Numerical investigation of the internal and external thermal fields for a nacelle in pusher configuration

Carozza, Antonio; Mingione, Giuseppe; Pezzella, Giuseppe; Serino, Gennaro

doi:10.1007/bf03404737

Cited by 2 publications

(7 citation statements)

References 11 publications

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“…Often both experiments and numerical simulations do not take into consideration the possible influence that the wall thickness and conduction can have on the internal temperatures. This, in the author's opinion, can be useful for the aero-engine designers, see also the publication 21 . At this aim, the geometry in Fig.5 was investigated, while some mesh lines are plotted on the right along an intermediate section, and taking into account the Table 3.…”

Section: Nacelle Heat Transfer Rates Through and On The Wallsmentioning

confidence: 91%

“…Bohn et al 9 followed a similar approach coupling a Navier-Stokes solver for the fluid zone to a thermal code solving the Fourier equation in the solid. Other studies on the matter are described in the articles [10][11][12][13][14][15][16][17][18][19][20][21][22] . In their papers, the researchers studied the thermal shield effect over an internal cooled blade.…”

Section: Introductionmentioning

confidence: 99%

“…For all of them, neverthless, the engine is still a complex machine composed of more elements at different temperatures that in conjunction with the nacelle experiments coupled heat transfer mechanisms. Often the nacelle cooling/ventilation systems are not sufficient to lower the temperatures, therefore one of the critical issues is the engine/nacelle coupled thermal study, as in Carozza et al 21 .…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Nacelle Heat Transfer Rates Through and On The Wallsmentioning

confidence: 91%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Numerical study on heat transfer in aeronautical systems by CHT methods

Carozza

2016

46th AIAA Thermophysics Conference

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“…The ESPOSA (2016) project studied the infrared radiation of small aircraft by use of two major methodologies. The theoretical investigations had objectives aero-thermal analysis and evaluation of the engine airframe integration and reducing the temperature distribution (by this infrared radiation) of the airframe elements heated by working engines (Buonomo et al, 2013;Carozza et al, 2015;Veress, Bicsak and Rohacs, 2016).…”

Section: Radiation Simulationmentioning

confidence: 99%

“…(Buonomo et al, 2013) The Fig. 11 shows the wall temperature contours of nacelle of the same EM-11 ORKA aircraft for the engine idle condition (Carozza et al, 2015). For easier evaluation of the results the idle condition was chosen as 101325 Pa air pressure and 300 K air temperature.…”

Section: Theoretical Investigationsmentioning

confidence: 99%

Small Aircraft Infrared Radiation Measurements Supporting the Engine Airframe Aero-thermal Integration

Rohács

Jankovics

Gál

et al. 2018

Period. Polytech. Transp. Eng.

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The large, EU Supported ESPOSA (Efficient Systems and propulsion for Small Aircraft) project has developed new small gas turbines for small aircraft. One of the important tasks was the engine - airframe aero-thermal radiation integration that included task of minimizing the infrared radiation of the small aircraft, too. This paper discusses the factors influencing on the aircraft infrared radiation, its possible simulation and measurements and introduces the results of small aircraft infrared radiation measurements. The temperature of aircraft hot parts heated by engines were determined for validation of methodology developed and applied to engine - aircraft thermal integration.

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Numerical investigation of the internal and external thermal fields for a nacelle in pusher configuration

Cited by 2 publications

References 11 publications

Numerical study on heat transfer in aeronautical systems by CHT methods

Numerical study on heat transfer in aeronautical systems by CHT methods

Small Aircraft Infrared Radiation Measurements Supporting the Engine Airframe Aero-thermal Integration

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