CFD-Based Analysis of Installed Fuel Consumption and Aerodynamics of Transonic Transport Aircraft during Cruise Flight

Andrea Magrini (), Denis Buosi, Francesco Poltronieri, Elena De Leo and Ernesto Benini ()
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Andrea Magrini: Dipartimento di Ingegneria Industriale, Università Degli Studi di Padova, via Venezia 1, 35131 Padova, Italy
Denis Buosi: Hit09 S.r.l., Piazzetta Bettiol 15, 35137 Padova, Italy
Francesco Poltronieri: Dipartimento di Ingegneria Industriale, Università Degli Studi di Padova, via Venezia 1, 35131 Padova, Italy
Elena De Leo: Dipartimento di Ingegneria Industriale, Università Degli Studi di Padova, via Venezia 1, 35131 Padova, Italy
Ernesto Benini: Dipartimento di Ingegneria Industriale, Università Degli Studi di Padova, via Venezia 1, 35131 Padova, Italy

Energies, 2023, vol. 16, issue 8, 1-15

Abstract: Gas turbine fuel burn for an aircraft engine can be obtained analytically using thermodynamic cycle analysis. For large-diameter ultra-high bypass ratio turbofans, the impact of nacelle drag and propulsion system integration must be accounted for in order to obtain realistic estimates of the installed specific fuel consumption. However, simplified models cannot fully represent the complexity of installation effects. In this paper, we present a method that combines thermodynamic cycle analysis with detailed Computational Fluid Dynamics (CFD) modelling of the installation aerodynamics to obtain the fuel consumption at a given mission point. The flow field and propulsive forces arising in a transport aircraft powered by an ultra-high bypass ratio turbofan at cruise are first examined to characterise the operating conditions and measure the sensitivity to variations of the incidence at transonic flight. The proposed methodology, in which dynamic balance of the vehicle is achieved at each integration point, is then applied along a cruise segment to calculate the cumulative fuel burn and the change in the specific fuel consumption.

Keywords: installation effects; specific fuel consumption; ultra-high bypass ratio; NASA Common Research Model; propulsion system integration (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2023
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