Numerical Simulation on the Ventilation Cooling Performance of the Engine Nacelle under Hover and Forward Flight Conditions

Xie, Yongqi; Gao, Hongxia; Yu, Jing; Xiao, Jing

doi:10.4271/2011-01-0513

Cited by 5 publications

(2 citation statements)

References 4 publications

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“…Smaïli et al (2006, 2012) presented a two-dimensional axisymmetric numerical model for analysis the cooling process of a wind turbine nacelle operating in a cold and in hot climate. In Xie et al (2011) authors compared numerical analysis results regarding to helicopter engine nacelle ventilation system under hover and forward flight conditions with data obtained during real flight 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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“…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. A three-dimensional (3D) numerical investigations of the engine nacelle ventilation systems of a helicopter were performed by Xie et al (2006, 2011). In the first paper, analyses of five design configurations of the nacelle cooling system were carried out while in the second one the performance of different nacelle ventilations systems under hover and forward flight conditions were investigated.…”

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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Simplified thermo-fluid model of an engine cowling in a small airplane

Łapka

Seredyński

Furmański

et al. 2014

Aircraft Eng & Aerospace Tech

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Purpose – The purpose of this study is to developed a simplified thermo-fluid model of an engine cowling in a small airplane. An aircraft engine system is composed of different elements operating at various temperatures and in conjunction with the composite nacelle creates a region with high intensity of heat transfer to be covered by the cooling/ventilation systems. Therefore a thermal analysis, accounting for the complex heat transfer modes, is necessary in order to verify that an adequate cooling is ensured and that temperatures of the nacelle are maintained within the operating limits throughout the whole aircraft's flight. Design/methodology/approach – Simplified numerical simulations of conductive, convective and radiative heat transfer in the engine bay of the small airplane I-23 in a tractor arrangement were performed for different air inlet and outlet configurations and for varying conditions existing in air inlets during the flight. The model is based on the control volume approach for heat and fluid flow as well as for thermal radiation and on k-ɛ turbulence model. Findings – The flow and temperature distributions inside the cowling were determined, and high-temperature spots on the internal side of the nacelle and on other airplane systems located close to the turboprop engine and the exhaust system were found. The thermal radiation was found to play the key role in heat transfer inside the engine bay. The optimal configuration of air inlets and outlets was determined. Practical implications – The obtained results will help in future studies on ventilation and cooling systems and will contribute to the selection of materials for parts of the engine bay and the nacelle as well as in developing solutions for reducing the temperature inside the cowling of the airplane I-23. Originality/value – A complete simplified thermo-fluid model of heat transfer inside the engine bay of the airplane I-23 was developed. Additionally, influence of the thermal radiation on temperature distribution at the nacelle was investigated.

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Numerical Simulation on the Ventilation Cooling Performance of the Engine Nacelle under Hover and Forward Flight Conditions

Cited by 5 publications

References 4 publications

CFD simulation of engine nacelle cooling on pusher configuration aircraft

CFD simulation of engine nacelle cooling on pusher configuration aircraft

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

Simplified thermo-fluid model of an engine cowling in a small airplane

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