Design methods of modern air-jet engines turbine rotor blades film cooling system improvement

Aerospace propulsion engineering


Аuthors

Nesterenko V. G.*, Matushkin A. A.

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

*e-mail: valerynesterenk@yandex.ru

Abstract

Main principles of a choice of parametres and feature of designing of system of film cooling of a profile part of a feather of working shovels of high-temperature turbines GTE are considered at high sizes gas temperatures 1650К <(Т *) gas <1850 … 1900К for сопловым the turbine device on an input in the driving wheel. The expediency of orientation of channels of protecting cooling at an angle to a turbine axis is revealed, is close to a radial direction. In this case discrete streams of individual channels form a uniform protecting veil and their thermal efficiency becomes comparable to the system of cooling consisting of separate cracks. Also possibilities of economy of the expense of the cooling air spent for cooling of blades of the driving wheel of the turbine are investigated. With that end in view, various sites of a feather on shovel height, and also its bent and выпуклою the parties, it is necessary to cool differentially, in conformity with available distribution of temperature of gas to a profile part of a feather of a blade and level of non-uniformity radial distribution diagram gas temperatures on an input in the turbine.

Keywords:

airfoil; blade; cascade; rotor; heat-transfer; film-cooling; design; stage; rib


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