Direct Method of Design and Stress Analysis of Rotating Disks with Temperature Gradient,
Abstract
A method is presented for the determination of the contour of disks, typified by those of aircraft gas turbines, to incorporate arbitrary elastic-stress distributions resulting from either centrifugal or combined centrifugal and thermal effects. The specified stresses may be radial, tangential, or any combination of the two. For example, the equivalent stress may be specified at each radius inasmuch as this stress is generally used as the criterion of the occurrence of plastic flow. Use is made of the finite-difference approach in solving the stress equations, the amount of computation necessary in the evolution of a design being greatly reduced by the judicious selection of point stations and by the aid of a design chart. Use of the charts and of a preselected schedule of point stations is also applied to the direct problem of finding the elastic- and plastic-stress distribution in disks of a given design, thereby effecting a great reduction in the amount of calculation compared with previously published methods. Illustrative examples are presented to show computational procedured in the determination of a new design, and in analyzing an existing design for elastic stress and for stresses resulting from plastic flow.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1950
- Accession Number
- ADA298719
Entities
People
- S. S. Manson
Organizations
- National Aeronautics and Space Administration