Cooling system optimisation of turbine guide vane

Nowak, Grzegorz; Wróblewski, Włodzimierz

doi:10.1016/j.applthermaleng.2008.03.015

Cited by 21 publications

(9 citation statements)

References 7 publications

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“…A correct selection of the cooling system geometry and parameters is a complex and e consequently e a difficult task. Solving it requires a more and more detailed identification of the thermal and flow phenomena for complex geometrical configurations, as well as the use of optimization methods [2]. Experimental testing is widely used to investigate cooling conditions despite the fact that such tests are very expensive and difficult, mainly due to the high temperature and rotation-related phenomena [3,4].…”

Section: Introductionmentioning

confidence: 99%

Heat transfer intensification using acoustic waves in a cavity

Rulik

Wróblewski

Nowak

et al. 2015

Energy

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Section: Introductionmentioning

confidence: 99%

Heat transfer intensification using acoustic waves in a cavity

Rulik

Wróblewski

Nowak

et al. 2015

Energy

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“…A simplified geometry of the honeycomb is adopted in this case, which makes it possible to substantially reduce the geometrical mesh size and, consequently, to carry out a full optimization process. Another example of optimization drawing on genetic algorithms are works [4,5], which concern the thermal and flow optimization of the turbine blades cooling system.…”

Section: Introductionmentioning

confidence: 99%

Metamodel-Based Optimization of the Labyrinth Seal

Rulik

Wróblewski

Frączek

2017

Archive of Mechanical Engineering

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The presented paper concerns CFD optimization of the straight-through labyrinth seal with a smooth land. The aim of the process was to reduce the leakage flow through a labyrinth seal with two fins. Due to the complexity of the problem and for the sake of the computation time, a decision was made to modify the standard evolutionary optimization algorithm by adding an approach based on a metamodel. Five basic geometrical parameters of the labyrinth seal were taken into account: the angles of the seal's two fins, and the fin width, height and pitch. Other parameters were constrained, including the clearance over the fins. The CFD calculations were carried out using the ANSYS-CFX commercial code. The in-house optimization algorithm was prepared in the Matlab environment. The presented metamodel was built using a Multi-Layer Perceptron Neural Network which was trained using the Levenberg-Marquardt algorithm. The Neural Network training and validation were carried out based on the data from the CFD analysis performed for different geometrical configurations of the labyrinth seal. The initial response surface was built based on the design of the experiment (DOE). The novelty of the proposed methodology is the steady improvement in the response surface goodness of fit. The accuracy of the response surface is increased by CFD calculations of the labyrinth seal additional geometrical configurations. These configurations are created based on the evolutionary algorithm operators such as selection, crossover and mutation. The created metamodel makes it possible to run a fast optimization process using a previously prepared response surface. The metamodel solution is validated against CFD calculations. It then complements the next generation of the evolutionary algorithm. b -parameter specifying the non-uniform rate (b = 2), [-]

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“…[12] experimentally and numerically investigated showerhead cooled turbine guide vanes and concluded that 18% and 44% of temperature peaks are reduced at the leading edge. [13] optimized the size and number of passages in the gas turbine guide vanes. The authors analyzed circular holes varies in number, size and locations.…”

Section: Introductionmentioning

confidence: 99%

Structural Investigation on Cooling Design Influences in Rene-77 made Gas Turbine Guide Vanes

Saravanan¹,

Reddy²

2017

ijastems

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-Even though high temperature materials are preferred for gas turbine blades and guide vanes, appropriate design of its cooling is imperative. Selection of cooling and its design is very intricate task. With extreme care, knowledge and sophisticated facilities required to perform them. This research investigates the cooling designs on gas turbine guide vane made-up of Rene -77. Both existing impingement cooling designs as well as an improved showerhead cooling design are investigated. The structural design and finite element analysis performed in Pro/E. The result shows that the improved design out performs.

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Cooling system optimisation of turbine guide vane

Cited by 21 publications

References 7 publications

Heat transfer intensification using acoustic waves in a cavity

Heat transfer intensification using acoustic waves in a cavity

Metamodel-Based Optimization of the Labyrinth Seal

Structural Investigation on Cooling Design Influences in Rene-77 made Gas Turbine Guide Vanes

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