Study of cyclonic cooling system geometry parameters impact of gas turbine blade leading edge on its thermo-hydraulic characteristics

Aeronautical and Space-Rocket Engineering


DOI: 10.34759/vst-2021-4-232-244

Аuthors

Shevchenko I. V.*, Sokolov V. P.**, Rogalev A. N.***, Vegera A. N.****, Osipov S. K.*****

National Research University “Moscow Power Engineering Institute”, 14, Krasnokazarmennaya str., Moscow, 111250 Russia

*e-mail: ShevchenkoIV@mpei.ru
**e-mail: vl.sokolov2013@mail.ru
***e-mail: RogalevAN@mpei.ru
****e-mail: VegeraAN@mpei.ru
*****e-mail: OsipovSK@mpei.ru

Abstract

Cyclonic systems for the leading edge cooling are an effective way of heat transfer intensification, which ensures low pressure losses in the cooling channels and the lowest possible coolant consumption. One of the basic tasks the designer faces when developing a cooling system for a gas turbine blade with the leading edge cyclonic cooling consists in determining rational diameters of the intake and outtake orifices and the step of their placement, which allow ensuring maximum heat removal from the surface with a minimum temperature field asymmetry. An important feature of cyclone cooling is the high sensitivity of the heat transfer intensity and the nature of the heat transfer coefficients distribution over the surface of the cyclone chamber to the geometric parameters of the cooling system. These parameters are the orifices diameters ratio, their step, the cyclonic chamber size and shape, and the orifices shape. In this regard, numerical studies conduction is required for each particular blade structure to determine geometry parameters of the cyclonic chamber to obtain the required cooling efficiency. The presented work deals with numerical study of the heat transfer in the closed cyclonic channel, which is assumed to be applied for convective cooling of the turbine blade leading edge.

The thermal and hydraulic characteristics studies of a closed cyclone have been conducted to ensure the nozzle blade development for the high-temperature turbine with convective cooling of the leading edge. The intake orifices diameter was being varied from 1 mm to 2 mm, the outtake orifices diameter was being varied from 2 mm to 3 mm, and the cyclonic chamber was of 6.2 mm diameter. The article shows that area increasing of the intake and outtake orifices in the cyclonic chamber changes the heat transfer coefficients distribution profile. The local heat transfer coefficients were computed, and criterion equations for the dependence of the Nusselt number in the cyclone chambers on their geometric and operating parameters were elaborated.

It was found practical to reduce the outtake orifices diameter with conjoined step reduction for the heat transfer coefficients values increasing, which would ensure the non-uniformity reduction in the heat transfer coefficients distribution over the cyclonic channel height.

With the fixed pressure drop in the outtake and intake channels, the throughput of the cyclone channel is determined mainly by the area of the intake orifices, which allows the leading edge cooling efficiency enhancing, by increasing the outtake orifices area.

Keywords:

gas turbine, cooled blades, blade airfoil leading edge, cyclonic cooling, thermo-hydraulic processes

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