Effect of cavity fore wall modifications in supersonic flow

4th AEROTECH- Innovation in Aerospace Engineering and Technology

航空航天工程

Jeyakumar, S.^1 ; Yuvaraj, K. Arun^1 ; Jayaraman, K.^2 ; Cardona, F.^3 ; Sultan, M.T.H.^3

Department of Mechanical Engineering, Kalasalingam University, India^1

Department of Aerospace Engineering, Veltech University, Chennai, India^2

Aerospace Manufacturing Research Centre (AMRC), Universiti Putra Malaysia, Malaysia^3

关键词: Axisymmetric cavities;    Circular cross-sections;    Fillet radius;    Momentum flux;    Operating condition;    Stagnation pressures;    Static pressure;    Supersonic combustors;   

Others  :  https://iopscience.iop.org/article/10.1088/1757-899X/152/1/012002/pdf
DOI  :  10.1088/1757-899X/152/1/012002

学科分类：航空航天科学

来源: IOP

【 摘 要 】

Understanding the complex behaviour of the cavity flow is essential for the design of supersonic combustor. The characteristics of the axisymmetric aft ramp cavity with fore wall modification have been experimentally studied in a blow-down type supersonic flow facility. The facility consists of a conventional CD nozzle that issues a flow Mach number of 1.88 to a supersonic combustor of circular cross section, which is placed immediately downstream of the nozzle. The axisymmetric cavities are incorporated within the combustor. The cavities are of open type and their length is kept constant while their depth varies. The aft wall of the cavities is inclined with three ramp angles and the fore wall is provided with a constant fillet radius of 3 mm. The performance of the cavity is analysed based on wall static pressures, momentum flux distribution at the exit of the combustor and stagnation pressure loss across the combustor. The study reveals that fore wall fillet cavities provide less cavity drag and stagnation pressure loss for various aft ramp angles under identical operating conditions.