Effect of zero penetration angle chevrons in supersonic jet noise and screech tone mitigation

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-04-17 DOI:10.1515/tjj-2022-0073

Kaleeswaran Periyasamy, Kadiresh P. Natarajan, Bogadi Surendra, Khandai Suresh Chandra

引用次数: 0

Abstract

Abstract An experimental study is conducted to determine the effect of chevrons with zero penetration angles at the CD nozzle exit on an emitted noise field. The implication of passive control is to reduce the blockage of the nozzle exit area with minimal engine thrust penalty. The cold air jets issued at design Mach numbers 1.5 and 1.75 from the De Laval nozzles of the circular section were investigated. This passive control eliminates screech tones at the over and ideally expanded conditions at 60° and 90° in the azimuth plane. The acoustic data measurements have also been observed for the chosen jet Mach numbers. The schlieren images reveal the shock cell pattern to eliminate the effect of shock-associated noise levels at supersonic jets. The results show that 10 chevrons with no penetration act as an effective eliminator of screech tone and noise suppression average ∆OASPL value up to 3 dB at Mach number 1.75.

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零贯穿角人字形对超音速喷气噪声的影响及尖声抑制

摘要通过实验研究了CD喷管出口零侵彻角线形对发射噪声场的影响。被动控制的意义在于以最小的发动机推力损失来减少喷管出口区域的堵塞。研究了圆形截面De Laval喷嘴在设计马赫数为1.5和1.75时发出的冷空气射流。这种被动控制消除了在60°和90°的方位角平面上的过度和理想扩展条件下的刺耳音调。对选定的射流马赫数也进行了声学数据测量。纹影图像揭示了冲击细胞模式，以消除超音速射流中与冲击相关的噪声水平的影响。结果表明，10条无穿透的线形线对噪声抑制效果较好，在1.75马赫数下噪声抑制平均∆OASPL值可达3 dB。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.