Fig.1

Placement of two types of strut

Fig.2

Mach number， flame index， pressure gradient contours for strut-baesd combustor with expansion （z=0.001 2 m）［16］

Fig.3

Flame imaging of different combustion modes at trailing edge of strut［17］

Fig.4

Different strut configurations［19］

Fig.5

Geometric details of two bumpy struts investigated［20］

Fig.6

Geometry of lobed strut injector［21］

Fig.7

Contours of Mach number of combustor with sturt［24］

Fig.8

Schematic diagram of intelligent strut［26］

Fig.9

Double struts proposed by Choubey， et al［31］ （left）， structure of recirculation zone （center）， and contours of temperature （right）

Fig.10

Geometric models of double-nozzle strut injector scramjet combustor［32］

Fig.11

Schematic diagram of active jet configuration proposed by Pu et al［33］ with three struts

Fig.12

Schematic diagram of scramjet combustor equipped with oxygen injector from trailing edge of strut［36］

Fig.13

Contours of Ykero， Rkero， and |∇ρ| in spanwise planes with oxygen supplementation （z/D=0）［36］

Table 1

Summary of research content of strut-based supersonic combustors［16-21， 24， 26-36］

Fig.14

Schematic diagram of three popular cavity structures

Fig.15

Schematic diagram of cavity flow field structure［38］

Fig.16

Flame base stabilization locations［44］

Fig.17

Perspective views of extended Takeno flame index conditioned on Q for different flame stabilization mechanisms［46］

Fig.18

Instantaneous contours of heat release rate and vorticity in different combustion regions［47］

Fig.19

Pathlines from fuel injector colored with residence time for baseline， square cavity， and inclined cavity configurations［48］

Fig.20

Two types of cavities［55］

Fig.21

Schematic diagram of tandem cavity and parallel cavity［9］

Fig.22

Schematic diagram of tandem cavities at various axial positions［39］

Fig.23

Comparison of H2 mass fractions on jet planes of different injection methods［66］

Fig.24

Flame stabilization modes of different injection positions［69］

Fig.25

Cavity configurations used to tailor mean pressure gradient［72］

Table 2

Summary of research content of cavity-based supersonic combustors［39，43-55，57-60，65-67，69-70，72，78-83］

Fig.26

Velocity and pressure fields in flow direction section of horizontal strut［88］

Fig.27

Velocity and pressure fields in flow direction section of vertical strut［88］

Fig.28

Schematic diagram of recirculation zone structure of strut-cavity combustor［7］

Fig.29

Shadowgraph image of shock and schematic diagram of cavity oscillations［89］

Fig.30

Static temperature contours comparison in a double dual cavity in 3-struted geometry and 4-struted geometry［99］

Fig.31

Images of Mach number contour structure and numerical shadowgraph of DLR scramjet model with twin cavity configurations of varying locations［101］

Fig.32

Circle shaped injector， square shaped injector and rectangle shaped injector［102］

Fig.33

Schematic diagram of air-assistant cavity-strut based combustor［103］

Table 3

Detailed information of studies on strut-cavity combined devices［6-7，86，89-93，95］