Convective Cooling Optimization of a Blade for a Supercritical Steam Turbine

Nowak, Grzegorz; ́blewski, Włodzimierz Wro; Nowak, Iwona

doi:10.1115/gt2011-46821

Cited by 3 publications

(3 citation statements)

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“…The results of the simulations are assessed showing a way to check the standard of those cooling ducts [32]. Nowak et al [33] presents the application of conjugate heat transfer prediction for optimization of a cooling system configuration. The search procedure used the evolutionary algorithmic rule.…”

Section: Numerical Simulation Of the Cooling Of Turbine Blades Through Jet Impingementmentioning

confidence: 99%

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Sharma¹,

Kumar²,

Singh³

et al. 2021

IJHT

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Developments in the gas turbine technology have caused widespread usage of the Turbomachines for power generation. With increase in the power demand and a drop in the availability of fuel, usage of turbines with higher efficiencies has become imperative. This is only possible with an increase in the turbine inlet temperature (TIT) of the gas. However, the higher limit of TIT is governed by the metallurgical boundary conditions set by the material used to manufacture the turbine blades. Hence, turbine blade cooling helps in drastically controlling the blade temperature of the turbine and allows a higher turbine inlet temperature. The blade could be cooled from the leading edge, from the entire surface of the blade or from the trailing edge. The various methods of blade cooling from leading edge and its comparative study were reviewed and summarized along with their advantages and disadvantages.

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Section: Numerical Simulation Of the Cooling Of Turbine Blades Through Jet Impingementmentioning

confidence: 99%

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Sharma¹,

Kumar²,

Singh³

et al. 2021

IJHT

View full text Add to dashboard Cite

show abstract

“…This can remove from our research scope many optimal shapes. Nowak et al [45] optimized the maximum thermal gradient and temperature using the genetic algorithm method with four curves of Bezier. Some controlling points were constrained for decreasing the design variable numbers.…”

Section: Figure 2 Geometry Model With Boundary Walls [24]mentioning

confidence: 99%

Cooling Process of Gas Turbine Blade: A Comparison Study

Ballaoot¹,

Hamza

2020

QJES

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The gas turbine engines are occupied an important sector in the energy production and aviation industry and this important increase day after day for their features. One of the most important parameters that limit the gas turbine engine power output is the turbine inlet temperature. The higher is the turbine inlet temperature, the higher is the power output or thrust but this increases of risks of blade thermal failure due to metallurgical limits. Thus the need for a good and efficient process of blade cooling can lead to the best compromise between a powerful engine and safe operation. There are two major methods: film or external cooling and internal cooling inside the blade itself. . In the past number of years there has been considerable progress in turbine cooling research and this paper is limited to review a few selected publications to reflect recent development in turbine blade film cooling. The maximum drop in the surface temperature of the gas turbine blade and associated thermal stress – due to incorporating cooling systems- were 735 ˚C, 1217 N/mm2 respectively.

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“…Therefore, intensive research and development efforts have been invested in developing materials that can withstand high temperature and pressure [8,9]. At the same time, research on cooling systems is being carried out to prevent fatigue failure arising at critical locations such as blade roots and turbine casings due to very high temperature [10,11].…”

Section: Introductionmentioning

confidence: 99%