Conjugate Heat Transfer Analysis for Gas Turbine Cooled Blade

Ho, Kuo-San; Urwiller, Christopher; Konan, S. Murthy; Liu, Jong S.; Aguilar, Bruno

doi:10.1115/gt2014-25952

Cited by 2 publications

(1 citation statement)

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“…Therefore total number of 36 million elements is generated for the whole simulation file where Table 1 shows each domain cell number one by one. [8] with automatic wall treatment approach performed for fluid simulation. The purpose of automatic wall treatments is to make results insensitive with respect to wall mesh refinement [9].…”

Section: Grid Generationmentioning

confidence: 99%

Temperature Calculation in an Uncooled Low-pressure Stage of a Heavy-duty Gas Turbine Using Conjugate Heat Transfer Analysis

Salemkar

Poursamad

Torabideh

et al. 2017

JGPP

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In this paper, conjugate heat transfer (CHT) simulation is performed for a low-pressure stage of MGT-70, a heavy-duty gas turbine (GT) manufactured by MAPNA Group. Although the vane and the blade are uncooled, CHT analysis is performed to assess the validity of using the fluid temperature of an adiabatic simulation as the uncooled vanes or blades temperature, and also to model the heat transfer between root or shroud and vane or blade profile. To compare the resultant temperatures of CHT and adiabatic flow analysis both simulations are done, using the same boundary conditions. The vane shroud extends over the blade tip, which is of free-standing type, and there is not a shroud segment. In fact, the vane and blade share the shroud. In order to predict the shroud temperature more accurately, the vane and the blade are simulated simultaneously as a stage using appropriate interfaces. A single vane CHT simulation is also performed to evaluate the effect of blade tip flow on the shroud temperature. Furthermore, the cavity above the shroud, containing the cooling and sealing flow, is also included in the model to better prediction of the shroud temperature. In addition, the rim cavity and the labyrinth seal under the vane platform are included in the model to better predict the vane platform temperature and to capture the effect of purge flows on vane and blade temperature. Simulation results show that, although, the average bulk temperature of the profile in both CHT and adiabatic simulations are close to each other, there are great differences in temperature distribution over the suction side and pressure side. These differences are because of heat flux through the profile in CHT simulation, which results in a more realistic metal temperature distribution. Comparing the results of the single vane simulation and stage simulation no remarkable difference is observed in the temperature distribution, except for the shroud region above blade tip. This reveals that, although, the tip leakage flow is better captured in the stage simulation, it is only useful when the shroud temperature is of interest and it does not affect the vane profile temperature distribution. Finally, the inclusion rim cavity and labyrinth seal in the simulation helps to predict the mass flow distribution of purge flows and the effect of these flows on platform temperature distribution in vane and blade.

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Section: Grid Generationmentioning

confidence: 99%

Temperature Calculation in an Uncooled Low-pressure Stage of a Heavy-duty Gas Turbine Using Conjugate Heat Transfer Analysis

Salemkar

Poursamad

Torabideh

et al. 2017

JGPP

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Analysis of the aerothermal performance of modern commercial high-pressure turbine rotors using different levels of fidelity

Carta,

Shahpar,

Ghisu

2024

Proceedings of the Institution of Mechanical Engineers, Part A:

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In the field of design and optimization of sophisticated geometries such as film-cooled turbine blades of modern jet engines, Computational Fluid Dynamics (CFD) simulation is commonly employed. As the pursuit for higher turbine entry temperatures intensifies, it becomes crucial for computational analyses to offer accurate predictions of metal temperatures and heat transfer coefficients on these critical components. This study investigates the impact of key physical factors that characterize the operation of these components on the accuracy of the computational model. In particular, the effects of including the exchange of thermal energy between the fluid and solid domains, as well as modelling the unsteady interaction between the rotor and stator are studied. The research focuses on a fully featured one-and-a-half stage high-pressure turbine of a commercial jet engine, utilizing proprietary software for conducting 3D Reynolds-Averaged Navier-Stokes flow simulations. To model the fluid-solid thermal interaction, steady-state Conjugate Heat Transfer (CHT) simulations are performed. The CHT results are then compared with experimental data obtained from a thermal paint test, achieving good levels of agreement. Additionally, phase-lag simulations are executed under adiabatic-wall conditions to evaluate the influence of stator-rotor interaction on near-wall gas temperatures. This work shows that, by modelling the periodic unsteadiness at the stator-rotor interface with a phase-lag technique, the maximum near-wall gas temperature prediction is significantly increased, sometimes more than 100K, with respect to the steady-state model one. Findings from this work also suggest that simplified “strip” source terms used to model the presence of film cooling hole rows on the surface of a blade can be used with satisfactory accuracy only for nominal conditions. The mass flows delivered by each source strip should not be linearly scaled based on mainstream quantities for use in different conditions, but they should be recalculated from scratch for the new conditions.

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Conjugate Heat Transfer Analysis for Gas Turbine Cooled Blade

Cited by 2 publications

References 0 publications

Temperature Calculation in an Uncooled Low-pressure Stage of a Heavy-duty Gas Turbine Using Conjugate Heat Transfer Analysis

Temperature Calculation in an Uncooled Low-pressure Stage of a Heavy-duty Gas Turbine Using Conjugate Heat Transfer Analysis

Analysis of the aerothermal performance of modern commercial high-pressure turbine rotors using different levels of fidelity

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