Effect of Secondary Flows on Heat Transfer of a Gas Turbine Blade

El-Batsh, Hesham M.; Nada, S.A.; Abdo, Samia Nasreldin; Eltayesh, Abdelgalil

doi:10.1155/2013/797841

Cited by 2 publications

(3 citation statements)

References 23 publications

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“…Numerical three-dimensional (3D) simulations were performed using the CFX and Ansys software to calculate the temperature distributions and heat transfer coefficients. Hesham et al [8] investigated the three-dimensional heat transfer characteristics of a gas turbine blade. The numerical results presented good agreement with experimental measurements.…”

Section: Literature Reviewmentioning

confidence: 99%

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Heat Transfer Analysis in a Single Spool Gas Turbine by Using Calculated-Estimated Coefficients with the Finite Element Method

et al. 2020

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In this paper, a calculation procedure is presented to estimate the heat transfer coefficients of a single spool gas turbine designed to generate 5 kN of thrust. These heat transfer coefficients are the boundary conditions which govern the heat interaction between the solid parts and the working fluid in the gas turbine. However, the calculation of these heat transfer coefficients is not a trivial task, since it depends on complex fluid flow conditions. Empirical correlations and assumptions have been used to find convective heat transfer coefficients over most components, including stator vanes, rotor blades, disc faces, and disc platforms. After defining the heat transfer coefficients, the finite element method was used to determine the temperature distribution in one eighth section of the gas turbine making use of the problem cyclic symmetry. Both static and rotating assemblies have been modeled. The results allowed the prediction of the thermal expansion behavior of the whole single spool gas turbine with special attention to the safety margin of clearances. Furthermore, having the temperature distribution defined, it is possible to calculate the thermal stresses in any mechanical component. Additionally, it is possible to specify suitable metallic alloys for achieving appropriate performance in every case. The structural integrity of all components was then assured with the temperature distribution and thermal expansion behavior under knowledge. Thus, the mechanical drawings could be released to manufacturing.

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Section: Literature Reviewmentioning

confidence: 99%

“…Equations ( 6), (8), and (10) are used to estimate the heat transfer coefficient distribution over the turbine blades and vanes. The same correlations apply to compressor blades and diffuser vanes.…”

Section: Stator Vanes and Disc Bladesmentioning

confidence: 99%

Heat Transfer Analysis in a Single Spool Gas Turbine by Using Calculated-Estimated Coefficients with the Finite Element Method

et al. 2020

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“…al. [16], investigated the three-dimensional heat transfer characteristics of a gas turbine blade. The numerical results presented good agreement with experimental measurements.…”

Section: Literature Reviewmentioning

confidence: 99%

Finite Element Analysis to Verify the Structural Integrity of an Aeronautical Gas Turbine Disc Made from Inconel 713LC Superalloy

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Creci

Jesus

et al. 2019

AEF

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Gas turbines are very important because they can be used in several areas, such as aeronautics and electric power generation systems. The operation of a gas turbine can be done by less pollutant fuels when compared to traditional kerosene, for example, resulting in less degradation to environment. Gas turbines may fail from a variety of sources, with the possibility of serious damage results. In this work, the structural integrity of the hot disc of an aeronautical gas turbine is addressed. Several numerical analyses have been performed by the finite element method: Temperature Distributions, Thermal Stresses and Dilatations, Structural Stresses and Deformations, Modal Behaviors and Fatigue Analysis. Creep of blades has also been considered. These are the most important failure modes that can happen to the studied hot disc under operating service. All these analysis have been performed considering the boundary conditions at the design point with maximum rotational speed. The mesh of the problem has been strictly evaluated by adaptive refinement of nodes and elements combined with a convergence analysis of results. Then, the material and basic properties of the hot disc have been defined to assure a normal operation free from failures. Therefore, the mechanical drawings of the studied hot turbine disc have been released for manufacturing and the construction of the first prototype of the aeronautical gas turbine is in testing phase showing that the results presented in this work are consistent.

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Effect of Secondary Flows on Heat Transfer of a Gas Turbine Blade

Cited by 2 publications

References 23 publications

Heat Transfer Analysis in a Single Spool Gas Turbine by Using Calculated-Estimated Coefficients with the Finite Element Method

Heat Transfer Analysis in a Single Spool Gas Turbine by Using Calculated-Estimated Coefficients with the Finite Element Method

Finite Element Analysis to Verify the Structural Integrity of an Aeronautical Gas Turbine Disc Made from Inconel 713LC Superalloy

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