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Journal articles on the topic 'Aero-thermal model'

Author: Grafiati

Published: 4 June 2021

Last updated: 16 February 2022

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1

Ba, Wei, Chunwei Gu, Xiaodong Ren, and Xuesong Li. "Convective cooling model for aero-thermal coupled through-flow method." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 231, no. 2 (2017): 133–44. http://dx.doi.org/10.1177/0957650916685911.

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The aero-thermal coupled phenomenon is significant in the modern cooled turbine, and it is necessary to consider the cooling effect and predict the coolant requirement in the through-flow design. A new cooling model was developed for the aero-thermal coupled through-flow method in this paper to predict the temperatures of both the pressure and suction surfaces of the blade. Based on the given blade temperature limitation rather than the mean blade surface temperature in the formal cooling model, the coolant requirement prediction can be more accurate. The equivalent blade thickness and heat ex

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2

Dai, Huaren, Zhe Chen, Wei Guo, and Ju Wang. "Thermal simulation model of aero-engine blade material forging simulation." Thermal Science 25, no. 4 Part B (2021): 3169–77. http://dx.doi.org/10.2298/tsci2104169d.

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During the high temperature forging process, the thermal parameters such as the temperature field and strain field in the blank have an important influence on the crack damage and micro-structure in the forging. We use the rigid viscoelastic finite element method to carry out the forging process of a heavy aero-engine blade the finite element numerical simulation was carried out to obtain the temperature field, strain field and forging load change law in the forging process with time, and on this basis, combined with the crack damage and repair mechanism and the re?crystallization structure ev

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3

Qian, Wei, Yuguang Bai, Xiangyan Chen, and Taojun Lu. "Aero-servo-elastic analysis of a hypersonic aircraft." Journal of Low Frequency Noise, Vibration and Active Control 37, no. 3 (2017): 534–53. http://dx.doi.org/10.1177/1461348417725956.

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Aero-servo-elastic analysis of a complex hypersonic aircraft is presented in this paper. A structure geometry was designed and built based on the X-43A vehicle. First, a three-dimensional structural finite element model was proposed with effective two-dimensional elements, which can obtain effective modal analysis results without useless local modes. Second, computational fluid dynamic (CFD) simulation was adopted to find aero-heating distribution of thermal mode via this structure. Aero-heating effect was included to study thermal-modal characteristics of the present structure. Influence due

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Ba, Wei, Xuesong Li, Xiaodong Ren, and Chunwei Gu. "Aero-thermal coupled through-flow method for cooled turbines with new cooling model." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 3 (2017): 254–65. http://dx.doi.org/10.1177/0957650917731629.

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The aero-thermal–coupled phenomenon is significant in modern cooled turbines, and an aero-thermal coupled through-flow method has previously been developed by the authors for considering the influence of heat transfer and coolant mixing in through-flow design. However, the original cooling model is not capable of calculating the distribution of the coolant mass flow rate and pressure loss in complex cooling structures. Therefore, in this paper, a one-dimensional flow calculation for the internal coolant is introduced into the heat transfer calculation to further improve the through-flow coolin

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Yazar, Isil, Tolga Yasa, and Emre Kiyak. "Simulation-based steady-state aero-thermal model for small-scale turboprop engine." Aircraft Engineering and Aerospace Technology 89, no. 2 (2017): 203–10. http://dx.doi.org/10.1108/aeat-02-2015-0062.

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Purpose An aircraft engine control system consists of a large scale of control parameters and variables because of the complex structure of aero-engine. Monitoring and adjusting control variables and parameters such as detecting, isolating and reconfiguring the system faults/failures depend on the controller design. Developing a robust controller is based on an accurate mathematical model. Design/methodology/approach In this study, a small-scale turboprop engine is modeled. Simulation is carried out on MATLAB/Simulink for design and off-design operating conditions. Both steady-state and transi

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Jafari, Soheil, Ahmed Bouchareb, and Theoklis Nikolaidis. "Thermal Performance Evaluation in Gas Turbine Aero Engines Accessory Gearbox." International Journal of Turbomachinery, Propulsion and Power 5, no. 3 (2020): 21. http://dx.doi.org/10.3390/ijtpp5030021.

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This paper presents a methodological approach for mathematical modelling and physics-based analysis of accessory gearbox (AGB) thermal behavior in gas turbine aero engines. The AGB structure, as one of the main sources of heat in gas turbine aero engines, is firstly described and its power losses will be divided into load-dependent and no-load dependent parts. Different mechanisms of heat generation are then identified and formulated to develop a toolbox for calculation of the churning, sliding friction, and rolling friction losses between contact surfaces of the AGB. The developed tool is als

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7

Ji, Fen Zhu, Xiao Xu Zhou, and Mi Tian. "Study on Thermal Management for Cooling System of Aero-Piston Engine." Advanced Materials Research 516-517 (May 2012): 452–56. http://dx.doi.org/10.4028/www.scientific.net/amr.516-517.452.

