Sign in to use this feature.

Years

Between: -

Subjects

Journals

Article Types

Countries / Regions

Search Results (2)

Search Parameters:
Authors = Samaneh Rouina

Order results
Result details
Results per page
Select all
Export citation of selected articles as:
25 pages, 6036 KiB  
Review
The Aero-Thermal Performance of Purge Flow and Discrete Holes Film Cooling of Rotor Blade Platform in Modern High Pressure Gas Turbines: A Review
by Giovanna Barigozzi, Hamed Abdeh, Samaneh Rouina and Nicoletta Franchina
Int. J. Turbomach. Propuls. Power 2022, 7(3), 22; https://doi.org/10.3390/ijtpp7030022 - 4 Jul 2022
Cited by 15 | Viewed by 4143
Abstract
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 [...] Read more.
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. Full article
Show Figures

Figure 1

13 pages, 4802 KiB  
Article
Combined Experimental and CFD Investigation of Flat Plate Film Cooling through Fan Shaped Holes
by Samaneh Rouina, Silvia Ravelli and Giovanna Barigozzi
Int. J. Turbomach. Propuls. Power 2019, 4(2), 7; https://doi.org/10.3390/ijtpp4020007 - 14 May 2019
Cited by 12 | Viewed by 4522
Abstract
The present paper reports the results of an experimental and computational investigation of flat plate film cooling jets discharged from three fan-shaped holes. Measurements have been carried out at near unity density ratio in a low-speed wind tunnel, at low inlet turbulence intensity, [...] Read more.
The present paper reports the results of an experimental and computational investigation of flat plate film cooling jets discharged from three fan-shaped holes. Measurements have been carried out at near unity density ratio in a low-speed wind tunnel, at low inlet turbulence intensity, with blowing ratios (BR) of 1 and 2. Aerodynamic results have shown that the jet stays attached to the flat plate. Thermal measurements have revealed that film cooling effectiveness decreases downstream of the holes, and BR equal to 1 provides the best trade-off between cooling air consumption and thermal protection. Consequently, BR = 1 was selected for assessing the performance of different turbulence models, implemented in STAR-CCM+, according with the steady Reynolds-averaged Navier–Stokes (RANS) approach. Predictions from realizable k-ε (RKE), shear stress transport k-ω (SST KW) and Reynolds stress model (RSM) were compared against measurements of laterally averaged and centerline adiabatic effectiveness, as well as off-the-wall velocity maps and profiles of stress components. RSM provided the most accurate predictions. Full article
Show Figures

Figure 1

Back to TopTop