Parametric design of non-axisymmetric separate-jet aero-engine exhaust systems

被引：8
|
作者：
Otter, John J. [1 ]
Christie, Robert [1 ]
Goulos, Ioannis [1 ]
MacManus, David G. [1 ]
Grech, Nicholas [2 ]
机构：
[1] Cranfield Univ, Ctr Prop Engn, Sch Aerosp Transport & Mfg, Cranfield MK43 0AL, Beds, England
[2] Rolls Royce PLC, Installat Aerodynam, Derby, England
来源：
AEROSPACE SCIENCE AND TECHNOLOGY | 2019年 / 93卷
关键词：
Exhaust nozzle; Class Shape Transformation; Non-axisymmetric; Aero-engine; Computational fluid dynamics; Propulsion integration;
D O I：
10.1016/j.ast.2019.05.038
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
Future civil air vehicles are likely to feature propulsion systems which are more closely integrated with the airframe. For a podded underwing configuration, this close coupling is expected to require non-axisymmetric design capabilities for the aero-engine exhaust system. This work presents the development of a novel parametric representation of non-axisymmetric aero-engine exhaust system geometries based on Intuitive Class Shape Transformation (iCST) curves. An exhaust design method was established and aerodynamic analyses of a range of non-axisymmetric configurations was demonstrated. At typical flight conditions, the introduction of non-axisymmetric separate-jet nozzles was shown to increase the engine net propulsive force by 0.12% relative to an axisymmetric nozzle. (C) 2019 Rolls-Royce plc. Published by Elsevier Masson SAS.
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页数：12
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