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A model of thermal management for cooling system of aero-piston engine was presented in this study. The models of main parts in this system were also founded. Based on the measured value of temperature and pressure in the cylinder, the heat transfer coefficient between gas-fired and the cylinder wall was calculated by using the empirical formula. A heat transfer boundary condition between fins and cooling air was determined according to various Reynolds number of the air flow. Moreover, the method of finite element analysis was utilized to calculate the temperature of cylinder block. In the sp

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Javiya, Umesh, John Chew, Nick Hills, and Timothy Scanlon. "Coupled FE–CFD thermal analysis for a cooled turbine disk." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 229, no. 18 (2015): 3417–32. http://dx.doi.org/10.1177/0954406215572430.

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This paper presents transient aero-thermal analysis for a gas turbine disk and the surrounding air flows through a transient slam acceleration/deceleration “square cycle” engine test, and compares predictions with engine measurements. The transient solid–fluid interaction calculations were performed with an innovative coupled finite element (FE) and computational fluid dynamics (CFD) approach. The computer model includes an aero-engine high pressure turbine (HPT) disk, adjacent structure, and the surrounding internal air system cavities. The model was validated through comparison with the engi

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Zheng, Min, Fan Shen, and Pei Luo. "Vibration Fatigue Analysis of the Structure under Thermal Loading." Advanced Materials Research 853 (December 2013): 559–64. http://dx.doi.org/10.4028/www.scientific.net/amr.853.559.

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The fatigue problem of structures under concurrent thermal and vibration loading has not been thoroughly studied even though it is common in applications of aero-engine combustor liners. Here we attempt to explore such a problem using a simplified combustor liner model that is implemented by the commercial finite element software ANSYS Workbench. The modal parameters at various temperatures are calculated and the fatigue behavior under stochastic base excitation and thermal environment are analyzed. The results show that thermal loading not only has an effect on dynamic characteristics but als

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10

Wang, Jiang-Feng, Jia-Wei Li, Fa-Ming Zhao, and Xiao-Feng Fan. "Numerical method of carbon-based material ablation effects on aero-heating for half-sphere." Modern Physics Letters B 32, no. 12n13 (2018): 1840011. http://dx.doi.org/10.1142/s0217984918400110.

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A numerical method of aerodynamic heating with material thermal ablation effects for hypersonic half-sphere is presented. A surface material ablation model is provided to analyze the ablation effects on aero-thermal properties and structural heat conduction for thermal protection system (TPS) of hypersonic vehicles. To demonstrate its capability, applications for thermal analysis of hypersonic vehicles using carbonaceous ceramic ablators are performed and discussed. The numerical results show the high efficiency and validation of the method developed in thermal characteristics analysis of hype

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11

Tang, Hong, Guo Guang Chen, and Hui Zhu He. "An Aero-Thermo-Elasticity Method Applied on the Supersonic Aircraft Model." Applied Mechanics and Materials 215-216 (November 2012): 438–42. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.438.

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Coupling between the vibration frequencies and the unsteady aerodynamic will reduce the flutter speed and ride quality through the aerodynamic heat transfer. As the flight speed improved, the aeroelastic analysis has become an essential means of aircraft design. The method of aero-thermo-elastic (ATE) analysis is coupled with aircraft aeroelastic analysis and thermal deformation, and is more realistic reflection of the actual flight of the aircraft. In this paper, an ATE analysis of aircraft adopted by computational fluid dynamics/computational structural dynamics (CFD/CSD) methods, and compar

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Jasa, John P., Benjamin J. Brelje, Justin S. Gray, Charles A. Mader, and Joaquim R. R. A. Martins. "Large-Scale Path-Dependent Optimization of Supersonic Aircraft." Aerospace 7, no. 10 (2020): 152. http://dx.doi.org/10.3390/aerospace7100152.

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Aircraft are multidisciplinary systems that are challenging to design due to interactions between the subsystems. The relevant disciplines, such as aerodynamic, thermal, and propulsion systems, must be considered simultaneously using a path-dependent formulation to assess aircraft performance accurately. In this paper, we construct a coupled aero-thermal-propulsive-mission multidisciplinary model to optimize supersonic aircraft considering their path-dependent performance. This large-scale optimization problem captures non-intuitive design trades that single disciplinary models and path-indepe

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13

Qiao, Lei, Jun-Qiang Bai, Jia-Kuan Xu, Jing-Lei Xu, and Yang Zhang. "Modeling of Supersonic/Hypersonic Boundary Layer Transition Using a Single-Point Approach." International Journal of Nonlinear Sciences and Numerical Simulation 19, no. 3-4 (2018): 263–74. http://dx.doi.org/10.1515/ijnsns-2017-0011.

