某型飞机发动机短舱防冰系统设计计算

朱永峰; 方玉峰; 封文春

某型飞机发动机短舱防冰系统设计计算

1.
北京航空航天大学航空科学与工程学院,北京 100191
2.
中航工业第一飞机设计研究院环控救生研究所,西安 710089
3.
中国航空工业集团公司飞机公司,北京 100089

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出版历程
- 收稿日期: 2011-07-25
- 刊出日期: 2012-06-28

Design and calculation of aircraft nacelle anti-icing system

1.
School of Aeronautics Science and Engineering, Beijing University of Aeronautic and Astronautic,Beijing 100191,China
2.
The Environment Control and Life Support System Design and Research Department, First Aircraft Institute of Aviation Industry Corporation of China,Xi'an 710089,China
3.
Aircraft Corporation,Aviation Industry Corporation of China,Beijing 100089,China

摘要

摘要: 介绍了某型飞机发动机短舱防冰系统的结构形式和防冰原理,按照可利用热量应大于所需热量的原则,通过计算完全蒸发和湿状态下的热载荷,确定了发动机短舱防冰严酷状态及所需热流量.基于机翼水收集系数和数据相似原则,利用欧拉法两相流计算方法,确定了短舱防冰系统水收集系数.按照在湿状态下允许有一定结冰量存在的设计原则,根据发动机的吞冰能力,利用VSAERO/ICE工具对发动机短舱防冰系统进行了计算,计算结果表明,在严酷状态下,防冰系统能够满足允许结冰厚度要求.
- 防冰系统 /
- 发动机短舱 /
- 水收集系数 /
- 吞冰能力 /
- 笛形管
Abstract: The structure and theory of engine nacelle anti-icing (NAI) system were introduced.According to the principle that the heat available should be larger than the heat required,the critical design point and required flows of NAI were determining by calculating the required bleed air at complete evaporation and running wet station respectively.The coefficient of water collection of NAI system was determined using Euler method based on the coefficient of water collection of wing and the data similarity rule.According to the theory of allowed maximum thickness of ice,the performance of NAI system was calculated using the VSAERO/ICE software.The result of simulation shows that the maximum thickness of ice can meet at the critical condition.
- anti-icing system /
- nacelle of engine /
- coefficient of water collection /
- max accretion of an ice /
- piccolo tube

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参考文献(15)

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