The aim of the research is to create the classification for shock wave triple configurations and their existence regions of various types: type 1, type 2, type 3. Analytical solutions for limit Mach numbers and passing shock intensity that define existence region of every type of triple configuration have been acquired. The ratios that conjugate intensities of three shock in triple configuration and flow turn angle on them are presented. The transition (boundary) shock wave triple configurations have been reviewed. The acquired results can be used to design shock wave structures with set properties in detonation engines, air collectors, technological plants, when analyzing shock wave influence on objects during an explosion. Triple configurations of type 1 are used in internal compression air intakes that are based on interaction of oncoming shocks. Triple configurations of type 2 can be found in supersonic gas jets, at Mach reflection of shock and detonative waves from solid walls. Triple configurations of type 3 are used in supersonics multishock air intakes of external or mixed compression.