FLAME STABILIZATION CHARACTERISTICS OF STRUT DIVIDED INTO 2 PARTS IN SUPERSONIC AIR-FLOW

Flame stabilization experiments were conducted in a supersonic airflow of Mach number 1.5, using a strut divided streamwise into two parts. Hydrogen gas was injected into the interval between the two parts of t he strut. The Dame stabilization was definitely affected by whether th e combustion region could be established in this space, and the flame stabilization characteristics changed drastically according to the dis tance between the two parts of the strut. A shadowgraph and schlieren photographs showed that no shock waves or expansion waves existed in t he intervening space, and that waves did not directly control the flam e-stabilization mechanism that was altered by the distance between two parts. In order to explain the present characteristic flame-stabiliza tion from the standpoint of the competition between mass transfer and reaction, the velocity fields were measured by laser Doppler velocimet er, and the residence times in the intervening space were estimated. T hrough these observations and measurements, the flame-stabilization me chanism was clarified and the usefulness of this type of strut was dem onstrated.