Simulation of Cooling Systems in Gas Turbines PUBLIC ACCESS

[+] Author Affiliations
G. Ebenhoch, T. M. Speer

MTU Motoren- und Turbinen-Union München GmbH, München, Germany

Paper No. 94-GT-049, pp. V001T01A018; 8 pages
  • ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • The Hague, Netherlands, June 13–16, 1994
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7883-5
  • Copyright © 1994 by ASME


The design of cooling systems for gas turbine engine blades and vanes calls for efficient simulation programs. The main purpose of the described program is to determine the complete boundary condition at the coolant side to support a temperature calculation for the solid.

For the simulation of convection and heat pick up of the coolant flow, pressure loss, and further effects to be found in a rotating frame, the cooling systems are represented by networks of nodes and flow elements. Within each flow element the fluid flow is modelled by a system of ordinary differential equations based on the one-dimensional conservation of mass, momentum, and energy. In this respect, the computer program differs from many other network computation programs.

Concerning cooling configurations in rotating systems, the solution for a single flow element or the entire flow system is not guaranteed to be unique. This is due to rotational forces In combination with heat transfer and causes considerable computational difficulties which can be overcome by a special path following method in which the angular velocity is selected as the parameter of homotopy.

Results of the program are compared with measurements for three applications.

Copyright © 1994 by ASME
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