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AbstractDuring the process of aerodynamic shape design of supersonic and hypersonic space planes, laminar flow design and boundary layer transition prediction play important roles in aero-thermal numerical simulations and aero-thermal protection design. Therefore, in this study, a computational fluid dynamics compatible transition closure model for high speed laminar-to-turbulent transitional flows is formulated with consideration of the analysis results from stability theory. The proposed model contains two transport equations to describe the transition mechanism using local variables. Specif

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14

Bayona-Roa, Camilo, J. S. Solís-Chaves, Javier Bonilla, A. G. Rodriguez-Melendez, and Diego Castellanos. "Computational Simulation of PT6A Gas Turbine Engine Operating with Different Blends of Biodiesel—A Transient-Response Analysis." Energies 12, no. 22 (2019): 4258. http://dx.doi.org/10.3390/en12224258.

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Instead of simplified steady-state models, with modern computers, one can solve the complete aero-thermodynamics happening in gas turbine engines. In the present article, we describe a mathematical model and numerical procedure to represent the transient response of a PT6A gas turbine engine operating at off-design conditions. The aero-thermal model consists of a set of algebraic and ordinary differential equations that arise from the application of the mass, linear momentum, angular momentum and energy balances in each engine’s component. The solution code has been developed in Matlab-Simulin

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15

Yang, Jinguang, Min Zhang, and Yan Liu. "Numerical simulations and optimizations for turbine-related configurations." Thermal Science 24, no. 1 Part A (2020): 367–78. http://dx.doi.org/10.2298/tsci190404295y.

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In order to accelerate the numerical simulation and optimization of gas turbine-related configurations, a source based computational fluid dynamics (SCFD) approach is developed for flow and heat transfer simulations. Different sources de-pending on the fluid porosity at each grid node in the computational domain are introduced to the continuity, momentum, energy and turbulence model equations, so that both the fluid and solid regions can be solved as one region. In the present paper, test cases including a ribbed channel and a winglet shrouded turbine cascade with tip injection are investigate

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16

Dong, Yiwei, Weiguo Yan, Tao Liao, Qianwen Ye, and Yancheng You. "Model characterization and mechanical property analysis of bimetallic functionally graded turbine discs." Mechanics & Industry 22 (2021): 4. http://dx.doi.org/10.1051/meca/2021001.

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In advanced propulsive systems, a turbine disc bears vast mechanical and thermal loads under its working conditions of high-temperature gradients and high rotational velocity.The complex working conditions of aero-engine turbine discs place stringent performance requirements on the materials used. With dual organizations and superior composite performances, bimetallic functionally graded turbine discs have become a focus in the research of high thrust-to-weight ratio aero-engines. To study the mechanical properties of new bimetallic functionally graded materials under service conditions, we pr

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17

Yu, Ling, and Amit Shukla. "Comparison of Transient Response of a Skin Panel under Uniform and Non-Uniform Thermal Loading." Applied Mechanics and Materials 224 (November 2012): 33–38. http://dx.doi.org/10.4028/www.scientific.net/amm.224.33.

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This paper presents transient response of a skin panel under combined mechanical loading and provides a comparison of uniform and non-uniform thermal loading. A finite element model of a representative structural panel is used to evaluate the performance of an aero-structure subjected to severe aerodynamic heating and fluctuating pressure. This structure exhibits complex nonlinear response including thermal buckling and snap-through. In this study, uniform and non-uniform temperature distribution are used to understand the influence of spatial thermal distribution on the nonlinear response of

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18

Lou, De Cang, Wen Guo, Zhi Guo Wang, and Yong Hong Wang. "Integrated Thermal Management System Design for Advanced Propulsion System." Applied Mechanics and Materials 232 (November 2012): 723–29. http://dx.doi.org/10.4028/www.scientific.net/amm.232.723.

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Thermal management system (TMS) design is considered to be a key technology for advanced aero engines and supersonic or hypersonic propulsion systems. In this paper, the concepts of coupling flow and thermodynamic networks are proposed for TMS design. In this method, the propulsion system is considered to be a zero-dimensional flow system. Components, subsystems and hence the entire engine system can be modelled using some basic flow and thermodynamics networks. The platform for TMS design, ThermalM, is developed based on this model. As an example, modelling for a Turbine Based Combined Cycle

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19

Beniaiche, A., M. Nadir, M. Cerdoun, C. Carcasci, and B. Facchini. "Effect of turbulence models' choice on the aero-thermal flow numerical validations within a ribbed trailing edge geometry." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 233, no. 1 (2018): 52–77. http://dx.doi.org/10.1177/0957650918772678.

