Thermal test bench designing for turbojet engines turbines studying

Аuthors

Medvedeva A. V.^*, Khopin P. N.

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: simvolik-berk@yandex.ru

Abstract

The article presents a draft proposal for the thermal test bench development for conducting research tests of full-scale turbines of turbojet engines with a combustion chamber with the heat flows reconstitution close to the full-scale ones. A sketchy option of the bench layout, the list of parameters under study, as well as 3D-model of the intake device, being proposed for the bench with ready-made compressor supply line, based testing center with pre-installed equipment are presented. The consumed electric power is 734 MW, which ensures simulation of the altitudevelocity flight conditions in the 0–27 km altitude range, Mach numbers of 0–4 for the air-jet engine with the takeoff thrust up to 25 ton-force.

Keywords:

test bench, turbine, combustion chamber, turbojet engine, intake device

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