Turbine Disks for Jet Propulsion Units: An Account of Work of the Disk Panel of the Ministry of Supply, Gas Turbine Collaboration Committee, during the years 1941–1949

Abstract

In the first two parts of this paper attention has been directed to determination of the stresses in a disk as dependent upon elastic and plastic strain, including creep effects which may occur at the rim region. The problem has so far, however, been treated without complication introduced by the blade fastenings and therefore, in effect, the disk has been investigated as far as the base of the blade grooves or slots. It has, however, been realized that the projections forming blade root fastenings present their own problems, differing from those of the disk, and these problems have been left to be dealt with in this third portion of the paper. Nevertheless, in Parts I and II the fact that the root fastenings applied an interrupted radial loading at the outside, and not a perfectly distributed load as assumed in the analysis, was not overlooked.

Citation

Johnson, A.E. (1956), "Turbine Disks for Jet Propulsion Units: An Account of Work of the Disk Panel of the Ministry of Supply, Gas Turbine Collaboration Committee, during the years 1941–1949", Aircraft Engineering and Aerospace Technology, Vol. 28 No. 10, pp. 348-356. https://doi.org/10.1108/eb032744