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In this paper, the commercial ANSYS Fluent software was used to achieve a numerical survey of the effect of five (05) turbulence models’ formulation on the aero-thermal computational fluid dynamics validation of two 30:1 scaled models reproducing an original internal ribbed trailing edge prototype. Tests were conducted for stationary and rotation conditions, for Re = 10,000–40,000 and Ro = 0–0.23. Particle image velocimetry and thermochromic liquid crystal experimental data were employed to check the consistence computational fluid dynamics results qualitatively and quantitatively, aerodynamic

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20

Schoenenborn, Harald, Ernst Ebert, Burkhard Simon, and Paul Storm. "Thermomechanical Design of a Heat Exchanger for a Recuperative Aeroengine." Journal of Engineering for Gas Turbines and Power 128, no. 4 (2006): 736–44. http://dx.doi.org/10.1115/1.1850510.

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Within the framework programs of the EU for Efficient and Environmentally Friendly Aero-Engines (EEFEA) MTU has developed a highly efficient cross-counter flow heat exchanger for the application in intercooled recuperated aeroengines. This very compact recuperator is based on the profile tube matrix arrangement invented by MTU and one of its outstanding features is the high resistance to thermal gradients. In this paper the combined thermomechanical design of the recuperator is presented. State-of-the-art calculation procedures for heat transfer and stress analysis are combined in order to per

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21

Marimuthu, S., D. Clark, J. Allen, et al. "Finite element modelling of substrate thermal distortion in direct laser additive manufacture of an aero-engine component." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 227, no. 9 (2012): 1987–99. http://dx.doi.org/10.1177/0954406212470363.

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The shape complexity of aerospace components is continuously increasing, which encourages researchers to further refine their manufacturing processes. Among such processes, blown powder direct laser deposition process is becoming an economical and energy efficient alternative to the conventional machining process. However, depending on their magnitudes, the distortion and residual stress generated during direct laser deposition process can affect the performance and geometric tolerances of manufactured components. This article reports an investigation carried out using the finite element analy

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22

Reed, R. C., H. J. Stone, S. M. Roberts, and J. M. Robinson. "The development and validation of a model for the electron beam welding of aero-engine components." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 211, no. 6 (1997): 421–28. http://dx.doi.org/10.1243/0954410971532785.

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Electron beam welding is used to manufacture high-integrity structures, for example compressor assemblies, for the latest generation of Rolls-Royce aero-engines. For such applications, the welding variables (for example welding current, voltage, beam focusing parameters) must be optimized, such that any distortion induced by the process is insignificant when compared to the dimensional tolerances allowed by the designers. Furthermore, the residual stresses induced by the process must be described and characterized, since these are required for estimates of component life. A model for such elec

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23

Rinaldi, Claudia, Valerio Bicego, and Pier Paolo Colombo. "Validation of CESI Blade Life Management System by Case Histories and in situ NDT." Journal of Engineering for Gas Turbines and Power 128, no. 1 (2004): 73–80. http://dx.doi.org/10.1115/1.2056534.

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A life management system was developed for hot components of large industrial gas turbines, in the form of a software tool for predicting component lives under typical operational transients (normal and also abnormal) and steady-state periods. The method utilizes results of previous thermo-mechanical finite element and finite volume fluid mechanics analyses. The basic idea of this method is using data from structural and aero-thermal analyses (pressures and temperatures), blade life theory, and material properties as an input to algorithms, and using operational and historical data to validate

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24

Fueyo, N., V. Gambo´n, C. Dopazo, and J. F. Gonza´lez. "Computational Evaluation of Low NOx Operating Conditions in Arch-Fired Boilers." Journal of Engineering for Gas Turbines and Power 121, no. 4 (1999): 735–40. http://dx.doi.org/10.1115/1.2818534.

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In the present paper, a computational model is used to simulate the aero-dynamic, thermal, and chemical conditions inside an arch-fired coal boiler. The model is based on the Eulerian-Eulerian concept, in which Eulerian conservation equations are solved both for the gas and the particulate phases. A NOx formation and destruction submodel is used to calculate the local concentration of NO. The model is used to simulate a range of operating conditions in an actual, 350 MW, arch-fired boiler, with the aim of reducing, using primary measures, the emissions of NOx. The model results shed some light

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25

Shi, Xiujiang, Jiqiang Wu, Bin Zhao, Xuan Ma, and Xiqun Lu. "Mixed thermal elastohydrodynamic lubrication analysis with dynamic performance of aero ball bearing during start-up and shut-down." Proceedings of the Institution of Mechanical Engineers, Part J: Journal of Engineering Tribology 234, no. 6 (2020): 873–86. http://dx.doi.org/10.1177/1350650119900401.

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In this study, a coupling model is developed to include the aero ball bearing dynamic performance in the mixed thermal elastohydrodynamic lubrication analysis, and the low-speed and heavy-load conditions during start-up and shut-down are involved. Based on the bearing quasi-dynamics, the inside motion state of the main loading surface is obtained, and the mixed thermal elastohydrodynamic lubrication is conducted to get bearing lubrication state and properties. The numerical lubrication model under low-speed and heavy-load conditions is validated against published tested data, which reveal well

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Filipek, Robert, Marek Danielewski, E. Tyliszczak, M. Pawełkiewicz, and S. Datta. "Thermal Stability of NiAl-Base Coatings for High Temperature Application." Defect and Diffusion Forum 237-240 (April 2005): 709–14. http://dx.doi.org/10.4028/www.scientific.net/ddf.237-240.709.

