Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-08-29 DOI:10.1515/tjj-2023-0068

N. Subramani, S. M, Gowtham Gajapathy

引用次数: 0

Abstract

Abstract This paper presents the numerical analysis of a convergent-divergent circular nozzle with the exit Mach number of 1.69 with and without passive control at the exit. The passive control method opted for this analysis was inward and outward ascending triangular protrusion. This paper explores the influence of the passive control geometry and its blockage area concerning the nozzle exit. The nozzle pressure ratio (NPR) used for carrying out the flow analysis were 3, 4.932, and 6. Two different inward and outward protrusions were used with a height of 1.5 mm and 3 mm. From the results, the potential core length of the protrusion 1.5 mm height was not much changed in the both outward and inward cases. But when the height of the protrusion was increased to 3 mm, there was a noticeable core length reduction at all NPR but with different cases. At the NPR of 6, the potential core length of the inward protrusions 3 mm was reduced by 44 % compared to the plain CD nozzle.

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被动控制几何结构对超声速射流混合增强影响的数值分析

摘要本文对出口马赫数为1.69的收敛-发散圆形喷嘴进行了数值分析，在出口处有和没有被动控制。本次分析采用的被动控制方法是向内和向外上升的三角形突起。本文探讨了被动控制几何结构及其堵塞面积对喷嘴出口的影响。用于进行流动分析的喷嘴压力比（NPR）分别为3、4.932和6。使用了两个不同的向内和向外突起，高度为1.5 mm和3 根据结果，突起的潜在核心长度为1.5 mm高度在向外和向内两种情况下变化不大。但当突起的高度增加到3 mm时，在所有NPR下都有明显的核心长度减少，但情况不同。在NPR为6时，向内突起3的潜在芯长度 毫米减少了44 % 与普通CD喷嘴相比。

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.