiuczenko, K.
Barnat, W.
Napadłek, W.
Bogdanowicz, Z.
Powiązania:: https://bibliotekanauki.pl/articles/243311.pdf
Data publikacji:: 2008
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: surface layer forming
mechanical shot peening
impact
numerical simulation
finite element method
Opis:: Mechanical peening is based on striking a worked material surface by hard balls (shot).In this work, a pneumatic method, applied for double-sided shot peening of the worked sample surface, was selected. The samples were made of the titanium alloy WT3-1 (Ti-6Al-2Cr-2Mo). The described work consists of two parts. The laboratory experiment was conducted in first part. After it realization, various observations were conducted. Observations of surface topography for samples were carried out before and after shot peening using scanning electron microscope (SEM). They revealed quite regular plastically deformed zones generated due to applied working. Neither microcracks, spallings nor delaminations in deformed surface layer of the titanium alloy were observed which attests to correct technological process of the surface hardening. The numeric simulation of the peening process was conducted in part second. The physical model described non-simultaneous impact of three steel balls onto rectangular metal sheet made of the above-mentioned titanium alloy. Numerical FEM analysis for nonlinear dynamics (explicit) was carried out using LS-Dyna software (Livermore Software Technology Corporation). In the paper are presented maps of the material effort in surface layers for times corresponding to conditions after impacts of the first, second, and the third ballof cast steel shot.
Źródło:: Journal of KONES; 2008, 15, 1; 137-144
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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