Electromagnetic inversion using a reduced-order three-dimensional homogeneous model

2004 ◽  
Vol 20 (6) ◽  
pp. S17-S26 ◽  
Author(s):  
Neil V Budko ◽  
Rob F Remis
2002 ◽  
Vol 124 (4) ◽  
pp. 988-993 ◽  
Author(s):  
V. Esfahanian ◽  
M. Behbahani-nejad

An approach to developing a general technique for constructing reduced-order models of unsteady flows about three-dimensional complex geometries is presented. The boundary element method along with the potential flow is used to analyze unsteady flows over two-dimensional airfoils, three-dimensional wings, and wing-body configurations. Eigenanalysis of unsteady flows over a NACA 0012 airfoil, a three-dimensional wing with the NACA 0012 section and a wing-body configuration is performed in time domain based on the unsteady boundary element formulation. Reduced-order models are constructed with and without the static correction. The numerical results demonstrate the accuracy and efficiency of the present method in reduced-order modeling of unsteady flows over complex configurations.


2003 ◽  
Vol 2 (1) ◽  
pp. 59-73 ◽  
Author(s):  
Yaxin Song ◽  
C. J. Hartwigsen ◽  
Lawrence A. Bergman ◽  
Alexander F. Vakakis

Author(s):  
Jürgen Seidel ◽  
Kelly Cohen ◽  
Selin Aradag ◽  
Stefan Siegel ◽  
Thomas McLaughlin

2018 ◽  
Vol 25 (2) ◽  
pp. 298-309
Author(s):  
Hao Zhou ◽  
Sheng Meng ◽  
Chunhong Mo ◽  
Lujun Wang ◽  
Xiukui Hu ◽  
...  

Thermoacoustic oscillation occurs in modern industrial furnaces, gas turbines, and liquid rockets. However, the thermoacoustic prediction tools for furnaces vibration are less developed. This paper presents a one-dimensional (1D) linear acoustic approach to analyze the three-dimensional acoustic modes of a 660 MWe oil-fuel furnace. The interaction between the flame and acoustic field is described with the flame transfer function. The global time delay is evaluated through a Reynolds averaged simulation. The results of the 1D acoustic approach are compared with real furnace test data. The unstable modes are close to the natural modes of the furnace, and the 30 Hz in the longitudinal mode is the strongest vibration frequency. The effects of inlet length reduction and separation plate removal are also examined. When the separation plates are removed, the time lag of flame in response to inlet flow decreases from 52.5 milliseconds (ms) to 43.8 ms. The results of the 1D approach and finite element method (FEM) show a same safe operation window. The reduced-order procedure and FEM adopted in this study give us a solution to mitigate the vibration in the furnace.


Author(s):  
Kiyoshi Takagi ◽  
Hidekazu Nishimura

Abstract This paper deals with modeling and control of a crane mounted on a tower-like flexible structure. A fast transfer of the load causes the sway of the load rope and the vibration of the flexible structure. Our object is to control both the sway and the vibration by the inherent capability of the tower crane. This paper makes its three-dimensional models for simulation and reduced-order-model in order to design the decentralized control system. Then, we design the decentralized H∞ compensator and verify the efficiency by simulations and experiments.


2020 ◽  
Vol 11 (4) ◽  
pp. 1045-1055 ◽  
Author(s):  
N. Neuert ◽  
D. Dinkler

Abstract The aeroelastic behaviour of a wing with an over-the-wing pylon-mounted ultra-high bypass ratio engine and high-lift devices is studied with a reduced-order model. Wing, pylon and engine structures are reduced separately using the modal approach and described by their natural frequencies and modes. The characteristic aerodynamic loads are investigated with steady and unsteady flow simulations of a two-dimensional profile section. These results indicate possible heave instabilities at strongly negative angles of attack. Three-dimensional effects are taken into account using an adapted lifting line theory according to Prandtl. Due to high circulations resulting from the high-lift systems, the effective angles of attack are in the range of the potential instabilities. The substructures and aerodynamic loads are coupled in modal space. For the wing without three-dimensional effects, the bending instability occurs at the corresponding negative angles of attack. Even though there is potential for improvement, including the three-dimensional effects shifts the endagered area to possible operation points.


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