Effect of Axisymmetric Aft Wall Angle Cavity in Supersonic Flow Field

Abstract

Cavity plays a significant role in scramjet combustors to enhance mixing and flame holding of supersonic streams. In this study, the characteristics of axisymmetric cavity with varying aft wall angles in a non-reacting supersonic flow field are experimentally investigated. The experiments are conducted in a blow-down type supersonic flow facility. The facility consists of a supersonic nozzle followed by a circular cross sectional duct. The axisymmetric cavity is incorporated inside the duct. Cavity aft wall is inclined with two consecutive angles. The performance of the aft wall cavities are compared with rectangular cavity. Decreasing aft wall angle reduces the cavity drag due to the stable flow field which is vital for flame holding in supersonic combustor. Uniform mixing and gradual decrease in stagnation pressure loss can be achieved by decreasing the cavity aft wall angle.

The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor

“…A robust flame holding mechanism is needed owing to the short residence time of airflow in the scramjet combustor. There are various injection and flame holding mechanisms, such as cavities [4][5][6][7][8][9][10], pylons [11][12][13][14] and struts [15][16][17][18][19][20][21][22][23][24][25][26][27][28]. The combinations of the aforementioned schemes [29][30][31][32] were succeeded to some extend by several studies.…”

Flow characteristics of Axisymmetric Cavity Rear Wall Divergence Angle in a Scramjet Combustor

“…Based on the aspect ratios (length to depth), the cavities are generally categorized as open and closed. Cavity possess L/D ratio less than 10 is noted as open cavity and the one with L/D ratio greater than 10 termed as closed cavity [12]. In order to minimise the effect of localized and ineffective fuel-air mixing associated with the cavities, improvements in the geometrical design of the combustor with the cavities could rectify various significant issues in the development of Scramjet technology.…”

Non-Reacting Examination on Transverse Injection Upstream of Aft Wall Angled Cavities in an Axisymmetric Supersonic Flow

“…It has also been proved by the combustion scientists that flame stabilization is dependent on the location of the fuel injection and the flow stagnation temperature. Most of the open literatures reveals open cavity-based injection studies in two-dimensional combustors and studies in axisymmetric models are scant [12] [13].…”