Tucker, PG and Long, CA (1992) Finite element analysis of compressor disc heat transfer using the transient conduction method with sparse boundary collocation points. In: UNSPECIFIED pp. 409-432..Full text not available from this repository.
Surface temperature measurements from two discs of a gas turbine compressor rig are used as boundary conditions for the transient conduction solution (inverse heat transfer analysis). The disc geometry is complex, and so the finite element method is used. There are often large radial temperature gradients on the discs, and the equations are therefore solved taking into account the dependence of thermal conductivity on temperature. The solution technique also makes use of a multigrid algorithm to reduce the solution time. This is particularly important since a large amount of data must be analyzed to obtain correlations of the heat transfer. The finite element grid is also used for a network analysis to calculate the radiant heat transfer in the cavity formed between the two compressor discs. The work discussed here proved particularly challenging as the disc temperatures were only measured at four different radial locations. Four methods of surface temperature interpolation are examined, together with their effect on the local heat fluxes. It is found that the choice of interpolation method depends on the available number of data points. Bessel interpolation gives the best results for four data points, whereas cubic splines are preferred when there are considerably more data points. The results from the analysis of the compressor rig data show that the heat transfer near the disc inner radius appears to be influenced by the central throughflow. However, for larger radii, the heat transfer from the discs and peripheral shroud is found to be consistent with that of a buoyancy-induced flow.
|Item Type:||Conference or Workshop Item (UNSPECIFIED)|
|Divisions:||Div A > Fluid Mechanics|
|Depositing User:||Cron Job|
|Date Deposited:||09 Dec 2016 18:10|
|Last Modified:||23 Feb 2017 06:11|