The Aero-Thermal Performance of Purge Flow and Discrete Holes Film Cooling of Rotor Blade Platform in Modern High Pressure Gas Turbines: A Review
Reviewartikel, 2022

Design of cooling systems for rotor platforms is critical due to the complex flow field and heat transfer phenomena related to the secondary flow structures originating at the blade leading edge. Horseshoe vortex and passage vortex are the fluid-dynamic features that largely influence the aerodynamic behaviour and the thermal protection level of the platform. The driving parameter is the coolant to mainstream momentum flux ratio, but several issues have to be considered in the design process of cooling technologies. As well acknowledged, an in-depth understanding of losses and heat transfer phenomena are deemed necessary to design effective cooling systems. In the present review, measurements and predictions on the behaviour of the HPT rotor cooled platform, obtained during the last two decades by several research groups, are gathered, described and analysed in terms of aerodynamic losses and heat transfer performance, and are compared with one another with respect to the effectiveness level that is ensured.

film cooling effectiveness

rotor platform cooling

secondary flows

gas-turbine

Författare

Giovanna Barigozzi

Universita degli Studi di Bergamo

Hamed Abdeh

Universita degli Studi di Bergamo

Samaneh Rouina

Chalmers, Mekanik och maritima vetenskaper, Fordonsteknik och autonoma system

Nicoletta Franchina

Universita degli Studi di Bergamo

International Journal of Turbomachinery, Propulsion and Power

2504186X (eISSN)

Vol. 7 3 22

Ämneskategorier

Maskinteknik

DOI

10.3390/ijtpp7030022

Mer information

Senast uppdaterat

2024-01-03