Full Three-Dimensional Optimization Platform of Turbine Blades Considering the Film Cooling

2013 ◽  
Author(s):  
Shaopeng Lu ◽  
Zhongran Chi ◽  
Songtao Wang ◽  
Fengbo Wen ◽  
Guotai Feng
Keyword(s):  
Film Cooling ◽  
Turbine Blades ◽  
Three Dimensional ◽  
Optimization Process ◽  
Pareto Optimal ◽  
Cooling Efficiency ◽  
Objective Functions ◽  
Nsga Ii ◽  
Aerodynamic Efficiency ◽  
Film Cooling Efficiency

In this paper, an optimization platform was established with Isight, cfx and the self-programming program which is used to generate the mesh. Film cooling effect can be taken into account. 15 parameters are selected as optimization variables. During the optimization process, the baseline blade and cooling holes are given by parameterized method. There are two objective functions during the optimization process. The first one is aerodynamic efficiency and the second one is film cooling efficiency. As there are two objective functions, NSGA-II is chosen as the multi-objective optimization algorithm. Then the Pareto-optimal front can be got. The results show that aerodynamic efficiency and film cooling efficiency restrict each other. It’s impossible to get the best solutions in one example, so the Pareto optimal set can provide a lot of choices. Different shapes make different effects on the aerodynamic efficiency and film cooling efficiency. From the above, it can be seen that the platform is helpful especially in the case that aerodynamic efficiency and film cooling efficiency restrict each other. This paper also discusses the prospects for platform applications.

scholarly journals Numerical Prediction of Film Cooling Effectiveness and the Associated Aerodynamic Losses With a Three-Dimensional Calculation Procedure

1990 ◽  
Author(s):  
G. H. Dibelius ◽  
R. Pitt ◽  
B. Wen
Keyword(s):  
Experimental Data ◽  
Film Cooling ◽  
Reverse Flow ◽  
Turbine Blades ◽  
Three Dimensional ◽  
Temperature Pattern ◽  
Main Stream ◽  
Cooling Efficiency ◽  
Film Cooling Effectiveness ◽  
Aerodynamic Losses

Film cooling of turbine blades by injecting air through holes or slots affects the main stream flow. A numerical model has been developed to predict the resulting three-dimensional flow and the temperature pattern under steady flow conditions. An elliptic procedure is used in the near injection area to include reverse flow situations, while in the upstream area as well as far downstream a partial-parabolic procedure is applied. As first step an adiabatic wall has been assumed as boundary condition, since for this case experimental data are readily available for comparison. At elevated momentum blowing rates, zones of reverse flow occur downstream of the injection holes resulting in a decrease of cooling efficiency. A variation of the relevant parameters momentum blowing rate m, injection angle α and ratio of hole spacing to diameter s/d revealed the combination of m ≈ 1, α ≈ 30° and s/d ≈ 2 to be the optimum with respect to the averaged cooling efficiency and to the aerodynamic losses. Cooling is more efficient with slots than with a row of holes not considering the related problems of manufacture and service life. The calculated temperature patterns compare well with the experimental data available.

Large eddy simulation of saw tooth plasma actuator for improving film cooling efficiency

2017 ◽  
Vol 231 (5) ◽  
pp. 357-370 ◽  
Author(s):  
Guozhan Li ◽  
Jianyang Yu ◽  
Fu Chen ◽  
Huaping Liu ◽  
Yanping Song ◽  
...  
Keyword(s):  
Large Eddy Simulation ◽  
Flat Plate ◽  
Film Cooling ◽  
Three Dimensional ◽  
Plasma Actuator ◽  
Cooling Efficiency ◽  
Flow Topology ◽  
Eddy Simulation ◽  
Large Eddy ◽  
Film Cooling Efficiency

This paper presents results on a saw tooth plasma actuator for the inducement of flow topology and the improvement of flat plate film cooling efficiency. A phenomenological plasma model is constructed to generate the three-dimensional plasma force vectors of the saw tooth plasma actuator. The dynamics of airflow induced by the saw tooth plasma actuator on a flat plate in quiescent air are numerically investigated. The results show that the saw tooth plasma actuator pushes the fluids in all three directions and induces a three-dimensional jet flow with counter rotating streamwise oriented vortices that propagate downstream. The flow field characteristics of both cylindrical hole with and without the saw tooth plasma actuator are studied by large eddy simulation, and a comparison is made. The saw tooth plasma actuator improves the cold jet adherent performance and promotes the spanwise spreading rate of the coolant. Meanwhile, the streamwise vortices induced by the saw tooth plasma actuator suppress the development of counter-rotating vortex pair, thus delaying the diffusion of coolant in the crossflow. Accordingly, the centerline cooling efficiency and the spanwise-averaged cooling efficiency are improved by 36% and 144% at x/ d = 15, compared with the baseline case without the saw tooth plasma actuator.

scholarly journals FILM COOLING OVER A FLAT PLATE WITH COOLANT SUPPLY IN TO TRIANGULAR INDENTATION

