多排圆盘和多冷却剂射流的头部锥形可压缩流的数值研究。

Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets.

机构信息

Faculty of Civil Engineering, K.N. Toosi University of Technology, Tehran, 158754416, Iran.

Department of Civil Engineering, College of Engineering, Cihan University-Erbil, Erbil, Iraq.

出版信息

Sci Rep. 2023 Jan 16;13(1):787. doi: 10.1038/s41598-023-28127-9.

DOI:10.1038/s41598-023-28127-9

PMID:36646787

原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC9842636/

Abstract

Due to sever aerodynamic heating, the protection of forebody of scramjet is crucial for hypersonic flight. In present work, a new cooling system is proposed and investigated for the protection of nose cone at hypersonic flight. Computational fluid dynamic is used for the simulation of the lateral and axial coolant jet released from the spike at high-velocity condition. The primary goal is to find optimum jet location for efficient cooling of nose and spike assembly. Influence of two coolant jets (Carbon dioxide and Helium) on the mechanism of cooling system are fully investigated. For simulation, RANS equations are coupled with species transport equation and SST turbulence model. Two different jet configurations (axial disk positions) are investigated to obtain efficient condition for protection of nose cone at hypersonic flight. Our results indicate that the presence of the spike on the nose cone decreases pressure up to 33% on the main body and the shifts the maximum pressure to higher angles because of the deflection of the air stream. Maximum pressure drops about 50% by injection of the coolant disk jet (C2) at angle of 55 deg.

摘要

由于严重的气动加热，超燃冲压发动机的前体防护对于高超音速飞行至关重要。在目前的工作中，提出并研究了一种新的冷却系统，用于高超音速飞行时的锥形头保护。计算流体动力学用于模拟高速条件下从尖刺释放的横向和轴向冷却射流。主要目标是找到最佳的射流位置，以实现对锥形头和尖刺组件的有效冷却。充分研究了两种冷却剂射流（二氧化碳和氦气）对冷却系统机制的影响。对于模拟，RANS 方程与物质传输方程和 SST 湍流模型相结合。研究了两种不同的射流配置（轴向盘位置），以获得在高超音速飞行中保护锥形头的有效条件。我们的结果表明，由于气流的偏转，锥形头上的尖刺会使主体上的压力降低多达 33%，并将最大压力转移到更高的角度。通过在 55 度角喷射冷却盘射流（C2），最大压力下降约 50%。