Accession Number : AD0667702

Title :   THERMAL STATE OF GAS-TURBINE ROTOR DISKS AND THEIR TEMPERATURE STRESSES,

Corporate Author : FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Kuzmin,G. A.

Report Date : 13 OCT 1967

Pagination or Media Count : 17

Abstract : Both the stationary and transient thermal states were considered. Thermal analysis was limited to the convective heat exchange, neglecting the relatively insignificant contributions of radiation and heat conductivity. Analysis of the stationary case was facilitated by assumptions of a thin rotor disk of uniform thickness and symmetrical heat dissipation, thus admitting a direct solution in terms of modified Bessel functions. Solutions for the non-stationary case of the engine start were obtained by a graphical method. It was noted that the rotor disk periphery temperature reaches its maximum (600C) soon after the engine start, while the central portion approaches its maximum temperature at a much slower rate. Thus the turbine rotor is seen to possess a high thermal inertia, and the maximum temperature difference between its periphery and center occurs soon after the engine start. This means that little thermal stress relief can be obtained by prolonging engine warm-up. Radial and circular stresses were calculated for theoretically and for experimentally determined data. Stress distributions are presented in graphs. (Author)

Descriptors :   (*GAS TURBINE ROTORS, *THERMAL STRESSES), THERMAL ANALYSIS, CONVECTION(HEAT TRANSFER), THICKNESS, BESSEL FUNCTIONS, TEMPERATURE, GRAPHICS, USSR

Subject Categories : Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE