Experimental and numerical study of the film cooling performance of the suction side of a turbine blade under the rotating condition

2019 ◽  
Vol 136 ◽  
pp. 436-448 ◽  
Author(s):  
Haichao Wang ◽  
Zhi Tao ◽  
Zhiyu Zhou ◽  
Feng Han ◽  
Haiwang Li
Keyword(s):  
Turbine Blade ◽  
Film Cooling ◽  
Numerical Study ◽  
Suction Side ◽  
Cooling Performance

Surface Curvature Effects on Film Cooling Performance for Shaped Holes on a Model Turbine Blade

2020 ◽  
Vol 142 (11) ◽  
Author(s):  
Jacob D. Moore ◽  
Christopher Yoon ◽  
David G. Bogard
Keyword(s):  
Flat Plate ◽  
Turbine Blade ◽  
Film Cooling ◽  
Gas Turbines ◽  
Convex Surface ◽  
Adverse Pressure Gradient ◽  
Suction Side ◽  
Surface Curvature ◽  
Cooling Performance ◽  
Curvature Effects

Abstract Surface curvature has been shown to have significant effects on the film cooling performance of round holes, but the literature include few studies of its effects on shaped holes despite their prevalence in gas turbines. Experiments were performed using two rows of holes placed on the suction side of a scaled-up turbine blade in a low Mach number linear cascade wind tunnel with low freestream turbulence. The rows were placed in regions of high and low convex surface curvature. Geometries and flow conditions for the rows were matched to those from previous flat plate studies. Comparison of the adiabatic effectiveness results from the high curvature and flat plate rows revealed the same trends as those in the literature using round holes, with increased performance for the high curvature row at lower blowing ratios and the opposite at higher ones. The low curvature row had similar performance to the flat plate row at lower blowing ratios, suggesting the mild convex curvature had little beneficial effect. At higher blowing ratios, the low curvature row had inferior performance, which was attributed to the local freestream adverse pressure gradient that generated additional turbulence, promoting jet-to-mainstream mixing and decreasing performance.

A study for the film cooling performance on the turbine blade suction side tip region under rotating conditions

2019 ◽  
Vol 138 ◽  
pp. 483-495
Author(s):  
Haichao Wang ◽  
Zhi Tao ◽  
Zhiyu Zhou ◽  
Huimin Zhou ◽  
Yiwen Ma ◽  
...  
Keyword(s):  
Turbine Blade ◽  
Film Cooling ◽  
Suction Side ◽  
Cooling Performance

Film Cooling in a Separated Flow Field on a Novel Lightweight Turbine Blade

2008 ◽  
Author(s):  
Yoji Okita ◽  
Chiyuki Nakamata ◽  
Masaya Kumada ◽  
Masahiro Ikeda
Keyword(s):  
Flow Field ◽  
Turbine Blade ◽  
Film Cooling ◽  
Separation Bubble ◽  
Separated Flow ◽  
Suction Side ◽  
Pressure Side ◽  
Effective Measure ◽  
Cooling Performance ◽  
Recirculation Flow

The primary contribution of this research is to clarify the feasibility of a novel lightweight turbine blade with internal and external cooling, which is invented aiming at drastic reduction of weight. With a considerably thinner airfoil, an extensive separation bubble is formed on the pressure side and film cooling performance in such a flow field has to be investigated. Experimental results with a curved duct setup, which simulates the flow field around the proposed airfoil, show that a film cooling is still an effective measure of cooling even in the vastly separated region and it behaves quite similarly to the conventional correlation except for lower blowing ratios where the thermal field is strongly affected by the intense recirculation flow. Comparisons between the experimental and numerical results verify that an affordable RANS simulation is useful to investigate the detailed physics of this flow field. With the numerical modeling, a cooling performance of the proposed blade under a typical engine operating condition is simulated and the metal temperatures of the blade are also predicted with a fluid-solid conjugate calculation. The resultant thermal distribution in the airfoil suggests that the trailing edge portion is inevitably most critical in the temperature and also a considerable thermal gradient across the blade is induced. Thermal profile, however, is partly recovered with some of the film coolant being bypassed from the pressure side to the suction side.

Film Cooling Performance on Turbine Blade Suction Side With Various Film Cooling Hole Arrangements

2020 ◽  
Author(s):  
Zhiyu Zhou ◽  
Haiwang Li ◽  
Gang Xie ◽  
Ruquan You
Keyword(s):  
Turbine Blade ◽  
Film Cooling ◽  
Stokes Equations ◽  
Suction Side ◽  
Suction Surface ◽  
Cooling Effectiveness ◽  
Cooling Performance ◽  
Film Cooling Effectiveness ◽  
Injection Angle ◽  
Blowing Ratio

Abstract Numerical simulations were carried out to study the film cooling effectiveness distributions of different hole arrangements on the suction side of a high pressure turbine blade under rotating condition. The chord length and the height of the blade are 60mm and 80mm, respectively. Totally 12 models with different hole arrangements and different injection angles were studied. Each blade model has three rows of round holes with diameter of 0.9mm on the suction surface. The first row and the third row are fixed at streamwise location of 12.4% and 34% respectively. Three injection angles, 30°, 45°, and 60°, were investigated. Simulations were conducted under three rotational speeds, 600rpm, 800rpm, 1000rpm, with blowing ratio varying from 0.5 to 2.0. The Mainstream Reynolds numbers corresponding to the rotational speeds are 40560, 54080, and 67600 respectively. The temperature of the mainstream and the coolant is set at 463K and 303K so as to control the density ratio at 1.47. Simulations were performed by using SST turbulence model and were solved by using the three-dimensional Reynolds-averaged Navier–Stokes equations. Results showed that on the rotating turbine blade suction surface, film trajectories are drawn toward the midspan. The film trajectory arrangement may be different from the hole arrangement. Inline film trajectory arrangement can achieve higher film cooling effectiveness with slightly larger injection angle. Staggered film trajectory arrangement is better for uniform film cooling effectiveness distribution in spanwise and can achieve higher film cooling effectiveness with smaller injection angle. A smaller distance between the first row and the second row can achieve better film cooling performance at the downstream. With the increase of rotational speed, the mainstream Reynolds number increases, which improves the film cooling performance with smaller blowing ratio.

Surface Curvature Effects on Film Cooling Performance for Shaped Holes on a Model Turbine Blade

2019 ◽  
Author(s):  
Jacob D. Moore ◽  
Christopher Yoon ◽  
David G. Bogard
Keyword(s):  
Flat Plate ◽  
Turbine Blade ◽  
Film Cooling ◽  
Gas Turbines ◽  
Convex Surface ◽  
Adverse Pressure Gradient ◽  
Suction Side ◽  
Surface Curvature ◽  
Cooling Performance ◽  
Curvature Effects

Abstract Surface curvature has been shown to have significant effects on the film cooling performance of round holes, but the literature includes few studies of its effects on shaped holes despite their prevalence in gas turbines. Experiments were performed using two rows of holes placed on the suction side of a scaled-up turbine blade in a low-Mach-number linear cascade wind tunnel with low freestream turbulence. The rows were placed in regions of high and low convex surface curvature, respectively. Geometries and flow conditions for the rows were matched to those from previous flat plate studies. Comparison of the adiabatic effectiveness results from the high curvature and flat plate rows revealed the same trends as those in the literature using round holes — with increased performance for the high curvature row at lower blowing ratios and the opposite at higher ones. The low curvature row had similar performance to the flat plate row at lower blowing ratios, suggesting the mild convex curvature had little beneficial effect. At higher blowing ratios, the low curvature row had inferior performance, which was attributed to the local freestream adverse pressure gradient that generated additional turbulence, promoting jet-to-mainstream mixing and decreasing performance.

An investigation for the turbine blade film cooling performance on the suction side tip region under rotating condition

2019 ◽  
Vol 150 ◽  
pp. 864-874 ◽  
Author(s):  
Haichao Wang ◽  
Zhi Tao ◽  
Zhiyu Zhou ◽  
Guoqin Zhao ◽  
Feng Han ◽  
...  
Keyword(s):  
Turbine Blade ◽  
Film Cooling ◽  
Suction Side ◽  
Cooling Performance

Film Cooling in a Separated Flow Field on a Novel Lightweight Turbine Blade

2010 ◽  
Vol 132 (3) ◽  
Author(s):  
Yoji Okita ◽  
Chiyuki Nakamata ◽  
Masaya Kumada ◽  
Masahiro Ikeda
Keyword(s):  
Flow Field ◽  
Turbine Blade ◽  
Film Cooling ◽  
Separation Bubble ◽  
Separated Flow ◽  
Suction Side ◽  
Pressure Side ◽  
Effective Measure ◽  
Cooling Performance ◽  
Recirculation Flow

The primary contribution of this research is to clarify the feasibility of a novel lightweight turbine blade with internal and external cooling, which is invented, aiming at drastic reduction in weight. With a considerably thinner airfoil, an extensive separation bubble is formed on the pressure side, and film cooling performance in such a flow field has to be investigated. Experimental results with a curved duct setup, which simulates the flow field around the proposed airfoil, show that a film cooling is still an effective measure of cooling even in the vastly separated region, and it behaves quite similarly to the conventional correlation, except for lower blowing ratios, where the thermal field is strongly affected by the intense recirculation flow. Comparisons between the experimental and numerical results verify that an affordable Reynolds-averaged Navier–Stokes simulation is useful to investigate the detailed physics of this flow field. With the numerical modeling, a cooling performance of the proposed blade under a typical engine operating condition is simulated, and the metal temperatures of the blade are also predicted with a fluid-solid conjugate calculation. The resultant thermal distribution in the airfoil suggests that the trailing edge portion is inevitably most critical in the temperature, and also a considerable thermal gradient across the blade is induced. Thermal profile, however, is partly recovered with some of the film coolant being bypassed from the pressure side to the suction side.

Experimental and Numerical Study on the Effects of the Relative Position of Film Hole and Orientation Ribs on the Film Cooling With Ribbed Cross-Flow Coolant Channel

2020 ◽  
Author(s):  
Bingran Li ◽  
Cunliang Liu ◽  
Lin Ye ◽  
Huiren Zhu ◽  
Fan Zhang
Keyword(s):  
Heat Transfer ◽  
Relative Position ◽  
Film Cooling ◽  
Numerical Study ◽  
Cross Flow ◽  
Internal Cooling ◽  
Transfer Coefficients ◽  
Cooling Performance ◽  
Heat Transfer Coefficients ◽  
Numerical Studies

Abstract To investigate the application of ribbed cross-flow coolant channels with film hole effusion and the effects of the internal cooling configuration on film cooling, experimental and numerical studies are conducted on the effect of the relative position of the film holes and different orientation ribs on the film cooling performance. Three cases of the relative position of the film holes and different orientation ribs (post-rib, centered, and pre-rib) in two ribbed cross-flow channels (135° and 45° orientation ribs) are investigated. The film cooling performances are measured under three blowing ratios by the transient liquid crystal measurement technique. A RANS simulation with the realizable k-ε turbulence model and enhanced wall treatment is performed. The results show that the cooling effectiveness and the downstream heat transfer coefficient for the 135° rib are basically the same in the three position cases, and the differences between the local effectiveness average values for the three are no more than 0.04. The differences between the heat transfer coefficients are no more than 0.1. The “pre-rib” and “centered” cases are studied for the 45° rib, and the position of the structures has little effect on the film cooling performance. In the different position cases, the outlet velocity distribution of the film holes, the jet pattern and the discharge coefficient are consistent with the variation in the cross flow. The related research previously published by the authors showed that the inclination of the ribs with respect to the holes affects the film cooling performance. This study reveals that the relative positions of the ribs and holes have little effect on the film cooling performance. This paper expands and improves the study of the effect of the internal cooling configuration on film cooling and makes a significant contribution to the design and industrial application of the internal cooling channel of a turbine blade.

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