Study of the Aerodynamic Characteristics on the ‎Computed Flowfield During Thrust Reversers Operation ‎

Publish Year: 1400
نوع سند: مقاله ژورنالی
زبان: English
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شناسه ملی سند علمی:

JR_JAFM-14-5_018

تاریخ نمایه سازی: 8 دی 1400

Abstract:

With the increasing of the bypass ratio of modern aero-engines, the problem of wing-engine interference is more prominent, especially for the layout design of engine nacelle. The reverse thrust cascade is widely used in turbofan engines with high bypass ratio. In order to meet the requirements of the integrated analysis of airframe, wing, engine nacelle and hanger, the aerodynamic characteristics of aircraft/engine integration configuration with reverse cascade is numerically studied via CFD (Computational Fluid Dynamics) method. The streamline distribution, iso-surface of total temperature, vorticity distribution and total reverse thrust efficiency on different engine nacelle layouts are compared and analyzed in details. The results show that the lift coefficient of the wing decreases by ۲۱.۲% and ۴۵.۰۲% respectively as the engine moves forwards horizontally by ۱۱%L and ۲۱.۲%L. The lift coefficient of the wing decreases by ۲.۴% and ۴.۸۲% respectively as the engine moves subsidence by -۳.۵%L and ۳.۵%L. The influential region of the reverser airflow in the radial and circumferential direction without airframe interference is significantly larger than that in the case with aircraft/engine integration. The reverser flow is susceptible to be interfered by the adjacent fuselage and wing sections, and the development of reverse thrust flow is significantly limited. Compared to the baseline nacelle location, the reverse thrust performs badly as engine nacelle moves backward and lateral horizontally. The total reverse thrust efficiency decreases gradually as the engine nacelle moves forward horizontally.

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Authors

S. Bi

Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing University of Aeronautics and ‎Astronautics, Nanjing ۲۱۰۰۱۶, China

J. Mao

Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing University of Aeronautics and ‎Astronautics, Nanjing ۲۱۰۰۱۶, China

X. Han

Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing University of Aeronautics and ‎Astronautics, Nanjing ۲۱۰۰۱۶, China

K. Cai

Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing University of Aeronautics and ‎Astronautics, Nanjing ۲۱۰۰۱۶, China

F. Wang

Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing University of Aeronautics and ‎Astronautics, Nanjing ۲۱۰۰۱۶, China