LES-Conjugate Heat Transfer Analysis of a Ribbed Cooling Passage Using the Immersed Boundary Method

Oh, Tae Kyung; Tafti, Danesh K.; Nagendra, Krishnamurthy

doi:10.1115/gt2019-90397

“…This model manipulates the density and thermal conductivity of solids through the application of the similarity theory, thereby achieving time scale control over transient heat conduction. Oh et al [30] artificially increased the solid thermal diffusivity and compared it to the actual physical diffusivity as a strategy to mitigate the substantial time scale discrepancies between the fluid and solid zones. Shi et al [31] introduced a time scale control model that is dependent on the Biot number (Bi) and Fourier number (Fo), drawing upon the principles of the similarity theory.…”

Section: Numerical Methods Of Conjugate Heat Transfer 21 Coupled Tech...mentioning

confidence: 99%

Conjugate Heat Transfer Advancements and Applications in Aerospace Engine Technology

Zha,

Xu,

Tang

et al. 2024

Applied Sciences

0

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Over the past few decades, conjugate heat transfer (CHT) technology has been instrumental in predicting temperature fields within aerospace engines, guiding engine design with its predictive capabilities. This paper comprehensively surveys the foundational technologies of CHT and their applications in engine design, backed by an extensive literature review. A novel coupling iteration methodology, su-F-TFTB, was proposed. Following this, it introduced grid splicing technology tailored for heat flux conservation, which significantly enhances the adaptability of CHT grids. Ultimately, this study employed the self-developed Aerospace Engine Numerical Simulation (AENS v4.0.1) software to perform CHT analyses on NASA-C3X turbine blades equipped with ten radial cooling systems. A comparative analysis of pressure distributions across various density meshes was undertaken to affirm mesh independence. Furthermore, the impacts of the Spalart–Allmaras (SA) one-equation model and k–ω Shear Stress Transport (SST) two-equation model on the temperature distribution in conjugate heat transfer were investigated. The results indicated that the k–ω SST model exhibited superior performance, aligning closely with NASA experimental data. This validation confirmed the effectiveness of the software.

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“…Validation and tuning with rig data is therefore required to calibrate predictions and it is fair to state that industrial practice still relies on a certain level of empiricism based on proprietary know-how. Higher order scale resolving methods such as LES [16,17] have the potential to overcome these deficiencies, but are computationally too demanding for day to day use in design. This is particularly the case when trying to address the simulation of interacting components with multi-physics effects since all these effects potentially lead to a wide range of spatial and time scales.…”

Section: Introductionmentioning

confidence: 99%

A Multifidelity Aero-Thermal Design Approach for Secondary Air Systems

Amirante

¹

,

Adami

²

,

Hills

³

2021

Journal of Engineering for Gas Turbines and Power

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The paper presents a multi-disciplinary approach for aero-thermal and heat transfer analysis for internal flows. The versatility and potential benefit offered by the approach is described through the application to a realistic low pressure turbine assembly. The computational method is based on a run time code coupling architecture that allows mixed models and simulations to be integrated together for the prediction of the sub-system aero thermal performance. In this specific application the model is consisting of two rotor blades, the embedded vanes, the inter-stage cavity and the solid parts. The geometry represents a real engine situation. The key element of the approach is the use of a fully modular coupling strategy that aims to combine (1) flexibility for design needs, (2) variable level of modelling for better accuracy and (3) in memory code coupling for preserving computational efficiency in large system and sub-system simulations. For this particular example Reynolds Averaged Navier-Stokes (RANS) equations are solved for the fluid regions and thermal coupling is enforced with the metal (conjugate heat transfer). Fluid-fluid interfaces use mixing planes between the rotating parts while overlapping regions are exploited to link the cavity flow to the main annulus flow as well as in the cavity itself for mapping of the metal parts and leakages. Metal temperatures predicted by the simulation are compared to those retrieved from a thermal model of the engine, and the results are discussed with reference to the underlying flow physics.

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A Multi-Fidelity Aero-Thermal Design Approach for Secondary Air Systems

Amirante¹,

Adami²,

Hills³

2021

Preprint

0

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The paper presents a multi-disciplinary approach for aero-thermal and heat transfer analysis for internal flows. The versatility and potential benefit offered by the approach is described through the application to a realistic low pressure turbine assembly. The computational method is based on a run time code-coupling architecture that allows mixed models and simulations to be integrated together for the prediction of the sub-system aero-thermal performance. In this specific application the model is consisting of two rotor blades, the embedded vanes, the inter-stage cavity and the solid parts. The geometry represents a real engine situation.The key element of the approach is the use of a fully modular coupling strategy that aims to combine (1) flexibility for design needs, (2) variable level of modelling for better accuracy and (3) in memory code coupling for preserving computational efficiency in large system and sub-system simulations.For this particular example Reynolds Averaged Navier-Stokes (RANS) equations are solved for the fluid regions and thermal coupling is enforced with the metal (conjugate heat transfer). Fluid-fluid interfaces use mixing planes between the rotating parts while overlapping regions are exploited to link the cavity flow to the main annulus flow as well as in the cavity itself for mapping of the metal parts and leakages. Metal temperatures predicted by the simulation are compared to those retrieved from a thermal model of the engine, and the results are discussed with reference to the underlying flow physics. Amirante GTP-20-1650Recent years have also seen a considerable increase in the use of Conjugate Heat Transfer (CHT) analysis with much of this work applied to blade cooling [2, 3], pre-swirl systems [4, 5] and disc cavities [6,7]. With the increase of computational power, aero-thermal studies have gradually moved from single-component analysis to more complex scenarios involving multiple cavities and transient regimes [8,9,10,11].Despite the recognised improvement achievable with simulations, when considering accuracy, efficiency and reduction of turn-around-time there are still a number of drawbacks that represent challenging hurdles to be addressed. First, heat transfer predictions based on RANS or URANS models suffer from inaccuracies linked to turbulence modelling and are notoriously poor for a variety of flows (most Amirante 3 GTP-20-1650

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LES-Conjugate Heat Transfer Analysis of a Ribbed Cooling Passage Using the Immersed Boundary Method

Cited by 4 publications

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Conjugate Heat Transfer Advancements and Applications in Aerospace Engine Technology

Conjugate Heat Transfer Advancements and Applications in Aerospace Engine Technology

A Multifidelity Aero-Thermal Design Approach for Secondary Air Systems

A Multi-Fidelity Aero-Thermal Design Approach for Secondary Air Systems

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