Impact of installation on a civil large turbofan exhaust system at idle descent conditions

Predicting the energy and exergy performance of F135 PW100 turbofan engine via deep learning approach

“…𝑷 𝟒=𝝅 𝑪 𝑷 𝟑 (6) where 𝜋 𝑐 is compressor pressure ratio of HPC and 𝑃 4 is HPC output pressure and 𝑃 3 is the fan exit air pressure the exit temperature of the compressor is obtained as follow;…”

“…Finally, the calculation results confirmed that the considered RMTC system proves potential application for high-speed military aircraft. Rao et al [6] studied to improve the propulsive efficiency of a civil aero-engine design aimed at lowering specific Thrust and idle descent conditions by swelling the bypass ratio. Also, the bypass ratio of discharge and core nozzles of a high-bypass ratio aeroengine have been studied in isolation and installed on an airframe.…”

Impact of Installation on the Performance of an Aero-Engine Exhaust at Wind-Milling Flow Conditions

“…This renders the mass flow discharged through the fan nozzle highly sensitive to the external static pressure field [12]. As a result, C Fan d can be sensitive to the effect of the pressure field produced by the airframe in-flight [13]. This effect can be further amplified by the presence of the high-lift surfaces [14,15].…”

“…This effect can be further amplified by the presence of the high-lift surfaces [14,15]. This "installed pressure field" can suppress the fan nozzle mass flow leading to a concurrent reduction in engine ingested mass flow [13]. Hence, it is essential to understand the impact of this "installed pressure field" on the aerodynamic behavior of the exhaust during wind-milling since it affects the engine ingested mass flow and the associated nacelle drag [16].…”

Coupled propulsive and aerodynamic analysis of an installed ultra-high bypass ratio powerplant at high-speed and high-lift conditions

“…For other design conditions, such as take-off, climb, descent and landing, the available information is the open literature is also quite limited. Rao et al [15] investigated the effects of descent conditions in the exhaust performance of a high bypass ratio engine. Subbian et al also evaluated the aerodynamics of UHBR engines for landing [16] and take-off conditions [17].…”