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Aluminide diffusion coatings act as a remedy against the aggressive environments in which modern aero-gas turbines operate. Platinum addition to basic aluminide coatings significantly improves the oxidation resistance of these coatings. The increase in operating temperatures of industrial energy systems and gas turbines, has led to the extensive use of coatings capable of providing improved service life. Interdiffusion plays a critical role in understanding the integrity of such coatings. The Danielewski-Holly model of interdiffusion which allows for the description of a wide range of processe

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Sun, Hengchao, Guoding Chen, Yonghong Zhang, and Li’na Wang. "Theoretical and experimental studies on the motion and thermal states of oil droplet in a bearing chamber." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 230, no. 14 (2016): 2596–614. http://dx.doi.org/10.1177/0954410016629690.

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Study on the motion and thermal states of oil droplet is an important part of research on the oil/air two-phase flow and heat transfer in an aero engine bearing chamber. In this paper, dimensional analysis is applied to the airflow analysis of bearing chamber. That makes the analysis model suitable for a wide range of geometric and operating conditions. Moreover, the temperature solution is added to the oil droplet motion analysis. That could promote the calculation accuracy of the droplet trajectory, velocity, and temperature. Firstly, the similarity criteria of the airflow in a bearing chamb

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Kumar, Amarnath, Prakash C. Patnaik, and Kuiying Chen. "Damage Assessment and Fracture Resistance of Functionally Graded Advanced Thermal Barrier Coating Systems: Experimental and Analytical Modeling Approach." Coatings 10, no. 5 (2020): 474. http://dx.doi.org/10.3390/coatings10050474.

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Enhancement of stability, durability, and performance of thermal barrier coating (TBC) systems providing thermal insulation to aero-propulsion hot-section components is a pressing industrial need. An experimental program was undertaken with thermally cycled eight wt.% yttria stabilized zirconia (YSZ) TBC to examine the progressive and sequential physical damage and coating failure. A linear relation for parameterized thermally grown oxide (TGO) growth rate and crack length was evident when plotted against parameterized thermal cycling up to 430 cycles. An exponential function thereafter with t

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Yang, Xing, Zhenping Feng, and Terrence W. Simon. "Conjugate heat transfer modeling of a turbine vane endwall with thermal barrier coatings." Aeronautical Journal 123, no. 1270 (2019): 1959–81. http://dx.doi.org/10.1017/aer.2019.56.

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ABSTRACTAdvanced cooling techniques involving internal enhanced heat transfer and external film cooling and thermal barrier coatings (TBCs) are employed for gas turbine hot components to reduce metal temperatures and to extend their lifetime. A deeper understanding of the interaction mechanism of these thermal protection methods and the conjugate thermal behaviours of the turbine parts provides valuable guideline for the design stage. In this study, a conjugate heat transfer model of a turbine vane endwall with internal impingement and external film cooling is constructed to document the effec

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Kim, Young Jin, Minsung Kim, Man Yeong Ha, and June Kee Min. "Numerical Study on Surface Air-Oil Heat Exchanger for Aero Gas-Turbine Engine Using One-Dimensional Flow and Thermal Network Model." Transactions of the Korean Society of Mechanical Engineers B 38, no. 11 (2014): 915–24. http://dx.doi.org/10.3795/ksme-b.2014.38.11.915.

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Zhao, Wei, Xiao Lin Han, and Qing Guo Fei. "Preliminary Research on the Aerothermoelastic Behaviours of Sweptback Wing." Applied Mechanics and Materials 138-139 (November 2011): 874–78. http://dx.doi.org/10.4028/www.scientific.net/amm.138-139.874.

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Natural modes and flutter of the sweptback wing are analyzed at different temperatures. Natural frequencies are reduced as temperature increasing, the temperature gradient in the structure tend to reduce model stiffness due to changing in material properties and development of thermal stress, which degrade the structure stability. Results in this paper show that the 1st~4thorder natural frequencies of sweptback wing in this paper decrease by about 12.09%, 15.06%, 14.31% and 12.57%respectively from room temperature to 450°C.The flutter frequency and velocity are also reduced as the decreasing o

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Majila, Anuradha Nayak, Rajeev Jain, Chandru Fernando D., and S. Ramachandra. "Experimental and Numerical Correlation of Impact of Spherical Projectile for Damage Analysis of Aero Engine Component." Defence Science Journal 66, no. 2 (2016): 193. http://dx.doi.org/10.14429/dsj.66.9130.

