混合并联TBCC动力的冲压流道跨声速流动及阻力特性
作者:
作者单位:

1.国防科技大学空天科学学院,长沙 410073;2.沈阳飞机设计研究所扬州协同创新研究院有限公司,扬州 225000;3.上海交通大学航空航天学院高超声速创新技术研究实验室,上海 200240

作者简介:

通讯作者:

张志雨,男,工程师,E-mail:zhiyu@mail.ustc.edu.cn。

中图分类号:

V434

基金项目:

航空科学基金(2019ZA0Z9001)。


On Flow and Drag Characteristics of Hybrid Over-Under TBCC Ramjet Channel in Transonic Flight Conditions
Author:
Affiliation:

1.College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China;2.Yangzhou Collaborative Innovation Research Institute Co., Ltd.,Shenyang Aircraft Design Institute, Yangzhou 225000, China;3.Hypersonic Innovation Technology Research Laboratory, College of Aeronautics and Astronautics, Shanghai Jiaotong University, Shanghai 200240, China

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    摘要:

    为了探究跨声速飞行工况下混合并联涡轮基组合循环(Turbo based combine cycle,TBCC)动力的冲压流道在冷通气状态下的流动及阻力特性,构建了一个巡航马赫数为4.0、基于混合并联TBCC动力的高马赫数飞机模型,通过三维定常数值模拟方法研究了其在Ma=0.7~1.6,H=11 km飞行环境下飞机-发动机内/外流动及其耦合特征。计算结果表明:跨声速状态下,冲压进气道入口处气流增压后的静压达到了自由来流滞止压力的85%~90%,气流接近于滞止状态,说明组合进气道存在强烈的节流效应,且冲压通道的喉道是组合进气道节流效应的主要贡献者;冲压发动机尾喷管的排气流动同时受到飞机绕流及涡轮通道排气系统等多方面的干扰,且涡轮通道排气射流对冲压发动机尾喷管气流本身就存在膨胀压缩及排气引射等多种干扰机制。阻力分析表明,压差阻力系数高出内表面摩擦阻力系数2个数量级,是跨声速状态下冲压流道阻力的主要来源;亚声速状态下,进气道阻力占比达到了60%~80%,是冲压流道的主要阻力部件,而Ma>1.0超声速状态下,进气道阻力占比随飞行马赫数的增大而逐步减小,尾喷管的阻力则快速增长,阻力贡献逐渐向尾喷管转移,两者趋于接近。

    Abstract:

    To investigate the flow and drag characteristics of the ramjet flowpath of a hybrid over-under turbo-based combine cycle(TBCC), TBCC engine under transonic flight conditions, a high-Mach aircraft model with a cruise Mach number of 4.0 based on hybrid over-under TBCC engine was designed, and its performance in Ma=0.7—1.6, H=11 km to simulate the aircraft-engine internal/external flow and its coupling characteristics in the flight environment. The results show that in the whole transonic state, the static pressure of the air pressurized at the inlet of the ramjet inlet reaches 85%—90% of the free flow stagnation pressure, and the air flow is close to the stagnation state, indicating that there is a strong throttling flow effect in the combined inlet, and the throat of the ramjet flowpath is the main contributor to the throttling effect of the combined inlet port. The exhaust flow of the ramjet tail nozzle is simultaneously interfered by the aircraft bypass flow and the exhaust system of the turbine channel, and the turbine channel exhaust jet has various interference mechanisms such as expansion compression and exhaust injection to the airflow of the ramjet tail nozzle itself. The drag analysis shows that the differential-pressure drag coefficient is two orders of magnitude higher than the friction drag coefficient of the inner surface, which is the main source of the drag of the ramjet engine under the transonic state. In the subsonic state, the inlet port drag accounts for 60%—80%, which is the main drag component of the ramjet engine, in the Ma>1.0 supersonic state, the inlet port drag ratio decreases with the flight Mach number and decreasing gradually, and the drag of the tail nozzle increases rapidly, indicating that the drag contribution gradually shifts to the tail nozzle, and the two tend to approach.

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引用本文

李宪开,张志雨,何淼生,缪俊杰,柳军.混合并联TBCC动力的冲压流道跨声速流动及阻力特性[J].南京航空航天大学学报,2022,54(4):552-563

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  • 收稿日期:2022-06-10
  • 最后修改日期:2022-07-10
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  • 在线发布日期: 2023-02-22
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