Solution of Temperature Fields of Gas Turbine Parts by the Electrical Analogy Method,
Abstract
In order to refine the computation of parts of an internal combustion turbine which are subjected to high loads, it is necessary to know the temperature field. To this end, a device was constructed at the SVUTT for solving stationary and nonstationary temperature fields. A solution of stationary temperature fields for the moving blade shows a relatively slight influence of the heat transfer coefficient on the temperature field and on the flow of temperature through the blade. On the contrary, the influence of temperature in the root section of the temperature distribution along the blade length and along the surrounding radiating bodies is considerable, and is essential from the standpoint of service life. The nonstationary temperature field of the rotor disk of an internal combustion engine is substantially affected by the cooling of the disk's faces. The temperature gradients on the outer perimeter are very steep at first, and may reach as much as four times the values corresponding to the steady run. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 04, 1968
- Accession Number
- AD0845088
Entities
People
- J. Bilek
Organizations
- National Air and Space Intelligence Center