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<p>Studies the impact response of flat Titanium alloy plate against spherical projectile for damage analysis of aero engine components using experimental and finite element techniques. Compressed gas gun has been used to impart speed to spherical projectile at various impact velocities for damage studies. Crater dimensions (diameter and depth) obtained due to impact have been compared with finite element results using commercially available explicit finite element method code LS-DYNA. Strain hardening, high strain rate and thermal softening effect along with damage parameters have been c

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Teodosio, Luigi, Giuseppe Alferi, Andrea Genovese, et al. "A numerical methodology for thermo-fluid dynamic modelling of tyre inner chamber: towards real time applications." Meccanica 56, no. 3 (2021): 549–67. http://dx.doi.org/10.1007/s11012-021-01310-w.

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AbstractThe characterization and reproduction of tyre behaviour for vehicle modelling is a topic of particular interest both for real-time driver in the loop simulations and for offline performance optimization algorithms. Since the accuracy of the tyre forces and moments can be achieved by the accurate physical modelling of all the phenomena concerning the tyre-road interaction, the link between the tyre thermal state and the tyre frictional performance turns into a crucial factor. An integrated numerical methodology, allowing to couple the full 3D CFD (Computational Fluid Dynamics) flux with

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Saleh, Zainab, Eldad J. Avital, and Theodosios Korakianitis. "Effect of in-service burnout on the transonic tip leakage flows over flat tip model." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 5 (2019): 655–69. http://dx.doi.org/10.1177/0957650919877057.

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Un-shrouded turbine blades are more common than shrouded ones in gas turbine aero-engines since they reduce the weight and avoid the centrifugal loading caused by the blades’ shrouds. Despite these important advantages, the absence of the shroud leads to leakage flows across the tip gap and exposes the blade tip to high thermal load and thermal damages. In addition, the leakage flows can contribute up to 30% of the aerodynamic loss in a turbine stage. In this study, the effect of in-service burnout is explored using a fundamental flat tip model of a high-pressure gas turbine blade. This invest

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Ранченко, Геннадий Степанович, та Анна Григорьевна Буряченко. "ПЕРСПЕКТИВИ РОЗВИТКУ ЕЛЕКТРОННИХ САУ ГТД". Aerospace technic and technology, № 7 (10 листопада 2018): 95–100. http://dx.doi.org/10.32620/aktt.2018.7.14.

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The analysis of the basic directions of electronic automatic control systems for aviation gas-turbine engines (FADEC) development is presented. This analysis is executed on the base of materials of the Scientific and Technical Congress of Aero-Engine Manufacturers. This Congress passed within the limits of the International engine forum in April 2018 in Moscow under aegis of the International association «Association of Aero-Engine Manufacturers» (ASSAD). The review of a modern condition of developing works of the specialized scientific enterprises in the field of application of onboard mathem

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Gottlieb, Joshua, Roger Davis, and John Clark. "Conjugate rotor-stator interaction procedure for film-cooled turbine sections." Aircraft Engineering and Aerospace Technology 89, no. 3 (2017): 365–74. http://dx.doi.org/10.1108/aeat-10-2014-0159.

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Purpose The authors aim to present a procedure for the parallel, steady and unsteady conjugate, Navier–Stokes/heat-conduction rotor-stator interaction analysis of multi-blade-row, film-cooled, turbine airfoil sections. A new grid generation procedure for multiple blade-row configurations, including walls, thermal barrier coatings, plenums, and cooling tubes, is discussed. Design/methodology/approach Steady, multi-blade-row interaction effects on the flow and wall thermal fields are predicted using a Reynolds’s-averaged Navier–Stokes (RANS) simulation in conjunction with an inter-blade-row mixi

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Wang, Qiang, Ya-Ping Hu, and Hong-Hu Ji. "An anisotropic porous media model for leakage analysis of finger seal." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 2 (2019): 280–92. http://dx.doi.org/10.1177/0954410019862080.

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Finger seal is a new type of compliant seal configuration, which is an important part of an aero-engine and its accessory systems. It has superior sealing performance compared with conventional labyrinth seals and a lower manufacturing cost than brush seals. However, numerical simulation of the leakage characteristics of an entitative finger seal structure are very difficult to implement, because the finger laminates are in close contact with one another and the radial deformation of the fingers caused by interference between seal and rotor as well as the centrifugal and thermal expansion of t

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Messenger, Andrew, and Thomas Povey. "Calibrated Low-Order Transient Thermal and Flow Models for Robust Test Facility Design." Journal of the Global Power and Propulsion Society 4 (July 3, 2020): 94–113. http://dx.doi.org/10.33737/jgpps/122270.

