Influence of simplifications of blade in gas turbine on film cooling performance. (5th January 2018)

• Record Type: Journal Article
• Authors: Zeng, Lingyu; Chen, Pingting; Li, Xueying; Ren, Jing; Jiang, Hongde
• Is Part Of: Applied thermal engineering. Volume 128(2018)
• Page Start: 877
• Page End: 886
• Publication Date: 2018-01-05
• Subjects: Film cooling -- Rotating -- Annular -- Twist blade; Heat engineering -- Periodicals; Heating -- Equipment and supplies -- Periodicals; Periodicals; 621.40205
• DOI: 10.1016/j.applthermaleng.2017.09.008
• Languages: English
• ISSNs: 1359-4311

Abstract

Highlights: Influence of blade cascade simplification on film cooling performance (η) was studied. The main difference between annular and linear cascade is in the area close to the hub. Significant error of η caused by simplifying blade form is at the leading edge regions. Rotation has little effect on the area averaged η, but large effect on the coolant distribution. The simplification of blade form has the most significant effect on film cooling. Abstract: With the development of gas turbine, twist blades are widely used in modern gas turbine designs. Under working conditions of gas turbine, twist blades rotate in the annular cascade. Under laboratory conditions, it is often simplified by using linear cascade, or using straight blades, or using non-rotating state to study film cooling performance. The influences of the three simplifications – annular cascade versus linear cascade, twist blade versus straight blade, rotation versus non-rotation on the film cooling performance are investigated. Twist blades serve as the reference model of the paper. Three rows of cylindrical film holes are arranged at the leading edge with a pitch-to-diameter ratio P/D = 8.0. One row of cylindrical film holes with a pitch-to-diameter ratio P/D = 8.4 is provided on the pressure side while two rows are provided on the suction side. The steady solutions are obtained by solving Reynolds-Averaged-Navier-Stokes equations with a finite volume method. The SST turbulence model coupled with γ-θ transition model is applied for the present simulations. A film cooling experiment of a turbine vane was done and the numerical results were in agreement with experimental data. It means the numerical methodology is feasible and reliable. Besides the reference case, three cases each of which is different with the reference case either in cascade form, or in blade form, or in movement state are simulated. As for the simplification of cascade form, the main difference between the annular cascade and linear cascade appears in the area which is close to the hub, as the location of vortex core in annular cascade passage is much lower than that in linear cascade passage near the hub because of curvature effect. As for the simplification of blade form, there is a significant error of film cooling effectiveness at the leading edge regions caused by the simplification of blade form. The pressure variety at the leading edge due to geometric differences between the twist blade and straight blade coupled with rotation leads to lift off. As for the simplification of movement state, there is little effect on the area averaged film effectiveness of the whole blade, but quite a little effect on the coolant distribution. Overall, the simplification of blade form from twist to straight has the most significant effect on film cooling. The film cooling characteristics of twist blade need to be taken into consideration in the design.