First principles of methodology of integrated optimization of image and parameters in hot section of gas turbine turboshaft engine

Аuthors

Nesterenko V. V.

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

e-mail: vladnesterenko@gmail.com

Abstract

The article is related to problems of integrated development ofturboshaft engines with axial-centrifugal or centrifugal compressor, rotary combustion chamber and axial-flow turbines of gas generator and power turbine with various cascade numbers. Criteria which define the choice of gas generator turbine and power turbine cascade number and construction arrangement are investigated. Development of inter-turbine transfer channel with minimal losses of gas energy and high level of gas dynamic stability on the base of experimental characteristics and criterial dependences of different versions ofdiffuser ring channels is examined. In conclusion, the advices for the choice of main parameters at development ofturboshaft gas turbine engines in power range 300... 3000 hp are given.

Keywords:

integrated development, turboshaft engine, matching, construction arrangement, rate, characteristics