Aero-Thermal Computations With Experimental Comparison Applied to Aircraft Engine Nacelle Compartment

Balland, Morgan; Verseux, Olivier; Esteve, Marie-Josephe

doi:10.1115/gt2005-68995

Cited by 6 publications

(4 citation statements)

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“…Segal (1997) proposed an one-dimensional model for the investigation of the engine bay for military aircraft which ensures its good ventilation and cooling. Furthermore, Balland et al (2005) deals with analysis of heat and fluid flow in the nacelle compartment of an aircraft engine. What is more we can find there a comparison of calculated data with results obtained during real engine tests.…”

Section: Introductionmentioning

confidence: 99%

CFD simulation of engine nacelle cooling on pusher configuration aircraft

Olejnik

Dziubiński

Kiszkowiak

2021

AEAT

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Purpose The purpose of this paper is to simulate with in-depth reconstruction of existing geometry a process of cooling of the aircraft engine in pusher configuration, which is more problematic than usually used, tractor configuration. Moreover, a complex thermal and fluid flow analysis is necessary to verify that an adequate cooling is ensured and that temperatures in the engine nacelle are maintained within the operating limits. Design/methodology/approach Methodology used in this research is based on computational fluid dynamics tools to model adequately the internal and the external flow, to find the state of cooling system and research the results of baffles modification inside the engine cover. Additionally, two types of the cover with different sizes of inlets and outlets are tested. Findings The results showed the influence of baffles modifications and changes in inlets and outlet sizes on the mass flow rate and temperature distributions inside the engine nacelle. The best configuration of air inlets and outlets was determined. Practical implications The method used in the research is the safest method in testing of such cases, provided the proper approach in modeling is taken. The collaboration of internal and external flow is crucial and should not be replaced with assumed flow rate through inlet and outlet area. The obtained results will help in future studies on cooling systems of engines in pusher configuration. Originality/value The work presents original results obtained by the authors during a complex fluid flow and heat transmission analysis and is a part of the design project of the OSA patrol aircraft.

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Section: Introductionmentioning

confidence: 99%

CFD simulation of engine nacelle cooling on pusher configuration aircraft

Olejnik

Dziubiński

Kiszkowiak

2021

AEAT

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“…Segal [7] proposed an onedimensional model for the investigation of the engine bay for military aircraft, which ensures its good IOP Publishing doi:10.1088/1757-899X/1226/1/012037 2 ventilation and cooling. Furthermore, Balland et al [8] deals with analysis of heat and fluid flow in the nacelle compartment of an aircraft engine. Nevertheless, in the literature there is a significant lack of information on cooling system analyses of a piston engine in pusher configuration.…”

Section: Introductionmentioning

confidence: 99%

Ventilation Analysis of Simplified Engine Nacelle for Pusher Aircraft

Olejnik

Kiszkowiak

Dziubmski

2022

IOP Conf. Ser.: Mater. Sci. Eng.

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The paper contains the results of CFD analysis of flow inside the simplified engine nacelle, containing the engine in a pusher configuration. The authors have tested a set of solutions to increase an efficiency of the cooling system of this type of engine. Unfortunately, all the positive effects of the fact, that the aircraft engine appears in the wake of the propeller during taxiing and waiting for takeoff, are nonexistent in this type of configuration. An engine overheating is here a problem, because an airflow has to be pulled through the nacelle to cool down the engine block and radiators of cylinder heads. That design demands to analyze the cover shape of the nacelle, to properly use the main propeller pressure jump on the one hand, and rather adequate and complicated flow inside the nacelle to be modelled on the other. The aircraft CAD geometry has been simplified to allow for simple changes of the nacelle cover shape and easily introducing new inlets and outlets. The results prove, that the proper application of scoops gives even better result, than simply removing the cover and baffles from the engine. The exhaust scoops should be placed near the propeller plane in such pusher configuration, because the engine is not covered by the propeller wake.

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“…In addition, a one-dimensional (1D) flow model of the analysed system was proposed. Balland et al (2005) studied radiative and convective heat transfer in the nacelle core compartment of an aircraft engine and compared the results obtained with a real engine data. Smaïli et al (2006, 2012) presented a two-dimensional (2D) axisymmetric numerical model of heat transfer and flow both inside and outside the wind turbine nacelle to investigate its thermal behaviour during operation in the cold and extremely hot climate conditions.…”

Section: Introductionmentioning

confidence: 99%

Comparison of 1D and 3D thermal models of the nacelle ventilation system in a small airplane

Łapka

Bakker

Furmański

et al. 2018

AEAT

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Purpose Insight in the temperature distribution on the internal and external surface of the nacelle is of great importance during the design phase of an aircraft. However, detailed information is not always needed. In a preliminary project stage or during parametric optimization, short analysis times are often more crucial than high accuracy. In such cases, the global insight in the temperature levels suffices to gain understanding of the relevance and influence of certain parameters. Nevertheless, estimating the maximum temperature for the most adverse conditions should also be done before a prototype is built. Therefore, this study aims to present and compare a simplified and an advanced methodology for the analysis of engine bay cooling and ventilation systems as well as heat transfer in the nacelle in a small airplane equipped with a turboprop engine in the tractor arrangement. Design/methodology/approach Both approaches included conductive, convective and radiative heat transfer in the engine bay of the small airplane I-23 as well as heat conduction in the nacelle made of material with anisotropic thermal conductivity. The one-dimensional (1D) model assumed that the nacelle with the air flow and engine was represented by a lumped thermal model in which heat was exchanged between the different lumped segments (the nodes) and the flowing air and engine. The three-dimensional (3D) model was based on the continuous control volume approach for heat, fluid flow and thermal radiation as well as on realizable k-ε turbulence model. Both models used commercial software. Findings The temperature distribution at the internal and external surface of the top nacelle was calculated. The 1D model predicted a temperature per node (per segment) while the 3D model was able to determine its values accurately and find the location of hot spots. Considering the complex geometry of the engine bay and nacelle and the assumed simplification, the obtained 1D and 3D results agreed quite well. Practical implications Both models will help in the development of new ventilation and cooling systems of the engine bay and nacelle as well as in the selection of materials for parts of the top cowling in the newly redesigned airplane I-23 equipped with a turboprop engine. In addition, the methodology presented in this paper might be applied in the development of other airplanes. Originality/value The 1D and 3D models of complex heat transfer inside the engine bay and in the nacelle of the newly re-designed airplane I-23 were elaborated and compared.

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Aero-Thermal Computations With Experimental Comparison Applied to Aircraft Engine Nacelle Compartment

Cited by 6 publications

References 0 publications

CFD simulation of engine nacelle cooling on pusher configuration aircraft

CFD simulation of engine nacelle cooling on pusher configuration aircraft

Ventilation Analysis of Simplified Engine Nacelle for Pusher Aircraft

Comparison of 1D and 3D thermal models of the nacelle ventilation system in a small airplane

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