Conjugate Heat Transfer Analysis of Internally Cooled Configurations

Rigby, David L.; Lepicovsky, J.

doi:10.1115/2001-gt-0405

Cited by 33 publications

(15 citation statements)

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“…Examples of such expanded CFD solvers for the conjugate analysis are NASA Glenn-HT code by Rigby and Lepicovsky (2001), and Aachen's CHTflow solver by Bohn et al (2001). A number of papers have been published showing application of the conjugate analysis for engine component temperature predictions, such as a real turbine rotor-stator system simulation by Okita and Yamawaki (2002), a blade film cooling prediction by Bohn et al (2003) and an internally cooled turbine blade application by Kusterer et al (2004).…”

Section: Conjugate Analysismentioning

confidence: 99%

Use of CFD for Thermal Coupling in Aeroengine Internal Air Systems Applications

Sun

Chew

Hills

2009

Fluid Machinery and Fluid Mechanics

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With the rapid progress of computational fluid dynamics (CFD) and computer technology, CFD has been increasingly used for aero-engine component temperature predictions. This paper presents a review of the latest progress in this aspect with emphasis on internal air system applications. The thermal coupling methods discussed include the traditional finite element analysis (FEA), the conjugate heat transfer, FEA/CFD coupling procedure and other thermal coupling techniques. Special attention is made to identify the merits and disadvantages between the various methodologies. Discussion is further extended on the steady and transient thermal coupling applications.

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Section: Conjugate Analysismentioning

confidence: 99%

Use of CFD for Thermal Coupling in Aeroengine Internal Air Systems Applications

Sun

Chew

Hills

2009

Fluid Machinery and Fluid Mechanics

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“…1 [5,6,7], Han et al [8], Rigbi et al [9] and Heidmann et al [10]. In summary, the conjugate wall effect on adiabatic wall temperatures has neither been noticed nor investigated in the previous studies.…”

Section: Introductionmentioning

confidence: 98%

An Investigation of Treating Adiabatic Wall Temperature as the Driving Temperature in Film Cooling Studies

Zhao

Wang

2012

Journal of Turbomachinery

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In film cooling heat transfer analysis, one of the core concepts is to deem film cooled adiabatic wall temperature (T aw ) as the driving potential for the actual heat flux over the filmcooled surface. Theoretically, the concept of treating T aw as the driving temperature potential is drawn from compressible flow theory when viscous dissipation becomes the heat source near the wall and creates higher wall temperature than in the flowing gas. But in conditions where viscous dissipation is negligible, which is common in experiments under laboratory conditions, the heat source is not from near the wall but from the main hot gas stream; therefore, the concept of treating the adiabatic wall temperature as the driving potential is subjected to examination. To help investigate the role that T aw plays, a series of computational simulations are conducted under typical film cooling conditions over a conjugate wall with internal flow cooling.The result and analysis support the validity of this concept to be used in the film cooling by showing that T aw is indeed the driving temperature potential on the hypothetical zero wall thickness condition, ie. T aw is always higher than T w with underneath (or internal) cooling and the adiabatic film heat transfer coefficient (h af ) is always positive.However, in the conjugate wall cases, T aw is not always higher than wall temperature (T w ), and therefore, T aw does not always play the role as the driving potential. Reversed heat transfer through the airfoil wall from downstream to upstream is possible, and this reversed heat flow will make T w > T aw in the near injection hole region. Yet evidence supports that T aw can be used to correctly predict the heat flux direction and always result in a positive adiabatic heat transfer coefficient (h af ).The results further suggest that two different test walls are recommended for conducting film cooling experiments: a low thermal conductivity material should be used for obtaining accurate T aw and a relative high thermal conductivity material be used for conjugate cooling experiment. Insulating a highconductivity wall will result in T aw distribution that will not provide correct heat flux or h af values near the injection hole.

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“…and Lepicovsky J. 5 have used the Glenn code to perform conjugate heat transfer simulations. Their approach extends the solver inside the metal imposing in that region a constant density and a nil velocity.…”

Section: Introductionmentioning

confidence: 99%

Numerical study on heat transfer in aeronautical systems by CHT methods

Carozza

2016

46th AIAA Thermophysics Conference

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The purpose of this paper is to show the results of the application of the CHT method to an aeronautical configuration of interest. To perform these analyses the three heat transfer mechanisms, conduction, radiation and convection, were considered joining the solutions of the solid and fluid regions at the interface. Numerically, the two domains are treated separately in a first moment and then, at the end of each iteration, they are coupled by imposing the equivalence of the gradients. Conductive walls where the Fourier heat flux is considered only in direction normal to the wall, are used. The fluid domain is studied, instead, by a finite volume, implicit and second order accurate code. After a preliminary study carried out on a 2D square cavity, a new generation turboprop nacelle built with three different metallic materials has been taken into consideration. Particular attention has been paid to the thermal fields and the heat exchange rates achieved on the skin both in cruise (T ∞ =253 ̶ 273 K; P ∞ =72500 Pa) and in idle (T ∞ =273 ̶ 293 K; P ∞ =101325 Pa). The results show how the CHT approach in the aerodynamic investigations can affect the aerodynamic predictions in not negligible manner. Indeed, the thermal conductivity plays a relevant role on the internal convective and radiative heat transfer on the single walls. Nomenclature κ = kinetic energy [m 2 s -2 ] µ = dynamic viscosity [N s m -2 ] ε = dissipation rate [s -1 ] α = thermal diffusivity [m 2 s -1 ] ε r = surface emissivity ρ = density [kg m -3 ] ν = kinematic viscosity [m 2 s -1 ] τ = stress tensor [Pa] T = Temperature [K] p = pressure [Pa] CHT = Conjugated Heat Transfer k = thermal conductivity [W m -2 K -1 ] k r = solid to fluid thermal conductivity ratio, = k s /k f q = heat flux [W m -2 ] ϑ =non dimensional temperature, = ∆T × k f /qH Subscripts c = convective f = fluid h = hot wall k = conductive i,j = i th and j th subdivisions o = opening r = radiative s = solid t = total ∞ = ambient p = pressure 0 =starting

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Conjugate Heat Transfer Analysis of Internally Cooled Configurations

Cited by 33 publications

References 0 publications

Use of CFD for Thermal Coupling in Aeroengine Internal Air Systems Applications

Use of CFD for Thermal Coupling in Aeroengine Internal Air Systems Applications

An Investigation of Treating Adiabatic Wall Temperature as the Driving Temperature in Film Cooling Studies

Numerical study on heat transfer in aeronautical systems by CHT methods

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