The paper is devoted to the use of mathematical simulation to investigate the possibilities of ensuring the admissible thermal mode of gas turbine packages equipped with aircraft and marine derivative gas turbine engines. The method proposed for complex heat transfer simulation in the gas turbine packages includes some models. A generalized mathematical model is formed to describe the thermophysical processes taking place in the gas turbine packages. A particular mathematical model of gas turbine engine casing heat transfer and a method to correct the boundary conditions are also developed. These models have been validated with the data collected from the heat transfer measurements in simple objects and from full-scale tests of turbo-compressor units. The proposed method of complex heat transfer simulation has been used to evaluate a temperature state of the gas turbine packages, in particular to ensure the effectiveness of covering the engine casing by thermal insulation.

This content is only available via PDF.
You do not currently have access to this content.