2018 ◽  
Vol 40 (3) ◽  
pp. 5-11
Author(s):  
А.А. Khalatov ◽  
N.A. Panchenko ◽  
О.О. Petliak
Keyword(s):  
Coriolis Force ◽  
Film Cooling ◽  
High Performance ◽  
Turbine Blades ◽  
Engineering Thermophysics ◽  
Cooling Efficiency ◽  
National Academy Of Sciences ◽  
Peak Displacement ◽  
Sst Turbulence Model ◽  
Film Cooling Efficiency

The modern high-performance gas turbine engines operate at the flow temperatures exceeding the melting temperature of materials, which require the blade cooling. However, the traditional scheme of film cooling is characterized by appearance of secondary vortex structures that destroy the coolant film. From the existing alternative schemes of film cooling, which allow protecting the turbine blades from influence of high temperatures, the scheme with triangular dimples has demonstrated good results in the stationary conditions. This cooling scheme was patented and tested in the Institute of Engineering Thermophysics, National Academy of Sciences of Ukraine. In order to determine the feasibility of such a scheme, it is necessary to consider the effect of the blade rotation influencing the film cooling efficiency. The results are given towards theoretical investigation of the film cooling efficiency of this scheme under rotation conditions. The study was performed using the ANSYS CFX package using SST-turbulence model. The blowing ratio was varied from 0.5 to 2.0. Numerical simulation performed for rotation parameters corresponding to the dominant influence of the Coriolis force – 10, 100 rpm, and centrifugal forces – 3000, 5000 and 7000 rpm. Оn the basis of computer simulation, it has been shown that rotation does not affect weakly the average efficiency of film cooling at Coriolis force, but causes a peak displacement of local adiabatic efficiency, at rotation parameter of 7000 rpm, when there is a distortion of the flow lines.

Measurement of Film Cooling Efficiency of Fan-shaped Holes on Endwall of Turbine Blades

2021 ◽  
Vol 24 (5) ◽  
pp. 5-15
Author(s):  
Heeyoon Chung ◽  
Seokmin Kim ◽  
Dong-Ho Rhee ◽  
Young-Seok Kang
Keyword(s):  
Film Cooling ◽  
Turbine Blades ◽  
Cooling Efficiency ◽  
Film Cooling Efficiency

scholarly journals Comparison of turbine blade film cooling efficiency between PSP and TLC techniques in a stationary wind tunnel

AIP Advances ◽  
2021 ◽  
Vol 11 (1) ◽  
pp. 015333
Author(s):  
Xiaojian He ◽  
Haiwang Li ◽  
Guoqin Zhao ◽  
Ruquan You
Keyword(s):  
Wind Tunnel ◽  
Turbine Blade ◽  
Film Cooling ◽  
Cooling Efficiency ◽  
Film Cooling Efficiency

scholarly journals Comparison of Two-Equation Turbulence Models for Prediction of Heat Transfer on Film-Cooled Turbine Blades

1997 ◽  
Author(s):  
Vijay K. Garg ◽  
Ali A. Ameri
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Film Cooling ◽  
Turbine Blades ◽  
Three Dimensional ◽  
Turbulence Models ◽  
Computer Time ◽  
Suction Surface ◽  
The Heat Transfer Coefficient

A three-dimensional Navier-Stokes code has been used to compute the heat transfer coefficient on two film-cooled turbine blades, namely the VKI rotor with six rows of cooling holes including three rows on the shower head, and the C3X vane with nine rows of holes including five rows on the shower head. Predictions of heat transfer coefficient at the blade surface using three two-equation turbulence models, specifically, Coakley’s q-ω model, Chien’s k-ε model and Wilcox’s k-ω model with Menter’s modifications, have been compared with the experimental data of Camci and Arts (1990) for the VKI rotor, and of Hylton et al. (1988) for the C3X vane along with predictions using the Baldwin-Lomax (B-L) model taken from Garg and Gaugler (1995). It is found that for the cases considered here the two-equation models predict the blade heat transfer somewhat better than the B-L model except immediately downstream of the film-cooling holes on the suction surface of the VKI rotor, and over most of the suction surface of the C3X vane. However, all two-equation models require 40% more computer core than the B-L model for solution, and while the q-ω and k-ε models need 40% more computer time than the B-L model, the k-ω model requires at least 65% more time due to slower rate of convergence. It is found that the heat transfer coefficient exhibits a strong spanwise as well as streamwise variation for both blades and all turbulence models.

Effects of flow turbulence on film cooling efficiency

1995 ◽  
Vol 38 (11) ◽  
pp. 2117-2125 ◽  
Author(s):  
V.P. Lebedev ◽  
V.V. Lemanov ◽  
S.Ya. Misyura ◽  
V.I. Terekhov
Keyword(s):  
Film Cooling ◽  
Cooling Efficiency ◽  
Flow Turbulence ◽  
Film Cooling Efficiency
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