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This paper describes an upgrade to high temperature operation of the Engine Component AeroThermal (ECAT) facility, an established engine-parts facility at the University of Oxford. The facility is used for high-TRL research and development, new technology demonstration, and for component validation (typically large civil-engine HP NGVs). In current operation the facility allows Reynolds number, Mach number, and coolant-to-mainstream pressure ratio to be matched to engine conditions. Rich-burn or lean-burn temperature, swirl and turbulence profiles can also be simulated. The upgrade will increa

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Hashmi, Muhammad Baqir, Tamiru Alemu Lemma, Shazaib Ahsan, and Saidur Rahman. "Transient Behavior in Variable Geometry Industrial Gas Turbines: A Comprehensive Overview of Pertinent Modeling Techniques." Entropy 23, no. 2 (2021): 250. http://dx.doi.org/10.3390/e23020250.

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Generally, industrial gas turbines (IGT) face transient behavior during start-up, load change, shutdown and variations in ambient conditions. These transient conditions shift engine thermal equilibrium from one steady state to another steady state. In turn, various aero-thermal and mechanical stresses are developed that are adverse for engine’s reliability, availability, and overall health. The transient behavior needs to be accurately predicted since it is highly related to low cycle fatigue and early failures, especially in the hot regions of the gas turbine. In the present paper, several cr

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Sha, Yun Dong, Hao Yuan Wang, and Huan Yu. "Nonlinear Response of Carbon-Carbon Laminated Panels to Random Acoustic Excitation under a Gradient Temperature Field." Applied Mechanics and Materials 696 (November 2014): 23–29. http://dx.doi.org/10.4028/www.scientific.net/amm.696.23.

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Future missions for aircraft will expose structures to severe thermal and acoustic loads. Efficient analysis methods for predicting nonlinear random response and fatigue life are urgently important. This paper presents a finite element model for analyzing nonlinear random dynamic behaviors of Carbon-Carbon composite panels under temperature gradients and Guassian excitations. The temperature distribution over the plate follows double sine curve. A finite element formulation combined with the equivalent linearization approach and normal mode method is established. The global system of equations

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Sun, Junfeng, Meihong Liu, Zhen Xu, et al. "Coupled Fluid–Solid Numerical Simulation for Flow Field Characteristics and Supporting Performance of Flexible Support Cylindrical Gas Film Seal." Aerospace 8, no. 4 (2021): 97. http://dx.doi.org/10.3390/aerospace8040097.

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A new type of cylindrical gas film seal (CGFS) with a flexible support is proposed according to the working characteristics of the fluid dynamic seal in high-rotational-speed fluid machinery, such as aero-engines and centrifuges. Compared with the CGFS without a flexible support, the CGFS with flexible support presents stronger radial floating characteristics since it absorbs vibration and reduces thermal deformation of the rotor system. Combined with the structural characteristics of a film seal, an analytical model of CGFS with a flexible wave foil is established. Based on the fluid-structur

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Taheri, Yaser, Meran Zargarabadi, and Mehdi Jahromi. "Multi-objective optimization of three rows of film cooling holes by genetic algorithm." Thermal Science, no. 00 (2020): 230. http://dx.doi.org/10.2298/tsci190805230t.

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Aero-thermal optimization on multi-rows of film cooling over a flat plate has been performed to optimize the inclination angles. Hence three cylindrical holes with injection angles of ?, ?, and ? have been considered. The cooling hole has a 3 mm diameter and an inclined angle between 25 to 35 degrees. Numerical simulations were performed at a fixed density ratio of 1.25 and blowing ratio of 0.5. The control-volume method with a SIMPLEC algorithm has been used to solve the steady-state RANS equations with SST k-? turbulent model. The injection angles of the holes are selected as the design vari

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Błachnio, Józef, and Wojciech I. Pawlak. "Non-Uniformity of the Combustor Exit Flow Temperature in Front of the Gas Turbine." Acta Mechanica et Automatica 8, no. 4 (2014): 209–13. http://dx.doi.org/10.2478/ama-2014-0038.

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Abstract Various types of damages to gas-turbine components, in particular to turbine blades, may occur in the course of gas turbine operation. The paper has been intended to discuss different forms of damages to the blades due to non-uniformity of the exit flow temperature. It has been shown that the overheating of blade material and thermal fatigue are the most common reasons for these damages. The paper presents results from numerical experiments with use of the computer model of the aero jet engine designed for simulations. The model has been purposefully modified to take account of the as

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Yazar, Isil, Emre Kiyak, Fikret Caliskan, and T. Hikmet Karakoc. "Simulation-based dynamic model and speed controller design of a small-scale turbojet engine." Aircraft Engineering and Aerospace Technology 90, no. 2 (2018): 351–58. http://dx.doi.org/10.1108/aeat-09-2016-0150.

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Purpose This paper aims to present a nonlinear mathematical model of a small-scale turbojet aeroengine and also a speed controller design that is conducted for the constructed nonlinear mathematical model. Design/methodology/approach In the nonlinear mathematical model of the turbojet engine, temperature, rotational speed, mass flow, pressure and other parameters are generated using thermodynamic equations (e.g. mass, energy and momentum conservation laws) and some algebraic equations. In calculation of the performance parameters, adaptive neuro fuzzy inference system (ANFIS) method is preferr

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Dhupal, D., B. Doloi, and B. Bhattacharyya. "Optimization of process parameters of Nd:YAG laser microgrooving of Al2TiO5 ceramic material by response surface methodology and artificial neural network algorithm." Proceedings of the Institution of Mechanical Engineers, Part B: Journal of Engineering Manufacture 221, no. 8 (2007): 1341–50. http://dx.doi.org/10.1243/09544054jem814.

