Inverse Determination of Smelter wall Erosion Shapes Using a Fourier Series Method
ABSTRACT An algorithm has been developed for the non-destructive determination of local thickness of the refractory material walls in smelter furnaces. This method uses measurements of temperature and heat flux at a number of points on the outer (fixed) surface of the furnace and assumes that the inner (guessed) surface of the furnace wall is isothermal. The temperature field is then predicted in the furnace wall subject to the measured temperature values on the external surface and the isothermal solidus temperature on the inner surface of the wall. The shape determination method then uses the difference between the measured and the computed heat fluxes on the outer surface of the furnace as a forcing function in an elastic membrane concept for the determination of the inner (melt refractory) surface shape. The initial guess of the wall inner shape can be significantly different from the final (unknown) wall shape. The entire wall shape determination procedure requires typically 5-15 temperature field analysis in the furnace wall material.
Inverse problems in engineering mechanics II : International Symposium on Inverse Problems in Engineering Mechanics 2000 (ISIP 2000), Nagano, Japan
Hardbound. Inverse Problems are found in many areas of engineering mechanics and there are many successful applications e.g. in non-destructive testing and characterization of material properties by ultrasonic or X-ray techniques, thermography, etc. Generally speaking, inverse problems are concerned with the determination of the input and the characteristics of a system, given certain aspects of its output. Mathematically, such problems are ill-posed and have to be overcome through development of new computational schemes, regularization techniques, objective functionals, and experimental procedures. Following the IUTAM Symposium on these topics, held in May 1992 in Tokyo, another in November 1994 in Paris, and also the more recent ISIP'98 in March 1998 in Nagano, it was concluded that it would be fruitful to gather regularly with researchers and engineers for an exchange of the newest research ideas. The most recent Symposium of this series Int
Efficient Transonic Shock-Free Wing Redesign Procedure Using a Fictitious Gas Method
A new method for transonic shock-free three-dimensional wing design based on the full potential tqutuion is presented. The method locally modifies (i.e., redesigns) the wing surface geometry beneath the supersonic region to produce a shock-free flow. Results for a redesigned nonlifting rectangular wing and for a redesigned lifting wing of ONERA M6 planform are illustrated. Significant drag reduction and improved lift-drag characteristics are achieved from the present redesign procedures. Methods of compensating for wing thickness reduction experienced in the redesign process and of correcting for viscous effects are discussed.