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The high-intensity pulsed Nd:YAG laser has the capability to produce both deep grooves and microgrooves on a wide range of engineering materials such as ceramics, composites, and diamond. The micromachining of ceramics is highly demanded in industry because of its wide and potential uses in various fields such as automobile, electronic, aerospace, and biomedical engineering. Engineering ceramic, i.e. aluminium titanate (Al2TiO5), has tremendous application in the automobile and aero-engine industries owing to its excellent thermal properties. The present paper deals with the artificial neural

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Mazzei, Lorenzo, Antonio Andreini, and Bruno Facchini. "Assessment of modelling strategies for film cooling." International Journal of Numerical Methods for Heat & Fluid Flow 27, no. 5 (2017): 1118–27. http://dx.doi.org/10.1108/hff-03-2016-0086.

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Purpose Effusion cooling represents one the most innovative techniques for the thermal management of aero-engine combustors liners. The huge amount of micro-perforations implies a significant computational cost if cooling holes are included in computational fluid dynamics (CFD) simulations; therefore, many efforts are reported in literature to develop lower-order approaches aiming at limiting the number of mesh elements. This paper aims to report a numerical investigation for validating two approaches for modelling film cooling, distinguished according to the way coolant is injected (i.e. thro

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Salvadori, Simone, Mauro Carnevale, Alessia Fanciulli, and Francesco Montomoli. "Uncertainty Quantification of Non-Dimensional Parameters for a Film Cooling Configuration in Supersonic Conditions." Fluids 4, no. 3 (2019): 155. http://dx.doi.org/10.3390/fluids4030155.

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In transonic high-pressure turbine stages, oblique shocks originating from vane trailing edges impact the suction side of each adjacent vane. High-pressure vanes are cooled to tolerate the combustor exit-temperature levels, then it is highly probable that shock impingement will occur in proximity to a row of cooling holes. The presence of such a shock, together with the inevitable manufacturing deviations, alters the location of the shock impingement and of the performance parameters of each cooling hole. The present work provides a general description of the aero-thermal field that occurs on

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Shukla, Sidharth Kumar, and Amrita Priyadarshini. "Application of Machine Learning Techniques for Multi Objective Optimization of Response Variables in Wire Cut Electro Discharge Machining Operation." Materials Science Forum 969 (August 2019): 800–806. http://dx.doi.org/10.4028/www.scientific.net/msf.969.800.

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Wire Cut Electrical Discharge Machining (WEDM) is a non-conventional thermal machining process which is capable of accurately machine alloys having high hardness or part having complex shapes that are very difficult to be machined by the conventional machining processes. The WEDM finds applications in automobiles, aero–space, medical instruments, tool and die industries, etc. The input parameters considered for WEDM are pulse on time, pulse off time, flushing pressure, servo voltage, wire feed rate and wire tension. Performance of WEDM is mainly assessed by output variables such as, material r

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Lopata, Stanislaw, Pawel Oclon, Tomasz Stelmach, and Pawel Markowski. "Heat transfer coefficient in elliptical tube at the constant heat flux." Thermal Science 23, Suppl. 4 (2019): 1323–32. http://dx.doi.org/10.2298/tsci19s4323l.

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Cross-flow heat exchangers with elliptical tubes are often used in industrial application. In comparison with round tubes, the elliptical tubes have a better aero-dynamic shape, which results in a lower pressure drop of working fluid flowing through the inter-tubular space of heat exchanger. Also, a higher heat flux is transferred from gas to the wall of such a tube due to the more intense heat exchange process. To prove this thesis, the values of the heat transfer coefficient from the wall of the elliptical pipe to the water flowing inside were determined, using the data from the conducted me

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Chereches, Tudor, Paul Lixandru, Sergiu Mazuru, Pavel Cosovschi, and Daniel Dragnea. "Numerical Simulation of Plastic Deformation Process of the Glass Mold Parts." Applied Mechanics and Materials 657 (October 2014): 126–31. http://dx.doi.org/10.4028/www.scientific.net/amm.657.126.

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In our present days numerical simulation became an important tool of engineering. Numerical simulation methods allow quantitative examination of the complex processes and phenomena in the general area of physics and also provide an insight in their dynamic evolution and even can become important tools for the discovery of new phenomena. In essence, the numerical simulation transfer important aspect of physical reality in discrete forms of mathematical description recreates and solves the problems on computer and finally, highlights issues that the analyst required. This modern numerical method

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